EP0518027B1 - Compresseur centrifugal - Google Patents

Compresseur centrifugal Download PDF

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Publication number
EP0518027B1
EP0518027B1 EP92106288A EP92106288A EP0518027B1 EP 0518027 B1 EP0518027 B1 EP 0518027B1 EP 92106288 A EP92106288 A EP 92106288A EP 92106288 A EP92106288 A EP 92106288A EP 0518027 B1 EP0518027 B1 EP 0518027B1
Authority
EP
European Patent Office
Prior art keywords
impeller
exit
centrifugal compressor
air
annular space
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
EP92106288A
Other languages
German (de)
English (en)
Other versions
EP0518027A1 (fr
Inventor
Koichiro C/O Nagasaki Shipyard & Eng. Imakiire
Keiichi C/O Nagasaki Shipyard & Eng. Shiraishi
Masanori C/O Nagasaki Shipyard & Eng. Kimura
Masayoshi C/O Nagasaki Shipyard & Eng. Tagawa
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP0518027A1 publication Critical patent/EP0518027A1/fr
Application granted granted Critical
Publication of EP0518027B1 publication Critical patent/EP0518027B1/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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5846—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling by injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B3/00—Engines characterised by air compression and subsequent fuel addition
    • F02B3/06—Engines characterised by air compression and subsequent fuel addition with compression ignition

Definitions

  • the present invention relates to a centrifugal compressor to be applied, for example, as a supercharger of an engine.
  • Fig. 3 is a longitudinal section showing the structure of a centrifugal compressor of the prior art
  • Fig. 4 is a section for explaining the operations of the same.
  • a labyrinth packing 5 which seals up a seal space 7 between the exit and back of the impeller 1.
  • the seal space 7 is vented to the outside through a ventilation hole 8 for releasing a slight amount of air, which comes into the seal space 7 along the labyrinth packing 5, to the outside thereby to drop the pressure in the seal space 7.
  • the air temperature at the exit of the impeller 1 becomes the higher at the higher pressure ratio of the centrifugal compressor. Even in case the air at the room temperature is sucked, for example, its temperature reaches 200°C or more at exit of the impeller 1 if the pressure ratio is about 4.0.
  • This hot air is additionally heated, while passing through the labyrinth packing 5, by the heat of friction which is produced by the rotations of the fins of the labyrinth packing 5 so that the impeller 1 has its back heated.
  • the centrifugal compressor of this single stage type inhaling the atmospheric air usually has its impeller made of an aluminum alloy, and the impeller 1 has its strength degraded due to its temperature rise when heated by the air at its back. This make it difficult to retain the high pressure ratio if it is made of an aluminum alloy.
  • the temperature rise of the impeller 1 in turn leads to a rise in the air temperature, thus causing an efficiency drop of the compressor.
  • An object of the present invention is to provide a centrifugal compressor which can solve the above-specified difficulty.
  • a centrifugal compressor which comprises: an impeller; a seal member arranged annularly and multiplexly at the back of said impeller for sealing up a gap between the exit of said impeller and a space at the back of said impeller and for forming an annular space; and a passage for feeding a cold gas under a higher pressure than that at the exit of said impeller into said annular space.
  • the seal member is so arranged annularly and multiplexly at the back of the impeller that it seals up the gap between the exit of the impeller and a space at the back of the impeller and forms the annular space.
  • This annular space is fed through the passage with a cold gas under a higher pressure than that at the exit of the impeller. Since the cold gas fed through the passage has a higher pressure than that at the exit of the impeller, the hot gas at the impeller exit is prevented from flowing into the space at the impeller back, but a small amount of cold gas will flow out of the space toward the impeller exit. As a result, the back of the impeller is not heated by the gas at the impeller exit but cooled by the cold gas fed through the passage.
  • Fig. 1 shows the structure of a centrifugal compressor according to one embodiment of the present invention
  • Fig. 2 illustrates the operations of the centrifugal compressor.
  • the centrifugal compressor according to the present embodiment is used as a supercharger of an engine.
  • a labyrinth packing 15 for sealing up a seal space 7 between the exit and back of the impeller 1.
  • the seal space 7 is vented to the outside through a ventilation hole 8 for releasing a slight amount of air, which comes into the seal space 7 along the labyrinth packing 5, to the outside thereby to drop the pressure in the seal space 7.
  • the air temperature at the exit of the impeller 1 is the higher at the higher pressure ratio of the centrifugal compressor. Even in case the air at the room temperature is sucked, for example, its temperature reaches 200°C or more at exit of the impeller 1 if the pressure ratio is about 4.0.
  • the labyrinth packing 15 of the present centrifugal compressor has its fines classified into two outer and inner groups, which form an annular space 6 inbetween. This annular space 6 is fed, as better seen from Fig. 2, through an air passage 9 from the outside with the cold air which has a higher pressure P2 than a pressure P1 at the exit of the impeller 1.
  • the air having left the centrifugal compressor has a higher pressure than that P1 at the exit of the impeller 1, like the compressed cold air under a high pressure to be fed from the supercharger through a cooler to the engine, and the compressed air is cooled down by an air cooler before it is used.
  • this cooled air may be guided to the labyrinth packing 15 at the back of the impeller 1.
  • the labyrinth packing 15 of the present centrifugal compressor has two outer and inner groups of fins and its intervening annular space 6 fed with the air under the higher pressure P2 than the pressure P1 at the exit of the impeller 1.
  • the air thus fed has the higher pressure P2 so that the air at the exit of the impeller 1 will not flow along the labyrinth packing 15 into the annular space 6.
  • a small amount of air fed to the annular space 6 will flow toward the exit of the impeller 1.
  • the back of the impeller 1 is not exposed to and accordingly heated by the air, which might otherwise flow from the exit of the impeller 1, but is cooled by the cold air fed from the outside via the air passage 9.
  • the impeller 1 can have its temperature rise suppressed so that its strength can be prevented from being degraded by the temperature rise.
  • the seal space 7 at the back of the impeller 1 and the annular space 6 are sealed up by the labyrinth packing 15, the air flow, if any to the seal space 7, is released from the ventilation hole 8 to drop a pressure P3 in the seal space 7.
  • the load upon the main thrust bearing 3 is not increased by the balanced thrust unlike the centrifugal compressor of the prior art.
  • the impeller back is not heated by the gas at the impeller exit but is cooled down by the cold gas.
  • the high pressure ratio can be retained even if the impeller is made of an aluminum alloy, and the temperature of the gas to be compressed by the impeller can be dropped to raise the compression efficiency.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (3)

  1. Compresseur centrifuge qui comprend : un rotor (1); un élément d'étanchéité (15) placé de manière annulaire et complexe à l'arrière dudit rotor pour rendre étanche un interstice compris entre la sortie dudit rotor et un espace (7) se trouvant à l'arrière dudit rotor, caractérisé en ce que l'élément d'étanchéité (15) forme un espace annulaire (6) et en ce que le compresseur comprend en outre un passage (9) servant à amener dans ledit espace annulaire un gaz froid sous une pression plus élevée que celle régnant à la sortie dudit rotor.
  2. Compresseur à centrifugation selon la revendication 1, dans lequel ledit gaz froid sous une pression élevée est l'air à la sortie du dispositif de refroidissement d'air d'un moteur.
  3. Compresseur à centrifugation selon la revendication 1, dans lequel ledit élément d'étanchéité (15) est placé à la fois au niveau des circonférences intérieure et extérieure dudit espace annulaire (6).
EP92106288A 1991-06-14 1992-04-10 Compresseur centrifugal Expired - Lifetime EP0518027B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP3143231A JP2934530B2 (ja) 1991-06-14 1991-06-14 遠心圧縮機
JP143231/91 1991-06-14

Publications (2)

Publication Number Publication Date
EP0518027A1 EP0518027A1 (fr) 1992-12-16
EP0518027B1 true EP0518027B1 (fr) 1995-07-05

Family

ID=15333954

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92106288A Expired - Lifetime EP0518027B1 (fr) 1991-06-14 1992-04-10 Compresseur centrifugal

Country Status (5)

Country Link
EP (1) EP0518027B1 (fr)
JP (1) JP2934530B2 (fr)
KR (1) KR950006873B1 (fr)
DE (1) DE69203293T2 (fr)
FI (1) FI921758A (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0284104A2 (fr) 1987-03-27 1988-09-28 Japan Synthetic Rubber Co., Ltd. Structure appropriée pour éléments électrochimiques solides
US6190123B1 (en) 1998-05-25 2001-02-20 Asea Brown Boverti Ag Centrifugal compressor
WO2001029425A1 (fr) 1999-10-20 2001-04-26 Abb Turbo Systems Ag Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines
WO2001029426A1 (fr) 1999-10-20 2001-04-26 Abb Turbo Systems Ag Procede et dispositif de refroidissement indirect de l'ecoulement dans des entrefers radiaux formes entre les rotors et les stators de turbomachines
US6238179B1 (en) 1998-05-25 2001-05-29 Asea Brown Boveri Ag Centrifugal compressor
US6416281B1 (en) 1998-10-02 2002-07-09 Asea Brown Boveri Ag Method and arrangement for cooling the flow in radial gaps formed between rotors and stators of turbomachines
CN101297118B (zh) * 2005-09-19 2011-09-28 英格索尔-兰德公司 用于离心压缩机的静止密封环
WO2012092501A1 (fr) * 2010-12-30 2012-07-05 Rolls-Royce Corporation Turbine à gaz dotée d'un circuit de circulation d'air secondaire
DE102010037356B4 (de) * 2010-09-06 2013-09-05 Kompressorenbau Bannewitz Gmbh Verdichterradkühlung

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0924386B1 (fr) * 1997-12-23 2003-02-05 ABB Turbo Systems AG Méthode et dispositif d'étanchéité pour isoler l'espace entre un rotor et un stator
KR100414103B1 (ko) * 2001-08-17 2004-01-07 엘지전자 주식회사 터보 압축기의 디퓨져 장착구조
US7252474B2 (en) * 2003-09-12 2007-08-07 Mes International, Inc. Sealing arrangement in a compressor
CN101287911A (zh) * 2005-09-19 2008-10-15 英格索尔-兰德公司 包括密封系统的离心压缩机
CN101268284A (zh) * 2005-09-19 2008-09-17 英格索尔-兰德公司 离心压缩机的叶轮
US7402020B2 (en) * 2005-12-14 2008-07-22 Hamilton Sundstrand Corporation ACM cooling flow path and thrust load design
JP5135981B2 (ja) * 2007-10-05 2013-02-06 株式会社Ｉｈｉ 遠心圧縮機
JP2010168968A (ja) * 2009-01-21 2010-08-05 Toyota Motor Corp ターボチャージャ
JP5700999B2 (ja) * 2010-10-06 2015-04-15 三菱重工業株式会社 遠心圧縮機
JP2014111905A (ja) 2012-12-05 2014-06-19 Mitsubishi Heavy Ind Ltd 遠心圧縮機およびこれを備えた過給機ならびに遠心圧縮機の運転方法
WO2014128877A1 (fr) * 2013-02-21 2014-08-28 トヨタ自動車株式会社 Dispositif de refroidissement d'appareil de suralimentation de moteur à combustion interne comprenant un dispositif de circulation de gaz perdu
WO2014163702A2 (fr) * 2013-03-08 2014-10-09 Lunsford Patrick L Roue à ailettes multi-pièce
ITFI20130237A1 (it) * 2013-10-14 2015-04-15 Nuovo Pignone Srl "sealing clearance control in turbomachines"
US11377954B2 (en) * 2013-12-16 2022-07-05 Garrett Transportation I Inc. Compressor or turbine with back-disk seal and vent
JP6225092B2 (ja) * 2014-10-17 2017-11-01 三菱重工業株式会社 ラビリンスシール、遠心圧縮機及び過給機
CN105240280A (zh) * 2015-10-30 2016-01-13 江苏大学 一种具有矩形齿泵前腔结构的离心泵
DE102016102923A1 (de) 2016-02-19 2017-08-24 Abb Turbo Systems Ag Verdichterradrückseitige Radialturbine
US11002291B2 (en) 2016-03-30 2021-05-11 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Compressor impeller
JP2018105268A (ja) * 2016-12-28 2018-07-05 日本電産株式会社 送風装置及びそれを備えた掃除機
JP7074442B2 (ja) * 2017-09-15 2022-05-24 三菱重工コンプレッサ株式会社 圧縮機
WO2021105047A1 (fr) * 2019-11-25 2021-06-03 Robert Bosch Gmbh Turbomachine
CN112628162A (zh) * 2020-12-23 2021-04-09 苏州苏磁智能科技有限公司 一种防离心压缩机高温高压气体回流的流道结构及方法，及离心压缩机
CN113513499B (zh) * 2021-07-02 2022-04-26 鑫磊压缩机股份有限公司 一种装配精度自矫正式压缩机
CN115450950B (zh) * 2022-11-08 2023-03-03 中国核动力研究设计院 压气机和超临界二氧化碳发电系统

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE249336C (fr) * 1900-01-01
FR379125A (fr) * 1907-06-21 1907-10-25 Wilhelm Heinrich Eyermann équilibrage de la pression axiale dans les turbines, pompes rotatives et compresseurs
US3650634A (en) * 1970-11-06 1972-03-21 Carrier Corp Centrifugal refrigeration compressor

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0284104A2 (fr) 1987-03-27 1988-09-28 Japan Synthetic Rubber Co., Ltd. Structure appropriée pour éléments électrochimiques solides
US6190123B1 (en) 1998-05-25 2001-02-20 Asea Brown Boverti Ag Centrifugal compressor
US6238179B1 (en) 1998-05-25 2001-05-29 Asea Brown Boveri Ag Centrifugal compressor
US6416281B1 (en) 1998-10-02 2002-07-09 Asea Brown Boveri Ag Method and arrangement for cooling the flow in radial gaps formed between rotors and stators of turbomachines
WO2001029425A1 (fr) 1999-10-20 2001-04-26 Abb Turbo Systems Ag Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines
WO2001029426A1 (fr) 1999-10-20 2001-04-26 Abb Turbo Systems Ag Procede et dispositif de refroidissement indirect de l'ecoulement dans des entrefers radiaux formes entre les rotors et les stators de turbomachines
CN101297118B (zh) * 2005-09-19 2011-09-28 英格索尔-兰德公司 用于离心压缩机的静止密封环
DE102010037356B4 (de) * 2010-09-06 2013-09-05 Kompressorenbau Bannewitz Gmbh Verdichterradkühlung
WO2012092501A1 (fr) * 2010-12-30 2012-07-05 Rolls-Royce Corporation Turbine à gaz dotée d'un circuit de circulation d'air secondaire
GB2501409A (en) * 2010-12-30 2013-10-23 Rolls Royce Corp Gas turbine engine with secondary air flow circuit
US9228497B2 (en) 2010-12-30 2016-01-05 Rolls-Royce Corporation Gas turbine engine with secondary air flow circuit

Also Published As

Publication number Publication date
DE69203293D1 (de) 1995-08-10
JPH04365997A (ja) 1992-12-17
FI921758A0 (fi) 1992-04-21
FI921758A (fi) 1992-12-15
EP0518027A1 (fr) 1992-12-16
KR950006873B1 (ko) 1995-06-23
KR930000807A (ko) 1993-01-15
DE69203293T2 (de) 1996-01-25
JP2934530B2 (ja) 1999-08-16

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