EP3551890A1 - Étage de retour - Google Patents

Étage de retour

Info

Publication number
EP3551890A1
EP3551890A1 EP18704418.5A EP18704418A EP3551890A1 EP 3551890 A1 EP3551890 A1 EP 3551890A1 EP 18704418 A EP18704418 A EP 18704418A EP 3551890 A1 EP3551890 A1 EP 3551890A1
Authority
EP
European Patent Office
Prior art keywords
stage
rch
span
scl
tle
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
EP18704418.5A
Other languages
German (de)
English (en)
Other versions
EP3551890B1 (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
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 EP3551890A1 publication Critical patent/EP3551890A1/fr
Application granted granted Critical
Publication of EP3551890B1 publication Critical patent/EP3551890B1/fr
Active 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
    • 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 vane stage, wherein the return stage extends annularly around an axis, wherein the return stage is defined radially inwardly by an inner boundary contour and radially outward of an outer boundary contour, wherein along a first return flow direction, the return stage extends radially outward in a first section, the return stage extending in a second section along the first flow direction arcuate deflection descriptive from radially outside to radially inside, wherein the return stage along the first flow direction in a third section extends radially outward to radially inward, wherein the return stage along the first flow direction in a fourth section, an arcuate deflection descriptive of radially inward to axially first extends, wherein the guide vane stage includes vanes, the Leitschau ⁇ blades each comprise a along a span extending airfoil, the flow around surfaces of an upstream leading edge as a pressure side and as a suction
  • Radial turbomachines are known as either radial turbo compressors or radial turboexpanders. The following statements relate - unless otherwise stated - to the design as a compressor.
  • the invention is basically just as applicable for expanders as for compressors, with a radial turbo-expander essentially providing a reverse flow direction of the process fluid compared with a radial turbocompressor.
  • impellers of the compressor is usually a process ⁇ fluid axially to a rotational axis or oblique to the Rota ⁇ tion axis with an axial velocity component and accelerate and compress this process fluid by means of the respective wheel - which is also referred to as impeller - that the direction of flow of the process fluid deflects in the radial direction.
  • the impeller is followed by a return stage downstream of a multi-stage radial turbocompressor when at least one further impeller is provided downstream.
  • EP 592 803 Bl each return stages of a multi-stage turbocompressor are shown.
  • An aerodynamic view of feedback stages include US 2010/0272564 AI and WO2014072288A1. From the essay "Design exploration of a return channel for multistage centrifugal compressors" of the conference
  • the invention proposes a recycling stage according to claim 1.
  • the Unteran ⁇ claims contain advantageous developments of the invention.
  • axial, radial, tangential, circumferential direction and the like are in this case or in this document in each case based on the central axis around which the return stage extends annularly. In a radial turbo machine, this axis is also the axis of rotation of a rotor or of the shaft with the wheels.
  • an impeller is to be equated with a stage of Radialturboma ⁇ machine. From the multi-stage, the requirement that in the case of the compressor, the radially flowing out of the impellers process fluid has to be guided back in the direction of the rota- tion axis and can flow with an axial Ge ⁇ velocity component in the subsequent impeller of downstream stage is obtained.
  • the flow guide which allows this return of the process fluid is called Therefore, "return step.”
  • the construction ⁇ part may be designed identical and merely passes through in the reverse ⁇ opposite direction.
  • the return levels according to the invention also guide vanes, which neutralize the impressed in the flow from the upstream swirl impeller at least partially or completely, or so ⁇ even a twist in the opposite direction stamp for entry into the next downstream stage.
  • a return ⁇ guide stage 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 other Auflagevorrich-. Furthermore, the return stage comprises a so-called paddle bottom, which is attached to the intermediate bottom with the already explained guide vanes to form a return channel. Through the return channel, the process fluid flows to the next impeller ⁇ inlet.
  • the guide vanes have two functions. On the one hand, the vanes have the aerodynamic function of imparting a counter - spin to the process fluid to such an extent that at least the twist from the
  • the guide vanes have the mechanical function to fasten the blade bottom at the intermediate bottom such that in spite of the dynamic loading, a secure hold is ensured.
  • the vane stage located in the recirculation stage includes vanes that circumferentially segment the annular shape of the recirculation stage into individual channels.
  • these guide vanes may also have interruptions (split), but according to the invention are preferably designed to be continuous along the first flow direction.
  • the Guide vanes have profiles which can be represented in two dimensions - correspondingly wound off ⁇ .
  • a two-dimensional representation is possible, for example, when the annular channel of the return stage is cut along a circumferentially extending central surface. This sectional surface of a single vane can be unwound into a plane to 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 ⁇ lline is also referred to as a skeleton line.
  • a profile center line coordinate or skeleton line up coordinate along the first flow direction along an average height of the respective vane can be defined.
  • the length of the vane along this coordinate is preferably normalized to a total length of 1 or 100%.
  • the height direction of the vane is present as the
  • the height of the blade or elevation direction refers to this document as the span or span direction of the blade.
  • the profile centerline of the vane immediately adjacent the outer limit contour of the annular channel of the recirculation stage is referred to herein as the outer track of the vane and the profile centerline of the profile profile of the vane immediately adjacent the inner limit contour is referred to as the inner track of the vane.
  • the outer boundary contour of the return step can advertising referred to as a shroud-side boundary contour, because a cover disk provided with a wheel having this cover plate on the side of the outer border contour.
  • the hub-side flow contour of the impeller is located opposite to the inner boundary contour of the return leading level, so that the inner limit contour of the feedback stage can also be referred to as a hub-side boundary contour.
  • the inner boundary contour may not always be considered radially inward than the outer boundary contour for equal positions along a mean flow line through the recirculation stage, so that such alternative terms are convenient for better understanding.
  • the deflection angle at the center of the span is in each case greater than the mean anglePolumlenkungs- each case based on the trailing edges of the Leitschau ⁇ feln.
  • the advantageous realization of the invention is as ⁇ rin that this shape of the vane on the one hand brings about a favorable for the efficiency of the return step flow of the subsequent impeller and on the other hand is accompanied by a relatively low cost in terms of both production and also assembly.
  • the Leitbeschau ⁇ felung is located substantially in a radially extending flow channel without compelling 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 favorably on the inflow into the impeller that a continuation of the vane into the downstream Um ⁇ steering in the axial direction is not required.
  • impeller brought out exit edges but provide for an unfavorable excitation of the impeller due to the resulting inhomogeneities in the circumferential direction.
  • An advantageous development of the invention provides that the exit edges each describe a straight line.
  • the differences in the deflection angle are preferably realized by means of different curvatures of the skeleton lines of different profiles of the span.
  • exit edges are bent or formed kinked.
  • the bending of the exit edges can be formed both in the circumferential direction and in the radial direction and, in addition, any combination of these displacements is also conceivable.
  • FIG. 1 shows an axial longitudinal section through the cutout of a housing of a radial turbomachine with a return stage and wheels
  • FIG. 2 shows a schematic perspective illustration of a guide blade according to the invention with different shapes of the trailing edge
  • Figure 3 is a schematic perspective view of a vane according to the invention shown in connection with a erfindungsge ⁇ MAESSEN return step
  • Figure 4 is a schematic perspective view of another embodiment of a guide vane according to the invention with the associated return stage.
  • FIG. 1 shows a feedback stage RCH of a radial turbomachine RTM, which is designed as a radial turbocompressor CO.
  • Radial turbo expander wherein a process fluid PF flows through these components in a radial turbocompressor CO in a first flow direction FD1 and in a radial turboexpander in an opposite second flow direction FD2.
  • the descriptions in this document always refer to the first flow direction FD1 or a radial turbocompressor CO, unless stated otherwise.
  • Figure 1 shows parts of two successively flowed through stages, a first stage ST1 and a second stage ST2, a detail of which is shown radial turbo machine RTM or radial turbo compressor CO, wherein a wastewaterstu ⁇ fe RCH between both stages ST1, ST2 here is shown fully schematically.
  • the two stages ST1, ST2 are here arranged to be rotatable about the rotation axis X.
  • Impellers a first impeller IP1 and a second impeller IP2 shown.
  • a process fluid PF first flows through the first impeller IP1 in an axially inflowing and radially outflowing manner along a first throughflow direction FD1.
  • an oppositely directed second flow direction FD2 is also indicated, as is the case with a radial expander.
  • Section SG2 and then into a radially inwardly directed ⁇ return of a third section SG3 of the return ⁇ leading stage RCH. Downstream of the third section SG3 ge ⁇ reached, the process fluid PF in a fourth section SG4 from flowing radially inwardly to axially flowing deflected into the second impeller IP2 to be ⁇ there to be accelerated radially outward again.
  • the return stage RCH comprises a blade floor RR, guide vanes VNS and an intermediate floor DGP.
  • the intermediate floor DGP is supported by means of at least one support SUP in an on ⁇ bearing device - here in a housing CAS - and positioned there.
  • the support SUP and the supporting Ab ⁇ section of the housing CAS are formed here as a tongue and groove connection form-fitting.
  • the scaffoldzhoustu ⁇ FE RCH or have the blade bottom RR and the intermediate bottom DGP on a parting line which extends in a common plane substantially along the axis X.
  • this parting line is located in the identical part of the joint plane, such as a parting line of the housing CAS, not shown.
  • the rotor it is also conceivable for the rotor to be divisible between two wheels or for the wheels to be axially displaceable relative to one another for the purpose of assembly, so that the return stages RTC are undivided. can be formed and gradually assembled with the Laufrä ⁇ ⁇ dern IP1, IP2 of the rotor together before a merger takes place with a surrounding housing.
  • the housing CAS can in any case be formed horizontally or vertically divided.
  • the conventional design of the return stage RCH provides that the blade floor RR, the guide vanes VNS and the intermediate floor DGP are fastened to one another. In the present case this is by means of screws ge SCR ⁇ makes the simplified means of dash-dotted lines represent ⁇ are provided. So that the screws SCR one hand, the scene ⁇ felboden sufficiently secure RR at the intermediate floor DGP and thus must have a minimum thickness, it must on the other hand a sufficiently large to be provided by ⁇ hole in the vanes VNS, so that the profile of the vanes VNS formed sufficiently strong have to be.
  • FIG. 2 shows a schematic perspective view of a vane VNS a scaffold manufactured by the vane VNS a scaffold manufactured by the Ach ⁇ se X and a perpendicular radial direction R.
  • a reference plane PRF which is spanned by the Ah ⁇ se X and the radial direction R, indicated in different locations in order to illustrate geometric relationships.
  • the vane VNS includes an extending along a Spannwei ⁇ te SPW airfoil VAF, the flow around surfaces SFT from the upstream inlet edge LDE as a pressure side PRS and as a Saugsei ⁇ te PCS along a skeleton line SCL from each other by profile sections PRC spaced up to a Extend the trailing edge TLE.
  • a vane design angle VCR to the radial-axial direction fresenzebene PRF for each point of the skeleton line SCL defi ⁇ ned is.
  • FIG. 2 shows in addition a curved exit edge TLE also a straight trailing edge TLE ⁇ and provided with two Kni ⁇ CKEN bent trailing edge TLE XX, which is caused by the continued cutting or omission of portions of the original airfoil VAF in the two end regions of the span SPW ,
  • FIG. 3 shows a built-in guide vane VNS of a feedback stage RCH according to the invention.
  • the range in which the vane VNS is provided in the return step RCH he ⁇ extends substantially radially from the outside radially inwardly along the first direction of flow of the FDI process zessfluids PF.
  • a screw SCR extends in spanwise direction through the blade leaf VAF.
  • FIG. 4 shows the same situation as FIG. 3 with a differently designed vane VNS.
  • the Leitschau- fei VNS of Figure 4 is cylindrical and has at both ends of the span SPW back cut regions of the exit edge TLE ⁇ ⁇ .
  • This embodiment corresponds to the representation of one (TLE XX ) of the three alternatives in FIG. 2.

Landscapes

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

Abstract

L'invention concerne un étage de retour (RCH) d'une turbomachine à écoulement radial (RTM) comprenant au moins un étage à aube directrice (VST), l'étage de retour (RCH) s'étendant de manière annulaire autour d'un axe (X). L'étage de retour (RCH) est défini, radialement vers l'intérieur, par un contour de délimitation interne (IDC) et, radialement vers l'extérieur, par un contour de délimitation externe (ODC). L'étage à aube directrice (VST) comprend des aubes directrices (VNS) dont les surfaces autour desquelles circule l'écoulement s'étendent à partir d'un bord d'attaque (LDE) situé en amont, en tant que côté de refoulement (PRS) et en tant que côté d'aspiration PCS), le long d'une ligne moyenne (SCL), à distance l'une de l'autre, autour de sections transversales de profilés (PRC), jusqu'à un bord de fuite (TLE). Une tangente sur la ligne moyenne (SCL) de chaque section transversale de profilé (PRC) à un plan de référence radial-axial (PRF) forme un angle structural d'aube (CVA) pour chaque point de la ligne moyenne (SCL). Une différence entre un angle structural d'aube (CVA) au niveau du bord d'attaque (LDE) et un angle structural d'aube (CVA) au niveau d'une position en aval définit un angle de renvoi (RDA) pour chaque point de la ligne moyenne (SCL) de chaque section transversale de profilé (PRC). Les aubes directrices (VNS) s'étendent au moins le long d'une partie de la troisième section (SG3), les bords de fuite (TLE) étant disposés dans la troisième section (SG3). Cette invention est caractérisée en ce qu'au niveau du bord de fuite (TLE), au milieu de l'amplitude (SPW), l'angle de renvoi (RDA) est respectivement supérieur à l'angle de renvoi total (RAM) moyen. Au niveau des deux limites de l'amplitude (SPW) jusqu'à respectivement au moins 10% de l'amplitude, chaque angle de renvoi (RDA) est inférieur à l'angle de renvoi total (RAM) moyen.
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 true EP3551890A1 (fr) 2019-10-16
EP3551890B1 EP3551890B1 (fr) 2021-02-24

Family

ID=58158840

Family Applications (2)

Application Number Title Priority Date Filing Date
EP17157126.8A Withdrawn EP3364039A1 (fr) 2017-02-21 2017-02-21 Étage de retour
EP18704418.5A Active EP3551890B1 (fr) 2017-02-21 2018-01-22 Etage de retour

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP17157126.8A Withdrawn EP3364039A1 (fr) 2017-02-21 2017-02-21 Étage de retour

Country Status (4)

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

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Publication number Priority date Publication date Assignee Title
JP2018173020A (ja) * 2017-03-31 2018-11-08 三菱重工業株式会社 遠心圧縮機
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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CA1252075A (fr) 1983-09-22 1989-04-04 Dresser Industries, Inc. Configuration de diffuseur pour compresseur centrifuge
DE4234739C1 (de) 1992-10-15 1993-11-25 Gutehoffnungshuette Man Getriebe-Mehrwellenturbokompressor mit Rückführstufen
JPH11173299A (ja) * 1997-12-05 1999-06-29 Mitsubishi Heavy Ind Ltd 遠心圧縮機
US7255530B2 (en) * 2003-12-12 2007-08-14 Honeywell International Inc. Vane and throat shaping
DE102009019061A1 (de) 2009-04-27 2010-10-28 Man Diesel & Turbo Se Mehrstufiger Radialverdichter
US20130280060A1 (en) * 2012-04-23 2013-10-24 Shakeel Nasir Compressor diffuser having vanes with variable cross-sections
ITCO20120055A1 (it) * 2012-11-06 2014-05-07 Nuovo Pignone Srl Pala di canale di ritorno per compressori centrifughi
US20150086396A1 (en) * 2013-09-26 2015-03-26 Electro-Motive Diesel Inc. Turbocharger with mixed flow turbine stage
DE102014203251A1 (de) 2014-02-24 2015-08-27 Siemens Aktiengesellschaft Rückführstufe für eine Radialturbomaschine
EP2921647A1 (fr) 2014-03-20 2015-09-23 Alstom Technology Ltd Aube de turbine à gaz avec bord d'attaque et bord de fuite courbés
JP6362980B2 (ja) * 2014-09-26 2018-07-25 株式会社日立製作所 ターボ機械
DE102014223833A1 (de) * 2014-11-21 2016-05-25 Siemens Aktiengesellschaft Rückführstufe
US10760587B2 (en) * 2017-06-06 2020-09-01 Elliott Company Extended sculpted twisted return channel vane arrangement

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
EP3551890B1 (fr) 2021-02-24
CN110325743B (zh) 2020-12-29

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