EP3460257A1 - Dispositif pouvant être traversé - Google Patents

Dispositif pouvant être traversé Download PDF

Info

Publication number
EP3460257A1
EP3460257A1 EP17192114.1A EP17192114A EP3460257A1 EP 3460257 A1 EP3460257 A1 EP 3460257A1 EP 17192114 A EP17192114 A EP 17192114A EP 3460257 A1 EP3460257 A1 EP 3460257A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
impeller
dff
axial
vne
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Withdrawn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
EP17192114.1A
Other languages
German (de)
English (en)
Inventor
Uwe Martens
Nico Petry
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 EP17192114.1A priority Critical patent/EP3460257A1/fr
Priority to PCT/EP2018/072378 priority patent/WO2019057412A1/fr
Priority to CN201880060877.6A priority patent/CN111133202B/zh
Priority to US16/645,098 priority patent/US11313384B2/en
Priority to JP2020516527A priority patent/JP7074959B2/ja
Priority to EP18759897.4A priority patent/EP3658780A1/fr
Publication of EP3460257A1 publication Critical patent/EP3460257A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2250/52—Outlet

Definitions

  • the invention relates to an arrangement which can be traversed by a process fluid along a main flow direction comprising an impeller rotatable about an axis in a direction of rotation and a stator-bladed stationary diffuser located downstream of the impeller, the impeller having an inlet for a substantially axial inflow and an outlet for a substantially radial outflow, wherein between a wheel disc and a cover disc of the impeller radially and axially extending blades are arranged, the impeller channels in a circumferential direction delimit each other, the diffuser extending along a main flow direction substantially radially, wherein the diffuser has an axial shroud side and an axial shroud side defining therebetween an axial channel width of the diffuser, the diffuser having a diffuser inlet for substantially radial inflow and a diffuser exit, wherein between the Radusionnseite and the cover plate side of the diffuser along a blade height direction axially and along a flow direction radially extending guide vanes are
  • the cover plate and wheel disc are formed on the outer circumference as conical surfaces.
  • the invention proposes an arrangement of the type defined above, which is further formed by means of the characterizing part of the main claim.
  • the individual vanes can be defined as a stack of blade profiles along a blade height.
  • the blade profiles here are two-dimensional geometries that define the blade outer contour in a specific blade height position.
  • the invention understands a ("imaginary") straight connecting line between the profile leading edge (profile nose) and a profile trailing edge under a profile chord of a blade profile.
  • the angle of attack of a blade profile corresponds to the angle between the tangent to the chord and the tangent to the circular motion of the rotor. Accordingly, the angle of attack along the extent of the blade is perpendicular to the blade height, ie substantially parallel to the main flow direction constant and can vary along the blade height.
  • a skeleton line describes a profile section or a profile of a blade in a certain height position in that the skeleton line (curvature line) is a line inscribed on the center points or on the suction side and pressure side of the profile.
  • a process fluid may in the present case be any gaseous, liquid or mixed-phase fluid.
  • the process fluid moves along a main flow direction through the assembly, which is typically part of a turbomachine.
  • the outflow direction is understood to mean the mean direction of travel of the process fluid in the region which is defined in the respective context of physical boundary walls.
  • the process fluid moves radially outwardly through a portion of the leading edges of the vanes radially outward in a range of exit edges of the vanes through individual vanes axially delimited and circumferentially confined flow channels. Since the guide vanes each have a curvature of the profile, it is only possible to speak of a substantially radial main flow direction. In any case, the term "main flow direction" ignores local vortexes and turbulences.
  • the impeller of the arrangement usually has a wheel disc and a cover plate.
  • the wheel disc limits flow channels of the impeller on the one hand radially (predominantly in the inflow) on the inside and on the other hand to the axial side (increasingly close to impeller outlet) through which axially opposite to the inflow and through which a process fluid does not flow into the impeller ,
  • the cover disc represents the boundary of the wheel disc opposite flow channels of the impeller.
  • the process fluid flows axially into the impeller and is deflected for the flow channels of the impeller radially outward.
  • the cover plate side could therefore be called the inflow side.
  • flow channels of the impeller are separated from each other by means of blades, wherein the blades connect the wheel disc and the cover disc with each other.
  • the wheel disc and the cover disc also define the wheel disc side and the cover disc side, respectively, to which reference will also be made in the description of the diffuser.
  • the inflow of the diffuser in the arrangement according to the invention always takes place radially from the inside to the outside.
  • the diffuser is also provided with a substantially radially outwardly directed outflow in the form of a diffuser exit.
  • the diffuser is also curved and optionally flows radially-axially, axially or radially inwards.
  • a section of the diffuser always extends substantially radially. This section can be located in front of a deflection of the flow in an axial or in a radially inward flow direction.
  • an entry edge angle for each axial blade height is defined as the angle between an entry edge tangent to a skeleton line at an entry edge of the respective guide blade and a peripheral tangent through the entry edge, wherein the entry edge angle cover plate side is smaller than the wheel disc side.
  • a circumferential tangent passing through the leading edge means that this peripheral tangent is perpendicular to a radial jet through the entry edge point of the respective profile section of the vane.
  • the entry edge angle here is the mathematically positive swept angle from the peripheral tangent to the entrance edge tangent to the skeleton line.
  • An advantageous development of the invention provides that the difference between the cover plate side and wheel disc side entry edge angle is at least 5 °.
  • An inventive embodiment of the invention in this order of magnitude leads to a significant improvement in the aerodynamic properties of the arrangement.
  • Another advantageous development of the invention provides that the angle of attack of the guide vanes cover plate side is smaller than the wheel disc side.
  • This embodiment takes into account the difference in the flow pattern after exiting the impeller between the cover plate side and the wheel disc side in addition, so that the aerodynamics is further improved.
  • Another development of the invention provides that the flow is prepared particularly expedient after exiting the impeller before entering the diffuser when the quotient of the axial channel width of the bladed diffuser to the maximum impeller outlet diameter is greater than 0.04.
  • Another advantageous development of the invention provides that the quotient of the axial channel width of the bladed diffuser to the axial channel width of the impeller at the maximum impeller outlet diameter is less than 0.95. In this way, the flow is accelerated with the entry into the diffuser, so that the vortex formation behind the impeller is reduced.
  • the guide vanes are designed such that an angle between a tangent to the skeleton line in the entry edge region to a tangent to the skeleton line in the exit edge region cover plate side is smaller than the wheel disc side.
  • this feature can be characterized in that a deflecting function predetermined by the respective profile is less strong on the cover plate side than on the wheel disk side.
  • a similar effect has another advantageous development of the arrangement according to the invention, in which the guide vanes are formed such that an angle between a tangent to the skeleton line in the entry edge region to the chord side cover plate side is smaller than the wheel disc side.
  • the angle between a tangent to the skeleton line in the entry edge region to the chord is defined as the mathematically positive angle from the tangent to the skeleton line in the entry edge region to the chord.
  • the guide vanes have an inclination such that the leading edge is offset on the cover disc side opposite the wheel disc-side leading edge against the rotational direction of the impeller by at least 10% of the axial channel width of the diffuser.
  • this embodiment also takes into account the differences between the cover plate side and the Radepticnseite in the flow pattern after exiting the impeller.
  • leading edge in the circumferential direction and the exit edge may be inclined in the circumferential direction, wherein it is particularly useful according to an advantageous embodiment of the arrangement, when the guide vanes are designed such that an offset against the direction of rotation of the impeller at the trailing edge of the Cover disk side opposite the Radepticnseite is lower than at the leading edge.
  • a harmonious, low-pressure flow control is achieved in particular when the axial course (course in the height direction) of the vanes of the diffuser from the cover plate side to the Radepticnseite is continuously curved.
  • FIG. 1 and 2 show a schematic representation of longitudinal sections through an inventive arrangement ARG, wherein FIG. 2 a denoted by II detail of FIG. 1 reproduces.
  • An inventive arrangement ARG is flowed through by a process fluid PFF along a main flow direction MFD from an inlet INL to an outlet EXT.
  • the arrangement ARG comprises an impeller IMP which is rotatable about an axis X in the direction of rotation RTD. Downstream of the impeller IMP is a vaned with vanes VNE standing diffuser DFF.
  • the impeller IMP has an inlet INI for a substantially axial inflow and a outlet EXI for substantially radial outflow.
  • the suitability for the essentially axial inflow or the essentially radial outflow of the impeller is characterized by the course of the flow channel or impeller channels ICH extending through the impeller. Between a wheel HWI and a cover plate SWI of the impeller IMP are radially and axially extending blades BLD. The blade channels ICH are through these blades BLD in a circumferential direction CDR delimited from each other as the Figures 3 and 4 is removable.
  • the diffuser DFF extends with diffuser flow channels along a main flow direction MFD that is substantially radial.
  • the diffuser DFF has an axial cover disk side SWS and an axial wheel disk side HWS.
  • the diffuser DFF has a diffuser inlet ILD for a substantially radial inflow and a diffuser outlet EXD.
  • the diffuser is divided into three sections extending along the main flow direction MFD, into a first diffuser third TS1, a second diffuser third TS2 and a third diffuser third TS3.
  • a first diffuser third TS1 a second diffuser third TS2
  • a third diffuser third TS3 a third diffuser third TS3.
  • the vanes VNE delimit individual vane channels DCH in a circumferential direction CDR from each other.
  • the Bucket profiles PRL themselves are two-dimensional geometries that define the bucket outer contour in a particular bucket elevation position.
  • the actual outer contour of the blade on the respective suction side SCS and pressure side PRS results as a surface interpolation between the linear boundary contours of the blade profiles PRL, which each indicate a linear specification in the respective blade height position (here also axial position).
  • FIG. 3 shows a schematic cross-section of the inventive arrangement ARG with an impeller IMP and a downstream downstream diffuser DFF, which is designed as a stator STA.
  • the impeller IMP rotates in the representation opposite to a circumferential direction CDR.
  • the individual guide vanes VNE of the diffuser DFF are merely reproduced as schematic skeleton lines BWL.
  • a skeleton line BWL here describes a profile section or a profile of a blade in a certain height position in that the skeleton line BWL, also sometimes called curvature line, is one of the center inscribed or the suction side and the pressure side of the profile tangent circles defined line.
  • FIG. 5 Using two circles CLC exemplified how pressure side PRF and suction side SCS a vane VNE by means of the inscribed circles CLC define the skeleton line BWL.
  • FIG. 5 shows the FIG. 5 only an axial section through the diffuser DFF in the region of a vane VNS, the figure for both the cover plate side SWS, and for the wheel disc side HWS has validity.
  • FIG. 4 shows similar relationships in conjunction with the impeller IMP.
  • the impeller IMP is divided in three along the main flow direction MFD successive third sections approximately from a blade inlet edge ILE to a blade outlet edge ITE.
  • the blade inlet edge ILE and the blade outlet edge ITE are not necessarily identical to the inlet INI of the impeller or outlet XEI of the impeller.
  • the main flow direction MFD also runs axially in the impeller IMP - ie in FIG. 4 also in the drawing plane.
  • the information about the axial extent goes in the axial projection of the blades BLD of the FIG. 4 naturally lost.
  • the impeller has a first impeller section IS1, a second impeller section IS2 and a third impeller section IS3.
  • FIG. 4 shows in each case dashed representation the cover disk side SWI and the wheel disk side HWI both for a rotor blade BLD and for a stator blade VNE.
  • an entry edge angle LEA for each axial vane is defined as the angle between an entry edge tangent TLV of the respective vane VNE and a circumferential tangent CTG through the entry edge DLE.
  • the entry edge angle LEA is mathematically positively measured from the circumferential tangent CTG on the entrance edge tangent TLV.
  • the circumferential tangent CTG is a tangent to the circumferential direction in the respective indicated position, here at the position of the leading edge DLE.
  • This circumferential tangent CTG can also be defined as being perpendicular to a radial ray RAD and the reference point, here including the leading edge DLE.
  • the profile chord VCH of the profile of the vane VNE is also shown in the respective section, which extends from an entry edge DLE to a trailing edge DTE as a straight line.
  • the pitch angle AOA is also defined as a mathematically positive measured angle from the circumferential tangent CTG to the chord VCH.
  • FIG. 4 shows these relationships for the cover plate side SWS and the wheel disc side HWS of the diffuser DFF.
  • the Arrangement ARG provides that the entry edge angle LEA cover plate side is smaller than the wheel side at the diffuser DFF.
  • the difference between the cover-disk-side and the wheel-disk-side entry edge angle LEA is preferably at least 5 degrees.
  • the quotient of the axial channel width SAC of the bladed diffuser DFF to the maximum impeller outlet diameter is more than 0.04. Also the FIG. 2 it can be seen that the quotient of the axial channel width SAC of the bladed diffuser to the axial channel width IAC of the impeller IMP at the maximum impeller outlet diameter DIE is less than 0.95.
  • the vane VNE is designed such that an angle, here called profile curvature angle VBA, between a tangent TLV on the skeleton line BWL in the entry edge region LEA to a tangent TTV on the skeleton line BWL in the exit edge region TEA is smaller than the wheel disc side.
  • the angle of curvature VBA is here again mathematically positively measured starting from the tangent TLV on the skeleton line BWL in the entry edge region LEA.
  • FIG. 5 an advantageous embodiment of the invention is shown such that an angle between the tangent TLV on the skeleton line BWL in the entry edge region LEA to the chord VCH cover plate side is smaller than the wheel disc side, wherein the angle is referred to here as competentsanstellwinkel VTC.
  • the conditions on the wheel disc side HWI or the cover disc side SWI basically schematically reproduces and accordingly represents both sides.
  • An entry edge DLE of the vanes VNE may be advantageous, as in FIG. 4 shown offset radially a distance downstream of the diffuser inlet DFF, wherein in FIG. 4 this radial offset is reported as CBS.
  • the guide vanes VNE have an inclination, such that the leading edge VLE is the cover plate opposite the wheel-disk-side leading edge VLE opposite to the rotational direction RTD of the impeller IMP offset by at least 10% of the axial channel width SAC of the diffuser DFF.
  • the vanes VNE are formed such that an offset against the rotation direction RTD of the impeller IMP at the trailing edge VTE of the cover plate side SWI against the Radepticnseite HWI is lower than at the leading edge VLE.
  • the axial course of the guide vanes of the diffuser DFF from the cover disk side SWI to the wheel disk side HWI is designed to be continuously curved.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17192114.1A 2017-09-20 2017-09-20 Dispositif pouvant être traversé Withdrawn EP3460257A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP17192114.1A EP3460257A1 (fr) 2017-09-20 2017-09-20 Dispositif pouvant être traversé
PCT/EP2018/072378 WO2019057412A1 (fr) 2017-09-20 2018-08-20 Dispositif pouvant être parcouru par un flux
CN201880060877.6A CN111133202B (zh) 2017-09-20 2018-08-20 可流动通过的装置
US16/645,098 US11313384B2 (en) 2017-09-20 2018-08-20 Flow-through arrangement
JP2020516527A JP7074959B2 (ja) 2017-09-20 2018-08-20 貫流構成体
EP18759897.4A EP3658780A1 (fr) 2017-09-20 2018-08-20 Dispositif pouvant être parcouru par un flux

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17192114.1A EP3460257A1 (fr) 2017-09-20 2017-09-20 Dispositif pouvant être traversé

Publications (1)

Publication Number Publication Date
EP3460257A1 true EP3460257A1 (fr) 2019-03-27

Family

ID=59923321

Family Applications (2)

Application Number Title Priority Date Filing Date
EP17192114.1A Withdrawn EP3460257A1 (fr) 2017-09-20 2017-09-20 Dispositif pouvant être traversé
EP18759897.4A Pending EP3658780A1 (fr) 2017-09-20 2018-08-20 Dispositif pouvant être parcouru par un flux

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP18759897.4A Pending EP3658780A1 (fr) 2017-09-20 2018-08-20 Dispositif pouvant être parcouru par un flux

Country Status (5)

Country Link
US (1) US11313384B2 (fr)
EP (2) EP3460257A1 (fr)
JP (1) JP7074959B2 (fr)
CN (1) CN111133202B (fr)
WO (1) WO2019057412A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3760876A1 (fr) 2019-07-04 2021-01-06 Siemens Aktiengesellschaft Diffuseur pour une turbomachine
EP3760871A1 (fr) 2019-07-04 2021-01-06 Siemens Aktiengesellschaft Diffuseur pour une turbomachine
EP3805572A1 (fr) 2019-10-07 2021-04-14 Siemens Aktiengesellschaft Diffuseur, turbocompresseur radial
CN113969855B (zh) * 2021-10-15 2022-08-02 清华大学 抑制水泵水轮机泵工况驼峰的叶片改型方法

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2372880A (en) * 1944-01-11 1945-04-03 Wright Aeronautical Corp Centrifugal compressor diffuser vanes
EP0648939A2 (fr) * 1993-10-18 1995-04-19 Hitachi, Ltd. Machine centrifuge pour fluides
WO2011011335A1 (fr) * 2009-07-19 2011-01-27 Cameron International Corporation Diffuseur de compresseur centrifuge
DE102010020379A1 (de) 2010-05-12 2011-11-17 Siemens Aktiengesellschaft Einstellbarer Radialverdichterdiffusor
EP2650546A1 (fr) 2010-12-10 2013-10-16 Hitachi, Ltd. Turbomachine centrifuge
EP2778431A2 (fr) * 2013-03-15 2014-09-17 Honeywell International Inc. Compresseurs centrifuges et procédés de conception d'aubes de diffuseur pour ceux-ci
DE102014219107A1 (de) 2014-09-23 2016-03-24 Siemens Aktiengesellschaft Radialverdichterlaufrad und zugehöriger Radialverdichter
DE102016201256A1 (de) 2016-01-28 2017-08-03 Siemens Aktiengesellschaft Strömungsmaschine mit beschaufeltem Diffusor

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3460748A (en) * 1967-11-01 1969-08-12 Gen Electric Radial flow machine
JPS5469811A (en) * 1977-11-14 1979-06-05 Hitachi Ltd Diffuser for centrifugal compressor
US7111643B2 (en) * 2005-01-26 2006-09-26 Invensys Building Systems, Inc. Flow characterization in a flowpath
US8016557B2 (en) * 2005-08-09 2011-09-13 Praxair Technology, Inc. Airfoil diffuser for a centrifugal compressor
US8313286B2 (en) * 2008-07-28 2012-11-20 Siemens Energy, Inc. Diffuser apparatus in a turbomachine
AU2009347137B2 (en) * 2009-05-27 2016-07-14 Flowserve Pte. Ltd. Fluid flow control devices and systems, and methods of flowing fluids therethrough
US8616836B2 (en) * 2010-07-19 2013-12-31 Cameron International Corporation Diffuser using detachable vanes
JP5010722B2 (ja) * 2010-08-31 2012-08-29 三菱重工業株式会社 遠心圧縮機のディフューザおよびこれを備えた遠心圧縮機
WO2015019901A1 (fr) * 2013-08-06 2015-02-12 株式会社Ihi Compresseur centrifuge et compresseur d'alimentation
EP3161325A1 (fr) 2014-06-24 2017-05-03 ABB Turbo Systems AG Diffuseur pour compresseur radial
JP6242775B2 (ja) * 2014-09-18 2017-12-06 三菱重工業株式会社 遠心圧縮機
CN204164041U (zh) * 2014-09-29 2015-02-18 杭州康联科技有限公司 一种离心式空气压缩机的静叶扩压器
GB2555567A (en) * 2016-09-21 2018-05-09 Cummins Ltd Turbine wheel for a turbo-machine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2372880A (en) * 1944-01-11 1945-04-03 Wright Aeronautical Corp Centrifugal compressor diffuser vanes
EP0648939A2 (fr) * 1993-10-18 1995-04-19 Hitachi, Ltd. Machine centrifuge pour fluides
WO2011011335A1 (fr) * 2009-07-19 2011-01-27 Cameron International Corporation Diffuseur de compresseur centrifuge
DE102010020379A1 (de) 2010-05-12 2011-11-17 Siemens Aktiengesellschaft Einstellbarer Radialverdichterdiffusor
EP2650546A1 (fr) 2010-12-10 2013-10-16 Hitachi, Ltd. Turbomachine centrifuge
EP2778431A2 (fr) * 2013-03-15 2014-09-17 Honeywell International Inc. Compresseurs centrifuges et procédés de conception d'aubes de diffuseur pour ceux-ci
DE102014219107A1 (de) 2014-09-23 2016-03-24 Siemens Aktiengesellschaft Radialverdichterlaufrad und zugehöriger Radialverdichter
DE102016201256A1 (de) 2016-01-28 2017-08-03 Siemens Aktiengesellschaft Strömungsmaschine mit beschaufeltem Diffusor

Also Published As

Publication number Publication date
CN111133202B (zh) 2021-04-23
WO2019057412A1 (fr) 2019-03-28
EP3658780A1 (fr) 2020-06-03
CN111133202A (zh) 2020-05-08
JP7074959B2 (ja) 2022-05-25
US11313384B2 (en) 2022-04-26
JP2020534474A (ja) 2020-11-26
US20200277967A1 (en) 2020-09-03

Similar Documents

Publication Publication Date Title
EP2473743B1 (fr) Aube mobile de compresseur pour un compresseur axial
EP2696029B1 (fr) Grille d'aube avec définition de contour de la paroi latérale et turbomachine
EP3460257A1 (fr) Dispositif pouvant être traversé
EP2096316B1 (fr) Structuration de boîtier pour compresseur axial dans la zone du moyeu
EP3225781B1 (fr) Canal d'aube, grille d'aube et turbomachine
EP3658781B1 (fr) Dispositif pouvant être traversé
EP2881548B1 (fr) Compresseur de turbine à gaz
EP2746533B1 (fr) Grille d'aube et turbomachine
EP2913478B1 (fr) Aubes en tandem d'une turbomachine
EP2505851B1 (fr) Aubage de stator pour un compresseur axial dans une turbomachine
EP3460255A1 (fr) Système pouvant être traversé
EP3404210A1 (fr) Segment de grille d'aubes d'une turbomachine avec paroi de plateforme non-axisymétrique , grille d'aubes, canal d'aube, plateforme, turbomachine associés
EP0798447B1 (fr) Aube pour une turbomachine
EP2626512A1 (fr) Turbomachine
EP3205883A1 (fr) Roue pour un turbocompresseur centrifuge
DE19722353A1 (de) Kreiselpumpe mit einer Einlaufleiteinrichtung
DE102014203605A1 (de) Schaufelreihengruppe
EP3246518A1 (fr) Aubage directeur, ensemble et procédé de montage associés
EP2607625A1 (fr) Turbomachine et étage de turbomachine
EP3358135B1 (fr) Contournage d'une plate-forme de grille d'aube
EP2607626A1 (fr) Turbomachine et étage de turbomachine
EP0943784A1 (fr) Veine profilée pour une turbomachine axiale
EP3404211A1 (fr) Segment de grille d'aubes d'une turbine avec paroi de plateforme contourée, grille d'aubes, canal d'aube, plateforme, turbine et moteur d'aéronef associés
EP2927503B1 (fr) Compresseur de turbine à gaz, moteur d'avion et méthode de dimensionnement
EP3375977A1 (fr) Contournage d'une plate-forme de grille d'aube

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20190928