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US20120087800A1 - Centrifugal impeller for a compressor - Google Patents

Centrifugal impeller for a compressor Download PDF

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Publication number
US20120087800A1
US20120087800A1 US13/376,014 US201013376014A US2012087800A1 US 20120087800 A1 US20120087800 A1 US 20120087800A1 US 201013376014 A US201013376014 A US 201013376014A US 2012087800 A1 US2012087800 A1 US 2012087800A1
Authority
US
United States
Prior art keywords
impeller
blades
fluid
rotation
compressor
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.)
Abandoned
Application number
US13/376,014
Other languages
English (en)
Inventor
Jerome Porodo
Nicolas Rochuon
Laurent Tarnowski
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.)
Safran Helicopter Engines SAS
Original Assignee
Turbomeca SA
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=41327964&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=US20120087800(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Turbomeca SA filed Critical Turbomeca SA
Assigned to TURBOMECA reassignment TURBOMECA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PORODO, JEROME, ROCHUON, NICOLAS, TARNOWSKI, LAURENT
Publication of US20120087800A1 publication Critical patent/US20120087800A1/en
Abandoned 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
    • F04D29/26—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
    • 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
    • F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
    • F04D29/282—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers the leading edge of each vane being substantially parallel to the rotation axis
    • 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
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together

Definitions

  • the invention relates to a centrifugal impeller through which a fluid, in particular a gas, can pass.
  • the impeller is intended particularly for a turbomachine compressor.
  • the impeller may be fitted to any type of turbomachine for stationary or aviation use, and in particular to a helicopter turbine engine.
  • the invention relates to a centrifugal impeller of the type presenting an axis of rotation, a front portion of small section, and a rear portion of large section, the impeller having blades each having a leading edge and a trailing edge.
  • the rotation of the impeller sucks fluid in through the front of the impeller, the axial speed of the fluid passing through the impeller being transformed progressively into radial speed, the fluid leaving the impeller via its outer periphery at the trailing edges of the blades.
  • Said blades are such that in a radial section plane intersecting the trailing edges of said blades, they are curved in the direction opposite to the direction of rotation of the impeller.
  • upstream and downstream are defined relative to the normal direction of fluid flow through the impeller.
  • the axis of rotation of the impeller is often referred to more simply as the “impeller axis”.
  • the axial direction corresponds to the direction of the impeller axis
  • a radial direction is a direction perpendicular to said axis and intersecting said axis.
  • an axial plane is a plane containing the axis of the impeller and a radial plane is a plane perpendicular to said axis.
  • the adverbs “axially” and “radially” refer respectively to the axial direction and to the radial direction.
  • the adjectives “inner” and “outer” are used relative to a radial direction, the inner portion (i.e. the radially inner portion) of an element being closer to the axis of the impeller than the outer portion (i.e. the radially outer portion) of the same element.
  • a compressor of an aviation turbomachine e.g. of a helicopter turbine engine
  • a compressor of an aviation turbomachine that is of the centrifugal type or of the mixed axial-and-centrifugal type includes one or more compression stages with a centrifugal impeller of the above-specified type (also referred to as a centrifugal wheel or rotor), a casing surrounds the blades of the impeller on the outside, and one or more diffusers are situated downstream from the impeller.
  • the absolute speed of the gas increases as a result of centrifugal acceleration, and the pressure of the gas increases as a result of the diverging section of the channels defined between the blades of the impeller.
  • the gas leaves the downstream ends of the blades, i.e. their trailing edges, at very high speed.
  • An object of the invention is to improve the performance (i.e. total pressure ratio and isentropic efficiency) of an impeller of the above-specified type, for given geometrical size and corrected flow rate.
  • an impeller wherein, in said radial section plane intersecting the trailing edge of the impeller blades, the trailing edge portion of the blades (i.e. the portion situated at the outer end of the rear portion of the blades) is redirected in the direction of rotation of the impeller so as to form respective end fins enabling the flow of fluid to be deflected by radially redirecting this flow.
  • the end fins serve to improve the performance of the impeller.
  • Such a centrifugal impeller for a compressor may have blades of two types: so-called “main” blades and so-called “intermediate” blades.
  • the optional intermediate blades are interposed between the main blades and they differ therefrom in that they are axially shorter: they present shorter front portions, with the leading edges of the intermediate blades being set back (i.e. rearwards) relative to the leading edges of the main blades.
  • the impeller has main blades only (i.e. no intermediate blades), and the main blades present end fins of the above-specified type.
  • the impeller has main blades and intermediate blades. Under such circumstances, either the main blades are the only blades to have end fins of the above-specified type, or the intermediate blades are the only blades to have end fins of the above-mentioned type, or both the main blades and the intermediate blades present end fins of the above-specified type.
  • said end fin co-operates with the blade portions situated immediately upstream therefrom to form an obtuse angle that is greater than or equal to 155°, and that is strictly less than 180°.
  • the end fins extend from the trailing edges of the main blades of the impeller over a length that, when measured along the (curvilinear) outer edges of the main blades, represents less than 15% of the total length of said outer edges, and in particular more than 2% and less than 10% of the total length of said outer edges.
  • said end fins extend from the trailing edges of the intermediate blades over a length that, when measured along the outer edges of the intermediate blades, represents less than 15% of the total length of said outer edges, and in particular more than 2% and less than 10% of the total length of said outer edges.
  • the invention also pertains to a compressor including a centrifugal impeller of the invention. It may be a compressor of the centrifugal type, i.e. a compressor having at least one compression stage fitted with a centrifugal impeller, or a compressor of the mixed axial-and-centrifugal type, i.e. a compressor having at least one compression stage fitted with an axial impeller and at least one compression stage fitted with a centrifugal impeller.
  • the invention also pertains to a turbomachine, and more particularly a helicopter turbine engine including a compressor of the invention.
  • FIG. 1 is a diagrammatic and fragmentary axial section view of a helicopter turbine engine with a compressor that includes a centrifugal impeller of the invention (the centrifugal impeller and the turbines of the engine being shown not in section, but rather in side view).
  • FIG. 2 is a diagram of the centrifugal impeller of FIG. 1 isolated from the remainder of the engine.
  • FIG. 3 is a diagrammatic and fragmentary perspective view showing the rear portions of two blades of the FIG. 1 centrifugal impeller.
  • FIG. 4 is a diagrammatic and fragmentary view of the rear portion of one of the blades of FIG. 3 , shown in section in a radial section plane intersecting the trailing edge of the blade, this section plane IV-IV being identified in FIG. 2 .
  • the example helicopter turbine engine 10 shown in FIG. 1 comprises a compressor 16 of the centrifugal type having a single compression stage.
  • the compressor 16 comprises a centrifugal impeller 18 of the invention and a casing 15 surrounding the outside of the blades 24 , 25 of the impeller 18 .
  • a diffuser 19 is situated downstream from the impeller 18 .
  • the engine 10 presents an air inlet 12 , the air passing via said inlet 12 to reach the compressor 16 .
  • the rotation of the impeller 18 about its axis of rotation A sucks in air via the front of the impeller and the axial speed of the fluid that passes thorough the impeller 18 becomes transformed progressively into radial speed, with the fluid leaving the impeller 18 via its outer periphery.
  • the air penetrates into the impeller 18 in a direction that is substantially parallel to the axis of rotation A of the impeller, as represented in the section of FIG. 1 by arrows F 1 , and it leaves the impeller 18 in a direction that is substantially perpendicular to the axis A, as represented by arrows F 2 .
  • the air leaving the impeller 18 passes through the diffuser 19 before reaching the combustion chamber 20 .
  • the combustion gas leaving the combustion chamber 20 drives a high-pressure turbine 22 and a low-pressure turbine 23 .
  • the impeller 18 is mounted on a shaft 21 that is driven in rotation by the high-pressure turbine 22 .
  • the impeller 18 presents a front portion of small section and a rear portion of large section.
  • the impeller 18 has a plurality of main blades 24 extending axially from the front face 18 A of the impeller to a radial plate 17 situated at the rear of the impeller 18 , and radially from the hub of the impeller to the outer periphery of the impeller.
  • Each of the main blades 24 presents a leading edge 24 A situated at the front end of the impeller 18 and a trailing edge 24 F situated at the outer periphery of the impeller 18 , immediately in front of the radial plate 17 .
  • the impeller 18 also includes intermediate blades 25 that are interposed between the main blades 24 and that differ from them in that they are axially shorter: the leading edges 25 A of these blades 25 are set back (i.e. rearwards) relative to the leading edges 24 A of the main blades 24 .
  • the trailing edges 25 F of the intermediate blades 25 are situated at the same radial distance from the axis A as the trailing edges 24 F of the blades 24 .
  • FIG. 3 is a perspective view showing in detail the rear portion of a main blade 24 and of an intermediate blade 25 of the impeller 18 .
  • a radial section plane i.e. a plane perpendicular to the axis A
  • intersecting the trailing edges 24 F and 25 F of the blades 24 and 25 of the impeller 18 such as the plane IV-IV of FIG. 2
  • the blades 24 and 25 are curved in the direction opposite to the direction of rotation of the impeller, the direction of rotation of the impeller 18 being symbolized by arrow R in FIGS. 3 and 4 .
  • the end fin 26 , 27 co-operates with the portion of the blade 24 , 25 situated immediately upstream from said fin 26 , 27 to form an obtuse angle T that is greater than or equal to 155° and that is strictly less than 180°.
  • This angle T is shown in FIG. 4 which is a section view of the main blade 24 in the radial section plane IV-IV of FIG. 2 .
  • both the main blades 24 and the intermediate blades 25 present end fins 26 , 27 . In other embodiments that are not shown, only the main blades 24 or only the intermediate blades 25 present such end fins.
  • the length (in curvilinear abscissa) of each end fin 26 measured along the curvilinear outer edge 24 E of said blade 24 represents no more than 15% of the total length of said outer edge 24 E.
  • the length of the end fin represents at least 2% and no more than 10% of the total length of the outer edge 24 E.
  • the length (in curvilinear abscissa) of each end fin 27 as measured along the curvilinear outer edge 25 E of said blade 25 represents no more than 15% of the total length of said outer edge 25 E.
  • the length of the end fin represents at least 2% and no more than 10% of the total length of the outer edge 25 E.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/376,014 2009-06-05 2010-06-02 Centrifugal impeller for a compressor Abandoned US20120087800A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0953757A FR2946399B1 (fr) 2009-06-05 2009-06-05 Rouet centrifuge de compresseur.
FR0953757 2009-06-05
PCT/FR2010/051078 WO2010139901A1 (fr) 2009-06-05 2010-06-02 Rouet centrifuge de compresseur.

Publications (1)

Publication Number Publication Date
US20120087800A1 true US20120087800A1 (en) 2012-04-12

Family

ID=41327964

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/376,014 Abandoned US20120087800A1 (en) 2009-06-05 2010-06-02 Centrifugal impeller for a compressor

Country Status (10)

Country Link
US (1) US20120087800A1 (ru)
EP (1) EP2438306B1 (ru)
JP (1) JP5705839B2 (ru)
KR (1) KR101750121B1 (ru)
CN (1) CN102459916B (ru)
CA (1) CA2762308A1 (ru)
FR (1) FR2946399B1 (ru)
PL (1) PL2438306T3 (ru)
RU (1) RU2525365C2 (ru)
WO (1) WO2010139901A1 (ru)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170298819A1 (en) * 2016-04-19 2017-10-19 Honda Motor Co.,Ltd. Turbine impeller
CN107989823A (zh) * 2017-12-26 2018-05-04 北京伯肯节能科技股份有限公司 叶轮、离心压缩机及燃料电池系统

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5722367B2 (ja) * 2013-02-28 2015-05-20 テラル株式会社 遠心送風機
CN103527510A (zh) * 2013-09-16 2014-01-22 苏州格园机械有限公司 一种打草机的风扇结构
JP6740271B2 (ja) * 2018-03-05 2020-08-12 三菱重工業株式会社 羽根車及びこの羽根車を備えた遠心圧縮機
FR3089576B1 (fr) 2018-12-05 2022-11-25 Safran Helicopter Engines Rouet centrifuge
CN110566500B (zh) * 2019-10-12 2024-08-16 浙江科贸智能机电股份有限公司 一种离心通风机的叶轮

Citations (5)

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US4543041A (en) * 1981-08-07 1985-09-24 Holset Engineering Company Limited Impellor for centrifugal compressor
US5951245A (en) * 1997-10-06 1999-09-14 Ford Motor Company Centrifugal fan assembly for an automotive vehicle
JP2001012389A (ja) * 1999-06-28 2001-01-16 Atago Seisakusho:Kk 多翼ファンの羽根車
JP2001082383A (ja) * 1999-09-09 2001-03-27 Sowa Denki Seisakusho:Kk 羽根車、遠心送風機および遠心ポンプ
US6508626B1 (en) * 1998-05-27 2003-01-21 Ebara Corporation Turbomachinery impeller

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EP0205001A1 (en) * 1985-05-24 1986-12-17 A. S. Kongsberg Väpenfabrikk Splitter blade arrangement for centrifugal compressors
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JPH1037893A (ja) * 1996-07-26 1998-02-13 Japan Servo Co Ltd 遠心ファン
JPH11280695A (ja) * 1998-03-26 1999-10-15 Kubota Corp 施肥装置用の遠心ブロワ
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JP2002332993A (ja) * 2001-05-09 2002-11-22 Toyota Central Res & Dev Lab Inc 遠心圧縮機のインぺラ
RU24253U1 (ru) * 2001-10-31 2002-07-27 Акционерное общество "Техника-Технология-Конструкции" Ротор водокольцевого компрессора
RU22978U1 (ru) * 2001-11-13 2002-05-10 Караджи Вячеслав Георгиевич Рабочее колесо радиального вентилятора
JP2005069183A (ja) * 2003-08-27 2005-03-17 Japan Servo Co Ltd 遠心ファンの羽根車
GB0403869D0 (en) * 2004-02-21 2004-03-24 Holset Engineering Co Compressor
JP4670285B2 (ja) * 2004-09-02 2011-04-13 パナソニック株式会社 インペラ及びそれを備えた送風ファン
JP2007192034A (ja) 2006-01-17 2007-08-02 Matsushita Electric Ind Co Ltd 電動送風機及びそれを用いた電気掃除機
JP2007247594A (ja) * 2006-03-17 2007-09-27 Teral Kyokuto Inc 後ろ向き羽根車を有する遠心送風機
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Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4543041A (en) * 1981-08-07 1985-09-24 Holset Engineering Company Limited Impellor for centrifugal compressor
US5951245A (en) * 1997-10-06 1999-09-14 Ford Motor Company Centrifugal fan assembly for an automotive vehicle
US6508626B1 (en) * 1998-05-27 2003-01-21 Ebara Corporation Turbomachinery impeller
JP2001012389A (ja) * 1999-06-28 2001-01-16 Atago Seisakusho:Kk 多翼ファンの羽根車
JP2001082383A (ja) * 1999-09-09 2001-03-27 Sowa Denki Seisakusho:Kk 羽根車、遠心送風機および遠心ポンプ

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170298819A1 (en) * 2016-04-19 2017-10-19 Honda Motor Co.,Ltd. Turbine impeller
CN107989823A (zh) * 2017-12-26 2018-05-04 北京伯肯节能科技股份有限公司 叶轮、离心压缩机及燃料电池系统

Also Published As

Publication number Publication date
JP2012528979A (ja) 2012-11-15
JP5705839B2 (ja) 2015-04-22
EP2438306B1 (fr) 2019-07-31
PL2438306T3 (pl) 2019-12-31
RU2525365C2 (ru) 2014-08-10
CA2762308A1 (fr) 2010-12-09
CN102459916A (zh) 2012-05-16
EP2438306A1 (fr) 2012-04-11
FR2946399B1 (fr) 2016-05-13
WO2010139901A1 (fr) 2010-12-09
CN102459916B (zh) 2015-04-29
RU2011153687A (ru) 2013-07-20
KR20120034670A (ko) 2012-04-12
KR101750121B1 (ko) 2017-06-22
FR2946399A1 (fr) 2010-12-10

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AS Assignment

Owner name: TURBOMECA, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:PORODO, JEROME;ROCHUON, NICOLAS;TARNOWSKI, LAURENT;REEL/FRAME:027351/0286

Effective date: 20110823

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION