EP0593797B1 - 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
EP0593797B1
EP0593797B1 EP92117780A EP92117780A EP0593797B1 EP 0593797 B1 EP0593797 B1 EP 0593797B1 EP 92117780 A EP92117780 A EP 92117780A EP 92117780 A EP92117780 A EP 92117780A EP 0593797 B1 EP0593797 B1 EP 0593797B1
Authority
EP
European Patent Office
Prior art keywords
ring
stabilization device
max
impeller
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.)
Expired - Lifetime
Application number
EP92117780A
Other languages
German (de)
English (en)
Other versions
EP0593797A1 (fr
Inventor
Daniel Arnet
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 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 DE59206751T priority Critical patent/DE59206751D1/de
Priority to EP92117780A priority patent/EP0593797B1/fr
Priority to US08/124,544 priority patent/US5403149A/en
Priority to KR1019930020797A priority patent/KR940009536A/ko
Priority to CZ932158A priority patent/CZ283618B6/cs
Priority to JP5258707A priority patent/JPH06193594A/ja
Priority to FI934570A priority patent/FI934570A/fi
Publication of EP0593797A1 publication Critical patent/EP0593797A1/fr
Application granted granted Critical
Publication of EP0593797B1 publication Critical patent/EP0593797B1/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
    • 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
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the invention relates to a stabilization device for expanding a characteristic map of a compressor according to the preamble of claim 1.
  • Such stabilization devices are known for axial and radial compressors, see e.g. GB-A-761 937, FR-A-1 528 797 or GB-A-798 480.
  • turbocompressors the aim is to achieve monotonically decreasing characteristics with increasing flow without hysteresis 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. For this reason, attempts are made to generate the desired characteristics using additional stabilization devices.
  • Patent specification EP 0 229 519 describes a stabilizing device for a radial compressor, which is characterized in that the inner housing has radial bores or slots as the sheathing of the impeller. that create a connection between the flow channel and the blading and are more or less covered by the blades on the blade side. As a result, the pump or stability limit is shifted in a characteristic curve, but at the same time the efficiency of the compressor is greatly reduced.
  • a centrifugal compressor (US Pat. No. 4,212,585) is also known, in which there is an additional housing with free recesses which extend in the direction of flow.
  • these recesses produce a pumping action, ie unstable characteristic curves, particularly in the part-load range.
  • the stabilizing device described in the patent specification CH 675 279 also consists of a recess in the housing of the radial compressor, but in this recess a stabilizing ring is integrated, which is arranged in front of the impeller and outside of the main flow and carries a number of blades on its outer circumference the inner contour of the recess are anchored.
  • the disadvantage of this solution is the complex design of the housing and the stabilization device.
  • the known technical solutions for stabilizing the compressor map include a special design of the compressor housing.
  • a recirculation flow is made possible through or in the openings arranged in the compressor housing.
  • the invention tries to avoid all these disadvantages. It is based on the task of broadening the compressor map to a small throughput by stabilizing the flow and at the same time eliminating the vibration and play problems in the impeller inlet area. Furthermore, it is based on the additional task of reducing the influence of the boundary layer on the flow conditions at the blade leading edges in the compressor with stabilizing device.
  • a recirculation channel is arranged between the ring and the housing of the compressor, which has an opening to the impeller at its rear end in the direction of flow, and only after the rear end of this opening between the impeller and the wall of the housing the close game that was usual up until now still exists.
  • the compressor consists of the housing 3 and the impeller 5.
  • the impeller 5 is equipped with a co-rotating, thin ring 2 connected to the blades 1.
  • the front edge of the ring 2 lying in the flow direction of the gas is located axially in front of the inlet edges of the rotor blades 1.
  • a recirculation channel 4 is arranged, which through the outer surface of the ring 2 and the inner surface of the compressor housing 3 is limited.
  • the recirculation channel 4 has an opening towards the impeller 5 at its rear end in the flow direction. Only from the rear end of this opening on the impeller 5 and the inner wall of the housing 3 have the usual tight play.
  • the ring 2 supports the blade leading edges in both the tangential and radial directions. As a result, the amplitudes of the blade vibrations are greatly reduced and the mechanical blade load is reduced. Due to the reduced blade load, the rotor blades 1 can be made thinner than is possible without a ring, which in turn increases the efficiency of the impeller.
  • the radial recirculation channel 4 located next to the impeller 5 primarily stabilizes the compressor map.
  • the recirculation flow stabilizing the flow can be formed when the compressor is throttled.
  • the compressor map is widened to small volume flows.
  • the map is also broadened towards large volume flows, since at very high throughput, when the speed of sound already exists in the narrowest impeller cross section, fluid can flow into impeller 5 through recirculation channel 4.
  • the boundary layer formed in the inflow area to the impeller 5 on the outer wall of the housing 3 no longer influences the flow conditions at the front edges of the rotor blades 1, since it flows past the blade inlet edges in the recirculation channel 4 located next to the impeller 5. Boundary layer compensation through an adapted blade shape is therefore not necessary.
  • the boundary layer which forms on the co-rotating, axially projecting ring 2 rotates with the ring 2. It therefore has a swirl component which is aligned with the rotation of the impeller. This reduces the Mach number the blade leading edges, which causes a better swallowing ability of the impeller.
  • Another advantage of the invention is that the large distance between the ring 2 and the housing 3 in the impeller entry area means that there are no more play problems and there are new degrees of freedom for the design of the outer contour of the impeller 5.
  • FIG. 2 shows further exemplary embodiments of the invention which relate to a different arrangement and design of the ring 2 on a radial compressor.
  • the ring 2 which is fixedly connected to the rotor blades 1, is flush with the blade inlet edges, while in FIG. 3 the edge of the ring 2, which is in the flow direction, is located axially behind the blade inlet edges.
  • FIG. 4 shows that the size of the radius of the ring 2 can be changed in the axial direction.
  • the surface of the ring 2 has a certain roughness because this has a favorable influence on the swirl of the boundary layer adhering to the ring 2.
  • the surface roughness R z should be in the range from 6.3 to max. 40, preferably 20.
  • the ratio of the common meridian arc length between the ring and the outer blade cut to the meridian arc length of the outer blade cut s 1 / s max is 0.05 up to max. 0.2, preferably 0.09.
  • the ratio of the meridian arc length from the blade leading edge to the end of the opening of the recirculation channel to the meridian arc length of the outer blade section s 2 / s max is 0.15 to max.
  • the ratio of the distance between the flow direction front edge of the ring 2 from the blade leading edge to the meridian arc length of the outer blade cut 1 / s max is -0.1 to max. 0.6, preferably 0.41 and the ratio of the height of the recirculation channel to the outer radius of the impeller ⁇ r / r 2 is 0.075 to max.0.2, preferably 0.11.
  • the stabilizing device according to the invention can of course also be installed in axial compressors.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur avec une bague (2) fixée aux aubes (1) et tournant avec elles, caractérisé par le fait qu'un canal de recirculation (4) est disposé entre la bague (2) et le boîtier (3) du compresseur, lequel est muni d'une ouverture en direction de la roue à aubes (5) au niveau de son extrémité arrière dans le sens du courant, le jeu restant entre la roue à aubes (5) et la paroi du boîtier (3) dans la jonction au niveau de l'extrémité arrière de cette ouverture n'étant ici que le faible jeu couramment obtenu jusqu'à présent.
  2. Dispositif de stabilisation conforme à la revendication 1, caractérisé par le fait que l'arête avant de la bague (2) se trouvant dans le sens du courant est à fleur avec les arêtes d'entrée des aubes (1).
  3. Dispositif de stabilisation conforme à la revendication 1, caractérisé par le fait que l'arête avant de la bague (2) se trouvant dans le sens du courant est disposée dans le sens axial avant les arêtes d'entrée des aubes (1).
  4. Dispositif de stabilisation conforme à la revendication 1, caractérisé par le fait que l'arête avant de la bague (2) se trouvant dans le sens du courant est disposée dans le sens axial après les arêtes d'entrée des aubes (1).
  5. Dispositif de stabilisation conforme à la revendication 1 et à l'une des revendications 2 à 4, caractérisé par le fait que le rayon de la bague (2) est modifiable dans le sens axial.
  6. Dispositif de stabilisation conforme à la revendication 1 et à l'une des revendications 2 à 4, caractérisé par le fait que la bague (2) présente une rugosité de surface Rz comprise entre 6,3 et 40 max.
  7. Dispositif de stabilisation conforme à la revendication 6, caractérisé par le fait que la rugosité de surface Rz de la bague (2) est de 20.
  8. Dispositif de stabilisation conforme à la revendication 1, caractérisé par le fait que dans le cas du positionnement axial de la bague (2), les dimensions du canal d'écoulement (4) sont définies à partir du rapport de la longueur de la courbure méridienne totale entre la bague et la tranche la plus élevée des aubes (s1) et de la longueur de la courbure méridienne de la tranche la plus à l'extérieur des aubes (smax) qui est compris entre 0,05 et 0,2 max., un rapport de la longueur de la courbure méridienne entre l'arête d'entrée des aubes et l'extrémité de l'ouverture du canal d'écoulement (s2) et de la longueur méridienne de la tranche la plus à l'extérieur des aubes (smaX) qui est compris entre 0,15 et 0,4 max., un rapport de l'écart entre l'arête avant de la bague se trouvant dans le sens du courant et l'arête d'entrée des aubes (1) et de la longueur de la courbure méridienne de la tranche la plus à l'extérieur des aubes (smax) qui est compris entre -0,1 et 0,6 max. et un rapport de la hauteur du canal de recirculation (Δr) et du rayon extérieur de la roue à aubes (r2) qui est compris entre 0,075 et 0,2 max.
  9. Dispositif de stabilisation conforme à la revendication 8, caractérisé par le fait que les rapports sont s1/smax = 0,09, s2/smax = 0,27, l/smax = 0,41 et Δr/r2 = 0,11.
EP92117780A 1992-10-17 1992-10-17 Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur Expired - Lifetime EP0593797B1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
DE59206751T DE59206751D1 (de) 1992-10-17 1992-10-17 Stabilisierungseinrichtung zur Kennfelderweiterung eines Verdichters
EP92117780A EP0593797B1 (fr) 1992-10-17 1992-10-17 Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur
US08/124,544 US5403149A (en) 1992-10-17 1993-09-22 Stabailization device for extending the characteristic map of a compressor
KR1019930020797A KR940009536A (ko) 1992-10-17 1993-10-08 압축기의 특성 지도를 확장하기 위한 안정화 장치
CZ932158A CZ283618B6 (cs) 1992-10-17 1993-10-13 Stabilizační zařízení pro rozšíření charakteristického pole kompresoru
JP5258707A JPH06193594A (ja) 1992-10-17 1993-10-15 圧縮機の特性ダイアグラムを拡大するための安定化装置
FI934570A FI934570A (fi) 1992-10-17 1993-10-15 Stabileringsapparatur foer utvidgning av en kompressors kurvskara

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92117780A EP0593797B1 (fr) 1992-10-17 1992-10-17 Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur

Publications (2)

Publication Number Publication Date
EP0593797A1 EP0593797A1 (fr) 1994-04-27
EP0593797B1 true EP0593797B1 (fr) 1996-07-10

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP92117780A Expired - Lifetime EP0593797B1 (fr) 1992-10-17 1992-10-17 Dispositif de stabilisation pour l'extension de la tolérance de pompage d'un compresseur

Country Status (7)

Country Link
US (1) US5403149A (fr)
EP (1) EP0593797B1 (fr)
JP (1) JPH06193594A (fr)
KR (1) KR940009536A (fr)
CZ (1) CZ283618B6 (fr)
DE (1) DE59206751D1 (fr)
FI (1) FI934570A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014222877A1 (de) 2014-11-10 2016-05-12 Siemens Aktiengesellschaft Laufrad einer Radialturbofluidenergiemaschine, Stufe

Families Citing this family (8)

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DE19513508A1 (de) * 1995-04-10 1996-10-17 Abb Research Ltd Verdichter
FR2806442B1 (fr) * 2000-03-17 2003-01-10 Turbomeca Turbomachine comportant un dispositif de suppression des vibrations dues aux resonances acoustiques
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
DE102005052466A1 (de) * 2005-11-03 2007-05-10 Mtu Aero Engines Gmbh Mehrstufiger Verdichter für eine Gasturbine mit Abblasöffnungen und Einblasöffnungen zum Stabilisieren der Verdichterströmung
US8061974B2 (en) * 2008-09-11 2011-11-22 Honeywell International Inc. Compressor with variable-geometry ported shroud
EP3530957B1 (fr) * 2017-02-08 2021-05-12 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Compresseur et turbocompresseur
WO2019087389A1 (fr) 2017-11-06 2019-05-09 三菱重工エンジン＆ターボチャージャ株式会社 Compresseur centrifuge et turbocompresseur de suralimentation comprenant ledit compresseur centrifuge

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US2827261A (en) * 1953-08-21 1958-03-18 Garrett Corp Fluid propulsion apparatus
GB761937A (en) * 1953-08-21 1956-11-21 Garrett Corp Improvements in or relating to a rotary fluid pressure converting device such as a turbine, compressor, pump or the like
GB798480A (en) * 1955-07-04 1958-07-23 Chrysler Corp Improvements in or relating to centrifugal compressors
FR1528797A (fr) * 1967-04-17 1968-06-14 Lyonnaise Ventilation Perfectionnements aux ventilateurs centrifuges
US4212585A (en) * 1978-01-20 1980-07-15 Northern Research And Engineering Corporation Centrifugal compressor
US4930979A (en) * 1985-12-24 1990-06-05 Cummins Engine Company, Inc. Compressors
EP0229519B2 (fr) * 1985-12-24 1996-11-13 Holset Engineering Company Limited Compresseurs
KR900007253B1 (ko) * 1986-05-19 1990-10-06 우수이 고꾸사이 산교 가부시기가이샤 고속축류팬용 블레이드
CH675279A5 (fr) * 1988-06-29 1990-09-14 Asea Brown Boveri
US4930978A (en) * 1988-07-01 1990-06-05 Household Manufacturing, Inc. Compressor stage with multiple vented inducer shroud
DE4027174A1 (de) * 1990-08-28 1992-03-05 Kuehnle Kopp Kausch Ag Kennfeldstabilisierung bei einem radialverdichter
US5304033A (en) * 1992-07-20 1994-04-19 Allied-Signal Inc. Rotary compressor with stepped cover contour
US5275531A (en) * 1993-04-30 1994-01-04 Teleflex, Incorporated Area ruled fan blade ends for turbofan jet engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014222877A1 (de) 2014-11-10 2016-05-12 Siemens Aktiengesellschaft Laufrad einer Radialturbofluidenergiemaschine, Stufe
WO2016074889A1 (fr) 2014-11-10 2016-05-19 Siemens Aktiengesellschaft Rotor d'une turbomachine à énergie fluidique radiale, étage

Also Published As

Publication number Publication date
US5403149A (en) 1995-04-04
JPH06193594A (ja) 1994-07-12
FI934570A (fi) 1994-04-18
DE59206751D1 (de) 1996-08-14
CZ283618B6 (cs) 1998-05-13
KR940009536A (ko) 1994-05-20
CZ215893A3 (en) 1994-05-18
EP0593797A1 (fr) 1994-04-27
FI934570A0 (fi) 1993-10-15

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