EP0614014A1 - Compresseur radial avec un carter stabilisant l'écoulement de fluides - Google Patents

Compresseur radial avec un carter stabilisant l'écoulement de fluides Download PDF

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Publication number
EP0614014A1
EP0614014A1 EP94102099A EP94102099A EP0614014A1 EP 0614014 A1 EP0614014 A1 EP 0614014A1 EP 94102099 A EP94102099 A EP 94102099A EP 94102099 A EP94102099 A EP 94102099A EP 0614014 A1 EP0614014 A1 EP 0614014A1
Authority
EP
European Patent Office
Prior art keywords
slots
radial
flow
blades
radial 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.)
Granted
Application number
EP94102099A
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German (de)
English (en)
Other versions
EP0614014B1 (fr
Inventor
Klaus Dr. Heinrich
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.)
ABB Management AG
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ABB Management AG
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 ABB Management AG filed Critical ABB Management AG
Publication of EP0614014A1 publication Critical patent/EP0614014A1/fr
Application granted granted Critical
Publication of EP0614014B1 publication Critical patent/EP0614014B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface

Definitions

  • Such a radial compressor is e.g. known from US-A-4,212,585.
  • FIG. 1 A solution referred to as "casing treatment” is described in the publication mentioned at the beginning.
  • casing treatment is described in the publication mentioned at the beginning.
  • the schematic representation in FIG. 1 it is characterized by a multiplicity of narrow stabilizer slots 5 provided in the compressor housing 4.
  • the stabilizer slots 5 begin at the blade leading edges 6 of the blades 3 of the impeller 2 or even a short distance upstream from them. They are inclined in the direction of rotation of the impeller 2 and are partially arranged at an angle to the machine axis 7.
  • the slots In the meridional section, the slots have a rectangular shape, the front wall 5a and the rear wall 5c being oriented approximately perpendicularly with respect to the machine axis 7.
  • the essence of the invention is to arrange the stabilizer slots in such a way that the recirculation vortices which form with increasing throttling can already be influenced by the slots before they are fully developed.
  • a first preferred embodiment of the compressor according to the invention is characterized in that the rear end of the stabilizer slots lies in the area of the beginning deflection from the axial inflow into the radial outflow.
  • a second preferred embodiment of the compressor according to the invention is characterized in that the rotor blades comprise main blades that extend from the axial inlet to the radial outlet and intermediate intermediate blades that start shortly after the axial inlet, and that the rear end of the stabilizer slots in the area of the beginning of the Intermediate blades lies.
  • the advantages of the previous embodiment can also be achieved with impellers with blades of different lengths.
  • the shape of the slots is adapted to the conditions in the recirculation vortex in terms of flow technology.
  • this is achieved in that the stabilizer slots each have a base which extends straight in the direction of flow and is oriented approximately tangentially to the adjacent outer contour of the blades, in that the stabilizer slots are each delimited at the rear end by a rear wall , which is flatter than the normal of the inner housing contour and includes an acute angle ( ⁇ ) with this standard, and that the rear wall merges into the floor with a constant tangent.
  • the known radial compressor with a stabilizing housing comprises an impeller 2 which is rotatably mounted on a machine axis 7 and which carries on a hub 9 a large number of rotor blades 3 which are arranged at a uniform angular distance on the circumference of the hub 9.
  • the impeller is housed in a compressor housing 4 (only partially indicated in Fig. 1).
  • the compressor housing 4 has an inner housing contour 4a on the inside, which is adapted to the outer contour of the rotor blades 3.
  • Inner housing contour 4a and hub 9 form a flow channel for the medium to be compressed, which leads from an axial inlet 10 to a radial outlet 11, the medium being successively deflected from an axial inflow into a radial outflow in a central region of the flow duct.
  • the known casing treatment now comprises a plurality of stabilizer slots 5, which are in the area of the blade leading edge 6 are arranged on the inner circumference of the housing with a regular angular distance.
  • the stabilizer slots 5, which are elongate in the direction of the machine axis 7, have an essentially rectangular cross section in the meridional plane and are delimited at the front and rear ends by a front wall 5a and rear wall 5c, each of which is oriented perpendicular to the machine axis 7.
  • the front wall 5a lies upstream in front of the blade leading edge 6.
  • the outer limit in the radial direction is provided by a base 5b running parallel to the machine axis 7.
  • the stabilizing effect of the slots in the inner housing wall is based on influencing the recirculation vortex in the front impeller area: the vortex is displaced out of the impeller into the slots and thus loses influence on the main flow.
  • the vortex does not occur directly at the blade leading edges 6 of the impeller 2. Rather, it arises downstream of the blade leading edge 6 in the region of the beginning of the deflection from the axial inflow into the radial outflow or in the region of the front edges of the intermediate blades (if the rotor blades are divided into main and intermediate blades).
  • the position of the stabilizer slots In order to shift the surge limit in the entire speed range of the compressor to smaller volume flows, the position of the stabilizer slots must first be optimally adapted to the position and shape of the recirculation vortex. Secondly, it should be possible for the weak vortex, which is just emerging, to flow into the slots. For this purpose, the contour of the slots should be shaped so that the slots have the lowest possible hydraulic resistance.
  • FIG. 2 A first preferred exemplary embodiment of such an optimized casing treatment is shown in FIG. 2.
  • the rotor blades 3 are each divided into longer main blades 3a, which extend from the axial inlet 10 to the radial outlet 11, and into intermediate, shorter intermediate blades 3b with their own leading edge 8 set back.
  • the stabilizer slots 5 are not only changed in their position, but also in their form compared to the prior art. They lie with their front end facing the axial inlet 10, i.e. with its front wall 5a, a predetermined distance downstream from the blade leading edge 6.
  • the rear end of the slots is placed in the region of the deflection of the axial inflow into the radial outflow, which in the division of the blades 3 shown in FIG. 2 (b) is equivalent to the region immediately behind the front edge 8 of the intermediate blades 3b.
  • the person skilled in the art can easily find the optimal position and length of the stabilizer slots 5 after a mathematical or experimental determination of the position and size of the recirculation vortex.
  • the slots can also be arranged inclined in the direction of rotation of the impeller 2.
  • the front wall 5a remains largely perpendicular to the machine axis 7.
  • the straight floor 5b is no longer parallel to the machine axis, but rather approximately tangential to the adjacent outer contour of the blades (3) and thus to Recirculation vortex oriented.
  • the stabilizer slots 5 are each delimited at the rear end by a rear wall 5c, which runs flatter than the normal of the inner housing contour 4a there and includes an acute angle ⁇ with this normal, the size of which also depends on the conditions to be determined in the vertebra.
  • the shape of the stabilizer slots 5 is simplified with the position unchanged compared to the example in FIG. 2. There is no longer a rear wall here. Rather, the bottom 5b of the slots runs in a wedge shape at the rear end into the inner housing contour 4a, which results in a simplified manufacture of the slots while also influencing the vertebra.
  • the invention provides a radial compressor that can be expanded significantly of the stable working area towards low volume flows in the entire map area.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP94102099A 1993-03-04 1994-02-11 Compresseur radial avec un carter stabilisant l'écoulement de fluides Expired - Lifetime EP0614014B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4306689 1993-03-04
DE4306689A DE4306689A1 (de) 1993-03-04 1993-03-04 Radialverdichter mit einem strömungsstabilisierenden Gehäuse

Publications (2)

Publication Number Publication Date
EP0614014A1 true EP0614014A1 (fr) 1994-09-07
EP0614014B1 EP0614014B1 (fr) 1996-05-29

Family

ID=6481874

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94102099A Expired - Lifetime EP0614014B1 (fr) 1993-03-04 1994-02-11 Compresseur radial avec un carter stabilisant l'écoulement de fluides

Country Status (8)

Country Link
US (1) US5466118A (fr)
EP (1) EP0614014B1 (fr)
JP (1) JPH06294397A (fr)
CN (1) CN1034606C (fr)
CZ (1) CZ48394A3 (fr)
DE (2) DE4306689A1 (fr)
PL (1) PL172603B1 (fr)
RU (1) RU2117825C1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2090786A3 (fr) * 2008-02-15 2011-04-20 Rolls-Royce Deutschland Ltd & Co KG Structuration de boîtier destinée à la stabilisation de l'écoulement dans une machine de traitement des écoulements
CN101761511B (zh) * 2010-02-09 2011-05-11 清华大学 开槽宽度为抛物线的离心压气机非对称自循环处理机匣
WO2016082916A1 (fr) * 2014-11-25 2016-06-02 Ihi Charging Systems International Gmbh Compresseur pour turbocompresseur à gaz d'échappement
RU2623323C2 (ru) * 2012-09-06 2017-06-23 Сименс Акциенгезелльшафт Турбомашина и способ ее работы

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6164911A (en) * 1998-11-13 2000-12-26 Pratt & Whitney Canada Corp. Low aspect ratio compressor casing treatment
JP3884880B2 (ja) * 1999-04-26 2007-02-21 淳一 黒川 羽根入口再循環流および羽根旋回失速を抑制したターボ機械
US6302643B1 (en) * 1999-04-26 2001-10-16 Hitachi, Ltd. Turbo machines
US6527509B2 (en) * 1999-04-26 2003-03-04 Hitachi, Ltd. Turbo machines
DE60036336T2 (de) * 1999-07-15 2008-06-12 Hitachi Plant Technologies, Ltd. Turbomaschinen
US6290458B1 (en) * 1999-09-20 2001-09-18 Hitachi, Ltd. Turbo machines
DE10029808C1 (de) 2000-06-16 2001-11-29 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
CN1323225C (zh) * 2003-07-16 2007-06-27 沈阳黎明航空发动机(集团)有限责任公司 一种利用涡轮风扇发动机改制成工业燃机的方法
EP1538752A1 (fr) * 2003-11-28 2005-06-08 Freescale Semiconductor, Inc. Appareil générateur d'impulsions d'horloge à gigue de phase réduite
KR100568183B1 (ko) * 2004-01-08 2006-04-05 삼성전자주식회사 터보압축기
JP4949882B2 (ja) * 2007-02-13 2012-06-13 三菱重工業株式会社 遠心圧縮機のインペラ及び遠心圧縮機
CN100457548C (zh) * 2007-11-09 2009-02-04 北京航空航天大学 一种非轴对称组合处理机匣
CN102066717A (zh) * 2008-06-17 2011-05-18 株式会社Ihi 涡轮增压机用的压缩机壳体
CN101749279A (zh) * 2010-02-09 2010-06-23 清华大学 基于变开槽位置的离心压气机非对称自循环处理机匣
CN101761512B (zh) * 2010-02-09 2011-06-15 清华大学 开槽位置为圆弧分布的离心压气机非对称自循环处理机匣
US9404370B2 (en) * 2010-08-26 2016-08-02 Borgwarner Inc. Exhaust-gas turbocharger component with microstructured surface
RU2014145610A (ru) 2012-04-23 2016-06-10 Боргварнер Инк. Ступица турбины с несплошностью поверхности и турбонагнетатель, содержащий такую ступицу
DE112013001660T5 (de) * 2012-04-23 2014-12-24 Borgwarner Inc. Turbolader-Schaufelversteifungsband mit kreuzweisen Nuten und Turbolader mit Turbolader-Schaufelversteifungsband mit kreuzweisen Nuten
CN102817873B (zh) * 2012-08-10 2015-07-15 势加透博（北京）科技有限公司 航空发动机压气机的梯状间隙结构
DE102013018286A1 (de) * 2013-10-31 2015-04-30 Man Diesel & Turbo Se Radialverdichter
US9644639B2 (en) 2014-01-27 2017-05-09 Pratt & Whitney Canada Corp. Shroud treatment for a centrifugal compressor
CN103953560B (zh) * 2014-04-18 2016-04-06 合肥通用机械研究院 一种压缩机扩稳系统以及应用于该系统的压缩机机构
DE112015004675T5 (de) * 2015-02-18 2017-07-06 Ihi Corporation Zentrifugalkompressor und Turbolader
CN106438475A (zh) * 2016-09-18 2017-02-22 江苏大学 一种抑制叶顶泄漏流的斜流泵
EP3589822A4 (fr) 2017-03-03 2020-12-09 Elliott Company Procédé et agencement pour minimiser le bruit et l'excitation de structures dues à des modes acoustiques de cavité
CN109882448B (zh) * 2019-02-25 2020-06-26 江苏大学 一种具有圆弧形泵送槽的混流泵转轮室
EP3969761A1 (fr) 2019-05-14 2022-03-23 Carrier Corporation Compresseur centrifuge comprenant une caractéristique d'égalisation de pression de diffuseur
JP2021124069A (ja) * 2020-02-06 2021-08-30 三菱重工業株式会社 コンプレッサハウジング、該コンプレッサハウジングを備えるコンプレッサ、および該コンプレッサを備えるターボチャージャ
CN111734655B (zh) * 2020-07-31 2020-12-29 宁波丰沃涡轮增压系统有限公司 呼吸机用涡轮风机

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3893787A (en) * 1974-03-14 1975-07-08 United Aircraft Corp Centrifugal compressor boundary layer control
US4212585A (en) * 1978-01-20 1980-07-15 Northern Research And Engineering Corporation Centrifugal compressor
EP0092955A2 (fr) * 1982-04-22 1983-11-02 A/S Kongsberg Väpenfabrikk Méthode et dispositif pour influencer la couche limite de médium dans un compresseur
GB2158879A (en) * 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
GB2202585A (en) * 1987-03-24 1988-09-28 Holset Engineering Co Rotary non-positive displacement compressor
US4781530A (en) * 1986-07-28 1988-11-01 Cummins Engine Company, Inc. Compressor range improvement means
GB2220447A (en) * 1988-07-01 1990-01-10 Schwitzer Us Inc Gas intake vents for surge and choke control in a compressor
WO1990014510A1 (fr) * 1989-05-18 1990-11-29 Sundstrand Corporation Passages de purge d'air menages dans l'enveloppe de protection d'un compresseur

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4063848A (en) * 1976-03-24 1977-12-20 Caterpillar Tractor Co. Centrifugal compressor vaneless space casing treatment
JPS5535173A (en) * 1978-09-02 1980-03-12 Kobe Steel Ltd Method of and apparatus for enlarging surge margin in centrifugal compressor and axial flow conpressor
FI69683C (fi) * 1982-02-08 1986-03-10 Ahlstroem Oy Centrifugalpump foer vaetskor innehaollande fasta aemnen
DE3670347D1 (de) * 1985-12-24 1990-05-17 Holset Engineering Co Kompressoren.
CH675279A5 (fr) * 1988-06-29 1990-09-14 Asea Brown Boveri
SU1756646A1 (ru) * 1990-08-14 1992-08-23 Уральский филиал Теплотехнического научно-исследовательского института им.Ф.Э.Дзержинского Рабочее колесо центробежного насоса
US5236301A (en) * 1991-12-23 1993-08-17 Allied-Signal Inc. Centrifugal compressor
US5277541A (en) * 1991-12-23 1994-01-11 Allied-Signal Inc. Vaned shroud for centrifugal compressor

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3893787A (en) * 1974-03-14 1975-07-08 United Aircraft Corp Centrifugal compressor boundary layer control
US4212585A (en) * 1978-01-20 1980-07-15 Northern Research And Engineering Corporation Centrifugal compressor
EP0092955A2 (fr) * 1982-04-22 1983-11-02 A/S Kongsberg Väpenfabrikk Méthode et dispositif pour influencer la couche limite de médium dans un compresseur
GB2158879A (en) * 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
US4781530A (en) * 1986-07-28 1988-11-01 Cummins Engine Company, Inc. Compressor range improvement means
GB2202585A (en) * 1987-03-24 1988-09-28 Holset Engineering Co Rotary non-positive displacement compressor
GB2220447A (en) * 1988-07-01 1990-01-10 Schwitzer Us Inc Gas intake vents for surge and choke control in a compressor
WO1990014510A1 (fr) * 1989-05-18 1990-11-29 Sundstrand Corporation Passages de purge d'air menages dans l'enveloppe de protection d'un compresseur

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2090786A3 (fr) * 2008-02-15 2011-04-20 Rolls-Royce Deutschland Ltd & Co KG Structuration de boîtier destinée à la stabilisation de l'écoulement dans une machine de traitement des écoulements
US8262351B2 (en) 2008-02-15 2012-09-11 Rolls-Royce Deutschland Ltd Co KG Casing structure for stabilizing flow in a fluid-flow machine
CN101761511B (zh) * 2010-02-09 2011-05-11 清华大学 开槽宽度为抛物线的离心压气机非对称自循环处理机匣
RU2623323C2 (ru) * 2012-09-06 2017-06-23 Сименс Акциенгезелльшафт Турбомашина и способ ее работы
WO2016082916A1 (fr) * 2014-11-25 2016-06-02 Ihi Charging Systems International Gmbh Compresseur pour turbocompresseur à gaz d'échappement
US10400789B2 (en) 2014-11-25 2019-09-03 Charging Systems International Gmbh Compressor for an exhaust gas turbocharger

Also Published As

Publication number Publication date
CZ48394A3 (en) 1994-09-14
EP0614014B1 (fr) 1996-05-29
PL302341A1 (en) 1994-09-05
CN1034606C (zh) 1997-04-16
DE59400303D1 (de) 1996-07-04
PL172603B1 (pl) 1997-10-31
CN1096347A (zh) 1994-12-14
DE4306689A1 (de) 1994-09-08
RU2117825C1 (ru) 1998-08-20
JPH06294397A (ja) 1994-10-21
US5466118A (en) 1995-11-14

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