EP0961033A1 - Compresseur radial - Google Patents

Compresseur radial Download PDF

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Publication number
EP0961033A1
EP0961033A1 EP98810486A EP98810486A EP0961033A1 EP 0961033 A1 EP0961033 A1 EP 0961033A1 EP 98810486 A EP98810486 A EP 98810486A EP 98810486 A EP98810486 A EP 98810486A EP 0961033 A1 EP0961033 A1 EP 0961033A1
Authority
EP
European Patent Office
Prior art keywords
compressor
compressor wheel
rear wall
radial
gap
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
EP98810486A
Other languages
German (de)
English (en)
Other versions
EP0961033B1 (fr
Inventor
Dirk Dr. Wunderwald
Martin Dr. Thiele
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems AG
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 Turbo Systems AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Turbo Systems AG
Priority to EP98810486A priority Critical patent/EP0961033B1/fr
Priority to DE59809867T priority patent/DE59809867D1/de
Priority to TW088107620A priority patent/TW517138B/zh
Priority to CZ19991779A priority patent/CZ290965B6/cs
Priority to KR1019990018501A priority patent/KR100551523B1/ko
Priority to US09/316,066 priority patent/US6190123B1/en
Priority to JP11145285A priority patent/JP2000054996A/ja
Priority to CN99107040A priority patent/CN1118637C/zh
Priority to CN99212100U priority patent/CN2378560Y/zh
Publication of EP0961033A1 publication Critical patent/EP0961033A1/fr
Application granted granted Critical
Publication of EP0961033B1 publication Critical patent/EP0961033B1/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
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C18/00—Rotary-piston pumps specially adapted for elastic fluids
    • F04C18/02—Rotary-piston pumps specially adapted for elastic fluids of arcuate-engagement type, i.e. with circular translatory movement of co-operating members, each member having the same number of teeth or tooth-equivalents
    • 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
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M39/00—Arrangements of fuel-injection apparatus with respect to engines; Pump drives adapted to such arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M55/00—Fuel-injection apparatus characterised by their fuel conduits or their venting means; Arrangements of conduits between fuel tank and pump F02M37/00
    • F02M55/02—Conduits between injection pumps and injectors, e.g. conduits between pump and common-rail or conduits between common-rail and injectors
    • F02M55/025—Common rails
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to a method for operating a radial compressor, according to the preamble of claim 1 and a corresponding radial compressor, according to the preamble of claim 6.
  • turbomachinery Seals For the sealing of rotating systems, there are no-contact in turbomachinery Seals, especially labyrinth seals, are widely used.
  • fluid flow Separation gap between rotating and standing parts occurs as a result of forming flow boundary layers a high friction. Thereby there is a heating of the fluid in the separation gap and thus also a heating the components surrounding the separation gap.
  • the high material temperatures have a reduction in the lifespan of the corresponding components Episode.
  • Exhaust gas turbochargers have an axial stroke of the exhaust gas turbine, depending on their design which counteracts that of the radial compressor or rectified like this one. In the latter case, the resulting pressure in the separation gap must be between the rotating rear wall of the compressor wheel and the neighboring one, stationary compressor housing can be dismantled. That is why there are such gaps tolerated very closely. In addition, they usually have a non-contact Poetry. In such narrow separating gaps there is a particularly high level of friction to be recorded. In addition, the redirection and swirling of the working fluid flowing through the separation gap at the throttle points of the seal to a constantly new mixing of the working fluid with a high momentum and heat exchange. Must be downstream of the throttle the working fluid on the rotating component is again accelerated in the circumferential direction be, whereby the friction and thus the heat development in this area continues to rise.
  • the invention tries to avoid all these disadvantages. It is based on the task a method for operating a simply constructed, in the field of Rear wall of the compressor wheel without sealing elements in the separating gap of the compressor wheel as well as to create a compressor with a radial compressor, which increases the service life of the radial compressor.
  • a device be provided to carry out the method.
  • this is achieved in that in a method according to the preamble of claim 1, downstream of the leakage flow of the working medium a cooling medium is introduced into the separation gap and the cooling medium after heat exchange is finally discharged again.
  • a cooling medium is introduced into the separation gap and the cooling medium after heat exchange is finally discharged again.
  • the cooling medium can be advantageous both with a higher than also with a lower pressure than the pressure of the main flow of the working medium be introduced into the separation gap.
  • a sealing element is arranged in the separating gap.
  • the supply channel of the cooling medium is approximately parallel or approximately diagonal to the shaft of the compressor wheel or approximately tangential to the rear wall of the compressor wheel arranged in the separating gap.
  • the cooling medium is supplied with a Impact cooling implemented. This can be particularly vulnerable areas of the rear wall of the compressor wheel can be cooled directly and effectively.
  • a radial Feeding the cooling medium realizes film cooling, with the help of which larger areas of the rear wall of the compressor wheel can also be cooled.
  • the diagonal feed of the cooling medium combines the advantages of the previous ones described solutions with a lower cooling effectiveness.
  • At least one of the feed channels takes up into the separation gap protruding and aligned to the rear wall of the compressor wheel Tubes open It is particularly advantageous for each of the tubes to open in the region of the radially outer wall part of the rear wall of the compressor wheel into the separating gap. Because the greatest temperature load can be recorded in this area thus an effective use of the cooling medium can be achieved.
  • a plurality of feed channels are arranged in the compressor housing are opposite the rear wall of the compressor wheel to the separation gap open annular space or at least a partial annular space formed in the compressor housing is and the feed channels with the annular space or at least two of each Feed channels are connected to a partial annulus. This allows a more even Supply of the cooling medium is reached over the circumference of the compressor wheel regardless of the number, design and arrangement of the feed channels.
  • the exhaust gas turbocharger shown only partially in Figure 1 consists of a radial compressor 1 and an exhaust gas turbine, not shown, which in a Bearing housing 2 supported shaft 3 are interconnected.
  • the radial compressor 1 has a machine axis 4 lying in the shaft 3 equipped with a compressor housing 5 in which a compressor wheel 6 rotates with the shaft 3 is connected.
  • the compressor wheel 6 has one with a variety of Blades 7 occupied hub 8. Between the hub 8 and the compressor housing 5, a flow channel 9 is formed. Downstream of the blades 7 connects to the flow channel 9 a radially arranged, bladed diffuser 10 on, which in turn opens into a spiral 11 of the radial compressor 1.
  • the Compressor housing 5 mainly consists of an air inlet housing 12, one Air outlet housing 13, a diffuser plate 14 and an intermediate wall 15 to the bearing housing 2.
  • the hub 8 has a rear wall 16 on the turbine side and a fastening sleeve 17 for the shaft 3, the latter and the fastening sleeve 17 together are connected.
  • the fastening sleeve 17 is of the intermediate wall 15 of the Compressor housing 5 added.
  • another suitable one Compressor wheel-shaft connection can be selected.
  • the use is also the same of a non-bladed diffuser possible.
  • a first gap area 19 runs parallel to the machine axis 4 and is with both the outlet of the compressor wheel 6 and one predominantly radial in the area of the rear wall 16 of the compressor wheel 6 extending, second gap region 20 connected.
  • the second gap area 20 goes into a formed between the fastening sleeve 17 and the intermediate wall 15 and also third, parallel to the machine axis 4 Gap area 21 over. The latter in turn communicates with one that is not shown Discharge line.
  • the rear wall 16 of the compressor wheel 6 has a radially inner one Wall part 22 and a radially outer wall part 23.
  • the second gap area 20 of the separation gap 18 opens parallel to the shaft 3 of the compressor wheel 6 a plurality of the intermediate wall 15 of the compressor housing 5 penetrating supply channels 24 for a gaseous cooling medium 25.
  • the mouths lie in the region of the radially outer wall part 23 of the rear wall 16 of the compressor wheel 6, while also the intermediate wall 15 of the compressor housing 5 penetrating discharge channel 26 for the cooling medium 25 in the area of the radially inner wall part 22 is arranged.
  • the compressor wheel 6 When the exhaust gas turbocharger is operating, the compressor wheel 6 sucks as the working medium 27 ambient air, which acts as a main flow 28 via the flow channel 9 and the diffuser 10 arrives in the spiral 11, further compressed there and finally for charging a not shown, connected to the exhaust gas turbocharger Internal combustion engine is used. On their way from the flow channel 9 to the diffuser 10 acts on the main flow heated in the radial compressor 1 28 of the working medium 27 as the leakage flow 29 also the first gap area 19 and thus the separation gap 18. At the same time, however, via the feed channels 24 the gaseous cooling medium 25 with a higher pressure than that Pressure of the main flow 28 of the working medium 27 in the second gap area 20 of the separation gap 18 introduced. For example, air from not shown outlet of the charge air cooler of the internal combustion engine used become. Of course, the use of other cooling media is also one external supply of these cooling media possible.
  • the cooling medium 25 hits the rear wall 16 of the compressor wheel 6 and causes it in its particularly stressed, radially outer wall part 23 an impingement cooling.
  • the cooling medium 25 is then distributed in the separation gap 18 and diluted the hot leakage flow 29.
  • Most of the cooling medium 25 and Leakage flow 29 is then via the discharge channel 26 from the Separation gap 18 passed.
  • the supply channels 24 for the cooling medium open out 25 also parallel to the shaft 3 of the compressor wheel 6 in the radial outer wall part 23 of the rear wall 16 of the compressor wheel 6 in the separation gap 18.
  • the feed channels 24 and the separation gap 18 there is a between the feed channels 24 and the separation gap 18 the feed channels 24 interconnecting and open to the separation gap 18 Annulus 30 formed (Fig. 2).
  • This can result in a relatively uniform application the rear wall 16 can be reached with the cooling medium 25.
  • the annular space 30 also several partial annular spaces in the intermediate wall 15 of the compressor housing 5, which are each at least Connect two adjacent feed channels 24 to one another (not shown).
  • Discharge channel 26 is arranged in the diffuser plate 14 of the compressor housing 5, so that the cooling medium 25 almost completely via the flow channel 9 of the Radial compressor 1 is discharged. In operation, the leakage flow is 29 the cooling medium 25 is almost completely shut off. Because of the repatriation of the cooling medium 25 in the flow channel 9 also the volumetric efficiency improved.
  • the feed channels 24 open diagonally to the shaft 3 of the compressor wheel 6 in the separating gap 18.
  • the feed channels take 24 each projecting into the separating gap 18 and onto the radial one outer wall part 23 of the rear wall 16 of the compressor wheel 6 aligned Tube 31 on (Fig. 3).
  • the cooling medium 25 hits targeted to the areas of the rear wall 16 which have the greatest temperature load exhibit.
  • the cooling medium 25 acts initially as impingement cooling. It can also move towards the first Apply a cooling film to the rear wall 16 of the gap area 19.
  • the derivation of the Cooling medium 25 in turn takes place via the discharge channel 26.
  • analog the second embodiment also a feedback of the cooling medium 25 in the flow channel 9 of the radial compressor 1 (not shown).
  • the feed channels 24 are the diffuser plate 14 arranged penetrating and open into the compressor wheel 6th facing region tangential to the rear wall 16 of the compressor wheel 6 in the Separation gap 18 a (Fig. 4).
  • the discharge channel 26 for the cooling medium 25 is in the Intermediate wall 15 of the compressor housing 5 is arranged.
  • the cooling medium 25 is discharged only through the discharge channel 26.
  • the diffuser plate 14 can its radially inner end can also be slotted. In this case, flow out the feed channels 24 into the slot of the diffuser plate 14, not shown.
  • the rear wall 16 of the compressor wheel is upstream 6 a sealing element 32 in the separation gap 18, i.e. in its first gap area 19, arranged (Fig. 5).

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)
EP98810486A 1998-05-25 1998-05-25 Compresseur radial Expired - Lifetime EP0961033B1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP98810486A EP0961033B1 (fr) 1998-05-25 1998-05-25 Compresseur radial
DE59809867T DE59809867D1 (de) 1998-05-25 1998-05-25 Radialverdichter
TW088107620A TW517138B (en) 1998-05-25 1999-05-11 Centrifugal compressor and method of operating the centrifugal compressor
CZ19991779A CZ290965B6 (cs) 1998-05-25 1999-05-19 Způsob provozu radiálního kompresoru a radiální kompresor k jeho provádění
KR1019990018501A KR100551523B1 (ko) 1998-05-25 1999-05-21 원심 압축기
US09/316,066 US6190123B1 (en) 1998-05-25 1999-05-21 Centrifugal compressor
JP11145285A JP2000054996A (ja) 1998-05-25 1999-05-25 ラジアル圧縮機とその運転法
CN99107040A CN1118637C (zh) 1998-05-25 1999-05-25 离心压缩机
CN99212100U CN2378560Y (zh) 1998-05-25 1999-05-25 离心压缩机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98810486A EP0961033B1 (fr) 1998-05-25 1998-05-25 Compresseur radial

Publications (2)

Publication Number Publication Date
EP0961033A1 true EP0961033A1 (fr) 1999-12-01
EP0961033B1 EP0961033B1 (fr) 2003-10-08

Family

ID=8236107

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810486A Expired - Lifetime EP0961033B1 (fr) 1998-05-25 1998-05-25 Compresseur radial

Country Status (8)

Country Link
US (1) US6190123B1 (fr)
EP (1) EP0961033B1 (fr)
JP (1) JP2000054996A (fr)
KR (1) KR100551523B1 (fr)
CN (2) CN1118637C (fr)
CZ (1) CZ290965B6 (fr)
DE (1) DE59809867D1 (fr)
TW (1) TW517138B (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2904036A1 (fr) * 2006-07-19 2008-01-25 Snecma Sa Systeme de ventilation d'une cavite aval de rouet de compresseur centrifuge
FR2904035A1 (fr) * 2006-07-19 2008-01-25 Snecma Sa Systeme de refroidissement du rouet d'un compresseur centrifuge.
EP1882815A1 (fr) * 2006-07-19 2008-01-30 Snecma Turbomachine comprenant un système de refroidissement de la face aval d'un rouet de compresseur centrifuge
FR3025260A1 (fr) * 2014-08-29 2016-03-04 Snecma Compresseur centrifuge a resistance amelioree
EP2993356A1 (fr) * 2014-09-02 2016-03-09 MAN Diesel & Turbo SE Étage de compresseur radial

Families Citing this family (33)

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DE10321572A1 (de) * 2003-05-14 2004-12-02 Daimlerchrysler Ag Ladeluftverdichter für eine Brennkraftmaschine, Brennkraftmaschine und Verfahren hierzu
US7252474B2 (en) * 2003-09-12 2007-08-07 Mes International, Inc. Sealing arrangement in a compressor
JP4043433B2 (ja) * 2003-11-14 2008-02-06 株式会社神戸製鋼所 空気圧縮機
EP2067999A1 (fr) 2007-12-06 2009-06-10 Napier Turbochargers Limited Rotor de turbocompresseur de suralimentation refroidi par liquide et procédé de refroidissement d'un rotor
EP2090788A1 (fr) 2008-02-14 2009-08-19 Napier Turbochargers Limited Rotor et turbocompresseur
CN102016326B (zh) 2008-03-13 2013-09-11 Aaf-麦克维尔公司 大容量制冷机压缩机
US8079805B2 (en) * 2008-06-25 2011-12-20 Dresser-Rand Company Rotary separator and shaft coupler for compressors
US8087249B2 (en) * 2008-12-23 2012-01-03 General Electric Company Turbine cooling air from a centrifugal compressor
US8147178B2 (en) * 2008-12-23 2012-04-03 General Electric Company Centrifugal compressor forward thrust and turbine cooling apparatus
AT508048B1 (de) * 2009-03-23 2010-12-15 Ge Jenbacher Gmbh & Co Ohg Brennkraftmaschine mit verdichtungseinrichtung
DE102010037356B8 (de) * 2010-09-06 2014-05-22 Kompressorenbau Bannewitz Gmbh Verdichterradkühlung
JP5700999B2 (ja) * 2010-10-06 2015-04-15 三菱重工業株式会社 遠心圧縮機
US9228497B2 (en) * 2010-12-30 2016-01-05 Rolls-Royce Corporation Gas turbine engine with secondary air flow circuit
ITFI20120124A1 (it) 2012-06-19 2013-12-20 Nuovo Pignone Srl "centrifugal compressor impeller cooling"
US8925317B2 (en) 2012-07-16 2015-01-06 General Electric Company Engine with improved EGR system
US9291089B2 (en) * 2012-08-31 2016-03-22 Caterpillar Inc. Turbocharger having compressor cooling arrangement and method
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
KR101765583B1 (ko) * 2014-07-29 2017-08-07 현대자동차 주식회사 공기 압축기의 냉각유닛
DE102014012765A1 (de) * 2014-09-02 2016-03-03 Man Diesel & Turbo Se Radialverdichterstufe
US10066639B2 (en) 2015-03-09 2018-09-04 Caterpillar Inc. Compressor assembly having a vaneless space
US10006341B2 (en) 2015-03-09 2018-06-26 Caterpillar Inc. Compressor assembly having a diffuser ring with tabs
DE102016200519A1 (de) * 2016-01-18 2017-07-20 Siemens Aktiengesellschaft Strömungsmaschine
US10830144B2 (en) * 2016-09-08 2020-11-10 Rolls-Royce North American Technologies Inc. Gas turbine engine compressor impeller cooling air sinks
DK201770269A1 (en) * 2017-04-18 2018-12-06 Spx Flow Technology Danmark A/S A PUMP FOR PUMPING HEAT-SENSITIVE FLUIDS
CN107448417B (zh) * 2017-09-01 2020-01-17 西北工业大学 离心压气机及叶轮冷却装置
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
CN115559913A (zh) 2018-01-19 2023-01-03 概创机械设计有限责任公司 具有分离的收集器的涡轮机
DE102018108828A1 (de) * 2018-04-13 2019-10-17 Trumpf Schweiz Ag Radialgebläse
CN108625917B (zh) * 2018-06-28 2024-05-24 西安交通大学 一种超临界二氧化碳布雷顿循环动力部件冷却密封隔热系统
CN108952951B (zh) * 2018-07-27 2020-07-17 中车大连机车研究所有限公司 一种涡轮增压器压力气体平衡系统结构
US11525393B2 (en) 2020-03-19 2022-12-13 Rolls-Royce Corporation Turbine engine with centrifugal compressor having impeller backplate offtake
US11773773B1 (en) 2022-07-26 2023-10-03 Rolls-Royce North American Technologies Inc. Gas turbine engine centrifugal compressor with impeller load and cooling control

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DE403277C (de) * 1924-09-30 Bbc Brown Boveri & Cie Vorrichtung zur Kuehlung von Kreiselverdichtern
US2260042A (en) * 1940-01-18 1941-10-21 Gen Electric Ventilating system
EP0076668A2 (fr) * 1981-10-06 1983-04-13 A/S Kongsberg Väpenfabrikk Turbomachines pourvues d'un dispositif de prélèvement
EP0518027A1 (fr) 1991-06-14 1992-12-16 Mitsubishi Jukogyo Kabushiki Kaisha Compresseur centrifugal
GB2277129A (en) * 1993-04-13 1994-10-19 Daimler Benz Ag Exhaust gas turbocharger
DE19548852A1 (de) 1995-12-27 1997-07-03 Asea Brown Boveri Radialverdichter für Abgasturbolader

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Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE403277C (de) * 1924-09-30 Bbc Brown Boveri & Cie Vorrichtung zur Kuehlung von Kreiselverdichtern
US2260042A (en) * 1940-01-18 1941-10-21 Gen Electric Ventilating system
EP0076668A2 (fr) * 1981-10-06 1983-04-13 A/S Kongsberg Väpenfabrikk Turbomachines pourvues d'un dispositif de prélèvement
EP0518027A1 (fr) 1991-06-14 1992-12-16 Mitsubishi Jukogyo Kabushiki Kaisha Compresseur centrifugal
GB2277129A (en) * 1993-04-13 1994-10-19 Daimler Benz Ag Exhaust gas turbocharger
DE19548852A1 (de) 1995-12-27 1997-07-03 Asea Brown Boveri Radialverdichter für Abgasturbolader

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2904036A1 (fr) * 2006-07-19 2008-01-25 Snecma Sa Systeme de ventilation d'une cavite aval de rouet de compresseur centrifuge
FR2904035A1 (fr) * 2006-07-19 2008-01-25 Snecma Sa Systeme de refroidissement du rouet d'un compresseur centrifuge.
EP1882825A1 (fr) * 2006-07-19 2008-01-30 Snecma Système de refroidissement du rouet d'un compresseur centrifuge
EP1882815A1 (fr) * 2006-07-19 2008-01-30 Snecma Turbomachine comprenant un système de refroidissement de la face aval d'un rouet de compresseur centrifuge
EP1882826A1 (fr) * 2006-07-19 2008-01-30 Snecma Système de ventilation d'une cavité aval de rouet de compresseur centrifuge
US7937951B2 (en) 2006-07-19 2011-05-10 Snecma System for cooling the impeller of a centrifugal compressor
US7942630B2 (en) 2006-07-19 2011-05-17 Snecma System for ventilating a downstream cavity of an impellor of a centrifugal compressor
FR3025260A1 (fr) * 2014-08-29 2016-03-04 Snecma Compresseur centrifuge a resistance amelioree
EP2993356A1 (fr) * 2014-09-02 2016-03-09 MAN Diesel & Turbo SE Étage de compresseur radial

Also Published As

Publication number Publication date
KR100551523B1 (ko) 2006-02-13
TW517138B (en) 2003-01-11
CN1118637C (zh) 2003-08-20
CN2378560Y (zh) 2000-05-17
JP2000054996A (ja) 2000-02-22
DE59809867D1 (de) 2003-11-13
CZ9901779A3 (cs) 2000-11-15
EP0961033B1 (fr) 2003-10-08
KR19990088488A (ko) 1999-12-27
CZ290965B6 (cs) 2002-11-13
US6190123B1 (en) 2001-02-20
CN1239192A (zh) 1999-12-22

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