EP2406500A1 - Compresseur axialo-centrifuge a angle de rake evolutif - Google Patents
Compresseur axialo-centrifuge a angle de rake evolutifInfo
- 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- Withdrawn
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)
Abstract
Description
Claims
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 (fr) | 2012-01-18 |
Family
ID=41057639
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10707910A Withdrawn EP2406500A1 (fr) | 2009-03-13 | 2010-03-10 | Compresseur axialo-centrifuge a angle de rake evolutif |
Country Status (9)
Country | Link |
---|---|
US (1) | US20110318188A1 (fr) |
EP (1) | EP2406500A1 (fr) |
JP (1) | JP5687215B2 (fr) |
KR (1) | KR101746870B1 (fr) |
CN (1) | CN102341602B (fr) |
CA (1) | CA2755017C (fr) |
FR (1) | FR2943103B1 (fr) |
RU (1) | RU2011141460A (fr) |
WO (1) | WO2010103055A1 (fr) |
Families Citing this family (15)
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 |
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 |
JP5705945B1 (ja) * | 2013-10-28 | 2015-04-22 | ミネベア株式会社 | 遠心式ファン |
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 |
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20070059179A1 (en) * | 2005-09-13 | 2007-03-15 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
-
2009
- 2009-03-13 FR FR0951604A patent/FR2943103B1/fr not_active Expired - Fee Related
-
2010
- 2010-03-10 WO PCT/EP2010/053057 patent/WO2010103055A1/fr active Application Filing
- 2010-03-10 RU RU2011141460/06A patent/RU2011141460A/ru unknown
- 2010-03-10 CN CN201080010678.8A patent/CN102341602B/zh not_active Expired - Fee Related
- 2010-03-10 EP EP10707910A patent/EP2406500A1/fr not_active Withdrawn
- 2010-03-10 JP JP2011553449A patent/JP5687215B2/ja not_active Expired - Fee Related
- 2010-03-10 KR KR1020117024047A patent/KR101746870B1/ko active IP Right Grant
- 2010-03-10 US US13/256,371 patent/US20110318188A1/en not_active Abandoned
- 2010-03-10 CA CA2755017A patent/CA2755017C/fr not_active Expired - Fee Related
Patent Citations (1)
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 |
---|---|
CN102341602A (zh) | 2012-02-01 |
CA2755017A1 (fr) | 2010-09-16 |
CA2755017C (fr) | 2017-04-04 |
KR20110129465A (ko) | 2011-12-01 |
KR101746870B1 (ko) | 2017-06-14 |
FR2943103B1 (fr) | 2011-05-27 |
JP5687215B2 (ja) | 2015-03-18 |
JP2012520412A (ja) | 2012-09-06 |
WO2010103055A1 (fr) | 2010-09-16 |
US20110318188A1 (en) | 2011-12-29 |
CN102341602B (zh) | 2015-07-01 |
FR2943103A1 (fr) | 2010-09-17 |
RU2011141460A (ru) | 2013-04-20 |
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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 |
|
17P | Request for examination filed |
Effective date: 20111012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): 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 SE SI SK SM TR |
|
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: BILLOTEY, GEOFFROY LOUIS-HENRI MARIE Inventor name: OUSTY, JEAN-PHILIPPE Inventor name: ROCHUON, NICOLAS |
|
DAX | Request for extension of the european patent (deleted) | ||
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SAFRAN HELICOPTER ENGINES |
|
17Q | First examination report despatched |
Effective date: 20180212 |
|
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: 20180623 |