EP3551890B1 - Etage de retour - Google Patents

Etage de retour Download PDF

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Publication number
EP3551890B1
EP3551890B1 EP18704418.5A EP18704418A EP3551890B1 EP 3551890 B1 EP3551890 B1 EP 3551890B1 EP 18704418 A EP18704418 A EP 18704418A EP 3551890 B1 EP3551890 B1 EP 3551890B1
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EP
European Patent Office
Prior art keywords
rch
return stage
section
stage
along
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.)
Active
Application number
EP18704418.5A
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German (de)
English (en)
Other versions
EP3551890A1 (fr
Inventor
Jörg Paul HARTMANN
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 Energy Global GmbH and Co KG
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Siemens Energy Global GmbH and Co KG
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Publication of EP3551890A1 publication Critical patent/EP3551890A1/fr
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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
    • 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
    • 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
    • F04D29/444—Bladed diffusers
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet

Definitions

  • the invention relates to a return stage of a radial turbo machine with at least one guide vane stage, the return stage extending in a ring around an axis, the return stage being defined radially inward by an inner boundary contour and radially outward by an outer boundary contour, the return stage along a first flow direction extends radially outward in a first section, wherein the return stage extends in a second section along the first flow direction, describing an arcuate deflection, from radially outside to radially inward, wherein the return stage extends along the first flow direction in a third section from radially outside to extends radially inward, the return stage extending along the first flow direction in a fourth section, describing an arcuate deflection, extending from radially inward to axially, the guide vane stage comprising guide vanes, where in which the guide vanes each comprise an airfoil extending along a span, the surfaces of which extend from an upstream leading edge as a pressure side and as a su
  • Radial turbo machines are known as either radial turbo compressors or radial turbo expanders. Unless otherwise stated, the following statements refer to the version as a compressor. In principle, the invention can be used for expanders in the same way as for compressors, a radial turbo expander essentially providing a reverse flow direction of the process fluid compared to a radial turbo compressor.
  • thermodynamically in the process fluid is converted into technical work by means of a drive of the impeller while a process fluid is relaxed and deflected.
  • impellers of the compressor usually suck in a process fluid axially to an axis of rotation or at an angle to the axis of rotation with an axial speed component and accelerate and compress this process fluid by means of the respective impeller - which is also referred to as an impeller - which controls the flow direction of the process fluid deflects radial direction.
  • the impeller is followed downstream by a return stage if at least one further impeller is provided downstream.
  • the WO2016047256 shows a recycle stage that has non-cylindrical guide vanes. Deflection angles are there not specified.
  • the documents US 2010/272564 A1 are there not specified.
  • JP H11 173299 A show aerodynamic designs of comparable configurations.
  • the invention has set itself the task of improving the aerodynamics of the feedback stages without having to accept such expenses.
  • the invention proposes a recycle stage according to claim 1.
  • the subclaims contain advantageous developments of the invention.
  • axial, radial, tangential, circumferential direction and the like are here or in this document each related to the central axis around which the return stage extends in an annular manner.
  • this axis is also the axis of rotation of a rotor or the shaft with the running wheels.
  • cylinder In the case of the terms cylinder or cylindrical, the invention is based on the general mathematical understanding of the term.
  • a plane curve in a plane is shifted by a fixed distance along a straight line that is not contained in the starting plane. Two corresponding points of the curves and the shifted curve are connected by a segment. The entirety of these parallel routes forms the associated cylinder surface (see also definition Wikipedia (https://de.wikipedia.org/wiki/Zylinder_(Geometrie)#Allgemein er_Zylinder)).
  • the cylinder is not limited to the shape of a circular cylinder.
  • a cylindrical design means that the blade - formed from individual profiles that are stacked along a threading line - are stacked along a straight threading line. It is irrelevant here whether the blade extends along a contoured or curved flow channel or whether the flow channel is straight. The decisive factor is the straight extension in the spanwise direction of the blade, which leads to the designation "cylindrical blade".
  • a multistage radial turbo machine means that several running wheels are arranged to be rotatable about the same axis of rotation.
  • an impeller is to be equated with a stage of the radial turbomachine.
  • the multistage requires that, in the case of the compressor, the process fluid flowing radially out of the impellers must be guided back in the direction of the axis of rotation and can flow into the subsequent impeller of the downstream stage with an axial speed component.
  • the flow guidance that enables this return of the process fluid is therefore called the "return stage".
  • the component can be of identical design and the flow is only flowed through in the opposite direction.
  • guide vanes are also provided in the return stages, which at least partially or completely neutralize a swirl created in the flow from the upstream impeller or even a swirl in the opposite direction imprint for entry into the next downstream stage.
  • a return stage preferred according to the invention provides that this entire component is supported and aligned by means of a so-called intermediate floor by means of suitable supports, usually in a housing or some other support device. Furthermore, the return stage comprises a so-called vane bottom, which is attached to the intermediate bottom with the guide vanes already explained, forming a return channel. The process fluid flows through the return channel to the next impeller inlet.
  • the guide vanes have two functions.
  • the guide vanes have the aerodynamic function of imposing a counter-swirl on the process fluid to the extent that at least the swirl from the upstream stage is largely compensated, and on the other hand, the guide vanes have the mechanical task of fastening the vane bottom to the intermediate bottom in such a way that, despite the dynamic load, a a secure hold is guaranteed.
  • the guide vane stage located in the return stage comprises guide vanes which segment the annular shape of the return stage into individual channels in the circumferential direction.
  • these guide vanes can also have interruptions (split), but according to the invention are preferably designed to be uninterrupted along the first flow direction.
  • the guide vanes have profiles which - if unwound accordingly - can also be represented in two dimensions. A two-dimensional representation is possible, for example, if the annular channel of the return stage is cut along a central surface extending in the circumferential direction. This cut surface of a single guide vane can be developed into a plane, for a two-dimensional representation.
  • a profile center line of the stacked profiles of the guide vanes can be generated by means of centers of inscribed circles in the profile. This profile center line is also referred to below as the skeleton line.
  • the profile center line can be used to define a profile center line running coordinate or skeletal line running coordinate along the first flow direction along a mean height of the respective guide vane.
  • the length of the guide vane along this coordinate is preferably normalized to a total length of 1 or 100%.
  • the height direction of the guide vane is defined in the present case as the direction which is oriented perpendicular to the flow direction - in particular to the first flow direction - and perpendicular to the circumferential direction.
  • the height of the blade or the height direction is referred to in this document as the span width or span direction of the blade.
  • the profile center line of the guide vane directly adjacent to the outer boundary contour of the annular channel of the return stage is referred to here as the outer track of the guide vane and the profile center line of the profile cross section of the guide vane located directly on the inner boundary contour is referred to as the inner track of the guide vane.
  • the outer boundary contour of the return stage can also be referred to as the boundary contour on the cover disk side, because an impeller provided with a cover disk has this cover disk on the side of the outer boundary contour.
  • the hub-side flow contour of the impeller is located opposite on the inner boundary contour of the return stage, so that the inner boundary contour of the return stage can also be referred to as the hub-side boundary contour. Due to the complex geometry of the return stage, the inner limit contour cannot always be viewed as being located radially further inward than the outer limit contour for the same positions along a central flow line through the return stage, so that such alternative designations are useful for better understanding.
  • the deflection angle in the middle of the span is greater than the average total deflection angle in each case based on the trailing edges of the guide vanes.
  • the advantageous knowledge of the invention consists in the fact that this shape of the guide vane on the one hand results in a flow to the downstream impeller which is favorable for the efficiency of the return stage and on the other hand is associated with relatively little effort both in terms of manufacture and assembly. Due to the fact that the leading edge is preferably only arranged behind the 180 ° deflection and the trailing edge upstream of the 90 ° deflection from the radially inward flow into the axially directed flow, the guide vanes are essentially located in a radially running flow channel without mandatory Axial components of the flow.
  • the guide vane shape according to the invention prepares the flow behind the 180 deflection and before the diversion in the axial direction so advantageously for the inflow into the impeller that a continuation of the guide vane in the downstream deflection in the axial direction is not necessary.
  • Conventional guide vane shapes in the recirculation stage either accept the unfavorable, inhomogeneous flow distribution in the spanwise direction, or are laboriously continued in the deflections of the second section and / or fourth section of the recirculation stage in order to ensure an advantageous flow to the downstream impeller.
  • the trailing edges brought up close to the impeller ensure an unfavorable excitation of the impeller due to the resulting inhomogeneities in the circumferential direction.
  • exit edges each describe a straight line.
  • differences in the deflection angle are preferably implemented by means of different curvatures of the skeleton lines of different profiles of the span.
  • exit edges are bent or kinked. In that case it is - in other words - not straight designs of the exit edges.
  • the bend of the exit edges can be both in the circumferential direction and in the radial direction be formed and any mixed form of these offsets is also conceivable.
  • skeleton lines of the profile cross-sections there are formed shorter than a mean skeleton line length at least 7% of the span at both ends of the span.
  • a design can be achieved if, for example, in the case of a cylindrical blade or a non-cylindrical blade, the trailing edges in these two end regions of the span are shortened or the blade is slightly cut away or cut off at this point.
  • the reduced deflection required in principle according to the invention in the areas of the span ends is achieved in a particularly cost-effective manner.
  • Figure 1 shows a feedback stage RCH of a radial turbo machine RTM, which is designed as a radial turbo compressor CO.
  • a radial turbo compressor CO can also be implemented according to the invention as radial turbo expanders, with a process fluid PF flowing through these components in a radial turbo compressor CO in a first flow direction FD1 and in a radial turbo expander in an opposite, second flow direction FD2.
  • the descriptions in this document always relate to the first flow direction FD1 or a radial turbo compressor CO, unless stated otherwise.
  • Figure 1 shows parts of two successive stages, a first stage ST1 and a second stage ST2 of a radial turbo machine RTM or a radial turbo compressor CO shown in detail, a return stage RCH between the two stages ST1, ST2 being shown completely schematically.
  • the two stages ST1, ST2 are shown here with impellers arranged to be rotatable about the axis of rotation X, a first impeller IP1 and a second impeller IP2.
  • a process fluid PF first flows through the first impeller IP1, flowing in axially and flowing out radially along a first flow direction FD1.
  • An oppositely oriented second flow direction FD2 is also given as an example, as would be the case with a radial expander.
  • the process fluid PF flows radially outward and reaches a radially outwardly directed first section SG1 and is decelerated there, passes downstream in an approximately 180 ° deflection of a second section SG2 and then in a radially inward one Return of a third section SG3 of the return stage RCH.
  • the process fluid PF reaches the second impeller IP2 in a fourth section SG4, flowing from radially inward to axially flowing, in order to be accelerated radially outward again there.
  • the return stage RCH comprises a blade base RR, guide vanes VNS and an intermediate base DGP.
  • the intermediate floor DGP is supported by at least one support SUP in a support device - here in a housing CAS - and positioned there.
  • the support SUP and the supporting section of the housing CAS are designed as a tongue and groove connection in a form-fitting manner.
  • the return stage RCH or the blade bottom RR and the intermediate bottom DGP have a parting joint which runs in a common plane essentially along the axis X.
  • This parting line is conveniently located in the same parting line as a parting line, not shown, of the CAS housing.
  • the rotor is designed to be divisible between two impellers or the impellers are designed to be axially displaceable in relation to one another for the purpose of assembly, so that the return stages RTC can be designed in one piece and gradually assembled together with the impellers IP1, IP2 of the rotor before merging with a surrounding housing.
  • the housing CAS can in any case be designed to be divided horizontally or vertically.
  • the conventional design of the feedback stage RCH which is in the Figure 1 is shown, provides that the blade base RR, the guide vanes VNS and the intermediate base DGP are attached to one another. In the present case, this is done using SCR screws, which are shown in simplified form by means of dash-dotted lines. So that the SCR screws on the one hand the bucket bottom On the other hand, a sufficiently large through-hole must be provided in the guide vanes VNS so that the profile of the guide vanes VNS must be sufficiently strong.
  • FIG. 2 shows a schematic perspective illustration of a guide vane VNS of a return stage RCH according to the invention.
  • the guide vane VNS is shown in connection with the axis X and a radial direction R perpendicular thereto.
  • a reference plane PRF which is spanned by the axis X and the radial direction R, is indicated at different points in order to illustrate geometric relationships.
  • the guide vane VNS comprises an airfoil VAF extending along a span SPW, the surfaces SFT of which extend from the upstream leading edge LDE as a pressure side PRS and as a suction side PCS along a skeleton line SCL spaced from one another by profile cross sections PRC up to an exit edge TLE.
  • a tangent TGT on the skeleton line SCL shows that for every profile cross section PRC a blade construction angle VCR to the radial-axial reference plane PRF for each point of Skeleton line SCL is defined.
  • RDA RDA (SPW, SCL)
  • the Figure 2 shows in addition to a curved trailing edge TLE also a straight trailing edge TLE 'and one with two kinks provided kinked trailing edge TLE ", which was created by cutting away or leaving out portions of the original blade VAF in the two end regions of the span SPW.
  • Figure 3 shows a built-in guide vane VNS of a return stage RCH according to the invention.
  • the area in which the guide vane VNS is provided in the return stage RCH extends essentially from radially outside to radially inside along the first throughflow direction FD1 of the process fluid PF.
  • a screw SCR extends through the blade VAF in the spanwise direction.
  • the Figure 4 shows the same situation as that Figure 3 with a differently designed guide vane VNS.
  • the guide vane VNS of the Figure 4 is cylindrical and has cut back areas of the trailing edge TLE "at both ends of the span SPW. This embodiment corresponds to the representation of one (TLE") of the three alternatives in FIG Figure 2 .

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

Claims (6)

  1. Etage (RCH) de retour d'une turbomachine (RTM) radiale, comprenant au moins un étage (VST) d'aubes directrices, l'étage (RCH) de retour s'étendant annulairement autour d'un axe (X),
    dans lequel l'étage (RCH) de retour est défini, vers l'intérieur radialement, par un contour (IDC) limite intérieur et, vers l'extérieur radialement, par un contour (ODC) limite extérieur,
    dans lequel, suivant une première direction (FD1) d'écoulement, l'étage (RCH) de retour s'étend dans une première partie (SG1) vers l'extérieur radialement,
    dans lequel l'étage (RCH) de retour s'étend, suivant la première direction (FD1) d'écoulement, dans une deuxième partie (SG2), de l'extérieur radialement vers l'intérieur radialement, en décrivant un renvoi en forme d'arc,
    dans lequel l'étage (RCH) de retour s'étend, suivant la première direction (FD1) d'écoulement, dans une troisième partie (SG3), de l'extérieur radialement vers l'intérieur radialement,
    dans lequel l'étage (RCH) de retour s'étend, suivant la première direction (FD1) d'écoulement, dans une quatrième partie (SG4), de l'intérieur radialement vers l'axe, en décrivant un renvoi en forme d'arc,
    dans lequel l'étage (RCH) de retour comprend des aubes (VNS) directrices,
    dans lequel les aubes (VNS) directrices comprennent chacune un corps (VAF) d'aube, s'étendant suivant une envergure (SPW), dont les surfaces d'écoulement autour de lui s'étendent jusqu'à un bord (TLE) de sortie d'un bord (LDE) d'entrée se trouvant en amont, sous la forme d'un intrados (PRS) et sous la forme d'un extrados (PCS), en étant à distance les unes des autres, suivant une ligne (SCL) de squelette de la section (PRC) transversale de profil,
    dans lequel une tangente de la ligne (SCL) de squelette d'une section (PRC) transversale de profil quelconque fait un angle (VCA) de construction d'aube avec un plan (PRF) de référence radial-axial pour chaque point de la ligne (SCL) de squelette,
    dans lequel une différence entre un angle (VCA) de construction d'aube au bord (LDE) d'entrée et un angle (VCA) de construction d'aube à une position en aval définit un angle (RDA) de renvoi pour chaque point de la ligne (SCL) de squelette d'une section (PRC) transversale de profil quelconque,
    dans lequel un angle (RAM) de renvoi total en moyenne est un angle (RDA) de renvoi en moyenne sur l'envergure (SPW) au bord (TLE) de sortie,
    dans lequel les aubes (VNS) directrices s'étendent au moins suivant une partie de la troisième partie (SG3) et segmentent l'étage (RCH) de renvoi dans la direction du pourtour en canaux d'écoulement,
    dans lequel les bords (TLE) de sortie sont disposés dans la troisième partie (SG3),
    caractérisé en ce que, au bord (TLE) de sortie, au milieu de l'envergure (SPW), l'angle (RDA) de renvoi est, respectivement, plus grand que l'angle (RAM) de renvoi total en moyenne,
    dans lequel, au deux extrémités de l'envergure (SPW), pour, respectivement, au moins 10% de l'envergure, respectivement, l'angle (RDA) de renvoi est plus petit que l'angle (RAM) de renvoi total en moyenne.
  2. Etage (RCH) de renvoi suivant la revendication 1, dans lequel les bords (LDE) d'entrée sont disposés chacun dans la troisième partie (SG3).
  3. Etage (RCH) de renvoi suivant la revendication 1 ou 2, dans lequel les bords (TLE) de sortie décrivent chacun une droite.
  4. Etage (RCH) de renvoi suivant la revendication 1 ou 2, dans lequel les bords (TLE) de sortie sont incurvés ou coudés.
  5. Etage (RCH) de renvoi suivant la revendication 1, 2, 3 ou 4, dans lequel, aux deux extrémités de l'envergure (SPW), pour, respectivement, au moins 7% de l'envergure, les lignes (SCL) de squelette des sections (PRC) transversales de profil, qui s'y trouvent, sont plus courtes qu'une longueur (SCL) moyenne de lignes de squelette.
  6. Etage (RCH) de renvoi suivant les revendications 1, 2, 4 et 5, dans lequel les aubes (VNS) directrices ont un bord d'entrée droit et sont sensiblement cylindriques, à l'exception de la région aux deux extrémités de l'envergure (SPW), dans lequel aux bords (TLE) de sortie, pour, respectivement, au moins 7% de l'envergure, les lignes (SCL) de squelette des sections (PRC) transversales de profil, qui s'y trouvent, sont plus courtes qu'une longueur (SLL) moyenne des lignes de squelette.
EP18704418.5A 2017-02-21 2018-01-22 Etage de retour Active EP3551890B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP17157126.8A EP3364039A1 (fr) 2017-02-21 2017-02-21 Étage de retour
PCT/EP2018/051389 WO2018153583A1 (fr) 2017-02-21 2018-01-22 Étage de retour

Publications (2)

Publication Number Publication Date
EP3551890A1 EP3551890A1 (fr) 2019-10-16
EP3551890B1 true EP3551890B1 (fr) 2021-02-24

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EP18704418.5A Active EP3551890B1 (fr) 2017-02-21 2018-01-22 Etage de retour

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US (1) US10995761B2 (fr)
EP (2) EP3364039A1 (fr)
CN (1) CN110325743B (fr)
WO (1) WO2018153583A1 (fr)

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US10781705B2 (en) * 2018-11-27 2020-09-22 Pratt & Whitney Canada Corp. Inter-compressor flow divider profiling
EP3690254A1 (fr) 2019-01-31 2020-08-05 Siemens Aktiengesellschaft Roue à aubes d'une turbomachine radiale, turbomachine radiale
FR3106653B1 (fr) * 2020-01-23 2022-01-07 Safran Aircraft Engines Ensemble pour une turbomachine
DE102020118650A1 (de) 2020-07-15 2022-01-20 Ventilatorenfabrik Oelde, Gesellschaft mit beschränkter Haftung Radialventilator
EP4015832A1 (fr) 2020-12-18 2022-06-22 Siemens Energy Global GmbH & Co. KG Guidage d'écoulement statique, turbomachine radiale

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Also Published As

Publication number Publication date
US20190368497A1 (en) 2019-12-05
US10995761B2 (en) 2021-05-04
WO2018153583A1 (fr) 2018-08-30
EP3364039A1 (fr) 2018-08-22
CN110325743A (zh) 2019-10-11
CN110325743B (zh) 2020-12-29
EP3551890A1 (fr) 2019-10-16

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