EP3194792A1 - Recirculation stage - Google Patents

Recirculation stage

Info

Publication number
EP3194792A1
EP3194792A1 EP15797326.4A EP15797326A EP3194792A1 EP 3194792 A1 EP3194792 A1 EP 3194792A1 EP 15797326 A EP15797326 A EP 15797326A EP 3194792 A1 EP3194792 A1 EP 3194792A1
Authority
EP
European Patent Office
Prior art keywords
deflection
radial
radial deflection
feedback stage
flow direction
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.)
Granted
Application number
EP15797326.4A
Other languages
German (de)
French (fr)
Other versions
EP3194792B1 (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

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 return step of a radial turbo compressor ⁇ in the flow direction of a process fluid up ⁇ performs the following sections comprising:
  • said portions are each formed annularly around a rotational property ⁇ se of the radial extending turbocompressor, wherein the radial deflection is formed by an outer contour and an inner contour.
  • the fluid leaves the impeller ⁇ ra dial outwards and passes from there into the diffuser, which is also flows radially outwardly.
  • the process fluid is in the portion of the radial deflection, the so-called 180 degree arc from the radially outwardly flowing deflected into a flow radially Inside.
  • the flow path downstream of the 180 ° arc is bladed to prevent the swirl of the
  • vanes provided in the return duct are also referred to as return vanes. Downstream of
  • the process fluid is usually deflected from ei ⁇ ner radially inwardly directed flow in an axial direction, so that an axis-parallel inflow into the downstream compression stage can be done.
  • 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 downstream ⁇ Wind concept of the return duct provided for the 90 ° deflection in achspa- rallele direction for supplying the subsequent stage has according to the invention, no special configuration and is accordingly not described in detail.
  • a similar multi-stage centrifugal turbomachine namely, a radial turbine is already known from EP 2518280 Al ⁇ be 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 prior art provides that the radial deflection per ⁇ wells having inlet side and outlet side, 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 with a high pressure drop. 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
  • the invention Under a direction of flow, 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 turbo ⁇ compressor in general.
  • this flow direction can tung arrows mark by the middle channel course under appropriate delineation RICH.
  • the sections annulus, radial deflection, Rü + ck Crystalkanal and axial deflection of the return stage are each formed annularly extending around a rotational axis of the radial turbocompressor.
  • Return stage is a center line between the outer contour and the inner contour defined as the location of the centers of the circles contiguous by the two contours. Since the return step in the circumferential direction extending about the rotation axis of the centrifugal turbocompressor and thus an annular space de ⁇ finiert which is rotationally symmetrical to the axis of rotation substantially a center area between the three-dimensional inner contour and the three-dimensional outer contour as a surface of revolution of the center line around the rotation axis can at ⁇ be seen.
  • the description of the geometry is always related to a meridional section through the radial turbo compressor, wherein the meridional section extending along the axis of rotation and represents the de ⁇ -defined by the feedback stage flow channel in a section along an axially and radially extending plane.
  • Such sections along the axis of rotation are also be ⁇ as longitudinal sections.
  • the inventive combination of a decreasing curve ⁇ radius with simultaneous widening of the cross-sectional area perpendicular to the flow direction along the flow direction leads to an equalization of the load of the flow over the course of the radial deflection as a result of deceleration and deflection, so that the tendency to separation of the flow from the Inner contour or outer contour harmonized in an inventive design of the radial deflection and is 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 by QueritessaufWei ⁇ tion takes place.
  • this From ⁇ cut no delay is provided.
  • the average Strö ⁇ flow direction means a perpendicular to the center line between the inner contour and the outer contour of the radial deflection along the cross-sectional width - volumetric flow weighted average flow rate of the process fluid.
  • the invention is always considered the meridional ent ⁇ falls within a projection of the spatially oriented speed, the circumferential component, so that the mitt ⁇ sized flow velocity can be described as addition and an axial velocity Radialge ⁇ speed exclusively in the projec ⁇ on. Accordingly, the projected mean flow direction Rich ⁇ tion - 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 accordingly spre ⁇ accordingly a direct impact on the Strömungsgeschwindig ⁇ ness, so as a result of the widening in the direction of flow cross-sectional area results in a delay of Strö ⁇ tion.
  • decreasing radius of curvature continuously ⁇ border flow along the flow direction in the radial deflection is equivalent to an increasing curvature of the deflection.
  • Preferably in the range of the radial deflection of the ceremoninzu ⁇ acquisition of the cross-sectional area in the flow direction is continuously formed from ⁇ .
  • Particularly preferred is a degressive area increase of the cross-sectional area in the flow direction.
  • 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 curvature ⁇ increase the inner contour of the radial deflection in the flow direction and / or a steadily progressive curvature zunähme 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 channel begins, which conducts the process fluid essentially straight radially inward.
  • radially inward in the sense 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 Cross sectional area by the factor FCSS> 1.5 (FCSS> 1.5).
  • FCSS factor is at least 2.0 (FCSS> 2.0).
  • FCSS is between 2.3 - 3.3 (2, 3 ⁇ FCSS ⁇ 3, 3).
  • FCSS is greater than 1.4 (FCSS> 1.4), preferably greater than 1.5 (FCSS> 1.5), and 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 at a first axial plane he follows ⁇ , with the 1 ° e ⁇ preferably between g takes the center line in the radial deflection.
  • An advantageous development of the invention provides that in the meridional section, the axial extent of the deflection of the center line from radially outward to the axial ⁇ direction of the center line at a first axial plane, which preferably between the middle
  • 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.
  • FIG. 1 shows a meridional section through a stage of a Ra ⁇ dialturbover Actuallyrs with a return stage according to the invention in a schematic representation
  • Figure 2 shows a detail of Figure 1, which is designated there by II.
  • the feedback stage RS of a radial turbo ⁇ compressor RTC shown in Figure 1 is shown schematically in the meridional section or longitudinal section.
  • the meridional section extends along an axis of rotation X of a shaft SH of a rotor R of the radial turbocharger ⁇ 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. Dement ⁇ speaking, an extension in the circumferential direction of the axis of rotation X is not reproduced, as well as in Figure 2, which represents a reproduced with II in Figure 1 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 in the radial direction by means of
  • the feedback stage RS is part of a
  • Stators ST which is essentially composed of the components bucket bottom BD and intermediate bottom ID.
  • the bucket bottom BD is hereby means
  • the return stage RS comprises in the flow direction FD of the process fluid PF listed several sections SE, which form a flow channel from an impeller IMP to a downstream impeller IMP. These sections SE are:
  • the annulus RR can with annulus guide GVRR
  • 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 directs flow substantially from a radially outwardly facing direction in a radially inward direction, demenwitzend by about 180 °.
  • 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 shows schematically a detail which is indicated by "II" in FIG. 1 and which reproduces the radial deflection RT.
  • the radial deflection RT is also formed annularly in the circumferential direction around the rotation axis X.
  • Meridional section does not show the extent in the circumferential direction.
  • a process fluid PF flows into the radial deflection RT and is directed essentially radially outward, the outflow from the radial deflection RT taking place radially inward.
  • the deflection takes place along a flow direction FD, wherein in FIG. 2 only the projected mean flow direction PMFD is reproduced, which in the schematic representation is identical to the flow direction FD.
  • the actual flow has a significant proportion in the circumferential direction, so that 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.
  • a center line ML can draw, which coincide substantially with the flow rate FD and the mean flow direction proji ⁇ ed pmfd.
  • Perpendicular to the center line of the channel width as a function of B is extending along the center ⁇ lline ML in the flow direction FD coordinate plotted s.
  • a cross-CSS is congruent in the projek ⁇ tion of Meridional bains with Kanalbrei- te B (s) and on the one hand function of the channel width B (s) and on the other hand depends on the diameter of the position of the respective channel width.
  • the center line ML passes along the radial deflection RT with each of the coordinate s ⁇ dependent curve radius RBML (s). Also dependent on the coordinate s is the radius of curvature of the inner contour RBIC (s) and the Krüm ⁇ mungsradius the outer contour RBOC (s).
  • the meridional width of the cross-sectional area CSS widens with progressive
  • the increase in area is here a ⁇ gangs stronger than exit of - so designed decreasing.
  • the cross-sectional area may also be decreasing-in particular due to the decrease in diameter when traveling radially inward-so that slight accelerations may occur.
  • the radius of curvature of the center line ML is in the flow direction FD, as well as 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, decreasing decor with dark ⁇ tet.
  • the new design increases the maximum possible deceleration and thus redu ⁇ ed due to a lower speed levels, the losses in the deflection and subsequent components.
  • the radial deflection RT first brakes the flow and then redirects it. In this case, however, deflection and deceleration already take place upon entry into the radial deflection RT.
  • the focus of this shift the flow directing measures ⁇ is taking place from the catchy main delay towards more towards the exit koruptsumblelichen deflection.
  • the area increase of the cross-sectional area CSS is over the
  • the decrease in the radius of curvature in the flow direction FD of the center ⁇ lline ML, the outer contour and the inner contour OC 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 direction of flow FD is progressively steadily for the radius of curvature of the center ⁇ lline 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.
  • 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).
  • 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 exit 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, at an axial position between l2 9 are positioned axial extent of the center line ML of the radial deflection RT.

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

Abstract

The invention relates to a recirculation stage (RF) of a radial turbo compressor (RTC) comprising, in the flow direction (FD) of a process fluid (PF), the following sections (SE): a) an annular space (RR), b) a radial turn (RT), c) a recirculation channel (RC), wherein the sections (SE) are formed such that they each extend in annular fashion about an axis of rotation (X) of the radial turbo compressor (RTC), wherein the radial turn (RT) is formed by an outer contour (OC) and an inner contour (IC), wherein for each meridional section a midline (ML) between the outer contour (OC) and the inner contour (IC) is defined as the location of the center points of the circles to which the two contours are tangential. In order to minimize flow losses, it is proposed that in the meridional section the recirculation stage (RS) in the radial turn (RT) has, over at least the first 150° of the turn, a widening of the meridional width of the cross-sectional area (CSS) which extends perpendicular to the midline (ML) and is flowed through in the flow direction (FD), wherein the midline (ML) has a radius of curvature (BRML) which decreases in the flow direction (FD).

Description

Beschreibung description

Rückführstufe Die Erfindung betrifft eine Rückführstufe eines Radialturbo¬ verdichters in Strömungsrichtung eines Prozessfluids aufge¬ führt folgende Abschnitte umfassend: Return step, the invention relates to a return step of a radial turbo compressor ¬ in the flow direction of a process fluid up ¬ performs the following sections comprising:

a) einen Ringraum, a) an annulus,

b) eine Radialumlenkung, b) a radial deflection,

c) einen Rückführkanal, c) a return channel,

wobei die Abschnitte jeweils ringförmig um eine Rotationsach¬ se des Radialturboverdichters erstreckend ausgebildet sind, wobei die Radialumlenkung von einer Außenkontur und einer Innenkontur gebildet ist. wherein said portions are each formed annularly around a rotational property ¬ se of the radial extending turbocompressor, wherein the radial deflection is formed by an outer contour and an inner contour.

Bei Radialturboverdichtern verlässt das Fluid das Laufrad ra¬ dial nach außen und gelangt von dort in den Diffusor, welcher ebenfalls radial nach außen durchströmt wird. Um bei mehrstu¬ figen 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 desIn radial turbo compressors the fluid leaves the impeller ¬ ra dial outwards and passes from there into the diffuser, which is also flows radially outwardly. In order to feed the process fluid to the next stage in multistage ¬ figen Einwellenradialverdichtern that are expected in the terminology of the radial centrifugal compressors, the process fluid is in the portion of the radial deflection, the so-called 180 degree arc from the radially outwardly flowing deflected into a flow radially Inside. In general, the flow path downstream of the 180 ° arc is bladed to prevent the swirl of the

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. Converting fluids that make up part of the kinetic energy stored by the fluid into static pressure - akin to converting kinetic energy into potential energy.

Die in dem Rückführkanal vorgesehenen Schaufeln werden auch als Rückführschaufeln bezeichnet. Stromabwärts der The vanes provided in the return duct are also referred to as return vanes. Downstream of

Rückführschaufeln wird das Prozessfluid in der Regel aus ei¬ ner 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 stromab¬ wärts des Rückführkanals vorgesehene 90 ° -Umlenkung in achspa- rallele Richtung zur Zuführung der nachfolgenden Stufe weist nach der Erfindung keine besondere Gestaltung auf und wird dementsprechend nicht näher beschrieben. Return blades, the process fluid is usually deflected from ei ¬ ner radially inwardly directed flow in an axial direction, so that an axis-parallel inflow into the downstream compression stage can be done. 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 downstream ¬ Windwärts of the return duct provided for the 90 ° deflection in achspa- rallele direction for supplying the subsequent stage has according to the invention, no special configuration and is accordingly not described in detail.

Eine vergleichbare mehrstufige Radialturbomaschine, nämlich eine Radialturbine ist bereits aus der EP 2 518 280 AI be¬ kannt. 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 je¬ weils 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 mit 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 A similar multi-stage centrifugal turbomachine, namely, a radial turbine is already known from EP 2518280 Al ¬ be 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 present in this document, the prior art provides that the radial deflection per ¬ weils having inlet side and outlet side, 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 with a high pressure drop. 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

Druckverluste reduziert sind und der Wirkungsgrad des Radial- turboverdichters verbessert ist. Pressure losses are reduced and the efficiency of the radial turbo compressor is improved.

Zur Lösung der erfindungsgemäßen Aufgabe wird eine To achieve the object of the invention is a

Rückführstufe der eingangs genannten Art mit den zusätzlichen Merkmalen des kennzeichnenden Teils des Anspruchs 1 vorge- schlagen. Vorteilhafte Weiterbildungen der Erfindung sind in den Unteransprüchen angegeben. Neben den expliziten Rückbezü- gen der Unteransprüche sind der Erfindung auch beliebige sinnvolle Kombinationen der hier aufgeführten Merkmale bzw. Weiterbildungen mit den Merkmalen des Hauptanspruchs zuzurechnen . Return stage of the aforementioned type with the additional features of the characterizing part of claim 1 proposed. Advantageous developments of the invention are specified in the subclaims. In addition to the explicit back referencing of the subclaims, the invention can also be any meaningful combination of the features listed here or Add further developments with the features of the main claim.

Unter einer Strömungsrichtung versteht die Erfindung bezogen auf die ganze Rückführstufe eine Fortbewegung eines Prozess- fluids durch den mittels der Rückführstufe des Radialturbo¬ verdichters definierten Strömungskanal im Allgemeinen. Im We¬ sentlichen lässt sich diese Strömungsrichtung durch den mittleren Kanalverlauf unter Einzeichnung entsprechender Rich- tungspfeile kennzeichnen. Under a direction of flow, 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 turbo ¬ compressor in general. In ¬ We sentlichen this flow direction can tung arrows mark by the middle channel course under appropriate delineation RICH.

Die Abschnitte Ringraum, Radialumlenkung, Rü+ckführkanal und Axialumlenkung der Rückführstufe sind sich jeweils ringförmig um eine Rotationsachse des Radialturboverdichters erstreckend ausgebildet. The sections annulus, radial deflection, Rü + ckführkanal and axial deflection of the return stage are each formed annularly extending around a rotational axis of the radial turbocompressor.

Für jeden Meridionalschnitt durch eine erfindungsgemäße For each meridional section through an inventive

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 de¬ finiert, der im Wesentlichen rotationssymmetrisch zu der Rotationsachse ist, kann eine Mittelfläche zwischen der dreidi- mensionalen Innenkontur und der dreidimensionalen Außenkontur als Rotationsfläche der Mittellinie um die Rotationsachse an¬ gesehen werden. Return stage is a center line between the outer contour and the inner contour defined as the location of the centers of the circles contiguous by the two contours. Since the return step in the circumferential direction extending about the rotation axis of the centrifugal turbocompressor and thus an annular space de ¬ finiert which is rotationally symmetrical to the axis of rotation substantially a center area between the three-dimensional inner contour and the three-dimensional outer contour as a surface of revolution of the center line around the rotation axis can at ¬ be seen.

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 de¬ finierten Strömungskanal in einem Schnitt entlang einer axial und radial verlaufenden Ebene darstellt. Derartige Schnitte entlang der Rotationsachse werden auch als Längsschnitte be¬ zeichnet. Obwohl die real vorliegende Strömung durch die ent¬ sprechenden Ringräume der Rückführstufe, die zumindest teil¬ weise in Umfangsrichtung von Leitschaufeln unterbrochen sein können, in der Regel eine signifikante Umfangskomponente auf¬ weisen, bezieht sich die Terminologie der Erfindung stets auf radiale und axiale Komponenten der Strömungsgeschwindigkeit. Begriffe wie axial, radial, Umfangsrichtung oder sonstigeFor the purposes of the invention, the description of the geometry is always related to a meridional section through the radial turbo compressor, wherein the meridional section extending along the axis of rotation and represents the de ¬-defined by the feedback stage flow channel in a section along an axially and radially extending plane. Such sections along the axis of rotation are also be ¬ as longitudinal sections. Although the current present flow through the ent ¬ speaking annular spaces of the return stage, which are interrupted at least partially ¬ in the circumferential direction of vanes can, usually a significant circumferential component on ¬ point, the terminology of the present invention always refers to radial and axial components of the flow velocity. Terms such as axial, radial, circumferential or other

Termini, die sich auf eine Achse beziehen lassen, sind - soweit nicht anders angegeben - auf die Rotationsachse des Ra¬ dialturboverdichters bezogen. Terms that can be referenced to an axis, unless otherwise stated, related to the axis of rotation of Ra ¬ dialturboverdichters.

Die erfindungsgemäße Kombination eines abnehmenden Krümmungs¬ radius 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 QuerschnittsaufWei¬ tung erfolgt. Hierbei ist es auch möglich, dass in diesem Ab¬ schnitt gar keine Verzögerung vorgesehen ist. The inventive combination of a decreasing curve ¬ radius with simultaneous widening of the cross-sectional area perpendicular to the flow direction along the flow direction leads to an equalization of the load of the flow over the course of the radial deflection as a result of deceleration and deflection, so that the tendency to separation of the flow from the Inner contour or outer contour harmonized in an inventive design of the radial deflection and is 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 by QuerschnittsaufWei ¬ tion takes place. Here it is also possible that in this From ¬ cut no delay is provided.

In der Terminologie der Erfindung bedeutet die mittlere Strö¬ mungsrichtung eine senkrecht zu der Mittellinie zwischen der Innenkontur und der Außenkontur der Radialumlenkung entlang der Querschnittsbreite - volumenstromgewichtete gemittelte Strömungsgeschwindigkeit des Prozessfluids . In the terminology of the present invention, the average Strö ¬ flow direction means a perpendicular to the center line between the inner contour and the outer contour of the radial deflection along the cross-sectional width - volumetric flow weighted average flow rate of the process fluid.

Da die Erfindung stets den Meridionalschnitt betrachtet, ent¬ fällt im Rahmen einer Projektion der räumlich orientierten Geschwindigkeit die Umfangskomponente, so dass sich die mitt¬ lere Strömungsgeschwindigkeit ausschließlich in der Projekti¬ on als Addition einer Axialgeschwindigkeit und Radialge¬ schwindigkeit beschreiben lässt. Dementsprechend ist die projizierte mittlere Strömungsrich¬ tung - kurz Strömungsrichtung - als betragsnormalisierter Vektor der projizierten mittleren Strömungsgeschwindigkeit zu verstehen . Since the invention is always considered the meridional ent ¬ falls within a projection of the spatially oriented speed, the circumferential component, so that the mitt ¬ sized flow velocity can be described as addition and an axial velocity Radialge ¬ speed exclusively in the projec ¬ on. Accordingly, the projected mean flow direction Rich ¬ tion - short flow direction - is to be understood as a magnitude normalized vector of the projected average flow velocity.

Die Querschnittsfläche der Radialumlenkung hat dementspre¬ chend einen direkten Einfluss auf die Strömungsgeschwindig¬ keit, so dass infolge der sich in Strömungsrichtung erweiternde Querschnittsfläche es zu einer Verzögerung der Strö¬ mung kommt . The cross-sectional area of the radial deflection has accordingly spre ¬ accordingly a direct impact on the Strömungsgeschwindig ¬ ness, so as a result of the widening in the direction of flow cross-sectional area results in a delay of Strö ¬ tion.

Der erfindungsgemäß abnehmende Krümmungsradius mit fort¬ schreitender Strömung entlang der Strömungsrichtung in der Radialumlenkung ist gleichbedeutend mit einer zunehmenden Krümmung der Umlenkung. Bevorzugt ist im Bereich der Radialumlenkung die Flächenzu¬ nahme der Querschnittsfläche in Strömungsrichtung stetig aus¬ gebildet . According to the invention decreasing radius of curvature continuously ¬ border flow along the flow direction in the radial deflection is equivalent to an increasing curvature of the deflection. Preferably in the range of the radial deflection of the Flächenzu ¬ acquisition of the cross-sectional area in the flow direction is continuously formed from ¬.

Weiterhin besonders bevorzugt ist eine stetig ausgebildete Abnahme des Krümmungsradius in Strömungsrichtung.  Furthermore, a steadily formed decrease of the radius of curvature in the flow direction is particularly preferred.

Besonders bevorzugt ist eine degressive Flächenzunahme der Querschnittsfläche in Strömungsrichtung. Particularly preferred is a degressive area increase of the cross-sectional area in the flow direction.

Hervorragende Ergebnisse werden mit einer degressiven steti¬ gen Flächenzunahme der Querschnittsfläche in Strömungsrich¬ tung erzielt, die am Ende der Radialumlenkung stetig bis auf 0 abgenommen hat. Excellent results are obtained with a degressive Steti ¬ gen increase in area of the cross-sectional area in the flow Rich ¬ processing, which has been steadily declining at the end of the radial deflection up to 0.

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.  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.

Eine besonders ablösungsarme Ausbildung der Radialumlenkung kann erreicht werden durch eine stetig progressive Krümmungs¬ zunahme der Innenkontur der Radialumlenkung in Strömungsrich- tung und/oder eine stetig progressive Krümmungs zunähme der Außenkontur in Strömungsrichtung. A particularly low-release design of the radial deflection can be achieved by a steadily progressive curvature ¬ increase the inner contour of the radial deflection in the flow direction and / or a steadily progressive curvature zunähme the outer contour in the flow direction.

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. 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 Prozess- fluid 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 channel begins, which conducts the process fluid essentially 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 sense 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 Another advantageous development of the invention provides that the return stage in the region of the annular space

unbeschaufelt ausgebildet ist und ein Flächenverhältnis zwi¬ schen dem Eintritt der Radialumlenkung und dem Austritt der Radialumlenkung mindestens eine Vergrößerung der is designed without vanes and an area ratio zwi ¬ tween the entry of the radial deflection and the outlet of the radial deflection at least one increase in the

Querschnittsfläche um den Faktor FCSS > 1,5 (FCSS>1,5) vor- sieht. 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. Eine andere vorteilhafte Weiterbildung sieht vor, dass derCross 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 factor FCSS is between 2.3 - 3.3 (2, 3 <FCSS <3, 3). Another advantageous embodiment provides that the

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. 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 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 er¬ folgt, wobei die 1°e~ vorzugt zwischen g 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 at a first axial plane he follows ¬ , with the 1 ° e ~ preferably between g takes the center line in the radial deflection.

Hierbei ist postuliert, dass die Strömungsrichtung ohne Ab¬ weichung der Mittellinie folgt. It is postulated that the flow direction follows without devia ¬ tion of the center line.

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 Axial¬ richtung der Mittellinie an einer ersten Axialebene erfolgt, wobei die bevorzugt zwischen der Mitte The facts can thus also be expressed as follows: An advantageous development of the invention provides that in the meridional section, the axial extent of the deflection of the center line from radially outward to the axial ¬ direction of the center line at a first axial plane, which preferably between the middle

llinie in der Radialumlenkung einnimmt. Line in the radial deflection occupies.

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 er¬ läutert. Es zeigen: Figur 1 einen Meridionalschnitt durch eine Stufe eines Ra¬ dialturboverdichters mit einer erfindungsgemäßen Rückführstufe in schematischer Darstellung, In the following the invention with reference to a specific embodiment is closer he ¬ explained with reference to drawings. 1 shows a meridional section through a stage of a Ra ¬ dialturboverdichters with a return stage according to the invention in a schematic representation,

Figur 2 ein Detail aus Figur 1, das dort mit II bezeichnet ist . Figure 2 shows a detail of Figure 1, which is designated there by II.

Die in Figur 1 gezeigte Rückführstufe RS eines Radialturbo¬ verdichters RTC ist schematisch im Meridionalschnitt oder auch Längsschnitt dargestellt. The feedback stage RS of a radial turbo ¬ compressor RTC shown in Figure 1 is shown schematically in the meridional section or longitudinal section.

Der Meridionalschnitt erstreckt sich entlang einer Rotationsachse X einer Welle SH eines Rotors R des Radialturbover¬ dichters RTC. Weiterhin ist der Meridionalschnitt definiert durch die Radialrichtung, so dass die Rotationsachse X und die Radialrichtung die Ebene des Schnitts aufspannen. Dement¬ sprechend 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 an axis of rotation X of a shaft SH of a rotor R of the radial turbocharger ¬ 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. Dement ¬ speaking, an extension in the circumferential direction of the axis of rotation X is not reproduced, as well as in Figure 2, which represents a reproduced with II in Figure 1 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 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 in the radial direction by means of

Impellers IMP beschleunigt und in die Rückführstufe RS einge¬ leitet. Die Rückführstufe RS ist Bestandteil eines Impellers IMP accelerated and in the feedback stage RS ¬ introduces . The feedback stage RS is part of a

Stators ST, der im Wesentlichen aus den Bestandteilen Schaufelboden BD und Zwischenboden ID zusammengesetzt ist. Der Schaufelboden BD ist hierbei mittels Stators ST, which is essentially composed of the components bucket bottom BD and intermediate bottom ID. The bucket bottom BD is hereby means

Rückführkanalleitschaufein 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 Schau- felböden 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. Die Rückführstufe RS umfasst in Strömungsrichtung FD des Pro- zessfluids PF aufgeführt mehrere Abschnitte SE, die einen Strömungskanal von einem Impeller IMP zu einem stromabwärts gelegenen Impeller IMP bilden. Diese Abschnitte SE sind: Rückführkanalleitschaufein GVRC attached to the intermediate floor 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. As a rule, the showcase bottoms BD and the intermediate bottoms ID are designed to be divided in the circumferential direction, so that it is possible to join the rotor R to the stator ST by dividing the stator ST in a generally horizontal parting line. The return stage RS comprises in the flow direction FD of the process fluid PF listed several sections SE, which form a flow channel from an impeller IMP to a downstream impeller IMP. These sections SE are:

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 Lauf¬ rad . a) an annular space RR, b) a radial deflection RT and c) a return channel RC. To the sections can also be added to a less important for the invention section SE, Namely a downstream axial deflection AT for axial entry into the downstream Lauf ¬ rad.

Der Ringraum RR kann mit Ringraumleitschaufein GVRR The annulus RR can with annulus guide 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 Radial¬ umlenkung 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 dembe formed bladed or without blades, so without bluffing. 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 directs flow substantially from a radially outwardly facing direction in a radially inward direction, demensprechend by about 180 °. From the

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. Due to 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 Radialum- lenkung RT ringförmig sich in Umfangsrichtung erstreckend um die Rotationsachse X ausgebildet. Die Darstellungen im 2 shows schematically a detail which is indicated by "II" in FIG. 1 and which reproduces the radial deflection RT. Like the entire return stage RS, the radial deflection RT is also formed annularly in the circumferential direction around the rotation axis X. The illustrations in FIG

Meridionalschnitt zeigen die Ausdehnung in Umfangsrichtung nicht. Ein Prozessfluid PF strömt in die Radialumlenkung RT ein und ist dabei im Wesentlichen nach radial außen gerich- tet, 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 Strömungs- richtung 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 proji¬ zierten Strömungsrichtung PMFD. Senkrecht zu der Mittellinie ist die Kanalbreite B als Funktion einer entlang der Mitte¬ llinie ML in Strömungsrichtung FD verlaufenden Koordinate s eingezeichnet. Eine Querschnittsfläche CSS ist in der Projek¬ tion des Meridionalschnitts deckungsgleich mit der Kanalbrei- te B(s) und ist einerseits Funktion der Kanalbreite B(s) und andererseits abhängig von dem Durchmesser der Position der jeweiligen Kanalbreite. Die Mittellinie ML verläuft entlang der Radialumlenkung RT mit einem jeweils von der Koordinate s abhängigen Krümmungs¬ radius RBML(s) . Gleichfalls abhängig von der Koordinate s ist der Krümmungsradius der Innenkontur RBIC(s) und der Krüm¬ mungsradius der Außenkontur RBOC(s). Die meridionale Breite der Querschnittsfläche CSS weitet sich mit fortschreitenderMeridional section does not show the extent in the circumferential direction. A process fluid PF flows into the radial deflection RT and is directed essentially radially outward, the outflow from the radial deflection RT taking place radially inward. The deflection takes place along a flow direction FD, wherein in FIG. 2 only the projected mean flow direction PMFD is reproduced, which in the schematic representation is identical to the flow direction FD. The actual flow has a significant proportion in the circumferential direction, so that 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 and the outer contour IC OC is a center line ML can draw, which coincide substantially with the flow rate FD and the mean flow direction proji ¬ ed pmfd. Perpendicular to the center line of the channel width as a function of B is extending along the center ¬ llinie ML in the flow direction FD coordinate plotted s. A cross-CSS is congruent in the projek ¬ tion of Meridionalschnitts with Kanalbrei- te B (s) and on the one hand function of the channel width B (s) and on the other hand depends on the diameter of the position of the respective channel width. The center line ML passes along the radial deflection RT with each of the coordinate s ¬ dependent curve radius RBML (s). Also dependent on the coordinate s is the radius of curvature of the inner contour RBIC (s) and the Krüm ¬ mungsradius the outer contour RBOC (s). The meridional width of the cross-sectional area CSS widens with progressive

Strömungsrichtung FD von einem Eintritt zu einem Austritt der Radialumlenkung RT auf. Die Flächenzunahme ist hierbei ein¬ gangs stärker als ausgangs - also abnehmend gestaltet. Die Querschnittsfläche kann ausgangs der Radialumlenkung auch ab- nehmend 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 gestal¬ tet. 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 redu¬ ziert 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 fin- det jedoch eine Umlenkung und Abbremsung bereits bei Eintritt in die Radialumlenkung RT statt. Die Schwerpunkte dieser bei¬ den 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 denFlow direction FD from an inlet to an outlet of the radial deflection RT. The increase in area is here a ¬ gangs stronger than exit of - so designed 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 inward-so that slight accelerations may occur. The radius of curvature of the center line ML is in the flow direction FD, as well as 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, decreasing decor with dark ¬ tet. 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 redu ¬ ed due to a lower speed levels, the losses in the deflection and subsequent components. The radial deflection RT according to the invention first brakes the flow and then redirects it. In this case, however, deflection and deceleration already take place upon entry into the radial deflection RT. The focus of this shift the flow directing measures ¬ is taking place from the catchy main delay towards more towards the exit häuptsächlichen deflection. The area increase of the cross-sectional area CSS is over the

Verlauf der Radialumlenkung RT stetig gestaltet. Die Abnahme des Krümmungsradius in Strömungsrichtung FD der Mitte¬ llinie 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 Mitte¬ llinie 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. Course of Radialumlenkung RT steadily designed. The decrease in the radius of curvature in the flow direction FD of the center ¬ llinie ML, the outer contour and the inner contour OC 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 direction of flow FD is progressively steadily for the radius of curvature of the center ¬ llinie 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) 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)

(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  (Cross-sectional area at the outlet of the radial deflection RT) leads to an increase in area by the factor FCSS> 1.5, preferably between 2, 3 <FCSS <3, 3, in the present case, the factor

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. 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 Axial¬ richtung auf etwa der gesamten Axialerstreckung der Radi- alumlenkung 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 Radial¬ umlenkung 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 l2 9esam- ten axialen Erstreckung der Mittellinie ML der Radialumlenkung RT positioniert. Bevorzugt befindet sich die erste Axi¬ alebene AXP1 zwischen der Hälfte der gesamten Axialerstreckung und "Yg der gesamten Axialerstreckung. In der Position der ersten Axialebene AXP1 ist bereits mindestens 65% der ge¬ samten Flächenaufweitung der Radialumlenkung RT in Strömungsrichtung FD erreicht. In the meridional section, the axial extent of the deflection from radially outward of the center line ML up to the axial ¬ direction to about the entire axial extent of the Radialumlenkung RT. 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 exit 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, at an axial position between l2 9 are positioned axial extent of the center line ML of the radial deflection RT. Preferred is the first Axi ¬ alebene AXP1 between the half of the total axial and "Yg the entire axial extension. In the position the first axial AXP1 has already been reached in the flow direction FD at least 65% of the entire surface ge ¬ expansion of the radial deflection RT.

Claims

Patentansprüche claims 1. Rückführstufe (RF) eines Radialturboverdichters (RTC) in Strömungsrichtung (FD) eines Prozessfluids (PF) aufgeführt folgende Abschnitte (SE) umfassend: 1. Reverse stage (RF) of a radial turbo-compressor (RTC) in the flow direction (FD) of a process fluid (PF) listed the following sections (SE) comprising: a) einen Ringraum (RR) ,  a) an annulus (RR), b) eine Radialumlenkung (RT) ,  b) a radial deflection (RT), c) einen Rückführkanal (RC) ,  c) a return channel (RC), wobei die Radialumlenkung (RT) von einer Außenkontur (OC) und einer Innenkontur (IC) gebildet ist,  wherein the radial deflection (RT) is formed by an outer contour (OC) and an inner contour (IC), wobei für jeden Meridionalschnitt eine Mittellinie (ML) zwischen der Außenkontur (OC) und der Innenkontur (IC) definiert ist als der Ort der Mittelpunkte der von den beiden Konturen tangierten Kreise,  wherein, for each meridional section, a center line (ML) between the outer contour (OC) and the inner contour (IC) is defined as the location of the centers of the circles tangent to the two contours, dadurch gekennzeichnet, dass  characterized in that die Radialumlenkung (RT) im Meridionalschnitt über mindes¬ tens die ersten 150° der Umlenkung eine Aufweitung der senkrecht zur Mittellinie (ML) sich erstreckenden durchströmten meridionalen Breite der Querschnittsfläche (CSS) in Strömungsrichtung (FD) aufweist , the radial deflection (RT) in the meridional section through Minim ¬ least comprises the first 150 ° of the deflection a widening of the perpendicular to the center line (ML) extending through flocked meridional width of the cross-sectional area (CSS) in the direction of flow (FD), wobei die Mittellinie (ML) in der Radialumlenkung (RT) einen in Strömungsrichtung (FD) abnehmenden Krümmungsradius (BRML) aufweist. 2. Rückführstufe (RS) nach Anspruch 1,  wherein the center line (ML) in the radial deflection (RT) has a decreasing in the flow direction (FD) radius of curvature (BRML). 2. feedback stage (RS) according to claim 1, wobei eine Flächenzunahme der Querschnittfläche (CSS) in¬ folge der Zunahme der meridionalen Breite in Strömungsrichtung (FD) stetig ausgebildet ist. 3. Rückführstufe (RS) nach Anspruch 1, wherein an area increase of the cross-sectional area (CSS) in the wake of the increase in the meridional width in the flow direction (FD) is formed continuously. 3. feedback stage (RS) according to claim 1, wobei im Meridionalschnitt die Rückführstufe (RS) in der Radialumlenkung (RT) über mindestens die ersten 180° der Umlenkung eine Aufweitung der senkrecht zur Mittellinie (ML) sich erstreckenden durchströmten meridionalen Breite der Querschnittsfläche (CSS) in Strömungsrich¬ tung (FD) aufweist . wherein in the meridional section, the return stage (RS) in the radial deflection (RT) over at least the first 180 ° of the deflection has a widening of the perpendicular to the center line (ML) extending through perfected meridional width of the cross-sectional area (CSS) in flow Rich ¬ tion (FD). 4. Rückführstufe (RS) nach Anspruch 1, 2 oder 3, wobei ein Krümmungsradius der Mittellinie (ML) , der Außen¬ kontur (OC) oder der Innenkontur (IC) in Strömungsrichtung (FD) stetig abnehmend ausgebildet ist. 4. feedback stage (RS) according to claim 1, 2 or 3, wherein a radius of curvature of the center line (ML), the outer ¬ contour (OC) or the inner contour (IC) in the flow direction (FD) is formed continuously decreasing. 5. Rückführstufe (RS) nach einem der vorhergehenden Ansprü¬ che 1 bis 4, 5. feedback stage (RS) according to one of the preceding Ansprü ¬ che 1 to 4, wobei die Flächenzunahme der Querschnittsfläche (CSS) in Strömungsrichtung (FD) degressiv ist.  wherein the area increase of the cross-sectional area (CSS) in the flow direction (FD) is degressive. 6. Rückführstufe (RS) nach Anspruch 4, 6. feedback stage (RS) according to claim 4, wobei der Krümmungsradius progressiv abnehmend ausgebildet ist . 7. Rückführstufe (RS) nach einem der vorhergehenden Ansprüche 1 bis 6,  wherein the radius of curvature is formed progressively decreasing. 7. feedback stage (RS) according to one of the preceding claims 1 to 6, wobei der Ringraum (RR) unbeschaufelt ausgebildet ist und ein Flächenverhältnis (FCSS) der Querschnittsfläche (CSS) zwischen einem Eintritt der Radialumlenkung (RT) und einem Austritt der Radialumlenkung (RT) mindestens um einen Faktor (FCSS) von 1,5 unterschiedlich ist.  wherein the annular space (RR) is formed without vanes and an area ratio (FCSS) of the cross-sectional area (CSS) between an entrance of the radial deflection (RT) and an outlet of the radial deflection (RT) is different by at least a factor (FCSS) of 1.5. Rückführstufe (RS) nach Anspruch 7, Feedback stage (RS) according to claim 7, wobei der Faktor (FCSS) mindestens 2,0 beträgt.  where the factor (FCSS) is at least 2.0. Rückführstufe (RS) nach Anspruch 8, Feedback stage (RS) according to claim 8, wobei der Faktor (FCSS) zwischen 2,3 und 3,3 beträgt  where the factor (FCSS) is between 2.3 and 3.3 10. Rückführstufe (RS) nach einem der vorhergehenden Ansprü- che 1 bis 6, 10. feedback stage (RS) according to one of the preceding claims 1 to 6, wobei der Ringraum (RR) beschaufelt ausgebildet ist und das Flächenverhältnis der Querschnittsfläche (CSS) zwischen ei¬ nem Eintritt der Radialumlenkung (RT) und einem Austritt der Radialumlenkung (RT) sich um einen Faktor (FCSS) von mindestens 1,4 unterscheidet. wherein the annular space (RR) is formed bladed and the area ratio of the cross-sectional area (CSS) between ei ¬ nem entry of the radial deflection (RT) and an outlet of the radial deflection (RT) differs by a factor (FCSS) of at least 1.4. 11. Rückführstufe (RS) nach Anspruch 10, 11. feedback stage (RS) according to claim 10, wobei der Faktor (FCSS) mindestens 1,5 beträgt.  where the factor (FCSS) is at least 1.5. 12. Rückführstufe (RS) nach Anspruch 11, 12. feedback stage (RS) according to claim 11, wobei der Faktor (FCSS) kleiner als 2,5 ist.  where the factor (FCSS) is less than 2.5. 13. Rückführstufe (RS) nach mindestens einem der vorherge¬ henden Ansprüche, 13, return step (RS) according to at least one of vorherge ¬ Henden claims, wobei im Meridionalschnitt die axiale Erstreckung der Um- lenkung von radial nach außen der Mittellinie (ML) bis in die Axialrichtung sich bis zu einer ersten Axialebene (AXP1) bevorzugt zwischen len Erstreckung der Mittellinie (ML) der Radialumlenkung (RT) er- streckt. wherein in the meridional section, the axial extension of the deflection from radially outward of the center line (ML) to the axial direction preferably up to a first axial plane (AXP1) between len extending the center line (ML) of the radial deflection (RT). 14. Rückführstufe (RS) nach Anspruch 13, 14. feedback stage (RS) according to claim 13, wobei an der ersten Axialebene (AXP1) mindestens 65% der gesamten Flächenaufweitung der Radialumlenkung (RT) er- reicht sind.  wherein at the first axial plane (AXP1) at least 65% of the total area expansion of the radial deflection (RT) are reached.
EP15797326.4A 2014-11-21 2015-11-19 Recirculation stage Not-in-force EP3194792B1 (en)

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