EP3361101A1 - Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées - Google Patents

Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées Download PDF

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Publication number
EP3361101A1
EP3361101A1 EP17155607.9A EP17155607A EP3361101A1 EP 3361101 A1 EP3361101 A1 EP 3361101A1 EP 17155607 A EP17155607 A EP 17155607A EP 3361101 A1 EP3361101 A1 EP 3361101A1
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EP
European Patent Office
Prior art keywords
stage
section
rtc
profile
itr
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.)
Withdrawn
Application number
EP17155607.9A
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German (de)
English (en)
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 AG
Original Assignee
Siemens AG
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 filed Critical Siemens AG
Priority to EP17155607.9A priority Critical patent/EP3361101A1/fr
Priority to PCT/EP2018/050397 priority patent/WO2018145838A1/fr
Priority to US16/483,424 priority patent/US11073162B2/en
Priority to EP18702076.3A priority patent/EP3551889B1/fr
Priority to CN201880011227.2A priority patent/CN110291295B/zh
Publication of EP3361101A1 publication Critical patent/EP3361101A1/fr
Withdrawn legal-status Critical Current

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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
    • 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 flowing through a process fluid along a throughflow direction of a radial turbomachine, in particular a radial turbocompressor recirculation stage, wherein the recirculation stage extends annularly around an axis, wherein the recirculation stage is defined radially inward by an inner boundary contour and radially outwardly by an outer boundary contour.
  • the return stage extends radially outwardly in a first portion, wherein the return stage extends in a second portion 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 portion extending from radially outward to radially inward, wherein the return stage is a bend in a fourth portion along the first flow direction descriptively extending from radially inward to axially, at least one vane stage comprising vanes extending at least along a portion of the third portion and the return stage circumferentially segmented into flow channels, wherein each profile center line of a profile cross section of the vanes of the vane stage on the inner boundary contour an inner Track and defined by the outer boundary contour an outer track.
  • 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 turboexpander relative to a radial turbocompressor essentially provides a reverse flow direction of the process fluid.
  • impellers of the compressor generally suck a process fluid axially to an axis of rotation or obliquely to the axis of rotation with an axial velocity component and accelerate and compress this process fluid by means of the respective impeller - which is also referred to as an impeller -, the flow direction of the process fluid in the deflects 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.
  • a multi-stage radial turbomachine means in the terminology of this invention that multiple impellers are rotatably mounted about the same axis of rotation.
  • an impeller equate to one stage of the radial turbomachine.
  • the multistage results in the requirement that in the case of the compressor, the process fluid flowing radially out of the impeller must be guided back in the direction of the axis of rotation and can flow into the downstream impeller of the downstream stage with an axial velocity component.
  • the flow guide, which allows this return of the process fluid is called "return stage".
  • the component can be designed identically and is only flowed through in the reverse 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. 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 counterangle to the process fluid to the extent that at least the swirl from the upstream stage is largely compensated, and on the other hand, the vanes have the mechanical task of securing the blade bottom to the false floor in such a way that despite the dynamic load secure hold is guaranteed.
  • the prior art conventional recycle stages have several disadvantages that 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 blade height differences remain unnoticed and accordingly occur disproportionately large flow losses, which reduce the efficiency.
  • Other solutions, especially the return stage after 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.
  • 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 recirculation stage of a radial turbomachine serves to redirect the process fluid from an upstream impeller radially outward from the radially outwardly directed flow direction and to supply it axially to the downstream downstream impeller.
  • the terms 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. This axis is in 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 that can be displayed in two dimensions - accordingly unwound.
  • 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.
  • a profile center line travel 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 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 located immediately adjacent the inner limit contour is referred to as the inner track of the vane.
  • the outer limit contour of the return stage also referred to as cover plate side boundary contour, because a provided with a cover disc impeller has this cover plate on the side of the outer boundary contour.
  • the hub-side flow contour of the impeller is located opposite to the inner boundary contour of the feedback stage, so that the inner limit contour of the feedback stage can also be referred to as a hub-side boundary contour.
  • the inner limit contour may not always be considered to be radially inward than the outer limit contour for equal positions along a mean flow line through the recirculation stage, so that such alternative terms are convenient for better understanding.
  • the circumferential position angle determines the respective position in the circumferential direction of the referenced components - here substantially reference points or lines of the vanes, e.g. Points on profile center lines of certain profile cross sections.
  • the positive course direction of the circumferential position angle is in this case selected 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 the terminology of the feedback stage of the rotational direction of the turbomachine is basically not appropriate.
  • the guide blades in the second profile section have a recess extending from a point of the inner track to a point of the outer track for passing a fastening element between the inner boundary contour and the outer boundary contour.
  • This recess is preferably closed towards the lateral blade profile surfaces.
  • the recess has 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 inlet 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 in each case the angular difference of a projection of the respective throughflow direction, in particular of the first throughflow direction, of the return stage in an axial-radial plane at the exit to the considered deflecting section.
  • a further improvement of the aerodynamics results from the fact that the guide vanes are each arranged with an exit edge in each case in the fourth section, preferably in a region of the arcuate deflection of the fourth section between 0 ° -60 ° second deflection angle to the axis.
  • a radial turbomachine according to the invention comprises a return stage of the type already described, wherein the axis about which the return stage extends annularly with the axis of rotation of a rotor or a shaft carrying wheels, is identical.
  • the return stage in this case leads the flow along the first direction of flow from an impeller to a downstream impeller.
  • the invention makes it possible for the ratio of an intermediate diameter to an outlet diameter to be less than 1.5, in particular less than 1.4, wherein the exit diameter is the exit diameter of the impeller located upstream of the recirculation stage and the intermediate diameter is the diameter of the transition cross section of the recirculation stage from the first section to the second section.
  • FIG. 1 shows a recycling stage RC of a radial turbomachine RTM, which is designed as a radial turbocompressor CO.
  • a radial turbocompressor CO The components explained here by way of example for a radial turbocompressor CO are identical in construction according to the invention as a radial turboexpander, 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, unless stated otherwise.
  • FIG. 1 shows parts of two successively flowed through stages, a first stage ST1 and a second stage ST2 a partially illustrated radial turbomachine RTM or radial turbocompressor CO, wherein a feedback stage RTC between the two stages ST1, ST2 is shown here completely schematically.
  • the two stages ST1, ST2 are shown here with wheels rotatably arranged about the rotation axis X, a first impeller IP1 and a second impeller IP2.
  • 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.
  • the process fluid PF Downstream of the first impeller IP1, the process fluid PF reaches a radially outwardly directed first section SG1 and is decelerated there, passes downstream into an approximately 180 ° deflection of a second section SG2 and then into a radially inward direction Returning a third section SG3 of the feedback stage RTC.
  • the process fluid PF flows in a fourth section SG4 from radially inward into the second impeller IP2 in a direction of axial flow and is then again accelerated radially outward.
  • 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 in this case designed as a tongue and groove connection form-fitting.
  • the return stage RTC or the blade bottom 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 divisible between two wheels or the wheels are axially displaceable to each other for the purpose of assembly, so that the return stages RTC can be formed undivided and gradually with the wheels IP1, IP2 of the rotor are mounted together before merging with a surrounding enclosure.
  • the housing CAS can in any case be formed horizontally or vertically divided.
  • FIG. 2 schematically shows a cross section through a radial turbomachine RTM according to the invention, as shown in the FIG. 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 directions are marked radially horizontally and vertically.
  • the circumferential position angle ⁇ is positive against the rotational direction ROT.
  • the first impeller IP1 has, by way of example, rotor blades IPB of a rotor blade stage. For a bucket IPB, the trailing edge TEI is entered. Downstream of the first impeller IP1 extends the feedback stage RTC.
  • the feedback stage RTC has a vane stage VST, with guide vanes VNS, one of which is shown by way of example.
  • the schematically drawn vane VNS is shown only with its leading edge LER.
  • FIG. 2 shows FIG. 2 the relationship between the direction of rotation ROT of the shaft SH and the wheels IP1, IP2 and the circumferential position angle ⁇ .
  • FIG. 3 shows three-dimensional parts of the feedback stage RTC, namely the vane stage VST with the vanes VNS and their three-dimensional design.
  • FIG. 4 shows the variation of the circumferential position angle of the outer track to the inner track plotted against the profile centerline running coordinate L which is normalized to a total length of 1.
  • a first alternative ALT1 provides that the difference is initially positive and then drops to 0 at approx. 0.3L and remains constant there until it drops to negative at approx. 0.65L ⁇ .
  • 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 up to about 0.65L and then increases to positive, up to a local maximum, before dropping back into negative.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17155607.9A 2017-02-10 2017-02-10 Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées Withdrawn EP3361101A1 (fr)

Priority Applications (5)

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
US16/483,424 US11073162B2 (en) 2017-02-10 2018-01-09 Return stage of a multi-staged compressor or expander with twisted guide vanes
EP18702076.3A EP3551889B1 (fr) 2017-02-10 2018-01-09 Canal de retour de compresseur ou turbodétendeur multicellulaire avec aubes directrices vrillées
CN201880011227.2A CN110291295B (zh) 2017-02-10 2018-01-09 返回级，径流式涡轮机械

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP3361101A1 true EP3361101A1 (fr) 2018-08-15

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 After (1)

Application Number Title Priority Date Filing Date
EP18702076.3A Active EP3551889B1 (fr) 2017-02-10 2018-01-09 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3690254A1 (fr) 2019-01-31 2020-08-05 Siemens Aktiengesellschaft Roue à aubes d'une turbomachine radiale, turbomachine radiale

Families Citing this family (5)

* Cited by examiner, † Cited by third party
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
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

Citations (7)

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Publication number Priority date Publication date Assignee Title
JPS562499A (en) * 1979-06-22 1981-01-12 Hitachi Ltd Guide vane for multistage oblique flow pump
DE3430307A1 (de) 1983-09-22 1985-04-04 Dresser Industries, Inc., Dallas, Tex. Diffusorbauweise fuer einen kreiselkompressor
EP0592803B1 (fr) 1992-10-15 1997-03-05 MAN Gutehoffnungshütte Aktiengesellschaft Compresseur à arbres multiples et transmission
US20100272564A1 (en) 2009-04-27 2010-10-28 Man Turbo Ag Multi stage radial compressor
JP2012102712A (ja) * 2010-11-15 2012-05-31 Mitsubishi Heavy Ind Ltd ターボ型圧縮機械
WO2014072288A1 (fr) 2012-11-06 2014-05-15 Nuovo Pignone Srl Compresseur centrifuge avec aube à canal de retour torsadé
DE102014203251A1 (de) 2014-02-24 2015-08-27 Siemens Aktiengesellschaft Rückführstufe für eine Radialturbomaschine

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DE1403497A1 (de) * 1961-11-03 1969-01-23 Doelz Dipl Ing Heinrich Mehrstufiger Turbokompressor
CS175720B1 (fr) 1974-04-01 1977-05-31
JPS5641496A (en) * 1979-09-12 1981-04-18 Hitachi Ltd Return bend of single shaft multistage centrifugal compressor
JPH10331793A (ja) 1997-06-03 1998-12-15 Mitsubishi Heavy Ind Ltd 遠心圧縮機の戻り流路構造
JPH11173299A (ja) 1997-12-05 1999-06-29 Mitsubishi Heavy Ind Ltd 遠心圧縮機
JP2004150404A (ja) * 2002-11-01 2004-05-27 Mitsubishi Heavy Ind Ltd ベーンドディフューザ及び該ディフューザを備えた輻流ターボ機械
US7448852B2 (en) 2005-08-09 2008-11-11 Praxair Technology, Inc. Leaned centrifugal compressor airfoil diffuser
US7717672B2 (en) * 2006-08-29 2010-05-18 Honeywell International Inc. Radial vaned diffusion system with integral service routings
CN104121203A (zh) * 2014-07-14 2014-10-29 杨丽萍 一种污水用分段式多级泵的单段结构

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS562499A (en) * 1979-06-22 1981-01-12 Hitachi Ltd Guide vane for multistage oblique flow pump
DE3430307A1 (de) 1983-09-22 1985-04-04 Dresser Industries, Inc., Dallas, Tex. Diffusorbauweise fuer einen kreiselkompressor
EP0592803B1 (fr) 1992-10-15 1997-03-05 MAN Gutehoffnungshütte Aktiengesellschaft Compresseur à arbres multiples et transmission
US20100272564A1 (en) 2009-04-27 2010-10-28 Man Turbo Ag Multi stage radial compressor
JP2012102712A (ja) * 2010-11-15 2012-05-31 Mitsubishi Heavy Ind Ltd ターボ型圧縮機械
WO2014072288A1 (fr) 2012-11-06 2014-05-15 Nuovo Pignone Srl Compresseur centrifuge avec aube à canal de retour torsadé
DE102014203251A1 (de) 2014-02-24 2015-08-27 Siemens Aktiengesellschaft Rückführstufe für eine Radialturbomaschine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3690254A1 (fr) 2019-01-31 2020-08-05 Siemens Aktiengesellschaft Roue à aubes d'une turbomachine radiale, turbomachine radiale

Also Published As

Publication number Publication date
US20200011345A1 (en) 2020-01-09
US11073162B2 (en) 2021-07-27
CN110291295B (zh) 2020-11-03
WO2018145838A1 (fr) 2018-08-16
CN110291295A (zh) 2019-09-27
EP3551889B1 (fr) 2020-08-19
EP3551889A1 (fr) 2019-10-16

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