EP3551889A1 - Étage de retour d'un compresseur à étages multiples ou détendeur doté d'aubes directrices vrillées - Google Patents

Étage de retour d'un compresseur à étages multiples ou détendeur doté d'aubes directrices vrillées

Info

Publication number
EP3551889A1
EP3551889A1 EP18702076.3A EP18702076A EP3551889A1 EP 3551889 A1 EP3551889 A1 EP 3551889A1 EP 18702076 A EP18702076 A EP 18702076A EP 3551889 A1 EP3551889 A1 EP 3551889A1
Authority
EP
European Patent Office
Prior art keywords
stage
section
rtc
profile
return
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
EP18702076.3A
Other languages
German (de)
English (en)
Other versions
EP3551889B1 (fr
Inventor
Viktor Hermes
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 EP3551889A1 publication Critical patent/EP3551889A1/fr
Application granted granted Critical
Publication of EP3551889B1 publication Critical patent/EP3551889B1/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
    • 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
    • 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
    • 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
    • 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

Definitions

  • the invention relates to a recirculation stage for the flow through a process fluid along a flow direction of a radial turbomachine, in particular
  • a radial turbo compressor return stage wherein the return stage extends annularly about an axis, wherein the
  • Return stage is defined radially inward of an inner boundary contour and radially outward of an outer boundary contour, along a first flow direction, the return stage extends radially outwardly in a first portion, wherein the return stage in a second portion along the first flow direction an arcuate Describing extending radially outward to radi ⁇ al inside, wherein the return stage extends along the first flow direction in a third portion from radially outside to radially inside, wherein the
  • Return stage extends along the first flow direction in a fourth section descriptive arc-shaped deflection from radially inside to axially, wherein at least one vane stage comprising vanes extends at least along a portion of the third portion and segmented the return stage in the circumferential direction in Strö ⁇ mungskanäle, wherein in each case one profile center line of a profile cross section of the guide blade vanes of the guide vane stage defines an inner track on the inner boundary contour and an outer track on the outer boundary contour.
  • the invention relates to a radial turbomachine, in particular ⁇ a radial turbocompressor with at least one such feedback stage.
  • 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 to expanders as it is to compressors a radial turbo expander to a radial turbo compressor substantially provides a reverse flow direction of the process fluid. Under relaxation and deflection of a process fluid in a Radialturboexpander a conversion of the thermodynamically stored in the process fluid energy into technical work by means of drive of the impeller instead.
  • impellers of the compressor is usually a process ⁇ fluid axially to a rotational axis or at an angle to the rotational 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.
  • an impeller is to be equated with a stage of Radialturboma ⁇ machine.
  • the flow guide, to provide this recirculation of the process fluid is called "return step.”
  • the construction may be formed in part identical and merely passes through in the reverse ⁇ opposite direction.
  • a return 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 support device.
  • the feedback stage comprises a so-called bucket bottom, the one at the intermediate bottom with the already explained ⁇ be guide vanes with the formation of
  • the guide vanes have two functions. On the one hand, the guide vanes have the aerodynamic function, as far as impart the product zessfluid a counter-rotating, that at least the swirl from the upstream stage is largely kom ⁇ compensated and on the other hand, the guide vanes have the mechanical function to fasten the blade bottom at the intermediate bottom such that in spite the dynamic load is ensured a secure hold.
  • 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.
  • the conventional prior art feedback stages have several disadvantages which the invention seeks to avoid.
  • the geometrically rather simply designed return stages are for the most part aerodynamically less adapted to the fluidic task, so that the complex three-dimensional flow situation remains at least partially disregarded, especially on the show ⁇ fel Love differences remain unnoticed and accordingly occur disproportionately large flow losses, which reduce the efficiency.
  • Feedback stage according to WO2014072288A1 provide a completely three-dimensional trained blading the feedback stage, which is technically very difficult to implement and requires a complex individual design, so that in any case results in a better efficiency than the simple geometry.
  • there are major problems in the assembly of the return stage since the blading is often not able due to the three-dimensional design to allow conventional fasteners between the blade bottom and intermediate floor extending through the vanes. At this point expensive special solutions may have to be used, so that such a concept has no chance on the market.
  • the invention has therefore taken on the task of combining the characteristics of simplified production, optimized aerodynamics and ease of assembly with each other.
  • the return step a Radialturboma ⁇ machine serves to direct the process fluid from an upstream gelege ⁇ NEN impeller from the radially outwardly directed flow ⁇ direction again radially inward and axially supplied to the subsequent downstream impeller.
  • the terms axial, radial, tangential, circumferentially and similarity ⁇ Liche are in this case or in this document based in each case on the central axis around which extends the return step ⁇ ring-shaped. This axis is at a radial turbomachine also the axis of rotation of a rotor or the shaft with the wheels.
  • 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 vanes have profiles which - accordingly ⁇ wound - can also represent two dimensions. 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 in a plane to a two-dimensional Dar ⁇ position.
  • 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.
  • a profile centerline scroll 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 expediently normalized to a total length of 1.
  • the height direction of the guide blade is presently defined 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 outer track of the guide vane profile and the center line of the vane Profilguer bains located immediately at the Neren in ⁇ boundary contour is referred to as the inner track of the vane.
  • the outer boundary contour of the Return stage also be ⁇ as deck plate side boundary contour be ⁇ draws, because a provided with a cover disc impeller has this cover plate on the side of the outer Grenzkon ⁇ tur.
  • the hub-side flow contour of the impeller is located opposite to the inner Grenzkon ⁇ tur the feedback stage, so that the inner boundary contour of the feedback stage can also be referred to as a hub-side boundary contour.
  • the inner boundary contour is not always considered to be radially inward lying as the outer boundary contour for the same positions along a mean flow line through the feedback stage, so that such al ⁇ ternative terms are useful for better understanding.
  • the circumferential position angle determines the respective position in the circumferential direction of the components referred to - here essentially reference points or lines of the guide vanes, eg points on profile centerlines of certain profile cross sections.
  • the positive course direction of the circumferential position angle is selected here counter to the direction of rotation of the shaft or of the rotor.
  • the vertex of this angle coincides with the central axis.
  • the return stage is always connected to a fluidic task, so that a detachment of Be ⁇ handle world of the return stage of the rotational direction of the turbomachine is basically not appropriate.
  • the three profile sections of the guide vanes of the vane stage differ according to the invention on the basis of the focal points of their functions.
  • the first and the third profile section are strongly associated with egg ⁇ ner arcuate deflection of the process fluid, said second profile portion comprising less than the arc-shaped deflection fluidic task.
  • All three Profileab ⁇ cuts associated with either a tarry ⁇ tion or acceleration of the process fluid, so that there ⁇ going round demanding superimposed aerodynamic processes occur.
  • the second profile section is also particularly preferred, the passage of at least one fastener for the false floor on the show ⁇ felboden serve. These circumstances, the invention contributes to a special degree.
  • the invention homogenizes the flow over the height extent of the guide vanes by valid for values of L in the Profilab ⁇ cut:
  • this recess is closed to the lateral Schaufelpro ⁇ filoberfest out.
  • the Recess to a central straight extension axis and can be designed in particular as a bore.
  • the efficiency of the return stage can be further optimized if the guide vanes are each arranged with an entry edge in each case in the second section, preferably in a region of the arcuate deflection of the second section between 0 ° -90 ° of a first deflection angle to the central axis.
  • the deflection angle is at the arcuate deflections in the return stage respectively the angular difference of aggii ⁇ on the respective flow direction, in particular the first flow direction, the feedback stage in an axial-radial plane input to the output of the considered deflecting section.
  • a further improvement of aerodynamics arises because ⁇ by that the guide vanes each having a Austrittskan- te respectively in the fourth section are arranged before ⁇ Trains t in a range of the arc-shaped deflection of the fourth portion is between 0 ° -60 ° second deflection angle to the axis ,
  • a radial turbomachine according to the invention comprises a
  • the return stage in this case leads the flow along the first direction of flow from an impeller to a downstream impeller.
  • the invention allows the Ver ⁇ ratio of an intermediate diameter to an outlet diameter smaller than 1.5, in particular less than 1.4, wherein the outlet diameter of the outlet diameter of the upstream of the return stage located impeller and the intermediate diameter of the diameter of the transitional cross section of the return stage from the first section to the second section.
  • FIG. 1 shows a schematic representation of an axial longitudinal section through the cutout of a housing of a radial turbomachine with a return stage and impellers.
  • FIG shows the circumferential position angle difference curve between the outer track and the inner track of the profile center line of individual Leit ⁇ blades of the vane stage of
  • Return stage plotted over the profile length run coordinate normalized to 1 (dimensionless) along the first flow direction.
  • FIG. 1 shows a feedback stage RC of a radial turbomachine RTM, which is designed as a radial turbocompressor CO.
  • Figure 1 shows parts of two successively flowed through stages, a first stage ST1 and a second stage ST2, a partial radial turbo machine shown RTM or radial turbo compressor CO, wherein a return step RTC between both stages ST1, ST2 here is shown completely specific ⁇ automatically.
  • the two stages ST1, ST2 are here with the axis of rotation X arranged rotatably impellers, a first impeller and a second impeller IPL Darge ⁇ represents IP2.
  • a process fluid PF first flows through the first impeller IP1 in an axial inflowing and radially outflowing manner along a first throughflow direction FD1.
  • a first throughflow direction FD1 For example only and an oppositely directed from ⁇ second flow direction FD2 is indicated how these vorläge at a radial expander.
  • Downstream subsequent to the first impeller IPL reaches the process ⁇ fluid PF radially outwardly flowing a radially outwardly directed first portion SGI and is delayed there, ge ⁇ reached downstream in a 180 ° deflection of a second portion SG2 and then in a radially inwardly directed ge ⁇ recycling a third portion of the SG3
  • the return stage RTC comprises a blade floor RR, vanes VNS and an intermediate floor DGP.
  • the intermediate bottom DGP is supported by means of at least one support SUP in a support device - here in a housing CAS - and positioned there.
  • the support SUP and the supporting portion of the housing CAS are formed here as a tongue and groove connection form-fitting. In a manner not shown, the
  • Return stage RTC and the blade floor RR and the intermediate bottom DGP have a parting line which extends in a common plane substantially along the axis X. Expedient for the assembly, 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 is designed to be divisible between two wheels or the wheels are axially displaceable relative to each other for the purpose of assembly, so that the feedback stages RTC can be formed undivided and gradually with the Laufrä- Nder IP1, IP2 of the rotor together be mounted before one
  • the housing CAS can in any case be formed horizontally or vertically divided.
  • the conventional design of the return stage RTC which is shown in FIG. 1, 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, which are simplified by means of dash-dotted lines provided DAR.
  • 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.
  • the guide vanes are split along the first flow direction FD1 into three successive profile sections PS:
  • FIG. 2 shows schematically a cross section through an inven tion ⁇ proper radial turbomachine RTM, as shown in Figure 1 with II-II.
  • the first impeller IP1 mounted on the shaft SH is rotatably supported about the axis X along the rotational direction ROT.
  • the circumferential position angle ⁇ is positive counter to the rotational direction ⁇ RED.
  • the first impeller IP1 has been exemplarily ⁇ characterized IPB blades of a moving blade stage. For a bucket IPB, the trailing edge TEI is entered. Downstream of the first impeller IP1 extends the
  • the feedback stage RTC has a Leit ⁇ vane stage VST, with vanes VNS, one of which is shown by way of example. Schematicallymaschineichne- te vane VNS is provided only with their leading edge LER is ⁇ .
  • Figure 2 shows the relationship Zvi ⁇ rule the direction of rotation of the shaft SH RED or Laufrä ⁇ IP1, IP2 and the circumferential position angle ⁇ .
  • FIG. 3 shows three-dimensional parts of the return stage RTC, namely the vane stage VST with the guide vanes VNS and their three-dimensional design.
  • FIG. 4 shows the course of the difference between the circumferential position angle of the outer track to the inner track, plotted over the profile center line travel coordinate L, which is standardized to a total length 1.
  • a first alternative ALT1 provides that the difference is posi ⁇ tive first and then decreases to 0 at about 0.3L and there is constant until approximately 0,65LA6 drops into the negative.
  • a second alternative ALT2 provides that the circumferential position angle difference ⁇ is initially positive in the region of the leading edge LER, then decreases to the negative, has a local minimum there and rises again up to a difference of 0 at approximately 0.3L. There ⁇ remains constant until about 0, 65L and then rises to positive, up to a local maximum, before dropping back into negative.
  • a first profile PS1 cut the circumferential position angle difference (except egg ⁇ NEN intersection with the axis O) equal to 0, just as in the third profile section PS3.
  • the second Profilab ⁇ PS2 cut in the middle of each vane VNS results in a peripheral position angle difference of 0 con ⁇ stant.

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  • 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 (RTC) servant à l'écoulement au moyen d'un fluide de processus le long d'une direction d'écoulement d'une turbomachine radiale (RTM), en particulier un étage de retour de turbocompresseur radial (RCC), l'étage de retour (RTC) s'étendant de manière annulaire autour d'un axe (X), l'étage de retour (RTC) étant défini radialement vers l'intérieur par un contour limite intérieur (IDC) et radialement vers l'extérieur par un contour limite extérieur (ODC), au moins un étage (VST) comportant des aubes directrices (VNS) s'étendant au moins le long d'une partie de la troisième section (SG3) et l'étage de retour étant segmenté en canaux d'écoulement dans la direction périphérique, une ligne centrale profilée (PML) d'une section transversale profilée (PRC) des aubes directrices (VNS) de l'étage d'aubes directrices (VST) définissant respectivement une piste intérieure (ITR) du côté du contour limite intérieur (IDC) et une piste extérieure (OTR) du côté du contour limite extérieur (ODC). L'invention concerne en outre une turbomachine radiale (RTM), en particulier un turbocompresseur radial (CO) comprenant au moins un étage de retour de ce type. L'invention vise à améliorer le comportement aérodynamique. À cet effet, les aubes directrices (VNS) sont de forme sensiblement cylindrique dans une deuxième partie profilée centrale (PS2) et sont par ailleurs de configuration tridimensionnelle.
EP18702076.3A 2017-02-10 2018-01-09 Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées Active EP3551889B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP17155607.9A EP3361101A1 (fr) 2017-02-10 2017-02-10 Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées
PCT/EP2018/050397 WO2018145838A1 (fr) 2017-02-10 2018-01-09 Étage de retour d'un compresseur à étages multiples ou détendeur doté d'aubes directrices vrillées

Publications (2)

Publication Number Publication Date
EP3551889A1 true EP3551889A1 (fr) 2019-10-16
EP3551889B1 EP3551889B1 (fr) 2020-08-19

Family

ID=58043888

Family Applications (2)

Application Number Title Priority Date Filing Date
EP17155607.9A Withdrawn EP3361101A1 (fr) 2017-02-10 2017-02-10 Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées
EP18702076.3A Active EP3551889B1 (fr) 2017-02-10 2018-01-09 Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP17155607.9A Withdrawn EP3361101A1 (fr) 2017-02-10 2017-02-10 Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées

Country Status (4)

Country Link
US (1) US11073162B2 (fr)
EP (2) EP3361101A1 (fr)
CN (1) CN110291295B (fr)
WO (1) WO2018145838A1 (fr)

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Publication number Priority date Publication date Assignee Title
US10760587B2 (en) 2017-06-06 2020-09-01 Elliott Company Extended sculpted twisted return channel vane arrangement
KR102427392B1 (ko) * 2018-01-24 2022-07-29 한화에어로스페이스 주식회사 압축기용 디퓨저
EP3690254A1 (fr) 2019-01-31 2020-08-05 Siemens Aktiengesellschaft Roue à aubes d'une turbomachine radiale, turbomachine radiale
US11598347B2 (en) * 2019-06-28 2023-03-07 Trane International Inc. Impeller with external blades
JP2022184085A (ja) * 2021-05-31 2022-12-13 三菱重工コンプレッサ株式会社 遠心圧縮機
CN114593089A (zh) * 2022-01-26 2022-06-07 北京盈天航空动力科技有限公司 一种微小型涡喷发动机v型子午流道扩压器

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Also Published As

Publication number Publication date
EP3361101A1 (fr) 2018-08-15
US20200011345A1 (en) 2020-01-09
WO2018145838A1 (fr) 2018-08-16
US11073162B2 (en) 2021-07-27
EP3551889B1 (fr) 2020-08-19
CN110291295A (zh) 2019-09-27
CN110291295B (zh) 2020-11-03

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