EP3194792B1 - Recirculation stage - Google Patents

Recirculation stage Download PDF

Info

Publication number
EP3194792B1
EP3194792B1 EP15797326.4A EP15797326A EP3194792B1 EP 3194792 B1 EP3194792 B1 EP 3194792B1 EP 15797326 A EP15797326 A EP 15797326A EP 3194792 B1 EP3194792 B1 EP 3194792B1
Authority
EP
European Patent Office
Prior art keywords
radial
recirculation stage
flow direction
turn
fcss
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP15797326.4A
Other languages
German (de)
French (fr)
Other versions
EP3194792A1 (en
Inventor
Nico Petry
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP3194792A1 publication Critical patent/EP3194792A1/en
Application granted granted Critical
Publication of EP3194792B1 publication Critical patent/EP3194792B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the invention relates to a recycling stage according to claim 1.
  • the fluid leaves the impeller radially outward and from there into the diffuser, which is also flowed through radially outward.
  • the process fluid in the portion of the radial deflection, the so-called 180 ° arc is deflected from radially outward to radially inward flow.
  • the flow path downstream of the 180 ° arc is bladed to convert the swirl of the fluid, which is part of the kinetic energy stored by the fluid, into static pressure - comparable to converting kinetic energy into potential energy.
  • the vanes provided in the return duct are also referred to as return vanes. Downstream of the return vanes, the process fluid is usually deflected from a radially inwardly directed flow in an axial direction, so that an axially parallel inflow into the downstream compression stage can take place.
  • the actual baffles affecting the process fluid in the 180 ° arc and in the downstream 90 ° deflection can deviate from the names giving values 180 ° and 90 °.
  • the 180 ° deflection is therefore usually referred to in the terminology of the invention as a radial deflection.
  • the 90 ° deflection provided downstream of the return channel in the direction parallel to the axis for feeding the subsequent stage has no special design according to the invention and will accordingly not be described in detail.
  • a comparable multi-stage radial turbomachine namely a radial turbine is already out of the EP 2 518 280 A1 known. Even if the flow direction in a radial turbine runs counter to that in a radial compressor, it has hitherto been customary to form the respective return stage geometrically at least approximately the same.
  • the state of the art in this document provides that the radial deflection on the inlet side and outlet side each have a substantially identical axial width. Furthermore, it is provided that the radial deflection has a substantially constant radius both on an inner contour and on an outer contour. This design of the radial deflection corresponds to the simplest geometric design and tends as a result of separation phenomena at the Umlenkungsradien in operation to a high pressure loss.
  • the invention relates to a movement of a process fluid relative to the entire return stage through the flow channel defined by means of the return stage of the radial turbocompressor in general.
  • this direction of flow can be characterized by the middle channel course with the marking of corresponding directional arrows.
  • the sections annular space, radial deflection, return channel and axial deflection of the return stage are each formed annularly extending around a rotational axis of the radial turbocompressor.
  • a center line between the outer contour and the inner contour is defined as the location of the centers of the circles tangent to the two contours. Since the return stage extends in the circumferential direction about the axis of rotation of the radial turbocompressor and thus defines an annular space which is substantially rotationally symmetrical to the axis of rotation, a central area between the three-dimensional inner contour and the three-dimensional outer contour can be regarded as a rotation surface of the center line about the axis of rotation.
  • the description of the geometry is always based on a meridional section through the radial turbocompressor, wherein the meridional section extends along the axis of rotation and represents the flow channel defined by the return stage in a section along an axially and radially extending plane.
  • Such cuts along the axis of rotation are also referred to as longitudinal cuts.
  • the terminology of the invention always refers to radial and axial components of the flow velocity.
  • the inventive combination of a decreasing radius of curvature with simultaneous expansion of the cross-sectional area perpendicular to the flow direction along the flow direction leads to a homogenization of the load on the flow over the course of the radial deflection as a result of deceleration and deflection, so that the tendency to a separation of the flow from the inner contour or Outer contour harmonized in a design according to the invention of the radial deflection and reduced in the top.
  • the flow in the course of the radial deflection as far as it is possible under the specification of the deflection braked without undue increase the tendency to detachment before the flow is deflected with a correspondingly delayed speed, in this section of the radial deflection only one less delay due to cross-sectional expansion takes place. It is also possible that there is no delay in this section.
  • the average flow direction means an average flow-weighted average flow velocity of the process fluid, perpendicular to the center line between the inner contour and the outer contour of the radial deflection along the cross-sectional width. Since the invention always considers the meridional section, the circumferential component is omitted in the context of a projection of the spatially oriented velocity, so that the average flow velocity can be described exclusively in the projection as the addition of an axial velocity and a radial velocity.
  • the projected mean flow direction - short flow direction - is to be understood as a magnitude normalized vector of the projected average flow velocity.
  • the cross-sectional area of the radial deflection has a direct influence on the flow velocity, so that as a result of the cross-sectional area widening in the direction of flow, the flow is retarded.
  • the invention according to the decreasing radius of curvature with progressing flow along the flow direction in the radial deflection is synonymous with an increasing curvature of the deflection.
  • the area increase of the cross-sectional area in the flow direction is preferably formed continuously. Furthermore, a steadily formed decrease of the radius of curvature in the flow direction is particularly preferred. Particularly preferred is a degressive area increase of the cross-sectional area in the flow direction. Excellent results are achieved with a degressive steady surface increase of the cross-sectional area in the flow direction, which has steadily decreased to 0 at the end of the radial deflection.
  • a further advantageous development provides that the radius of curvature is formed progressively decreasing in the flow direction and steadily decreases to a minimum at the end of the radial deflection, so that there is given a maximum curvature of a center line between the inner contour and the outer contour.
  • a particularly low-release design of the radial deflection can be achieved by a steadily progressive increase in curvature of the inner contour of the radial deflection in the flow direction and / or a steadily progressive increase in curvature of the outer contour in the flow direction.
  • One end of the section of the radial deflection is defined in the sense of the invention by an end of the outer contour and inner contour guided deflection of the flow radially inward, wherein a further deflection in the same direction, in which the total fluid is deflected more than 180 °, for example, to reduce the axial distance between 2 stages, also the radial deflection is attributable ,
  • the radial deflection is accordingly designed to be limited in the flow direction when the center line no longer has a curvature in the deflection direction of the radial deflection. At this point, the return duct begins, which directs the process fluid substantially straight radially inward.
  • radially inward in the context of the invention is not necessarily meant perpendicular to the axis of rotation, but simply the inversion of the flow from radially outward to radially inward, the resulting Strömungsrichtrung may differ after the deflection of the strictly radial direction.
  • FCSS> 1.5 FCSS> 1, 5
  • FCSS> 2.0 FCSS> 2.0
  • FCSS is greater than 1.4 (FCSS> 1.4), preferably greater than 1.5 (FCSS> 1.5) and is more preferably between 1.5-2.5 (1.5 ⁇ FCSS ⁇ 2.5).
  • An advantageous development of the invention provides that in the meridional section, the axial extent of the deflection directed from radially outward to the axial direction of the Flow of the process fluid takes place at a first axial plane, wherein the first axial plane between 7/12 to 11/12, preferably occupies 2/3 ⁇ 1/6 of the total axial extent of the center line in the radial deflection. It is postulated that the flow direction follows without deviation of the center line.
  • An advantageous development of the invention provides that in the meridional section the axial extension of the deflection of the center line is directed from radially outward to the axial direction of the center line at a first axial plane, wherein the first axial plane between 7 / 12 to 11/12, preferably occupying between 2/3 ⁇ 1/6 of the total axial extent of the center line in the radial deflection.
  • a further advantageous development provides that at least 65% of the total area widening of the cross-sectional area of the radial deflection is achieved at the axial position of the first axial plane.
  • a radial turbocompressor RTC is shown schematically in meridional section or longitudinal section.
  • the meridional section extends along a rotation axis X of a shaft SH of a rotor R of the radial turbocompressor RTC. Furthermore, the meridional section is defined through the radial direction so that the axis of rotation X and the radial direction span the plane of the cut. Accordingly, an extension in the circumferential direction of the rotation axis X is not reproduced, as well as in FIG. 2 that one with II in FIG. 1 represents reproduced detail.
  • a process fluid PF enters an impeller IMP or an impeller of the rotor R in a flow direction FD.
  • the process fluid PF is accelerated in the radial direction by means of the impeller IMP and introduced into the return stage RS.
  • the return stage RS is part of a stator ST, which is composed essentially of the components bucket bottom BD and intermediate bottom ID.
  • the blade bottom BD is here attached by means of return duct guide vanes GVRC to the intermediate bottom ID.
  • several combinations of shelves ID and blade bottoms BD of the stator ST line up axially.
  • the blade floors BD and the shelves ID are formed divided in the circumferential direction, so that an assembly of the rotor R with the stator ST by division of the stator ST in a generally horizontal parting line is possible.
  • the return stage RS comprises in the flow direction FD of the process fluid PF listed multiple sections SE, which form a flow channel from an impeller IMP to a downstream impeller IMP.
  • These sections SE are: a) an annular space RR, b) a radial deflection RT and c) a return channel RC.
  • To the sections may also be added to a less important for the invention section SE, namely a downstream axial deflection AT for axial entry into the downstream impeller.
  • the annular space RR can be formed bladed with annulus guide vanes GVRR or without blades, that is, unencumbered.
  • the radial deflection RT which is defined by an inner contour IC and an outer contour OC of the stator ST.
  • the radial deflection RT deflects the flow essentially from a radially outward-pointing direction into a radially inward-pointing direction, ie approximately 180 °. Because of the 180 ° deflection, the radial deflection is also often referred to as 180 ° deflection or 180 ° bend (equivalent: 180 ° turn, u-turn). From the eponymous 180 ° deflection, the actual deflection may differ for various, especially aerodynamic reasons.
  • FIG. 2 schematically shows a detail that in the FIG. 1 is indicated with "II" and the radial deflection RT reflects.
  • the radial deflection RT is also annular in the circumferential direction and extends around the rotation axis X.
  • the representations in the meridional section do not show the extent in the circumferential direction.
  • a process fluid PF flows into the radial deflection RT and is directed substantially radially outward, wherein the outflow from the radial deflection RT takes place radially inward.
  • the deflection takes place along a flow direction FD, wherein in the FIG. 2 only the projected mean flow direction PMFD is reproduced, which is identical in the schematic representation with the flow direction FD.
  • the actual flow has a significant share in the circumferential direction, so that the FIG. 2 shows only the projected mean flow direction PMFD omitting the reproduction of the circumferentially oriented component.
  • the inner contour IC and the outer contour OC define the flow channel of the radial deflection RT. Between the inner contour IC and the outer contour OC, a center line ML can be inscribed which is substantially congruent with the flow velocity FD or the mean projected flow direction PMFD. Perpendicular to the center line, the channel width B is plotted as a function of a coordinate s running along the center line ML in the flow direction FD.
  • a cross-sectional area CSS is congruent with the channel width in the projection of the meridional section B (s) and on the one hand function of the channel width B (s) and on the other hand depending on the diameter of the position of the respective channel width.
  • the center line ML runs along the radial deflection RT with a respective radius of curvature RBML (s) dependent on the coordinate s. Also dependent on the coordinate s is the radius of curvature of the inner contour RBIC (s) and the radius of curvature of the outer contour RBOC (s).
  • the meridional width of the cross-sectional area CSS widens with increasing flow direction FD from an inlet to an outlet of the radial deflection RT. In the beginning, the increase in area is stronger than the initial one - that is, decreasing. At the outset of the radial deflection, the cross-sectional area may also be decreasing-in particular due to the decrease in diameter when traveling radially inwards-so that slight accelerations may occur.
  • the radius of curvature of the center line ML is designed to be decreasing in the flow direction FD, as is the radius of curvature RBIC (s) of the inner contour IC, as well as the radius of curvature RBOC (S) of the outer contour OC.
  • the new design increases the maximum possible deceleration and thus reduces the losses in the deflection and the subsequent components due to a lower speed level.
  • the radial deflection RT according to the invention first brakes the flow and then redirects it.
  • the area increase of the cross-sectional area CSS is continuous over the course of the radial deflection RT.
  • the decrease in the radius of curvature in the flow direction FD of the center line ML, the outer contour OC and the inner contour IC are also constantly designed.
  • the area increase of the cross-sectional area CSS in the flow direction FD is preferably degressive continuous for the cross-sectional area CSS.
  • the decrease in the radius of curvature in the flow direction FD is progressively continuous for the radius of curvature of the center line RBML (s).
  • the increase in area is decreasing in the direction of the course coordinate s or the flow direction FD, the decrease in the radius of curvature in this direction is increasingly formed.
  • the axial extension of the deflection from radially outward of the center line ML to the axial direction to about 2/3 of the total axial extent of the radial deflection RT is carried out.
  • the remaining approximately 90 ° deflection from the axial direction into the radially inward flow direction FD take place on the last third of the entire axial extension of the radial deflection RT, wherein the axial extent as the distance of the center line ML between the entrance of the radial deflection RT and the outlet of the radial deflection RT is understood.
  • this first axial plane AXP1 in which the flow has been deflected from radially outward directed in the axial direction, positioned at an axial position between 7/12 to 11/12 the entire axial extent of the center line ML of the radial deflection RT.
  • the first axial plane AXP1 is between half of the total axial extent and 5/6 of the total axial extent. In the position the first axial plane AXP1 is already at least 65% of the total area expansion of the radial deflection RT in the flow direction FD reached.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft eine Rückführstufe gemäß Anspruch 1.The invention relates to a recycling stage according to claim 1.

Bei Radialturboverdichtern verlässt das Fluid das Laufrad radial nach außen und gelangt von dort in den Diffusor, welcher ebenfalls radial nach außen durchströmt wird. Um bei mehrstufigen Einwellenradialverdichtern, die in der Terminologie zu den Radialturboverdichtern gerechnet werden, das Prozessfluid der nächsten Stufe zuzuführen, wird das Prozessfluid in dem Abschnitt der Radialumlenkung, dem sogenannten 180°-Bogen von radial nach außen strömend umgelenkt in eine Strömung nach radial innen. In der Regel ist der Strömungsweg stromabwärts des 180°-Bogens beschaufelt ausgeführt, um den Drall des Fluides, der einen Teil der von dem Fluid gespeicherten kinetischen Energie ausmacht, in statischen Druck umzuwandeln - vergleichbar mit einer Umwandlung kinetischer Energie in potentielle Energie.
Die in dem Rückführkanal vorgesehenen Schaufeln werden auch als Rückführschaufeln bezeichnet. Stromabwärts der Rückführschaufeln wird das Prozessfluid in der Regel aus einer nach radial innen gerichteten Strömung in eine axiale Richtung umgelenkt, damit eine achsparallele Zuströmung in die stromabwärts gelegene Verdichtungsstufe erfolgen kann. Die tatsächlichen Umlenkungen, die das Prozessfluid in dem 180°-Bogen und in der stromabwärts gelegenen 90°-Umlenkung erfährt, kann von den namensgebenden Werten 180° und 90° abweichen. Die 180°-Umlenkung ist daher in der Terminologie der Erfindung meist als Radialumlenkung bezeichnet. Die stromabwärts des Rückführkanals vorgesehene 90°-Umlenkung in achsparallele Richtung zur Zuführung der nachfolgenden Stufe weist nach der Erfindung keine besondere Gestaltung auf und wird dementsprechend nicht näher beschrieben.
Eine vergleichbare mehrstufige Radialturbomaschine, nämlich eine Radialturbine ist bereits aus der EP 2 518 280 A1 bekannt. Auch, wenn in einer Radialturbine die Strömungsrichtung entgegen derjenigen in einem Radialverdichter verläuft ist es bisher durchaus üblich, die jeweilige Rückführstufe geometrisch zumindest annähernd gleich auszubilden. Der in dieser Schrift vorliegende Stand der Technik sieht vor, dass die Radialumlenkung eintrittsseitig und austrittsseitig jeweils eine im Wesentlichen identische Axialbreite aufweisen. Weiterhin ist vorgesehen, dass die Radialumlenkung einen im Wesentlichen konstanten Radius sowohl auf einer Innenkontur als auch auf einer Außenkontur aufweist. Diese Ausbildung der Radialumlenkung entspricht der einfachsten geometrischen Gestaltung und neigt in Folge von Ablösungserscheinungen an den Umlenkungsradien im Betrieb zu einem hohen Druckverlust.
Ausgehend von den Nachteilen des Standes der Technik hat es sich die Erfindung zur Aufgabe gemacht, die Radialumlenkung der Rückführstufe eines Radialturboverdichters der eingangs definierten Art derart weiterzubilden, dass vermeidbare Druckverluste reduziert sind und der Wirkungsgrad des Radialturboverdichters verbessert ist.
Zur Lösung der erfindungsgemäßen Aufgabe wird eine Rückführstufe der eingangs genannten Art mit den zusätzlichen Merkmalen des kennzeichnenden Teils des Anspruchs 1 vorgeschlagen. Vorteilhafte Weiterbildungen der Erfindung sind in den Unteransprüchen angegeben. Neben den expliziten Rückbezügen der Unteransprüche sind der Erfindung auch beliebige sinnvolle Kombinationen der hier aufgeführten Merkmale bzw. Weiterbildungen mit den Merkmalen des Hauptanspruchs zuzurechnen.
Unter einer Strömungsrichtung versteht die Erfindung bezogen auf die ganze Rückführstufe eine Fortbewegung eines Prozessfluids durch den mittels der Rückführstufe des Radialturboverdichters definierten Strömungskanal im Allgemeinen. Im Wesentlichen lässt sich diese Strömungsrichtung durch den mittleren Kanalverlauf unter Einzeichnung entsprechender Richtungspfeile kennzeichnen.In radial turbo compressors, the fluid leaves the impeller radially outward and from there into the diffuser, which is also flowed through radially outward. In multi-stage single-shaft centrifugal compressors, which are reckoned in the terminology of radial turbocompressors, to feed the process fluid to the next stage, the process fluid in the portion of the radial deflection, the so-called 180 ° arc, is deflected from radially outward to radially inward flow. Typically, the flow path downstream of the 180 ° arc is bladed to convert the swirl of the fluid, which is part of the kinetic energy stored by the fluid, into static pressure - comparable to converting kinetic energy into potential energy.
The vanes provided in the return duct are also referred to as return vanes. Downstream of the return vanes, the process fluid is usually deflected from a radially inwardly directed flow in an axial direction, so that an axially parallel inflow into the downstream compression stage can take place. The actual baffles affecting the process fluid in the 180 ° arc and in the downstream 90 ° deflection can deviate from the names giving values 180 ° and 90 °. The 180 ° deflection is therefore usually referred to in the terminology of the invention as a radial deflection. The 90 ° deflection provided downstream of the return channel in the direction parallel to the axis for feeding the subsequent stage has no special design according to the invention and will accordingly not be described in detail.
A comparable multi-stage radial turbomachine, namely a radial turbine is already out of the EP 2 518 280 A1 known. Even if the flow direction in a radial turbine runs counter to that in a radial compressor, it has hitherto been customary to form the respective return stage geometrically at least approximately the same. The state of the art in this document provides that the radial deflection on the inlet side and outlet side each have a substantially identical axial width. Furthermore, it is provided that the radial deflection has a substantially constant radius both on an inner contour and on an outer contour. This design of the radial deflection corresponds to the simplest geometric design and tends as a result of separation phenomena at the Umlenkungsradien in operation to a high pressure loss.
Based on the disadvantages of the prior art, it has the object of the invention to further develop the radial deflection of the return stage of a radial turbocompressor of the type defined in such a way that avoidable pressure losses are reduced and the efficiency of the radial turbocompressor is improved.
To achieve the object of the invention, a return stage of the type mentioned is proposed with the additional features of the characterizing part of claim 1. Advantageous developments of the invention are specified in the subclaims. In addition to the explicit back references of the subclaims, the invention also any meaningful combinations of the features listed here or Add further developments with the features of the main claim.
In terms of a flow direction, the invention relates to a movement of a process fluid relative to the entire return stage through the flow channel defined by means of the return stage of the radial turbocompressor in general. In essence, this direction of flow can be characterized by the middle channel course with the marking of corresponding directional arrows.

Die Abschnitte Ringraum, Radialumlenkung, Rückführkanal und Axialumlenkung der Rückführstufe sind sich jeweils ringförmig um eine Rotationsachse des Radialturboverdichters erstreckend ausgebildet.
Für jeden Meridionalschnitt durch eine erfindungsgemäße Rückführstufe ist eine Mittellinie zwischen der Außenkontur und der Innenkontur definiert als der Ort der Mittelpunkte der von den beiden Konturen tangierten Kreise. Da sich die Rückführstufe in Umfangsrichtung um die Rotationsachse des Radialturboverdichters erstreckt und damit einen Ringraum definiert, der im Wesentlichen rotationssymmetrisch zu der Rotationsachse ist, kann eine Mittelfläche zwischen der dreidimensionalen Innenkontur und der dreidimensionalen Außenkontur als Rotationsfläche der Mittellinie um die Rotationsachse angesehen werden.
Im Sinne der Erfindung ist die Beschreibung der Geometrie stets auf einen Meridionalschnitt durch den Radialturboverdichter bezogen, wobei der Meridionalschnitt sich entlang der Rotationsachse erstreckt und den durch die Rückführstufe definierten Strömungskanal in einem Schnitt entlang einer axial und radial verlaufenden Ebene darstellt. Derartige Schnitte entlang der Rotationsachse werden auch als Längsschnitte bezeichnet. Obwohl die real vorliegende Strömung durch die entsprechenden Ringräume der Rückführstufe, die zumindest teilweise in Umfangsrichtung von Leitschaufeln unterbrochen sein können, in der Regel eine signifikante Umfangskomponente aufweisen, bezieht sich die Terminologie der Erfindung stets auf radiale und axiale Komponenten der Strömungsgeschwindigkeit.The sections annular space, radial deflection, return channel and axial deflection of the return stage are each formed annularly extending around a rotational axis of the radial turbocompressor.
For each meridional section through a return stage according to the invention, a center line between the outer contour and the inner contour is defined as the location of the centers of the circles tangent to the two contours. Since the return stage extends in the circumferential direction about the axis of rotation of the radial turbocompressor and thus defines an annular space which is substantially rotationally symmetrical to the axis of rotation, a central area between the three-dimensional inner contour and the three-dimensional outer contour can be regarded as a rotation surface of the center line about the axis of rotation.
For the purposes of the invention, the description of the geometry is always based on a meridional section through the radial turbocompressor, wherein the meridional section extends along the axis of rotation and represents the flow channel defined by the return stage in a section along an axially and radially extending plane. Such cuts along the axis of rotation are also referred to as longitudinal cuts. Although the actual flow through the respective annular spaces of the return stage, which are at least partially interrupted in the circumferential direction of vanes can, as a rule, have a significant circumferential component, the terminology of the invention always refers to radial and axial components of the flow velocity.

Begriffe wie axial, radial, Umfangsrichtung oder sonstige Termini, die sich auf eine Achse beziehen lassen, sind - soweit nicht anders angegeben - auf die Rotationsachse des Radialturboverdichters bezogen.Terms such as axial, radial, circumferential direction or other terms that can be related to an axis, unless otherwise stated, related to the axis of rotation of the radial turbocompressor.

Die erfindungsgemäße Kombination eines abnehmenden Krümmungsradius bei gleichzeitiger Aufweitung der Querschnittsfläche senkrecht zur Strömungsrichtung entlang der Strömungsrichtung führt zu einer Vergleichmäßigung der Belastung der Strömung über den Verlauf der Radialumlenkung in Folge von Verzögerung und Umlenkung, so dass die Neigung zu einer Ablösung der Strömung von der Innenkontur oder Außenkontur bei einer erfindungsgemäßen Gestaltung der Radialumlenkung harmonisiert und in der Spitze reduziert ist. Erfindungsgemäß wird die Strömung im Verlaufe der Radialumlenkung zunächst, soweit es im Rahmen der Vorgabe des Umlenkens möglich ist, abgebremst ohne die Neigung zur Ablösung ungebührlich zu erhöhen, bevor die Strömung mit dementsprechend verzögerter Geschwindigkeit umgelenkt wird, wobei in diesem Abschnitt der Radialumlenkung nur noch eine geringere Verzögerung durch Querschnittsaufweitung erfolgt. Hierbei ist es auch möglich, dass in diesem Abschnitt gar keine Verzögerung vorgesehen ist.The inventive combination of a decreasing radius of curvature with simultaneous expansion of the cross-sectional area perpendicular to the flow direction along the flow direction leads to a homogenization of the load on the flow over the course of the radial deflection as a result of deceleration and deflection, so that the tendency to a separation of the flow from the inner contour or Outer contour harmonized in a design according to the invention of the radial deflection and reduced in the top. According to the invention, the flow in the course of the radial deflection, as far as it is possible under the specification of the deflection braked without undue increase the tendency to detachment before the flow is deflected with a correspondingly delayed speed, in this section of the radial deflection only one less delay due to cross-sectional expansion takes place. It is also possible that there is no delay in this section.

In der Terminologie der Erfindung bedeutet die mittlere Strömungsrichtung eine senkrecht zu der Mittellinie zwischen der Innenkontur und der Außenkontur der Radialumlenkung entlang der Querschnittsbreite - volumenstromgewichtete gemittelte Strömungsgeschwindigkeit des Prozessfluids.
Da die Erfindung stets den Meridionalschnitt betrachtet, entfällt im Rahmen einer Projektion der räumlich orientierten Geschwindigkeit die Umfangskomponente, so dass sich die mittlere Strömungsgeschwindigkeit ausschließlich in der Projektion als Addition einer Axialgeschwindigkeit und Radialgeschwindigkeit beschreiben lässt.In the terminology of the invention, the average flow direction means an average flow-weighted average flow velocity of the process fluid, perpendicular to the center line between the inner contour and the outer contour of the radial deflection along the cross-sectional width.
Since the invention always considers the meridional section, the circumferential component is omitted in the context of a projection of the spatially oriented velocity, so that the average flow velocity can be described exclusively in the projection as the addition of an axial velocity and a radial velocity.

Dementsprechend ist die projizierte mittlere Strömungsrichtung - kurz Strömungsrichtung - als betragsnormalisierter Vektor der projizierten mittleren Strömungsgeschwindigkeit zu verstehen.
Die Querschnittsfläche der Radialumlenkung hat dementsprechend einen direkten Einfluss auf die Strömungsgeschwindigkeit, so dass infolge der sich in Strömungsrichtung erweiternde Querschnittsfläche es zu einer Verzögerung der Strömung kommt.
Der erfindungsgemäß abnehmende Krümmungsradius mit fortschreitender Strömung entlang der Strömungsrichtung in der Radialumlenkung ist gleichbedeutend mit einer zunehmenden Krümmung der Umlenkung.Accordingly, the projected mean flow direction - short flow direction - is to be understood as a magnitude normalized vector of the projected average flow velocity.
Accordingly, the cross-sectional area of the radial deflection has a direct influence on the flow velocity, so that as a result of the cross-sectional area widening in the direction of flow, the flow is retarded.
The invention according to the decreasing radius of curvature with progressing flow along the flow direction in the radial deflection is synonymous with an increasing curvature of the deflection.

Bevorzugt ist im Bereich der Radialumlenkung die Flächenzunahme der Querschnittsfläche in Strömungsrichtung stetig ausgebildet.
Weiterhin besonders bevorzugt ist eine stetig ausgebildete Abnahme des Krümmungsradius in Strömungsrichtung.
Besonders bevorzugt ist eine degressive Flächenzunahme der Querschnittsfläche in Strömungsrichtung.
Hervorragende Ergebnisse werden mit einer degressiven stetigen Flächenzunahme der Querschnittsfläche in Strömungsrichtung erzielt, die am Ende der Radialumlenkung stetig bis auf 0 abgenommen hat.
Eine weitere vorteilhafte Weiterbildung sieht vor, dass der Krümmungsradius progressiv abnehmend in Strömungsrichtung ausgebildet ist und stetig bis auf ein Minimum am Ende der Radialumlenkung abnimmt, so dass dort eine maximale Krümmung einer Mittellinie zwischen der Innenkontur und der Außenkontur gegeben ist.
Eine besonders ablösungsarme Ausbildung der Radialumlenkung kann erreicht werden durch eine stetig progressive Krümmungszunahme der Innenkontur der Radialumlenkung in Strömungsrichtung und/oder eine stetig progressive Krümmungszunahme der Außenkontur in Strömungsrichtung.
Ein Ende des Abschnitts der Radialumlenkung ist im Sinne der Erfindung definiert durch ein Ende der von der Außenkontur und Innenkontur geführten Umlenkung der Strömung nach radial innen, wobei eine weitergehende Umlenkung in die gleich Richtung, bei der das Fluid in Summe mehr als 180° umgelenkt wird, zum Beispiel, um den axialen Abstand zwischen 2 Stufen zu reduzieren, ebenfalls der Radialumlenkung zuzurechnen ist.In the region of the radial deflection, the area increase of the cross-sectional area in the flow direction is preferably formed continuously.
Furthermore, a steadily formed decrease of the radius of curvature in the flow direction is particularly preferred.
Particularly preferred is a degressive area increase of the cross-sectional area in the flow direction.
Excellent results are achieved with a degressive steady surface increase of the cross-sectional area in the flow direction, which has steadily decreased to 0 at the end of the radial deflection.
A further advantageous development provides that the radius of curvature is formed progressively decreasing in the flow direction and steadily decreases to a minimum at the end of the radial deflection, so that there is given a maximum curvature of a center line between the inner contour and the outer contour.
A particularly low-release design of the radial deflection can be achieved by a steadily progressive increase in curvature of the inner contour of the radial deflection in the flow direction and / or a steadily progressive increase in curvature of the outer contour in the flow direction.
One end of the section of the radial deflection is defined in the sense of the invention by an end of the outer contour and inner contour guided deflection of the flow radially inward, wherein a further deflection in the same direction, in which the total fluid is deflected more than 180 °, for example, to reduce the axial distance between 2 stages, also the radial deflection is attributable ,

Die Radialumlenkung ist dementsprechend in Strömungsrichtung begrenzt ausgebildet, wenn die Mittellinie keine Krümmung mehr in die Umlenkrichtung der Radialumlenkung aufweist. An dieser Stelle fängt der Rückführkanal an, der das Prozessfluid im Wesentlichen gerade nach radial innen leitet.The radial deflection is accordingly designed to be limited in the flow direction when the center line no longer has a curvature in the deflection direction of the radial deflection. At this point, the return duct begins, which directs the process fluid substantially straight radially inward.

Mit "radial innen" ist im Sinne der Erfindung nicht zwingend senkrecht zur Rotationsachse gemeint, sondern schlicht die Umkehrung der Strömung von radial nach außen nach radial innen, wobei die resultierende Strömungsrichtrung nach der Umlenkung von der strikt radialen Richtung abweichen kann.By "radially inward" in the context of the invention is not necessarily meant perpendicular to the axis of rotation, but simply the inversion of the flow from radially outward to radially inward, the resulting Strömungsrichtrung may differ after the deflection of the strictly radial direction.

Eine andere vorteilhafte Weiterbildung der Erfindung sieht vor, dass die Rückführstufe im Bereich des Ringraums unbeschaufelt ausgebildet ist und ein Flächenverhältnis zwischen dem Eintritt der Radialumlenkung und dem Austritt der Radialumlenkung mindestens eine Vergrößerung der Querschnittsfläche um den Faktor FCSS > 1,5 (FCSS>1,5) vorsieht. Eine weitere Verbesserung lässt sich verzeichnen, wenn der Faktor FCSS mindestens 2,0 (FCSS>2,0) beträgt. Besonders hohe Wirkungsgrade lassen sich erzielen, wenn der Faktor FCSS zwischen 2,3 - 3,3 (2,3<FCSS<3,3) beträgt.Another advantageous embodiment of the invention provides that the return stage in the region of the annular space is designed to be unencooled and an area ratio between the entry of the radial deflection and the outlet of the radial deflection at least an increase in the cross-sectional area by the factor FCSS> 1.5 (FCSS> 1, 5). A further improvement can be observed if the FCSS factor is at least 2.0 (FCSS> 2.0). Particularly high efficiencies can be achieved if the FCSS factor is between 2.3 - 3.3 (2.3 <FCSS <3.3).

Eine andere vorteilhafte Weiterbildung sieht vor, dass der Ringraum vor dem Eintritt in die Radialumlenkung beschaufelt ausgebildet ist und der Faktor FCSS größer als 1,4 (FCSS>1,4) ist, bevorzugt größer als 1,5 (FCSS>1,5) ist und besonders bevorzugt zwischen 1,5 - 2,5 (1,5<FCSS<2,5) beträgt.Another advantageous embodiment provides that the annular space is formed bladed before entering the radial deflection and the factor FCSS is greater than 1.4 (FCSS> 1.4), preferably greater than 1.5 (FCSS> 1.5) and is more preferably between 1.5-2.5 (1.5 <FCSS <2.5).

Eine vorteilhafte Weiterbildung der Erfindung sieht vor, dass im Meridionalschnitt die axiale Erstreckung der Umlenkung von radial nach außen gerichtet bis in die Axialrichtung der Strömung des Prozessfluids an einer ersten Axialebene erfolgt, wobei die erste Axialebene zwischen 7/12 bis 11/12, bevorzugt zwischen 2/3 ± 1/6 der gesamten axialen Erstreckung der Mittellinie in der Radialumlenkung einnimmt.
Hierbei ist postuliert, dass die Strömungsrichtung ohne Abweichung der Mittellinie folgt.
Der Sachverhalt lässt sich also auch derart ausdrücken: Eine vorteilhafte Weiterbildung der Erfindung sieht vor, dass im Meridionalschnitt die axiale Erstreckung der Umlenkung der Mittellinie von radial nach außen gerichtet bis in die Axialrichtung der Mittellinie an einer ersten Axialebene erfolgt, wobei die erste Axialebene zwischen 7/12 bis 11/12, bevorzugt zwischen 2/3 ± 1/6 der gesamten axialen Erstreckung der Mittellinie in der Radialumlenkung einnimmt.An advantageous development of the invention provides that in the meridional section, the axial extent of the deflection directed from radially outward to the axial direction of the Flow of the process fluid takes place at a first axial plane, wherein the first axial plane between 7/12 to 11/12, preferably occupies 2/3 ± 1/6 of the total axial extent of the center line in the radial deflection.
It is postulated that the flow direction follows without deviation of the center line.
The situation can thus also be expressed as follows: An advantageous development of the invention provides that in the meridional section the axial extension of the deflection of the center line is directed from radially outward to the axial direction of the center line at a first axial plane, wherein the first axial plane between 7 / 12 to 11/12, preferably occupying between 2/3 ± 1/6 of the total axial extent of the center line in the radial deflection.

Eine weitere vorteilhafte Weiterbildung sieht vor, dass an der Axialposition der ersten Axialebene mindestens 65% der gesamten Flächenaufweitung der Querschnittsfläche der Radialumlenkung erreicht sind.A further advantageous development provides that at least 65% of the total area widening of the cross-sectional area of the radial deflection is achieved at the axial position of the first axial plane.

Im Folgenden ist die Erfindung anhand eines speziellen Ausführungsbeispiels unter Bezugnahme auf Zeichnungen näher erläutert. Es zeigen:

Figur 1
einen Meridionalschnitt durch eine Stufe eines Radialturboverdichters mit einer erfindungsgemäßen Rückführstufe in schematischer Darstellung,
Figur 2
ein Detail aus Figur 1, das dort mit II bezeichnet ist.
In the following the invention with reference to a specific embodiment with reference to drawings is explained in more detail. Show it:
FIG. 1
1 a meridional section through a stage of a radial turbocompressor with a return stage according to the invention, in a schematic illustration,
FIG. 2
a detail from FIG. 1 which is denoted there by II.

Die in Figur 1 gezeigte Rückführstufe RS eines Radialturboverdichters RTC ist schematisch im Meridionalschnitt oder auch Längsschnitt dargestellt.In the FIG. 1 shown feedback stage RS a radial turbocompressor RTC is shown schematically in meridional section or longitudinal section.

Der Meridionalschnitt erstreckt sich entlang einer Rotationsachse X einer Welle SH eines Rotors R des Radialturboverdichters RTC. Weiterhin ist der Meridionalschnitt definiert durch die Radialrichtung, so dass die Rotationsachse X und die Radialrichtung die Ebene des Schnitts aufspannen. Dementsprechend ist eine Erstreckung in Umfangsrichtung der Rotationsachse X nicht wiedergegeben, wie auch in Figur 2, die ein mit II in Figur 1 wiedergegebenes Detail darstellt.The meridional section extends along a rotation axis X of a shaft SH of a rotor R of the radial turbocompressor RTC. Furthermore, the meridional section is defined through the radial direction so that the axis of rotation X and the radial direction span the plane of the cut. Accordingly, an extension in the circumferential direction of the rotation axis X is not reproduced, as well as in FIG. 2 that one with II in FIG. 1 represents reproduced detail.

Ein Prozessfluid PF tritt in einer Strömungsrichtung FD in einen Impeller IMP bzw. ein Laufrad des Rotors R ein. Das Prozessfluid PF wird in radiale Richtung mittels des Impellers IMP beschleunigt und in die Rückführstufe RS eingeleitet. Die Rückführstufe RS ist Bestandteil eines Stators ST, der im Wesentlichen aus den Bestandteilen Schaufelboden BD und Zwischenboden ID zusammengesetzt ist. Der Schaufelboden BD ist hierbei mittels Rückführkanalleitschaufeln GVRC an dem Zwischenboden ID angebracht. In der Abfolge mehrerer - hier nicht dargestellter - Verdichtungsstufen mit eigenen Impellern IMP reihen sich mehrere Kombinationen aus Zwischenböden ID und Schaufelböden BD des Stators ST axial aneinander. In der Regel sind die Schaufelböden BD und die Zwischenböden ID in Umfangsrichtung geteilt ausgebildet, so dass ein Zusammenfügen des Rotors R mit dem Stator ST durch Teilung des Stators ST in einer in der Regel horizontalen Teilfuge möglich ist.A process fluid PF enters an impeller IMP or an impeller of the rotor R in a flow direction FD. The process fluid PF is accelerated in the radial direction by means of the impeller IMP and introduced into the return stage RS. The return stage RS is part of a stator ST, which is composed essentially of the components bucket bottom BD and intermediate bottom ID. The blade bottom BD is here attached by means of return duct guide vanes GVRC to the intermediate bottom ID. In the sequence of several - not shown here - compression stages with their own impellers IMP several combinations of shelves ID and blade bottoms BD of the stator ST line up axially. In general, the blade floors BD and the shelves ID are formed divided in the circumferential direction, so that an assembly of the rotor R with the stator ST by division of the stator ST in a generally horizontal parting line is possible.

Die Rückführstufe RS umfasst in Strömungsrichtung FD des Prozessfluids PF aufgeführt mehrere Abschnitte SE, die einen Strömungskanal von einem Impeller IMP zu einem stromabwärts gelegenen Impeller IMP bilden. Diese Abschnitte SE sind: a) ein Ringraum RR, b) eine Radialumlenkung RT und c) ein Rückführkanal RC. Zu den Abschnitten kann außerdem ein für die Erfindung weniger wichtiger Abschnitt SE hinzugerechnet werden, nämliche eine stromabwärts gelegene Axialumlenkung AT für einen axialen Eintritt in das stromabwärts gelegene Laufrad.The return stage RS comprises in the flow direction FD of the process fluid PF listed multiple sections SE, which form a flow channel from an impeller IMP to a downstream impeller IMP. These sections SE are: a) an annular space RR, b) a radial deflection RT and c) a return channel RC. To the sections may also be added to a less important for the invention section SE, namely a downstream axial deflection AT for axial entry into the downstream impeller.

Der Ringraum RR kann mit Ringraumleitschaufeln GVRR beschaufelt ausgebildet sein oder ohne Schaufeln, also unbeschaufelt. Für die Erfindung von besonderem Interesse ist die Radialumlenkung RT, die von einer Innenkontur IC und einer Außenkontur OC des Stators ST definiert ist. Die Radialumlenkung RT lenkt die Strömung im Wesentlichen von einer radial nach außen weisenden Richtung in eine radial nach innen weisende Richtung um, demensprechend um etwa 180°. Aus dem Grund der 180°-Umlenkung wird die Radialumlenkung auch häufig als 180°-Umlenkung oder 180°-Bogen (englich: 180°-turn, u-turn) bezeichnet. Von der namensgebenden 180°-Umlenkung kann die tatsächliche Umlenkung aus verschiedenen, insbesondere aerodynamischen Gründen abweichen.The annular space RR can be formed bladed with annulus guide vanes GVRR or without blades, that is, unencumbered. Of particular interest to the invention the radial deflection RT, which is defined by an inner contour IC and an outer contour OC of the stator ST. The radial deflection RT deflects the flow essentially from a radially outward-pointing direction into a radially inward-pointing direction, ie approximately 180 °. Because of the 180 ° deflection, the radial deflection is also often referred to as 180 ° deflection or 180 ° bend (equivalent: 180 ° turn, u-turn). From the eponymous 180 ° deflection, the actual deflection may differ for various, especially aerodynamic reasons.

Figur 2 zeigt schematisch ein Detail, das in der Figur 1 mit "II" ausgewiesen ist und die Radialumlenkung RT wiedergibt. Wie die gesamte Rückführstufe RS ist auch die Radialumlenkung RT ringförmig sich in Umfangsrichtung erstreckend um die Rotationsachse X ausgebildet. Die Darstellungen im Meridionalschnitt zeigen die Ausdehnung in Umfangsrichtung nicht. Ein Prozessfluid PF strömt in die Radialumlenkung RT ein und ist dabei im Wesentlichen nach radial außen gerichtet, wobei die Ausströmung aus der Radialumlenkung RT nach radial innen erfolgt. Die Umlenkung erfolgt entlang einer Strömungsrichtung FD, wobei in der Figur 2 nur die projizierte mittlere Strömungsrichtung PMFD wiedergegeben ist, die in der schematischen Wiedergabe identisch ist mit der Strömungsrichtung FD. Die tatsächliche Strömung hat eine signifikante Anteiligkeit in Umfangsrichtung, so dass die Figur 2 nur die projizierte mittlere Strömungsrichtung PMFD unter Fortlassung der Wiedergabe der in Umfangsrichtung orientierten Komponente zeigt. Die Innenkontur IC und die Außenkontur OC definieren den Strömungskanal der Radialumlenkung RT. Zwischen der Innenkontur IC und der Außenkontur OC lässt sich eine Mittellinie ML einzeichnen, die im Wesentlichen deckungsgleich ist mit der Strömungsgeschwindigkeit FD bzw. der mittleren projizierten Strömungsrichtung PMFD. Senkrecht zu der Mittellinie ist die Kanalbreite B als Funktion einer entlang der Mittellinie ML in Strömungsrichtung FD verlaufenden Koordinate s eingezeichnet. Eine Querschnittsfläche CSS ist in der Projektion des Meridionalschnitts deckungsgleich mit der Kanalbreite B(s) und ist einerseits Funktion der Kanalbreite B(s) und andererseits abhängig von dem Durchmesser der Position der jeweiligen Kanalbreite. FIG. 2 schematically shows a detail that in the FIG. 1 is indicated with "II" and the radial deflection RT reflects. Like the entire return stage RS, the radial deflection RT is also annular in the circumferential direction and extends around the rotation axis X. The representations in the meridional section do not show the extent in the circumferential direction. A process fluid PF flows into the radial deflection RT and is directed substantially radially outward, wherein the outflow from the radial deflection RT takes place radially inward. The deflection takes place along a flow direction FD, wherein in the FIG. 2 only the projected mean flow direction PMFD is reproduced, which is identical in the schematic representation with the flow direction FD. The actual flow has a significant share in the circumferential direction, so that the FIG. 2 shows only the projected mean flow direction PMFD omitting the reproduction of the circumferentially oriented component. The inner contour IC and the outer contour OC define the flow channel of the radial deflection RT. Between the inner contour IC and the outer contour OC, a center line ML can be inscribed which is substantially congruent with the flow velocity FD or the mean projected flow direction PMFD. Perpendicular to the center line, the channel width B is plotted as a function of a coordinate s running along the center line ML in the flow direction FD. A cross-sectional area CSS is congruent with the channel width in the projection of the meridional section B (s) and on the one hand function of the channel width B (s) and on the other hand depending on the diameter of the position of the respective channel width.

Die Mittellinie ML verläuft entlang der Radialumlenkung RT mit einem jeweils von der Koordinate s abhängigen Krümmungsradius RBML(s). Gleichfalls abhängig von der Koordinate s ist der Krümmungsradius der Innenkontur RBIC(s) und der Krümmungsradius der Außenkontur RBOC(s). Die meridionale Breite der Querschnittsfläche CSS weitet sich mit fortschreitender Strömungsrichtung FD von einem Eintritt zu einem Austritt der Radialumlenkung RT auf. Die Flächenzunahme ist hierbei eingangs stärker als ausgangs - also abnehmend gestaltet. Die Querschnittsfläche kann ausgangs der Radialumlenkung auch abnehmend sein - insbesondere aufgrund der Durchmesserabnahme bei der Fortbewegung nach radial innen- so dass es zu geringen Beschleunigungen kommen kann. Der Krümmungsradius der Mittellinie ML ist in Strömungsrichtung FD, wie auch der Krümmungsradius RBIC(s) der Innenkontur IC, wie auch der Krümmungsradius RBOC(S) der Außenkontur OC, abnehmend gestaltet. Auf diese Weise wird die Belastung der Strömung, die bei Überschreiten einer gewissen Reynolds-Zahl zu Ablösungserscheinungen führen kann, in etwa konstant gehalten, so dass es im Betrieb nicht zu unnötigen Druckverlusten kommt. Das neue Design erhöht die maximal mögliche Verzögerung und reduziert somit aufgrund eines niedrigeren Geschwindigkeitniveaus die Verluste in der Umlenkung und den nachfolgenden Komponenten. Die Radialumlenkung RT nach der Erfindung bremst zunächst die Strömung ab und lenkt diese dann um. Hierbei findet jedoch eine Umlenkung und Abbremsung bereits bei Eintritt in die Radialumlenkung RT statt. Die Schwerpunkte dieser beiden strömungsleitenden Maßnahmen verschieben sich von der eingänglichen hauptsächlichen Verzögerung hin zur mehr in Richtung Ausgang stattfindender häuptsächlichen Umlenkung. Die Flächenzunahme der Querschnittsfläche CSS ist über den Verlauf der Radialumlenkung RT stetig gestaltet. Die Abnahme des Krümmungsradius in Strömungsrichtung FD der Mittellinie ML, der Außenkontur OC und der Innenkontur IC sind ebenfalls stetig gestaltet. Die Flächenzunahme der Querschnittsfläche CSS in Strömungsrichtung FD ist bevorzugt degressiv stetig für die Querschnittsfläche CSS. Gleichfalls ist die Abnahme des Krümmungsradius in Strömungsrichtung FD progressiv stetig für den Krümmungsradius der Mittellinie RBML(s). Mit anderen Worten: während in Richtung der Verlaufskoordinate s bzw. der Strömungsrichtung FD der Flächenzuwachs abnehmend ausgebildet ist, ist die Abnahme des Krümmungsradius in diese Richtung zunehmend ausgebildet.The center line ML runs along the radial deflection RT with a respective radius of curvature RBML (s) dependent on the coordinate s. Also dependent on the coordinate s is the radius of curvature of the inner contour RBIC (s) and the radius of curvature of the outer contour RBOC (s). The meridional width of the cross-sectional area CSS widens with increasing flow direction FD from an inlet to an outlet of the radial deflection RT. In the beginning, the increase in area is stronger than the initial one - that is, decreasing. At the outset of the radial deflection, the cross-sectional area may also be decreasing-in particular due to the decrease in diameter when traveling radially inwards-so that slight accelerations may occur. The radius of curvature of the center line ML is designed to be decreasing in the flow direction FD, as is the radius of curvature RBIC (s) of the inner contour IC, as well as the radius of curvature RBOC (S) of the outer contour OC. In this way, the load on the flow, which can lead to separation phenomena when a certain Reynolds number is exceeded, kept approximately constant, so that it does not come to unnecessary pressure losses during operation. The new design increases the maximum possible deceleration and thus reduces the losses in the deflection and the subsequent components due to a lower speed level. The radial deflection RT according to the invention first brakes the flow and then redirects it. Here, however, a deflection and deceleration already takes place upon entry into the radial deflection RT. The main focuses of these two flow-guiding measures shift from the initial main deceleration to the main deceleration, which is more towards the exit. The area increase of the cross-sectional area CSS is continuous over the course of the radial deflection RT. The decrease in the radius of curvature in the flow direction FD of the center line ML, the outer contour OC and the inner contour IC are also constantly designed. The area increase of the cross-sectional area CSS in the flow direction FD is preferably degressive continuous for the cross-sectional area CSS. Likewise, the decrease in the radius of curvature in the flow direction FD is progressively continuous for the radius of curvature of the center line RBML (s). In other words, while the increase in area is decreasing in the direction of the course coordinate s or the flow direction FD, the decrease in the radius of curvature in this direction is increasingly formed.

Ein Vergleich der Flächenzunahme über die Radialumlenkung RT, also der Querschnittsfläche CSS(SE) (Querschnittsfläche am Eintritt der Radialumlenkung RT) und CSS(SA) (Querschnittsfläche am Austritt der Radialumlenkung RT) führt zu einer Flächenzunahme um den Faktor FCSS > 1,5, bevorzugt zwischen 2,3<FCSS<3,3, vorliegend beträgt der Faktor FCSS=2,5. Diese Angaben gelten für einen unbeschaufelten Ringraum RR, wobei bei einem beschaufelten Ringraum RR der Faktor FCSS>1,4 ausgebildet ist und bevorzugt zwischen 1,5 und 2,5 (1,5<FCSS<2,5) liegt.A comparison of the area increase over the radial deflection RT, ie the cross-sectional area CSS (SE) (cross-sectional area at the entrance of the radial deflection RT) and CSS (SA) (cross-sectional area at the outlet of the radial deflection RT) leads to an area increase by the factor FCSS> 1.5, preferably between 2.3 <FCSS <3.3, in the present case the factor FCSS = 2.5. This information applies to an unearthed annulus RR, wherein in a bladed annulus RR, the factor FCSS> 1.4 is formed and preferably between 1.5 and 2.5 (1.5 <FCSS <2.5).

Im Meridionalschnitt ist die axiale Erstreckung der Umlenkung von radial nach außen der Mittellinie ML bis in die Axialrichtung auf etwa 2/3 der gesamten Axialerstreckung der Radialumlenkung RT erfolgt. Die restlichen etwa 90°-Umlenkung von der Axialrichtung in die nach radial innen gerichtete Strömungsrichtung FD erfolgen auf dem letzten Drittel der gesamten Axialerstreckung der Radialumlenkung RT, wobei die Axialerstreckung als der Abstand der Mittellinie ML zwischen dem Eintritt der Radialumlenkung RT und dem Austritt der Radialumlenkung RT verstanden wird. Im Rahmen der Erfindung ist diese erste Axialebene AXP1, in der die Strömung von radial nach außen gerichtet in die Axialrichtung umgelenkt worden ist, an einer Axialposition zwischen 7/12 bis 11/12 der gesamten axialen Erstreckung der Mittellinie ML der Radialumlenkung RT positioniert. Bevorzugt befindet sich die erste Axialebene AXP1 zwischen der Hälfte der gesamten Axialerstreckung und 5/6 der gesamten Axialerstreckung. In der Position der ersten Axialebene AXP1 ist bereits mindestens 65% der gesamten Flächenaufweitung der Radialumlenkung RT in Strömungsrichtung FD erreicht.In the meridional section, the axial extension of the deflection from radially outward of the center line ML to the axial direction to about 2/3 of the total axial extent of the radial deflection RT is carried out. The remaining approximately 90 ° deflection from the axial direction into the radially inward flow direction FD take place on the last third of the entire axial extension of the radial deflection RT, wherein the axial extent as the distance of the center line ML between the entrance of the radial deflection RT and the outlet of the radial deflection RT is understood. In the context of the invention, this first axial plane AXP1, in which the flow has been deflected from radially outward directed in the axial direction, positioned at an axial position between 7/12 to 11/12 the entire axial extent of the center line ML of the radial deflection RT. Preferably, the first axial plane AXP1 is between half of the total axial extent and 5/6 of the total axial extent. In the position the first axial plane AXP1 is already at least 65% of the total area expansion of the radial deflection RT in the flow direction FD reached.

Claims (14)

  1. Recirculation stage (RS) for a radial turbo compressor (RTC), implemented in the flow direction (FD) of a process fluid (PF), comprising the following sections (SE):
    a) an annular space (RR),
    b) a radial turn (RT),
    c) a recirculation channel (RC),
    wherein the radial turn (RT) is formed by an outer contour (OC) and an inner contour (IC),
    wherein for each meridional section there is defined a midline (ML), between the outer contour (OC) and the inner contour (IC), as the location of the midpoints of the circles tangential to both contours,
    characterized in that
    the radial turn (RT) has, in the meridional section, over at least the first 150° of the turn, a widening in the flow direction (FD) of the flowed-through meridional width, extending perpendicular to the midline (ML), of the cross-sectional surface area (CSS),
    wherein the midline (ML) has, in the radial turn (RT), a radius of curvature (BRML) that decreases in the flow direction (FD).
  2. Recirculation stage (RS) according to Claim 1,
    wherein an increase in the cross-sectional surface area (CSS), as a consequence of the increase in the meridional width, is designed to be constant in the flow direction (FD) .
  3. Recirculation stage (RS) according to Claim 1,
    wherein in the meridional section the recirculation stage (RS) has, in the radial turn (RT), over at least the first 180° of the turn, a widening in the flow direction (FD) of the flowed-through meridional width, extending perpendicular to the midline (ML), of the cross-sectional surface area (CSS).
  4. Recirculation stage (RS) according to Claim 1, 2 or 3,
    wherein a radius of curvature of the midline (ML), of the outer contour (OC) or of the inner contour (IC) is designed to be constantly decreasing in the flow direction (FD).
  5. Recirculation stage (RS) according to one of the preceding Claims 1 to 4,
    wherein the increase in the cross-sectional surface area (CSS) in the flow direction (FD) is constantly decreasing.
  6. Recirculation stage (RS) according to Claim 4,
    wherein the radius of curvature is designed to decrease progressively.
  7. Recirculation stage (RS) according to one of the preceding Claims 1 to 6,
    wherein the annular space (RR) is designed without blades and a surface area ratio (FCSS) of the cross-sectional surface area (CSS) between an entry to the radial turn (RT) and an exit from the radial turn (RT) differs by at least a factor (FCSS) of 1.5.
  8. Recirculation stage (RS) according to Claim 7,
    wherein the factor (FCSS) is at least 2.0.
  9. Recirculation stage (RS) according to Claim 8,
    wherein the factor (FCSS) is between 2.3 and 3.3.
  10. Recirculation stage (RS) according to one of the preceding Claims 1 to 6,
    wherein the annular space (RR) is designed with blades and the surface area ratio of the cross-sectional surface area (CSS) between an entry to the radial turn (RT) and an exit from the radial turn (RT) differs by a factor (FCSS) of at least 1.4.
  11. Recirculation stage (RS) according to Claim 10,
    wherein the factor (FCSS) is at least 1.5.
  12. Recirculation stage (RS) according to Claim 11,
    wherein the factor (FCSS) is less than 2.5.
  13. Recirculation stage (RS) according to at least one of the preceding claims,
    wherein in the meridional section the axial extent of the turn from radially outside the midline (ML) to the axial direction extends up to a first axial plane (AXP1) that extends between 7/12 and 11/12, preferably between 2/3-1/6 and 2/3+1/6, of the entire axial extent of the midline (ML) of the radial turn (RT).
  14. Recirculation stage (RS) according to Claim 13,
    wherein, at the first axial plane (AXP1), at least 65% of the entire surface area widening of the radial turn (RT) has taken place.
EP15797326.4A 2014-11-21 2015-11-19 Recirculation stage Not-in-force EP3194792B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014223833.1A DE102014223833A1 (en) 2014-11-21 2014-11-21 Return step
PCT/EP2015/077052 WO2016079222A1 (en) 2014-11-21 2015-11-19 Recirculation stage

Publications (2)

Publication Number Publication Date
EP3194792A1 EP3194792A1 (en) 2017-07-26
EP3194792B1 true EP3194792B1 (en) 2018-09-26

Family

ID=54601787

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15797326.4A Not-in-force EP3194792B1 (en) 2014-11-21 2015-11-19 Recirculation stage

Country Status (3)

Country Link
EP (1) EP3194792B1 (en)
DE (1) DE102014223833A1 (en)
WO (1) WO2016079222A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3364039A1 (en) * 2017-02-21 2018-08-22 Siemens Aktiengesellschaft Recirculation stage
EP3798453A1 (en) 2019-09-26 2021-03-31 Siemens Aktiengesellschaft Flow control of a radial turbomachine, recirculation stage, radial turbomachine, and method of manufacture

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1997033092A1 (en) * 1996-03-06 1997-09-12 Hitachi, Ltd. Centrifugal compressor and diffuser for the centrifugal compressor
JP3569087B2 (en) * 1996-11-05 2004-09-22 株式会社日立製作所 Multistage centrifugal compressor
JPH11173299A (en) * 1997-12-05 1999-06-29 Mitsubishi Heavy Ind Ltd Centrifugal compressor
JP2003083281A (en) * 2001-09-06 2003-03-19 Mitsubishi Heavy Ind Ltd Method for modifying multi-stage centrifugal compressor
JP2010216456A (en) * 2009-03-19 2010-09-30 Hitachi Plant Technologies Ltd Multistage centrifugal compressor, and method for remodeling multistage centrifugal compressor
JP2011132877A (en) 2009-12-24 2011-07-07 Mitsubishi Heavy Ind Ltd Multistage radial turbine
JP6140736B2 (en) * 2013-01-28 2017-05-31 三菱重工業株式会社 Centrifugal rotating machine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
WO2016079222A1 (en) 2016-05-26
DE102014223833A1 (en) 2016-05-25
EP3194792A1 (en) 2017-07-26

Similar Documents

Publication Publication Date Title
EP3167195B1 (en) Return channel of a multistage turbocompressor or turboexpander with rough wall surfaces
EP2993357B1 (en) Radial compressor stage
DE10350626B4 (en) Ripple seal and streamline configuration for a turbine
DE102009023100A1 (en) Turbomachine with a blade row group with meridionalem edge distance
CH710476B1 (en) Compressor with an axial compressor end wall device for controlling the leakage flow in this.
EP2913480B1 (en) Tandem blades of a turbo-machine
EP3568597B1 (en) Return stage and radial turbo fluid energy machine
DE102014012764A1 (en) Radial compressor stage
EP3417176A1 (en) Diffuser of a radial-flow compressor
EP3194792B1 (en) Recirculation stage
EP2597257B1 (en) Blades
EP2913481B1 (en) Tandem blades of a turbo-machine
EP1865148B1 (en) Flow machine with rotors with a high specific energy transfer
EP3737865B1 (en) Turbomachine inner housing
EP3390832B1 (en) Backfeed stage of a radial turbo fluid energy machine
WO2011036206A1 (en) Radial compressor diffuser
DE102014222877A1 (en) Impeller of a radial turbofan energy machine, stage
EP4015832A1 (en) Static flow guide, radial turbomachine
CH655357A5 (en) Method and device for reducing the axial thrust in turbo machines
EP0985803B1 (en) Turbine stage with radial inlet and axial outlet
WO2004001222A1 (en) Impeller for compact turbo machines
DE2351308C3 (en) Device for expanding the working range of axial flow machines
EP3173581B1 (en) Compressor of a turbomachine
DE102014218663A1 (en) Radial turbo fluid energy machine
DE1428170C (en) Runner for a multistage centrifugal compressor

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20170421

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20180507

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

Ref country code: AT

Ref legal event code: REF

Ref document number: 1046358

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181015

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502015006161

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180926

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181226

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181226

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181227

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190126

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190126

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015006161

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181119

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20181130

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

26N No opposition filed

Effective date: 20190627

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181119

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20151119

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180926

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180926

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20191119

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191119

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502015006161

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 20210202

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20210119

Year of fee payment: 6

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1046358

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201119

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201119

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20211119

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20211122

Year of fee payment: 7

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502015006161

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211130

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220601

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20221119

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20221130