EP3364039A1 - Étage de retour - Google Patents

Étage de retour Download PDF

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Publication number
EP3364039A1
EP3364039A1 EP17157126.8A EP17157126A EP3364039A1 EP 3364039 A1 EP3364039 A1 EP 3364039A1 EP 17157126 A EP17157126 A EP 17157126A EP 3364039 A1 EP3364039 A1 EP 3364039A1
Authority
EP
European Patent Office
Prior art keywords
stage
rch
span
section
scl
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Withdrawn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
EP17157126.8A
Other languages
German (de)
English (en)
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 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 EP17157126.8A priority Critical patent/EP3364039A1/fr
Priority to EP18704418.5A priority patent/EP3551890B1/fr
Priority to PCT/EP2018/051389 priority patent/WO2018153583A1/fr
Priority to CN201880013798.XA priority patent/CN110325743B/zh
Priority to US16/485,247 priority patent/US10995761B2/en
Publication of EP3364039A1 publication Critical patent/EP3364039A1/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Withdrawn legal-status Critical Current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
    • 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 recirculation stage of a radial turbomachine with at least one vane stage, the recirculation stage extending annularly around an axis, the recirculation stage being defined radially inward by an inner boundary contour and radially outward by an outer boundary contour, along a first flow direction the recirculation stage extends radially outward in a first section, wherein the return stage extends in a second portion along the first flow direction descriptive of an arcuate deflection from radially outside to radially inside, wherein the return stage along the first flow direction in a third portion from radially outside to extends radially inward, wherein the return stage extending along the first flow direction in a fourth section, an arcuate deflection descriptive from radially inside to axially, wherein the Leitschaufelstuf e comprises vanes, the vanes each comprising a vane blade extending along a span, the flow surfaces of which extend from an upstream leading edge as a pressure
  • 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, with a radial turbo expander essentially providing a reverse flow direction of the process fluid compared to a radial turbocompressor.
  • 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.
  • the invention proposes a recycling stage according to claim 1.
  • the subclaims 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.
  • This axis is in a radial turbomachine and the axis of rotation of a rotor or the shaft with the wheels.
  • 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 therefore "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 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 that can be displayed in two dimensions - accordingly handled. 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 line is also referred to below as a skeleton line.
  • a profile centerline run 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 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 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 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 can also be referred to as a cover plate-side boundary contour, 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 to the inner boundary contour of the feedback stage, so that the inner limit contour of the return 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 deflection angle in the middle of the span is in each case greater than the mean total deflection angle, in each case based on the outlet edges of the guide vanes.
  • This shaping of the guide blade on the one hand causes a favorable for the efficiency of the return stage flow of the following impeller and on the other hand, both in terms of manufacturing and assembly associated with a relatively low cost.
  • the inlet edge is preferably arranged only behind the 180 ° deflection and the outlet edge upstream of the 90 ° deflection from the radially inward flow into the axially directed flow, the guide blade is essentially in a radially extending flow channel without mandatory Axial portions of the flow.
  • the vane shape according to the invention prepares the flow behind the 180-deflection and before the diversion in the axial direction so advantageous to the inflow into the impeller that a continuation of the vane in the downstream deflection in the axial direction is not required.
  • Conventional vane forms in the recirculation stage either accept the unfavorable inhomogeneous flow distribution in the spanwise direction or are elaborately continued into the deflections of the second section and / or fourth section of the recirculation step in order to ensure a favorable flow of the following impeller.
  • the approaching edges brought close to the impeller cause 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 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.
  • an advantageous development of the invention in this context provides that at the two ends of the span to each at least 7% of the span, the skeleton lines of the local profile cross sections are shorter than a mean skeleton line length.
  • Such an embodiment can be achieved if, for example, in the case of a cylindrical blade or in the case of a non-cylindrical blade, the exit edges are shortened in these two end regions of the span or the blade is cut away or cut off at this point.
  • the invention basically required lower deflection in the areas of the spans ends is achieved in a particularly cost-effective manner.
  • FIG. 1 shows a feedback stage RCH of a radial turbomachine RTM, which is designed as a radial turbocompressor CO.
  • a radial turbocompressor CO can also be implemented as radial turbocharger 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 turbocharger 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.
  • 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 and a radial turbocompressor CO, wherein a feedback stage RCH 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 RCH.
  • 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 RCH 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 RCH 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 designed to be divisible between two wheels or that the wheels are designed to be displaceable axially relative to each other for the purpose of mounting, so that the return stages RTC are formed undivided can be 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 formed horizontally or vertically divided.
  • FIG. 2 shows a schematic perspective view of a vane VNS of a feedback stage RCH invention.
  • the 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, indicated at different points to illustrate geometric relationships.
  • the vane VNS includes an airfoil VAF extending along a span SPW, the sides of which flow around it SFT extending from the upstream leading edge LDE as a pressure side PRS and as a suction side PCS along a skeleton line SCL spaced apart by profile cross sections PRC to an exit edge TLE.
  • a span SPW span SPW
  • the sides of which flow around it SFT extending from the upstream leading edge LDE as a pressure side PRS and as a suction side PCS along a skeleton line SCL spaced apart by profile cross sections PRC to an exit edge TLE.
  • At the end of the span two tangents TGT are drawn on the skeleton line SCL and also on half the span 1 ⁇ 2SPW illustrates a tangent TGT on the skeleton line SCL that for each profile cross section PRC a vane construction angle VCR to the radial-axial reference plane PRF is defined for each point of the skeleton line SCL.
  • FIG. 2 In addition to a curved trailing edge TLE, it also shows a straight trailing edge TLE 'and a two kinked trailing trailing edge TLE "formed by cutting away portions of the original aerofoil VAF in the two end portions of the span SPW.
  • FIG. 3 shows a built-in vane VNS a feedback stage RCH invention.
  • the region in which the vane VNS is provided in the return stage RCH extends substantially from radially outward to radially inward along the first flow direction FD1 of the process fluid PF.
  • a screw SCR extends in the spanwise direction through the blade VAF.
  • FIG. 4 shows the same situation as the FIG. 3 with a differently designed vane VNS.
  • the vane VNS the FIG. 4 is cylindrically shaped and has recessed portions of the exit edge TLE "at both ends of the span SPW, which corresponds to the representation of one (TLE") of the three alternatives in FIG FIG. 2 ,

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17157126.8A 2017-02-21 2017-02-21 Étage de retour Withdrawn EP3364039A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP17157126.8A EP3364039A1 (fr) 2017-02-21 2017-02-21 Étage de retour
EP18704418.5A EP3551890B1 (fr) 2017-02-21 2018-01-22 Etage de retour
PCT/EP2018/051389 WO2018153583A1 (fr) 2017-02-21 2018-01-22 Étage de retour
CN201880013798.XA CN110325743B (zh) 2017-02-21 2018-01-22 返回级
US16/485,247 US10995761B2 (en) 2017-02-21 2018-01-22 Return stage

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP3364039A1 true EP3364039A1 (fr) 2018-08-22

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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 After (1)

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

Country Status (4)

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200165924A1 (en) * 2018-11-27 2020-05-28 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
EP4015832A1 (fr) 2020-12-18 2022-06-22 Siemens Energy Global GmbH & Co. KG Guidage d'écoulement statique, turbomachine radiale

Families Citing this family (3)

* Cited by examiner, † Cited by third party
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
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

Citations (8)

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Publication number Priority date Publication date Assignee Title
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
JPH11173299A (ja) * 1997-12-05 1999-06-29 Mitsubishi Heavy Ind Ltd 遠心圧縮機
US20100272564A1 (en) 2009-04-27 2010-10-28 Man Turbo Ag Multi stage radial compressor
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
WO2016047256A1 (fr) * 2014-09-26 2016-03-31 株式会社日立製作所 Machine à turbine
DE102014223833A1 (de) * 2014-11-21 2016-05-25 Siemens Aktiengesellschaft Rückführstufe

Family Cites Families (5)

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Publication number Priority date Publication date Assignee Title
US7255530B2 (en) * 2003-12-12 2007-08-14 Honeywell International Inc. Vane and throat shaping
US20130280060A1 (en) * 2012-04-23 2013-10-24 Shakeel Nasir Compressor diffuser having vanes with variable cross-sections
US20150086396A1 (en) * 2013-09-26 2015-03-26 Electro-Motive Diesel Inc. Turbocharger with mixed flow turbine stage
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
US10760587B2 (en) * 2017-06-06 2020-09-01 Elliott Company Extended sculpted twisted return channel vane arrangement

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
JPH11173299A (ja) * 1997-12-05 1999-06-29 Mitsubishi Heavy Ind Ltd 遠心圧縮機
US20100272564A1 (en) 2009-04-27 2010-10-28 Man Turbo Ag Multi stage radial compressor
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
WO2016047256A1 (fr) * 2014-09-26 2016-03-31 株式会社日立製作所 Machine à turbine
DE102014223833A1 (de) * 2014-11-21 2016-05-25 Siemens Aktiengesellschaft Rückführstufe

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200165924A1 (en) * 2018-11-27 2020-05-28 Pratt & Whitney Canada Corp. Inter-compressor flow divider profiling
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
EP4015832A1 (fr) 2020-12-18 2022-06-22 Siemens Energy Global GmbH & Co. KG Guidage d'écoulement statique, turbomachine radiale

Also Published As

Publication number Publication date
CN110325743A (zh) 2019-10-11
US20190368497A1 (en) 2019-12-05
EP3551890A1 (fr) 2019-10-16
EP3551890B1 (fr) 2021-02-24
CN110325743B (zh) 2020-12-29
US10995761B2 (en) 2021-05-04
WO2018153583A1 (fr) 2018-08-30

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