US20110318188A1 - Axial centrifugal compressor with scalable rake angle - Google Patents

Axial centrifugal compressor with scalable rake angle Download PDF

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Publication number
US20110318188A1
US20110318188A1 US13/256,371 US201013256371A US2011318188A1 US 20110318188 A1 US20110318188 A1 US 20110318188A1 US 201013256371 A US201013256371 A US 201013256371A US 2011318188 A1 US2011318188 A1 US 2011318188A1
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US
United States
Prior art keywords
trailing edge
head
blade
slope angle
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
US13/256,371
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English (en)
Inventor
Geoffroy Louis Henri Marie Billotey
Jean-Philippe Ousty
Nicolas Rochuon
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
Application filed by Turbomeca SA filed Critical Turbomeca SA
Assigned to TURBOMECA reassignment TURBOMECA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BILLOTEY, GEOFFROY LOUIS-HENRI MARIE, OUSTY, JEAN-PHILIPPE, ROCHUON, NICOLAS
Publication of US20110318188A1 publication Critical patent/US20110318188A1/en
Assigned to SAFRAN HELICOPTER ENGINES reassignment SAFRAN HELICOPTER ENGINES CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: TURBOMECA
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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the field of the present invention is that of turbomachines and more particularly that of turbomachine compressors comprising at least one centrifugal or mixed (axial-centrifugal) compression stage.
  • Aeronautical turbine engines and in particular turbine engines for helicopters generally comprise a compressor of the centrifugal or mixed type as a compression stage of the gas generator.
  • These compressors are formed by moving wheels or impellers which have a substantially axial air inlet and a more radial outlet, the blades being fixed on a base in the form of a bell which serves as a guide for the air flow and diverts it from the inlet direction toward the outlet direction. The flow thus circulates between this base and a compressor casing; it is compressed and propelled by the various blades of the impeller.
  • the head of the blading is free and positioned opposite the casing, or cover, which closes the air duct.
  • the trailing edge is rectilinear in the prior art and may be inclined with respect to the meridian plane of the impeller passing through the foot of the blade.
  • the angle which it makes with this meridian plane is designated by the term rake angle, or slope angle of the trailing edge, and constitutes one of the relevant geometric parameters for describing a centrifugal impeller blading.
  • the aim of the present invention is to overcome these disadvantages by providing a centrifugal or mixed axial-centrifugal compressor which does not have some of the disadvantages of the prior art and, in particular, which has a trailing edge with a significant slope angle at its foot, without there being produced a phenomenon of auto-engagement of the head of the blade in the case of contact thereof with the cover.
  • the subject of the invention is a moving wheel for a centrifugal or mixed axial-centrifugal compressor of a turbomachine, comprising a base on which a plurality of blades extending between a leading edge and a trailing edge are fixed by their feet, said trailing edge being inclined at the foot of the blade by a slope angle with respect to the meridian plane which passes through it at its foot, in the direction of rotation of said compressor, characterized in that the trailing edge has at the head of the blade a slope angle ⁇ which is less than its slope angle ⁇ at the blade foot.
  • the slope angle at the head is smaller, the corner formed by the trailing edge and the head of the blade moves more tangentially with respect to the casing and is therefore less capable of penetrating therein in the case of accidental contact.
  • the slope angle ⁇ of the trailing edge at the blade head is close to zero, or even zero. Even more preferably, the slope angle ⁇ of the trailing edge at the blade head is negative.
  • the curvature of the trailing edge is constant between the foot and the head of said trailing edge.
  • the trailing edge thus has the shape of an arc of a circle.
  • the curvature of the trailing edge is continuously variable between the foot and the head of said trailing edge.
  • the trailing edge thus has the shape of a helix.
  • the invention also relates to a turbomachine comprising a compressor having one of the characteristics described above. Finally, it relates to an aircraft equipped with such a turbomachine.
  • FIG. 1 is a perspective view of a centrifugal compressor impeller according to an embodiment of the invention
  • FIG. 2 is a front view of a trailing edge of a centrifugal compressor blade according to the prior art
  • FIG. 3 is a front view of a trailing edge of a centrifugal compressor blade according to an embodiment of the invention.
  • a centrifugal compressor 1 comprising a base 2 , in the form of a bell, on which compressor blades 3 distributed uniformly over the periphery of the base 2 are fixed.
  • the base 2 terminates at its upper part, which corresponds to the inlet plane of the air to be compressed, in a cylinder forming a hub 4 for the compressor, and, at its lower part, in a disk 5 oriented radially with respect to the axis of rotation of said compressor.
  • the blades 3 are held by the base 2 at their feet 6 ; the heads 7 of these blades are free and rotate inside a compressor casing (not shown). In the direction of flow of the air stream, the blades extend between a leading edge 8 situated at the hub 4 and a trailing edge 9 situated at the disk 5 .
  • FIG. 2 there can be seen a trailing edge 9 of a compressor blade 3 , according to the prior art.
  • This trailing edge is, at its foot, inclined with respect to the meridian plane which passes through it, in the direction of rotation, by a slope angle ⁇ .
  • This trailing edge 9 is rectilinear, that is to say that it has the same inclination, equal to its value ⁇ at the blade foot, over all its height, from the foot to the head of the trailing edge 9 .
  • the trailing edge 9 has a shape which is changeable along its height. It is inclined by a slope angle ⁇ in the direction of rotation, at the foot 6 of the blade 3 , which is defined as in the prior art, but this angle becomes progressively smaller in the upward direction along the trailing edge so as to reach a value ⁇ at the head 7 of the blade 3 , which is less than ⁇ .
  • This value ⁇ may be zero or even negative, that is to say that the head of the blade is then inclined in the opposite direction to the direction of rotation of the impeller.
  • the proposed invention therefore consists in choosing, at the trailing edge 9 , a large slope angle ⁇ at the blade foot 6 , then in applying a curvature to the blading 3 so as to find a smaller, or even zero or negative, slope angle at the head of the blading.
  • a large slope angle ⁇ at the blade foot 6 makes it possible to reduce the bending stresses at the foot, whereas the small slope angle ⁇ at the head 7 reduces the risks of auto-engagement of the blade 3 in the casing in the case of accidental contact between the head 7 of the blade at the trailing edge 9 and the casing.
  • the invention therefore allows a saving in mass and inertia or, with equal mass and equal inertia, an increase in the speed of rotation without degrading the behavior in the case of contact between the blade 3 and the casing.
  • the curvature may, for example, be constant, the trailing edge having the shape of an arc of a circle, or else be continuously variable, the profile of the trailing edge then having the shape of a helix.
  • the curvature between the foot and the head of the blade is chosen according to the impact that it has on the aerodynamic performance of the compressor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/256,371 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle Abandoned US20110318188A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0951604A FR2943103B1 (fr) 2009-03-13 2009-03-13 Compresseur axialo-centrifuge a angle de rake evolutif
FR0951604 2009-03-13
PCT/EP2010/053057 WO2010103055A1 (fr) 2009-03-13 2010-03-10 Compresseur axialo-centrifuge a angle de rake evolutif

Publications (1)

Publication Number Publication Date
US20110318188A1 true US20110318188A1 (en) 2011-12-29

Family

ID=41057639

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/256,371 Abandoned US20110318188A1 (en) 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle

Country Status (9)

Country Link
US (1) US20110318188A1 (ja)
EP (1) EP2406500A1 (ja)
JP (1) JP5687215B2 (ja)
KR (1) KR101746870B1 (ja)
CN (1) CN102341602B (ja)
CA (1) CA2755017C (ja)
FR (1) FR2943103B1 (ja)
RU (1) RU2011141460A (ja)
WO (1) WO2010103055A1 (ja)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130224009A1 (en) * 2012-02-29 2013-08-29 David A. Little Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
US8997486B2 (en) 2012-03-23 2015-04-07 Bullseye Power LLC Compressor wheel
US20150118037A1 (en) * 2013-10-28 2015-04-30 Minebea Co., Ltd. Centrifugal fan
US20180058468A1 (en) * 2015-03-30 2018-03-01 Mitsubishi Heavy Industries, Ltd. Impeller and centrifugal compressor
US20200400052A1 (en) * 2017-10-05 2020-12-24 Joint-Stock Company "United Engine Corporation" Accessory Gearbox

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8951009B2 (en) 2011-05-23 2015-02-10 Ingersoll Rand Company Sculpted impeller
CN104854325B (zh) * 2012-12-27 2017-05-31 三菱重工业株式会社 辐流式涡轮动叶片
CN106164496A (zh) * 2014-01-07 2016-11-23 诺沃皮尼奥内股份有限公司 具有非线性叶片前缘的离心压缩机叶轮及相关联的设计方法
CN103758783B (zh) * 2014-02-17 2016-04-27 南通大通宝富风机有限公司 一种减小根部弯曲应力的控制棒驱动机构冷却风机叶片
JP6532215B2 (ja) * 2014-11-10 2019-06-19 三菱重工サーマルシステムズ株式会社 羽根車及び遠心圧縮機
JP6210459B2 (ja) * 2014-11-25 2017-10-11 三菱重工業株式会社 インペラ、及び回転機械
JP2017186914A (ja) * 2016-04-01 2017-10-12 株式会社日立製作所 遠心羽根車、およびこれを備える遠心式流体機械
FR3062431B1 (fr) * 2017-01-27 2021-01-01 Safran Helicopter Engines Pale de rouet pour turbomachine, comprenant une ailerette a son sommet et au bord d'attaque
EP3696425B1 (en) * 2017-10-11 2023-05-03 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Impeller for centrifugal rotating machine, and centrifugal rotating machine
JP6992504B2 (ja) * 2017-12-27 2022-01-13 トヨタ自動車株式会社 インペラの製造方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4502837A (en) * 1982-09-30 1985-03-05 General Electric Company Multi stage centrifugal impeller
US4923370A (en) * 1988-11-28 1990-05-08 Allied-Signal Inc. Radial turbine wheel
US20070059179A1 (en) * 2005-09-13 2007-03-15 Ingersoll-Rand Company Impeller for a centrifugal compressor
US20100263373A1 (en) * 2007-11-16 2010-10-21 Borgwarner Inc. Low blade frequency titanium compressor wheel

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US2354653A (en) * 1940-06-11 1944-08-01 Gen Electric Impeller
GB587514A (en) * 1942-09-03 1947-04-29 Power Jets Ltd Improvements relating to centrifugal compressors, pumps and the like
FR2393176A1 (fr) * 1977-06-01 1978-12-29 Alsthom Atlantique Compresseur centrifuge a haut rapport de pression
US4819884A (en) * 1985-01-31 1989-04-11 Microfuel Corporation Means of pneumatic comminution
DE4403224A1 (de) * 1994-02-03 1995-08-10 Vorwerk Co Interholding Radialgebläserad
US5730582A (en) * 1997-01-15 1998-03-24 Essex Turbine Ltd. Impeller for radial flow devices
DE69932408T2 (de) * 1998-01-14 2007-03-08 Ebara Corp. Radiale strömungsmaschine
CN1189666C (zh) * 2002-06-06 2005-02-16 孙敏超 离心式叶轮机械中的一种后弯叶片叶轮

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4502837A (en) * 1982-09-30 1985-03-05 General Electric Company Multi stage centrifugal impeller
US4923370A (en) * 1988-11-28 1990-05-08 Allied-Signal Inc. Radial turbine wheel
US20070059179A1 (en) * 2005-09-13 2007-03-15 Ingersoll-Rand Company Impeller for a centrifugal compressor
US20100263373A1 (en) * 2007-11-16 2010-10-21 Borgwarner Inc. Low blade frequency titanium compressor wheel

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130224009A1 (en) * 2012-02-29 2013-08-29 David A. Little Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
US9476355B2 (en) * 2012-02-29 2016-10-25 Siemens Energy, Inc. Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
US8997486B2 (en) 2012-03-23 2015-04-07 Bullseye Power LLC Compressor wheel
US20150118037A1 (en) * 2013-10-28 2015-04-30 Minebea Co., Ltd. Centrifugal fan
US20180058468A1 (en) * 2015-03-30 2018-03-01 Mitsubishi Heavy Industries, Ltd. Impeller and centrifugal compressor
US10947988B2 (en) * 2015-03-30 2021-03-16 Mitsubishi Heavy Industries Compressor Corporation Impeller and centrifugal compressor
US20200400052A1 (en) * 2017-10-05 2020-12-24 Joint-Stock Company "United Engine Corporation" Accessory Gearbox

Also Published As

Publication number Publication date
KR101746870B1 (ko) 2017-06-14
CA2755017A1 (fr) 2010-09-16
FR2943103B1 (fr) 2011-05-27
JP2012520412A (ja) 2012-09-06
KR20110129465A (ko) 2011-12-01
CA2755017C (fr) 2017-04-04
WO2010103055A1 (fr) 2010-09-16
RU2011141460A (ru) 2013-04-20
JP5687215B2 (ja) 2015-03-18
CN102341602B (zh) 2015-07-01
CN102341602A (zh) 2012-02-01
EP2406500A1 (fr) 2012-01-18
FR2943103A1 (fr) 2010-09-17

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AS Assignment

Owner name: TURBOMECA, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BILLOTEY, GEOFFROY LOUIS-HENRI MARIE;OUSTY, JEAN-PHILIPPE;ROCHUON, NICOLAS;REEL/FRAME:026927/0215

Effective date: 20110614

STCB Information on status: application discontinuation

Free format text: ABANDONED -- AFTER EXAMINER'S ANSWER OR BOARD OF APPEALS DECISION

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Owner name: SAFRAN HELICOPTER ENGINES, FRANCE

Free format text: CHANGE OF NAME;ASSIGNOR:TURBOMECA;REEL/FRAME:046127/0021

Effective date: 20160510