EP2406500A1 - Axialkreiselverdichter mit skalierbarem neigungswinkel - Google Patents

Axialkreiselverdichter mit skalierbarem neigungswinkel

Info

Publication number
EP2406500A1
EP2406500A1 EP10707910A EP10707910A EP2406500A1 EP 2406500 A1 EP2406500 A1 EP 2406500A1 EP 10707910 A EP10707910 A EP 10707910A EP 10707910 A EP10707910 A EP 10707910A EP 2406500 A1 EP2406500 A1 EP 2406500A1
Authority
EP
European Patent Office
Prior art keywords
trailing edge
blade
head
compressor
foot
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Withdrawn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
EP10707910A
Other languages
English (en)
French (fr)
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
Publication of EP2406500A1 publication Critical patent/EP2406500A1/de
Withdrawn legal-status Critical Current

Links

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 turboshaft engines and in particular helicopter turboshaft engines generally comprise a compressor of the centrifugal or mixed type, as the compression stage of the gas generator.
  • These compressors are formed of moving wheels or wheels, which have a substantially axial air inlet and a more radial outlet, the vanes being fixed on a bell-shaped base, which serves as a guide to the flow of air and the deviation of the direction of entry to the exit direction. The flow thus circulates between this base and a compressor casing; it is compressed and propelled by the different vanes of the wheel.
  • the head of the blades is free and positioned facing the housing, or cover, which closes the air vein.
  • the trailing edge is rectilinear in the prior art and may be inclined relative to the meridian plane of the wheel passing through the root of the blade. The angle it makes with this meridian plane is referred to as the rake angle, or slope angle of the trailing edge, and is one of the relevant geometrical parameters for describing a spinning wheel impeller.
  • the object of the present invention is to remedy these drawbacks by proposing a centrifugal or mixed axial-centrifugal compressor which does not have some of the drawbacks of the prior art and, in particular, which has a trailing edge with a significant slope angle. at its foot, without a phenomenon of self-engagement of the dawn head in case of contact of the latter with the lid.
  • the subject of the invention is a mobile wheel for a centrifugal or mixed axial-centrifugal turbomachine compressor, comprising a base on which are fixed by their feet a plurality of blades extending between a leading edge and a trailing edge, said trailing edge being inclined at the root of the blade of an angle of inclination with respect to the meridian plane which passes through it in its foot, in the direction of rotation of said compressor, characterized in that the edge leakage present at the head of the blade an angle of slope ⁇ less than its slope angle ⁇ at the bottom of the blade.
  • the wedge formed by the trailing edge and the head of the blade moves more tangentially with respect to the housing and is therefore less able to penetrate into it. accidental contact.
  • the slope angle ⁇ of the trailing edge at the head of the blade is close to zero, or even zero.
  • even more preferential slope angle ⁇ of the trailing edge at the head of blade is negative.
  • the curvature of the trailing edge is continuously variable between the foot and the head of said trailing edge.
  • the trailing edge is then in the form 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 one 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 one embodiment of the invention.
  • centrifugal compressor 1 comprising a base 2, bell-shaped, on which are fixed compressor blades 3 regularly distributed on the periphery of the base 2.
  • the base 2 ends at its part upper, which corresponds to the plane of entry of the air to be compressed by a hub cylinder 4 for the compressor, and at its bottom by a disk 5 oriented radially relative to the axis of rotation of said compressor.
  • the blades 3 are held by the base 2 at their foot 6; the heads 7 of these blades are free and rotate inside a compressor housing (not shown).
  • the vanes In the direction of the flow of the air vein the vanes extend between a leading edge 8 located at the hub 4 and a trailing edge 9 located at the disc 5.
  • FIG 2 shows a trailing edge 9 of a compressor blade 3, according to the prior art.
  • This trailing edge is, at its foot, inclined relative to the meridian plane which passes through, in the direction of rotation, 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 bottom of the blade, over its entire height, from the foot to the head of the edge of 9.
  • the trailing edge 9 has an evolutionary shape along its height.
  • the proposed invention thus consists in choosing, at the trailing edge 9, a slope angle ⁇ high at the blade root 6, then applying a curvature to the blade 3 so as to find a lower slope angle or even zero or negative at the head of blading.
  • a high slope angle ⁇ at the blade root 6 makes it possible to reduce the bending stresses in the foot, whereas the low angle of inclination ⁇ at the level of the head 7 reduces the risks of self-engagement of the blade 3 in the housing in case of accidental contact between the head 7 of the blade at the trailing edge 9 and the housing.
  • the invention therefore allows a gain in mass and inertia, or iso-mass and iso-inertia an increase in the speed of rotation, without degrading the behavior in case of contact between the blade 3 and the housing.
  • the curvature may for example be constant, the trailing edge having a shape of an arc of circle, or be continuously variable, the profile of the trailing edge then having the shape of a helix.
  • the choice of curvature between the foot and the head of the dawn is based on the impact it has on the aerodynamic performance of the compressor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10707910A 2009-03-13 2010-03-10 Axialkreiselverdichter mit skalierbarem neigungswinkel Withdrawn EP2406500A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0951604A FR2943103B1 (fr) 2009-03-13 2009-03-13 Compresseur axialo-centrifuge a angle de rake evolutif
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
EP2406500A1 true EP2406500A1 (de) 2012-01-18

Family

ID=41057639

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10707910A Withdrawn EP2406500A1 (de) 2009-03-13 2010-03-10 Axialkreiselverdichter mit skalierbarem neigungswinkel

Country Status (9)

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

Families Citing this family (15)

* 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
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
WO2014102981A1 (ja) * 2012-12-27 2014-07-03 三菱重工業株式会社 ラジアルタービン動翼
JP5705945B1 (ja) * 2013-10-28 2015-04-22 ミネベア株式会社 遠心式ファン
US10634157B2 (en) 2014-01-07 2020-04-28 Nuovo Pignone Srl Centrifugal compressor impeller with non-linear leading edge and associated design method
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
JP6627175B2 (ja) * 2015-03-30 2020-01-08 三菱重工コンプレッサ株式会社 インペラ、及び遠心圧縮機
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
RU2667251C1 (ru) * 2017-10-05 2018-09-18 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Коробка приводных агрегатов
JP6842563B2 (ja) * 2017-10-11 2021-03-17 三菱重工エンジン＆ターボチャージャ株式会社 遠心式回転機械のインペラ及び遠心式回転機械
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 (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070059179A1 (en) * 2005-09-13 2007-03-15 Ingersoll-Rand Company Impeller for a centrifugal compressor

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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
US4502837A (en) * 1982-09-30 1985-03-05 General Electric Company Multi stage centrifugal impeller
US4819884A (en) * 1985-01-31 1989-04-11 Microfuel Corporation Means of pneumatic comminution
US4923370A (en) * 1988-11-28 1990-05-08 Allied-Signal Inc. Radial turbine wheel
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
US6338610B1 (en) * 1998-01-14 2002-01-15 Ebara Corporation Centrifugal turbomachinery
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
US8696316B2 (en) * 2007-11-16 2014-04-15 Borg Warner Inc. Low blade frequency titanium compressor wheel

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070059179A1 (en) * 2005-09-13 2007-03-15 Ingersoll-Rand Company Impeller for a centrifugal compressor

Also Published As

Publication number Publication date
CN102341602B (zh) 2015-07-01
RU2011141460A (ru) 2013-04-20
CA2755017A1 (fr) 2010-09-16
FR2943103A1 (fr) 2010-09-17
JP5687215B2 (ja) 2015-03-18
WO2010103055A1 (fr) 2010-09-16
KR20110129465A (ko) 2011-12-01
CA2755017C (fr) 2017-04-04
US20110318188A1 (en) 2011-12-29
FR2943103B1 (fr) 2011-05-27
JP2012520412A (ja) 2012-09-06
CN102341602A (zh) 2012-02-01
KR101746870B1 (ko) 2017-06-14

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Inventor name: BILLOTEY, GEOFFROY LOUIS-HENRI MARIE

Inventor name: OUSTY, JEAN-PHILIPPE

Inventor name: ROCHUON, NICOLAS

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Owner name: SAFRAN HELICOPTER ENGINES

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