EP2438306A1 - Rouet centrifuge de compresseur. - Google Patents
Rouet centrifuge de compresseur.Info
- Publication number
- EP2438306A1 EP2438306A1 EP10734214A EP10734214A EP2438306A1 EP 2438306 A1 EP2438306 A1 EP 2438306A1 EP 10734214 A EP10734214 A EP 10734214A EP 10734214 A EP10734214 A EP 10734214A EP 2438306 A1 EP2438306 A1 EP 2438306A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blades
- wheel
- impeller
- trailing edge
- blade
- 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.)
- Granted
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
- 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 compressor wheel intended to be traversed by a fluid and, in particular, by a gas.
- This wheel is intended, in particular, to equip a turbomachine compressor.
- This wheel can equip any type of turbomachine, land or aeronautics, including a helicopter turbine engine.
- the invention relates to a centrifugal wheel of the type having an axis of rotation, a front portion of small section and a rear portion of large section, the wheel comprising blades each having an upstream edge, or leading edge, and a downstream edge, or trailing edge.
- the rotation of this impeller draws fluid from the front of the impeller, the axial velocity of the fluid passing through the impeller is progressively transformed into radial velocity, the fluid exiting at the outer periphery of the impeller, at the trailing edge of the blades.
- Said blades are such that, in a radial cutting plane intersecting the trailing edge of these blades, they are bent in the opposite direction of the rotation of the impeller.
- upstream and downstream are defined relative to the normal flow direction of the fluid passing through the impeller.
- the axis of rotation of the impeller is often called more simply "axis of the impeller".
- the axial direction corresponds to the direction of the axis of the wheel, and a radial direction is a direction perpendicular to this axis and intersecting this axis.
- an axial plane is a plane containing the axis of the wheel and a radial plane is a plane perpendicular to this axis.
- the adverbs "axially” and “radially” respectively refer to the axial direction and to a radial direction.
- the adjectives "inner” and “outer” are used with reference to a radial direction, the inner (ie radially inner) part of an element being closer to the axis of the wheel than the outer part (ie radially outside) of the same element.
- An aeronautical turbomachine compressor for example a helicopter turbine engine of the centrifugal type or of the mixed axial-centrifugal type comprises one or more compression stages with a centrifugal impeller of the aforementioned type (also called a rotor or centrifugal wheel), an enclosing casing externally the blades of this wheel, and one or more diffusers located downstream of this wheel.
- a centrifugal impeller of the aforementioned type also called a rotor or centrifugal wheel
- an enclosing casing externally the blades of this wheel
- diffusers located downstream of this wheel.
- Such a compressor is traversed by a fluid which is a gas, usually air.
- the absolute speed of the gas increases due to the centrifugal acceleration and the pressure of the gas increases due to the diverging section of the channels delimited between the impeller blades.
- the gas leaves the downstream end of the blades, or trailing edge, at very high speed.
- a known example of a centrifugal compressor impeller is disclosed in US Patent No. 3973872.
- the object of the invention is to improve the performance (i.e. total pressure ratio and isentropic efficiency) of a wheel of the aforementioned type, with a corrected flow rate and with a given geometric size.
- Such a centrifugal compressor wheel may comprise two types of blades: so-called “main” blades and so-called “intermediate” blades.
- the intermediate blades are interposed between the main blades and are different from the latter in that they are shorter axially; they have a shorter front part, the leading edge of the intermediate blades being set back (ie behind) with respect to the leading edge of the main blades.
- the wheel comprises only main blades (i.e. no intermediate blades) and these main blades have end fins of the aforementioned type.
- the impeller comprises main blades and intermediate blades.
- the main blades are the only ones to present end fins of the aforementioned type, or the intermediate blades are the only ones to present end fins of the aforementioned type, or the main and intermediate blades have end fins of the aforementioned type.
- said end fin forms with the part of the blade located just upstream of this end fin an obtuse angle greater than or equal to at 155 ° and strictly less than 180 °.
- this end fin extends from the trailing edge of a main blade of the impeller over a length which, measured along the edge outer (curvilinear) of this main blade, represents less than 15% of the total length of this outer edge and, in particular, more than 2% and less than 10% of the total length of this outer edge.
- said end fin extends from the trailing edge of the intermediate blade over a length which, measured along the outer edge thereof intermediate blade, represents less than 15% of the total length of this outer edge and, in particular, more than 2% and less than 10% of the total length of this outer edge.
- the ranges of angle values and fin length above allow, alone or in combination, to further improve the performance of the wheel.
- the invention also relates to a compressor comprising a centrifugal wheel according to the invention.
- It may be a centrifugal type compressor, that is to say a compressor having at least one compression stage equipped with a centrifugal impeller, or a compressor of axial-centrifugal mixed type, that is to say a compressor having at least one compression stage equipped with an axial impeller and at least one compression stage equipped with a centrifugal impeller.
- the invention also relates to a turbomachine and, more particularly, to a helicopter turbine engine comprising a compressor according to the invention.
- FIG. 1 shows schematically and partially, in axial section, a helicopter turbine engine with a compressor comprising a centrifugal wheel according to the invention (the centrifugal impeller and the turbine engine turbines not being shown in section but in side view) .
- FIG. 1 schematically shows the centrifugal wheel of Figure 1, isolated from the rest of the turbine engine.
- FIG. 3 schematically and partially, in perspective, the rear part of two blades of the centrifugal impeller of FIG.
- FIG. 4 schematically and partially shows the rear portion of one of the blades of FIG. 3, seen in section in a radial section plane intersecting the trailing edge of this blade, this section plane IV-IV being marked in FIG. 2.
- FIG. 10 The example of a helicopter turbine engine 10 shown in FIG.
- This compressor 16 comprises a centrifugal wheel 18 according to the invention and a housing 15 surrounding externally the blades 24, 25 of the wheel 18.
- a diffuser 19 is located downstream of the wheel 18.
- the turbine engine 10 has an air inlet 12, the air passing through this inlet 12 to reach the compressor 16.
- the rotation of the wheel 18 about its axis of rotation A draws air from the front of the wheel and the axial velocity of the fluid passing through the wheel 18 is progressively transformed into radial velocity, the fluid exiting the outer periphery of the wheel 18.
- the air leaving the wheel 18 passes through the diffuser 19 before reaching the combustion chamber 20.
- the combustion gases leaving the chamber 20 drive a high pressure turbine 22 and a low pressure turbine 23.
- the wheel 18 is mounted on a shaft 21 which is rotated by the high-pressure turbine 22.
- the wheel 18 has a front portion of small section and a rear portion of large section.
- the wheel 18 comprises a plurality of main blades 24 extending axially from the front face 18A of the wheel to a radial flange 17 located at the rear of the wheel 18 and, radially, from the hub of the wheel to the outer periphery of the wheel.
- Each of the main blades 24 has a leading edge 24A located at the front end of the wheel 18 and a trailing edge 24F located at the outer periphery of the wheel 18, just in front of the radial flange 17.
- the wheel 18 further comprises intermediate blades 25, interposed between the main blades 24 and which are different from the latter in that they are shorter axially: the leading edge 25A of these blades 25 is set back (ie back) relative to the Leading edge 24A of the main blades 24.
- the trailing edge 25F of the intermediate blades 25 is at the same radial distance from the axis A as the trailing edge 24F of the blades 24.
- FIG. 3 shows in detail, in perspective, the rear portion of a main blade 24 and an intermediate blade 25 of the wheel 18.
- the trailing edge portion of said blades 24, 25, is straightened in the direction of rotation of the impeller so that it forms an end fin 26, 27, to deflect the rotor. flow of air by radially straightening it.
- FIG. 4 is a sectional view of the main blade 24 in the radial section plane IV-IV of FIG. 2.
- the main blades 24 and the intermediate blades 25 have end fins 26, 27. In other embodiments, not shown, only the main blades 25 or only the intermediate blades 25 have such blades. end fins.
- the length (in curvilinear abscissa) of each end fin 26 measured along the curvilinear outer edge 24E of said blade 24 does not represent more than 15% of the total length of this outer edge 24E.
- the length of the end vane is at least 2% and not more than 10% of the total length of the outer edge 24E.
- the length (in curvilinear abscissa) of each end fin 27 measured along the curvilinear outer edge 25E of said blade 25 does not represent more than 15% of the total length of this outer edge 25E.
- the length of the end fin represents at least 2% and not more than 10% of the total length of the outer edge 25E.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL10734214T PL2438306T3 (pl) | 2009-06-05 | 2010-06-02 | Wirnik odśrodkowy sprężarki |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0953757A FR2946399B1 (fr) | 2009-06-05 | 2009-06-05 | Rouet centrifuge de compresseur. |
PCT/FR2010/051078 WO2010139901A1 (fr) | 2009-06-05 | 2010-06-02 | Rouet centrifuge de compresseur. |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2438306A1 true EP2438306A1 (fr) | 2012-04-11 |
EP2438306B1 EP2438306B1 (fr) | 2019-07-31 |
Family
ID=41327964
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10734214.9A Active EP2438306B1 (fr) | 2009-06-05 | 2010-06-02 | Rouet centrifuge de compresseur. |
Country Status (10)
Country | Link |
---|---|
US (1) | US20120087800A1 (fr) |
EP (1) | EP2438306B1 (fr) |
JP (1) | JP5705839B2 (fr) |
KR (1) | KR101750121B1 (fr) |
CN (1) | CN102459916B (fr) |
CA (1) | CA2762308A1 (fr) |
FR (1) | FR2946399B1 (fr) |
PL (1) | PL2438306T3 (fr) |
RU (1) | RU2525365C2 (fr) |
WO (1) | WO2010139901A1 (fr) |
Families Citing this family (7)
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 |
JP2017193985A (ja) * | 2016-04-19 | 2017-10-26 | 本田技研工業株式会社 | タービンインペラ |
CN107989823B (zh) * | 2017-12-26 | 2023-12-01 | 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 |
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 |
CN110566500A (zh) * | 2019-10-12 | 2019-12-13 | 浙江科贸智能机电股份有限公司 | 一种离心通风机的叶轮 |
Family Cites Families (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3973872A (en) * | 1975-08-01 | 1976-08-10 | Konstantin Pavlovich Seleznev | Centrifugal compressor |
JPS55134797A (en) * | 1979-04-06 | 1980-10-20 | Hitachi Ltd | Centrifugal vane |
EP0072177B1 (fr) * | 1981-08-07 | 1987-01-07 | Holset Engineering Company Limited | Rotor pour compresseur centrifuge |
SU1231273A1 (ru) * | 1984-11-23 | 1986-05-15 | Всесоюзный Научно-Исследовательский И Проектно-Конструкторский Институт Атомного И Энергетического Насосостроения | Рабочее колесо центробежного насоса |
EP0205001A1 (fr) * | 1985-05-24 | 1986-12-17 | A. S. Kongsberg Väpenfabrikk | Ensemble d'interpales pour compresseurs centrifuges |
DE19516515A1 (de) * | 1995-05-05 | 1996-11-07 | Sel Alcatel Ag | Radialgebläse |
JPH1037893A (ja) * | 1996-07-26 | 1998-02-13 | Japan Servo Co Ltd | 遠心ファン |
US5951245A (en) * | 1997-10-06 | 1999-09-14 | Ford Motor Company | Centrifugal fan assembly for an automotive vehicle |
JPH11280695A (ja) * | 1998-03-26 | 1999-10-15 | Kubota Corp | 施肥装置用の遠心ブロワ |
GB2337795A (en) * | 1998-05-27 | 1999-12-01 | Ebara Corp | An impeller with splitter blades |
JP2000145693A (ja) * | 1998-11-09 | 2000-05-26 | Hitachi Ltd | 多翼前向ファン |
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 |
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 |
DE102007017822A1 (de) * | 2007-04-16 | 2008-10-23 | Continental Automotive Gmbh | Abgasturbolader |
US8007241B2 (en) * | 2007-11-27 | 2011-08-30 | Nidec Motor Corporation | Bi-directional cooling fan |
-
2009
- 2009-06-05 FR FR0953757A patent/FR2946399B1/fr active Active
-
2010
- 2010-06-02 PL PL10734214T patent/PL2438306T3/pl unknown
- 2010-06-02 WO PCT/FR2010/051078 patent/WO2010139901A1/fr active Application Filing
- 2010-06-02 CA CA2762308A patent/CA2762308A1/fr not_active Abandoned
- 2010-06-02 CN CN201080024936.8A patent/CN102459916B/zh active Active
- 2010-06-02 JP JP2012513661A patent/JP5705839B2/ja not_active Expired - Fee Related
- 2010-06-02 RU RU2011153687/06A patent/RU2525365C2/ru not_active IP Right Cessation
- 2010-06-02 KR KR1020117030892A patent/KR101750121B1/ko active IP Right Grant
- 2010-06-02 US US13/376,014 patent/US20120087800A1/en not_active Abandoned
- 2010-06-02 EP EP10734214.9A patent/EP2438306B1/fr active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2010139901A1 * |
Also Published As
Publication number | Publication date |
---|---|
FR2946399A1 (fr) | 2010-12-10 |
CN102459916A (zh) | 2012-05-16 |
CA2762308A1 (fr) | 2010-12-09 |
FR2946399B1 (fr) | 2016-05-13 |
KR101750121B1 (ko) | 2017-06-22 |
US20120087800A1 (en) | 2012-04-12 |
CN102459916B (zh) | 2015-04-29 |
KR20120034670A (ko) | 2012-04-12 |
RU2525365C2 (ru) | 2014-08-10 |
PL2438306T3 (pl) | 2019-12-31 |
EP2438306B1 (fr) | 2019-07-31 |
JP5705839B2 (ja) | 2015-04-22 |
WO2010139901A1 (fr) | 2010-12-09 |
RU2011153687A (ru) | 2013-07-20 |
JP2012528979A (ja) | 2012-11-15 |
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