EP0601227A1 - Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur - Google Patents

Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur Download PDF

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Publication number
EP0601227A1
EP0601227A1 EP92120867A EP92120867A EP0601227A1 EP 0601227 A1 EP0601227 A1 EP 0601227A1 EP 92120867 A EP92120867 A EP 92120867A EP 92120867 A EP92120867 A EP 92120867A EP 0601227 A1 EP0601227 A1 EP 0601227A1
Authority
EP
European Patent Office
Prior art keywords
compressor
ring
impeller
recess
housing
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
EP92120867A
Other languages
German (de)
English (en)
Other versions
EP0601227B1 (fr
Inventor
Klaus Dr.-Ing. 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 Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP92120867A priority Critical patent/EP0601227B1/fr
Priority to DE59208865T priority patent/DE59208865D1/de
Priority to US08/153,427 priority patent/US5375974A/en
Priority to KR1019930024777A priority patent/KR940015291A/ko
Priority to CZ932503A priority patent/CZ283127B6/cs
Priority to PL93301303A priority patent/PL172608B1/pl
Priority to JP5305071A priority patent/JPH06235398A/ja
Priority to CN93120889A priority patent/CN1034605C/zh
Publication of EP0601227A1 publication Critical patent/EP0601227A1/fr
Application granted granted Critical
Publication of EP0601227B1 publication Critical patent/EP0601227B1/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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • 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
    • F04D29/40—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

Definitions

  • the invention relates to a stabilization device for expanding a characteristic map of a compressor.
  • the aim is to achieve monotonically falling characteristic curves with no hysteresis as the flow increases, in order to achieve high reliability in part-load operation.
  • Such continuous characteristics are called stable.
  • stable characteristics are more difficult to achieve the greater the pressure ratio at the design point. That's why you try to generate the desired stable characteristic curves by means of additional stabilizing devices.
  • the stabilization device described for example in the patent specification CH 675 279 consists of a recess in the housing of a radial compressor, a stabilization ring being integrated into this recess.
  • the recess or the stabilizing ring are arranged in front of the impeller and outside the main flow.
  • Stabilizing blades are present on the outer circumference of the stabilizing ring and are anchored to the inner contour of the recess.
  • the disadvantage of this solution is the complex design of the housing, the ring and the stabilizing blades.
  • the already high vibration load on the rotor blades in the entry area is increased by the stabilizing device.
  • This device consists of a ring fixedly connected to the blades, a relatively large radial recirculation channel being arranged between the ring and the housing of the compressor.
  • a recirculation flow is made possible, which contributes to the stabilization of the map.
  • the ring supports the blade leading edges in both the radial and tangential directions and thereby reduces the blade vibrations.
  • the disadvantage of this solution is the necessity of the relatively large recirculation channel and the fact that with some radial compressors an undesirably strong recirculation occurs.
  • the invention tries to avoid all these disadvantages. It is based on the task of a compressor in the impeller inlet area to prevent the formation of the harmful gap flow from one blade side to the other and thus to expand the compressor map by stabilizing the flow and at the same time to eliminate the vibration problems in the impeller inlet area.
  • the stabilization device consists of a ring fixedly attached to the rotor blades and a recess in the housing of the compressor in the form of a rotationally symmetrical groove, the ring being attached in the inlet area of the impeller such that the ring rotates when the impeller rotates the recess is movable, with only a usual close play between the ring and the wall of the housing.
  • the advantages of the invention can be seen, inter alia, in the fact that no vortices or only vortices occur to a reduced extent in the inlet part of the impeller.
  • the efficiency of the compressor is increased and the stable range of the compressor characteristic is widened.
  • the blades support the blades in the tangential and radial directions, so that the vibration load is reduced. Since the ring is only limited to the inlet part of the impeller and the radius there is smaller than at the impeller outlet, the centrifugal force is relatively small and therefore manageable.
  • FIG. 1 An embodiment of the invention is shown using a radial compressor.
  • the single figure shows a partial meridian section of the compressor with the stabilization device. Only the elements essential for understanding the invention are shown.
  • the direction of flow of the working fluid is indicated by an arrow.
  • part of a radial compressor is shown with the stabilization device according to the invention.
  • the compressor consists of the housing 4 and the impeller 3.
  • the impeller 3 is equipped with a ring 1 fixed to the blades 2 in the form of a short cover plate. This cover plate is only limited to the inlet part of the impeller 3.
  • a recess 5 in the form of a rotationally symmetrical groove is present in the housing 4 of the compressor.
  • the dimensions of the recess 5 are matched to the dimensions of the ring 1 such that the ring 1 is easily movable in the recess 5 when the impeller 3 rotates, but only the usual close play exists between the ring 1 and the wall of the housing 4, which z. B. is also present between the upper edges of the blades 2 and the wall of the housing 4.
  • the ring 1 supports the blade leading edges in the radial and tangential directions. The result is that the blade vibration amplitudes are greatly reduced and the mechanical blade load is reduced. Since the ring 1 is only limited to the inlet part of the impeller 3, where the radius is significantly smaller than at the impeller outlet, the centrifugal force is also significantly smaller and therefore manageable. A destruction of the ring 1 due to excessive centrifugal force thus does not take place.
  • the ring 1 rotating in the recess 5 with the impeller 3 prevents the formation of the gap flow over the outer edges of the blades in the impeller region in which the gap flow would contribute to the formation of a harmful vortex.
  • the vortex does not arise at all or only in a reduced scope. This increases the efficiency of the compressor and widens the stable range of the compressor characteristic.
EP92120867A 1992-12-08 1992-12-08 Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur Expired - Lifetime EP0601227B1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP92120867A EP0601227B1 (fr) 1992-12-08 1992-12-08 Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur
DE59208865T DE59208865D1 (de) 1992-12-08 1992-12-08 Stabilierungseinrichtung zur Kennfelderweiterung eines Verdichters
US08/153,427 US5375974A (en) 1992-12-08 1993-11-16 Stabilizing device for extending the characteristic diagram of a compressor
KR1019930024777A KR940015291A (ko) 1992-12-08 1993-11-19 압축기의 특성 선도(線圖)확장용 안정화 장치
CZ932503A CZ283127B6 (cs) 1992-12-08 1993-11-22 Stabilizační zařízení pro rozšíření charakteristického pole kompresoru
PL93301303A PL172608B1 (pl) 1992-12-08 1993-12-03 Urzadzenie stabilizujace do rozszerzania pola charakterystyki sprezarki PL PL
JP5305071A JPH06235398A (ja) 1992-12-08 1993-12-06 圧縮機の特性線図を拡大するための安定化装置
CN93120889A CN1034605C (zh) 1992-12-08 1993-12-08 用于扩展离心式压缩机的特性曲线的稳定装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92120867A EP0601227B1 (fr) 1992-12-08 1992-12-08 Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur

Publications (2)

Publication Number Publication Date
EP0601227A1 true EP0601227A1 (fr) 1994-06-15
EP0601227B1 EP0601227B1 (fr) 1997-09-03

Family

ID=8210287

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92120867A Expired - Lifetime EP0601227B1 (fr) 1992-12-08 1992-12-08 Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur

Country Status (8)

Country Link
US (1) US5375974A (fr)
EP (1) EP0601227B1 (fr)
JP (1) JPH06235398A (fr)
KR (1) KR940015291A (fr)
CN (1) CN1034605C (fr)
CZ (1) CZ283127B6 (fr)
DE (1) DE59208865D1 (fr)
PL (1) PL172608B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10223876A1 (de) * 2002-05-29 2003-12-11 Daimler Chrysler Ag Verdichter für eine Brennkraftmaschine

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7189059B2 (en) * 2004-10-27 2007-03-13 Honeywell International, Inc. Compressor including an enhanced vaned shroud
DE102005019938A1 (de) * 2005-04-29 2006-11-09 Daimlerchrysler Ag Abgasturbolader für eine Brennkraftmaschine
EP2171283A4 (fr) * 2007-02-14 2013-01-30 Borgwarner Inc Carter de compresseur
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
JP6159798B2 (ja) * 2012-06-25 2017-07-05 ボーグワーナー インコーポレーテッド 排気ガスターボチャージャ
KR101501477B1 (ko) * 2013-03-25 2015-03-12 두산중공업 주식회사 원심압축기
US9822698B2 (en) * 2015-02-06 2017-11-21 Honeywell International Inc. Passive and semi-passive inlet-adjustment mechanisms for compressor, and turbocharger having same
DE112015004675T5 (de) * 2015-02-18 2017-07-06 Ihi Corporation Zentrifugalkompressor und Turbolader
JP6770594B2 (ja) * 2017-02-08 2020-10-14 三菱重工エンジン＆ターボチャージャ株式会社 遠心圧縮機及びターボチャージャ
US11313379B2 (en) * 2017-11-06 2022-04-26 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Centrifugal compressor and turbocharger including the same
DE102018132978A1 (de) * 2018-12-19 2020-06-25 Ebm-Papst Mulfingen Gmbh & Co. Kg Turboverdichter mit angepasster Meridiankontur der Schaufeln und Verdichterwand
CN109723674B (zh) * 2019-01-24 2024-01-26 上海海事大学 一种用于压气机转子的可转动内端壁机匣

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE204622C (fr) *
FR907976A (fr) * 1943-10-18 1946-03-27 Sulzer Ag Compresseur centrifuge
US2594042A (en) * 1947-05-21 1952-04-22 United Aircraft Corp Boundary layer energizing means for annular diffusers
CH675279A5 (fr) * 1988-06-29 1990-09-14 Asea Brown Boveri
US5105616A (en) * 1989-12-07 1992-04-21 Sundstrand Corporation Gas turbine with split flow radial compressor

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191313134A (en) * 1913-06-06 1914-04-23 Bertrams Ltd Improvements in Centrifugal Pumps.
GB555888A (en) * 1941-10-25 1943-09-10 Scintilla Ltd Method of making runners for blowers
NO276573L (fr) * 1973-07-05 1975-02-03 Thune Eureka As
FI61235C (fi) * 1979-01-29 1982-06-10 Nokia Oy Ab Vinghjul hos en centrifugalflaekt
IT1174991B (it) * 1983-07-06 1987-07-01 Pompe F B M Spa Pompa centrifuga per materiali e prodotti molto densi e/o viscosi
FR2559544B1 (fr) * 1984-02-10 1988-07-08 Creusot Loire Procede de realisation d'une roue a aubes fermee et roue obtenue au moyen de ce procede
JPS61138899A (ja) * 1984-12-11 1986-06-26 Matsushita Electric Ind Co Ltd 斜流送風機
US5304033A (en) * 1992-07-20 1994-04-19 Allied-Signal Inc. Rotary compressor with stepped cover contour

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE204622C (fr) *
FR907976A (fr) * 1943-10-18 1946-03-27 Sulzer Ag Compresseur centrifuge
US2594042A (en) * 1947-05-21 1952-04-22 United Aircraft Corp Boundary layer energizing means for annular diffusers
CH675279A5 (fr) * 1988-06-29 1990-09-14 Asea Brown Boveri
US5105616A (en) * 1989-12-07 1992-04-21 Sundstrand Corporation Gas turbine with split flow radial compressor

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10223876A1 (de) * 2002-05-29 2003-12-11 Daimler Chrysler Ag Verdichter für eine Brennkraftmaschine

Also Published As

Publication number Publication date
KR940015291A (ko) 1994-07-20
EP0601227B1 (fr) 1997-09-03
DE59208865D1 (de) 1997-10-09
CN1034605C (zh) 1997-04-16
PL301303A1 (en) 1994-06-13
JPH06235398A (ja) 1994-08-23
US5375974A (en) 1994-12-27
CN1096858A (zh) 1994-12-28
CZ250393A3 (en) 1994-06-15
CZ283127B6 (cs) 1998-01-14
PL172608B1 (pl) 1997-10-31

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