WO2001029425A1 - Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines - Google Patents

Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines Download PDF

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Publication number
WO2001029425A1
WO2001029425A1 PCT/CH1999/000496 CH9900496W WO0129425A1 WO 2001029425 A1 WO2001029425 A1 WO 2001029425A1 CH 9900496 W CH9900496 W CH 9900496W WO 0129425 A1 WO0129425 A1 WO 0129425A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling fluid
cooling
stator part
radial gap
radial
Prior art date
Application number
PCT/CH1999/000496
Other languages
German (de)
English (en)
Inventor
Dirk Wunderwald
Mihajlo-Rüdiger BOTHIEN
Ulf Christian MÜLLER
Joachim Bremer
Jürg Greber
Helmut Gieszauf
Original Assignee
Abb Turbo Systems 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 Turbo Systems Ag filed Critical Abb Turbo Systems Ag
Priority to CNB998169617A priority Critical patent/CN1258648C/zh
Priority to DE59906615T priority patent/DE59906615D1/de
Priority to JP2001531986A priority patent/JP2003515690A/ja
Priority to PCT/CH1999/000496 priority patent/WO2001029425A1/fr
Priority to EP99947180A priority patent/EP1222399B1/fr
Priority to AU60757/99A priority patent/AU6075799A/en
Priority to KR1020027003417A priority patent/KR100637643B1/ko
Publication of WO2001029425A1 publication Critical patent/WO2001029425A1/fr

Links

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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • 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
    • 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

Definitions

  • the invention relates to a method and a device for cooling the flow in radial gaps formed between rotors and stators of turbomachinery, according to the preamble of claim 1 and the preamble of claim 7, but in particular for cooling the flow in the radial gap between the compressor wheel and the housing of a radial compressor.
  • non-contact seals especially labyrinth seals
  • turbomachinery construction To seal rotating systems, non-contact seals, especially labyrinth seals, are widely used in turbomachinery construction.
  • a high level of friction occurs as a result of the flow boundary layers that form. This leads to heating of the fluid in the separation gap and thus also to heating of the components surrounding the separation gap.
  • the high material temperatures reduce the lifespan of the corresponding components.
  • Air cooling for radial compressors with a sealing geometry on the rear side of the compressor wheel is known from EP 0 518 027 B1. This is between the individual sealing elements, an additional annular space is formed on the housing wall side of the radial compressor. A cold gas is introduced into this annular space, which has a higher pressure than the pressure prevailing at the outlet of the compressor wheel. The air supplied acts as impingement cooling. It divides in the sealing area and flows mainly radially inwards and outwards. This is also intended to achieve a blocking effect against the flow of hot compressor air from the outlet of the compressor wheel.
  • the cooling effect that can be achieved in this way is limited due to several factors.
  • the air injection leads to an increase in pressure and thrust, which increases the bearing load.
  • the temperature of the available air is also a limiting element. Particularly in the case of high-speed compressor wheels and high pressure ratios, as are common in modern turbocharger construction, situations can arise in which this type of cooling is not sufficient.
  • indirect cooling of the rear wall of the compressor wheel or of the medium flowing through the separation gap is also known from DE 196 52 754 A1.
  • a supply and distribution device connected to the lubricating oil system of the turbocharger is arranged on or in the rear part of the housing part which forms the separating gap.
  • the oil used for bearing lubrication serves as the cooling medium, for which purpose the lubricating oil circuit of the turbocharger is tapped.
  • a disadvantage of this cooling is the relatively high oil requirement and the additional amount of heat to be dissipated by the oil cooler. This leads to an increased construction volume of the cooler.
  • the cooling effect that can be achieved with indirect cooling is also limited, for which, in addition to the temperature of the cooling fluids that can be used in practice, the small construction volume available can be identified as the cause. Presentation of the invention
  • the invention tries to avoid all these disadvantages. It is the object of the invention to provide a method for cooling the flow in radial gaps formed between rotors and stators of turbomachines which is improved with regard to its cooling effect. In addition, a simple, inexpensive and robust device for implementing the method is to be specified.
  • both a stator part adjacent to the radial gap is acted on by a first cooling fluid and a second, gaseous cooling fluid is introduced into the radial gap.
  • At least one recess is formed in the interior of the stator part adjacent to the radial gap or at least one cavity is arranged on the stator part.
  • the recess or the cavity is connected both to a supply line and to a discharge line for the first cooling fluid.
  • at least one feed channel and a discharge device for the second cooling fluid are arranged on the radial gap.
  • Water is particularly advantageously used as the first cooling fluid and air as the second cooling fluid.
  • Water has a slightly higher density than the known lubricating oils and an approximately twice as large specific heat capacity. Since it has a cooling medium to be dissipated heat flow is proportional to the product of density and specific heat capacity, there is a clear advantage when using water as the first cooling fluid compared to oil cooling. With the same mass flow and temperature of the water, a larger amount of heat can thus be extracted from the medium flowing through the radial gap via the stator part to be cooled. The cooling effect on the areas of the rotor adjacent to the radial gap is therefore also greater. Conversely, a smaller mass flow of cooling water is required to dissipate the same amount of heat compared to lubricating oil, as a result of which the supply and discharge device for the cooling fluid can be dimensioned correspondingly smaller.
  • air as the second cooling fluid proves to be particularly advantageous because it is available in sufficient quantities, with sufficient pressure and at a suitably low temperature both in the environment and in the turbomachine itself.
  • the first cooling fluid In a system consisting of an internal combustion engine, a charge air cooler and an exhaust gas turbocharger, either fresh water from outside the system or advantageously water present in the system is used as the first cooling fluid.
  • the cooling water located in a cooling water circuit of the charge air cooler is used, which is branched off upstream of the charge air cooler.
  • the fixed stator part is a housing part ei ⁇ nes radial compressor, which delimits the radial gap to the rotor, that is, to the rotating compressor wheel of a turbocharger.
  • oil is used as the first cooling fluid, it can advantageously be branched off from the lubricating oil system, which is already present in the bearing housing of the turbomachine. In this way, a relatively simple and therefore inexpensive device can be created.
  • the first cooling fluid is a gaseous medium, it can be used for both direct and indirect cooling.
  • first and / or second cooling fluid When using helium or gases from low-temperature fluids, such as liquid nitrogen, carbon tetrachloride and benzin nitride, as the first and / or second cooling fluid, a particularly good cooling effect can be achieved.
  • low-temperature fluids such as liquid nitrogen, carbon tetrachloride and benzin nitride
  • Figure 1 is a schematic representation of the exhaust gas turbocharger connected to the internal combustion engine.
  • FIG. 1 shows a schematic representation of an exhaust gas turbocharger 2 that interacts with an internal combustion engine 1 designed as a diesel engine.
  • the latter consists of a radial compressor 3 and an exhaust gas turbine 4, which have a common shaft 5.
  • the radial compressor 3 is connected to the combustion air via a charge air line 6 and the exhaust gas turbine 4 via an exhaust line 7 engine 1 connected.
  • a charge air cooler 8 is arranged in the charge air line 6, ie between the radial compressor 3 and the internal combustion engine 1.
  • the charge air cooler 8 has a cooling water circuit 9 with a supply or discharge, not shown.
  • the radial compressor 3 is equipped with a compressor housing 10, in which a rotor 11 designed as a compressor wheel and connected to the shaft 5 is arranged.
  • the compressor wheel 11 has a hub 13 with a plurality of rotor blades 12.
  • a flow channel 14 is formed between the hub 13 and the compressor housing 10. Downstream of the blades 12, a radially arranged, bladed diffuser 15 adjoins the flow channel 14, which in turn opens into a spiral 16 of the radial compressor 3.
  • the compressor housing 10 mainly consists of an air inlet housing 17, an air outlet housing 18, a diffuser plate 19 and a stator part 20 designed as an intermediate wall to a bearing housing 21 of the exhaust gas turbocharger 2 (FIG. 2).
  • the hub 13 has a rear wall 22 on the turbine side and a fastening sleeve 23 for the shaft 5.
  • the fastening sleeve 23 is received by the intermediate wall 20 of the compressor housing 10.
  • another suitable compressor wheel / shaft connection can also be selected. It is also possible to use an unbladed diffuser.
  • a circumferential recess 26 is formed in the intermediate wall 20 of the compressor housing 10 and is connected to both a supply line and a discharge line 27, 28 for a first cooling fluid 29.
  • the intermediate wall 20 on the compressor wheel side of the recess 26 is made as thin as possible.
  • a corresponding core is cast in during the manufacture of the intermediate wall 20, which must then be removed again.
  • a thin-walled tube that is closed at both ends can also be cast into the intermediate wall 20, the interior of which then forms the recess 26 (not shown).
  • the compressor wheel 11 When the exhaust gas turbocharger 2 is operating, the compressor wheel 11 sucks in ambient air as the working medium 31, which, as a main flow 32, enters the spiral 16 via the flow channel 14 and the diffuser 15, compresses there further and finally via the charge air line 6 for charging the exhaust gas turbocharger 2 connected internal combustion engine 1 is used.
  • the working medium 31 heated during the compression process is cooled beforehand in the charge air cooler 8.
  • the main flow 32 of the working medium 31 heated in the radial compressor 3 also acts on the radial gap 24 as a leakage flow 33, as a result of which the compressor wheel 11 is additionally heated.
  • Cooling water which is branched off from the cooling water circuit 9 of the charge air cooler 8 is introduced as cooling fluid 29 into the recess 26 of the intermediate wall 20 which is arranged directly adjacent to this critical area. There is thus indirect cooling of the leakage flow 33 located in the radial gap 24 and thus also of the compressor wheel 11.
  • the cooling fluid 29 is branched off upstream of the charge air cooler 8, so that effective cooling can be achieved with the relatively cold cooling water.
  • the now heated Kuhlfluid is after the cooling ⁇ process stream 29 via the drain line 28 ⁇ fed back into the cooling water circuit 9 from the charge air cooler 8 (Fig. 1).
  • Na ⁇ Moslich can take place in the system of the internal combustion engine 1, the charge air cooler 8 and Exhaust gas turbocharger 2 existing cooling water and fresh water from outside the system as cooling fluid 29 (not shown).
  • direct cooling of the leakage flow 33 is provided.
  • a plurality of feed channels 40 for a second cooling fluid 41 opening tangentially to the rear wall 22 of the compressor wheel 11 and arranged in the radial gap 24 are arranged so as to penetrate both the bearing housing 21 and the diffuser plate 19 (FIG. 2).
  • the supply channels 40 are connected downstream of the charge air cooler 8 to the charge air line 6, so that cooled charge air is used as the second cooling fluid 41 (FIG. 1).
  • the second cooling fluid 41 can also be introduced into the radial gap at a different point (not shown).
  • a pure film cooling of the entire rear wall 22 of the compressor wheel 11 is achieved by the tangential introduction of the second cooling fluid 41.
  • the second cooling fluid 41 replaces the hot leakage flow 33, so that the boundary layer which forms on the rear wall 22 of the compressor wheel 11 is formed from the start, above all, by the cooled charge air.
  • the subsequent discharge of the second cooling fluid 41 takes place via a discharge device 42 which engages in the intermediate wall 20 of the compressor housing 10.
  • cooling media such as helium or gases from low-temperature fluids (e.g. liquid nitrogen, carbon tetrachloride, benzene nitride, etc.) can also be used as the first and second cooling fluids 29, 41.
  • low-temperature fluids e.g. liquid nitrogen, carbon tetrachloride, benzene nitride, etc.
  • oil is used as the first cooling fluid 29, it can be supplied externally or advantageously branched off from the lubricating oil system which is already present in the bearing housing 21 of the exhaust gas turbocharger 2 (not shown). To this A relatively simple and therefore inexpensive supply of this likewise suitable cooling fluid is possible.

Abstract

L'invention concerne un procédé de refroidissement amélioré de l'écoulement dans des fentes radiales formées entre les rotors et les stators de turbomachines. L'invention concerne également un dispositif simple, économique et robuste permettant de mettre en oeuvre ce procédé. A cet effet, un élément stator (20) adjacent à la fente radiale (24) est alimenté d'un premier fluide de refroidissement (29) et un deuxième fluide de refroidissement gazeux (41) est introduit dans la fente radiale (24). L'élément stator (20) adjacent à la fente radiale (24) abrite au moins un évidement (26) ou présente au moins une cavité. L'évidement (26) ou la cavité est relié à une conduite d'alimentation (27) comme à une conduite d'évacuation (28) pour le premier fluide de refroidissement (29). En outre, au moins un canal d'alimentation (40) et un dispositif d'évacuation (42) sont placés au niveau de la fente radiale (24) pour le deuxième fluide de refroidissement (41).
PCT/CH1999/000496 1999-10-20 1999-10-20 Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines WO2001029425A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
CNB998169617A CN1258648C (zh) 1999-10-20 1999-10-20 涡轮增压器压缩机转子和定子间的径向隙缝中气流的冷却方法和装置
DE59906615T DE59906615D1 (de) 1999-10-20 1999-10-20 Verfahren und vorrichtung zur kühlung der strömung in zwischen rotoren und statoren von turbomaschinen ausgebildeten radialspalten
JP2001531986A JP2003515690A (ja) 1999-10-20 1999-10-20 タービン機械のロータとステータとの間に形成された半径方向間隙における流れを冷却するための方法及び装置
PCT/CH1999/000496 WO2001029425A1 (fr) 1999-10-20 1999-10-20 Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines
EP99947180A EP1222399B1 (fr) 1999-10-20 1999-10-20 Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines
AU60757/99A AU6075799A (en) 1999-10-20 1999-10-20 Method and device for cooling the flow in the radial gaps formed between rotors and stators of turbine-type machines
KR1020027003417A KR100637643B1 (ko) 1999-10-20 1999-10-20 터빈식 기계의 로터와 스테이터 사이에 형성된 방사상간극에서의 유동을 냉각하는 방법 및 장치

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CH1999/000496 WO2001029425A1 (fr) 1999-10-20 1999-10-20 Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines

Publications (1)

Publication Number Publication Date
WO2001029425A1 true WO2001029425A1 (fr) 2001-04-26

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH1999/000496 WO2001029425A1 (fr) 1999-10-20 1999-10-20 Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines

Country Status (7)

Country Link
EP (1) EP1222399B1 (fr)
JP (1) JP2003515690A (fr)
KR (1) KR100637643B1 (fr)
CN (1) CN1258648C (fr)
AU (1) AU6075799A (fr)
DE (1) DE59906615D1 (fr)
WO (1) WO2001029425A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
DE102007001487B4 (de) * 2007-01-10 2015-07-16 Caterpillar Energy Solutions Gmbh Verfahren und Vorrichtung zur Verdichterradkühlung eines Verdichters

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005018771B4 (de) * 2005-04-22 2015-06-18 Man Diesel & Turbo Se Brennkraftmaschine
CN105143636B (zh) * 2013-02-21 2018-01-09 丰田自动车株式会社 具备窜缸混合气环流装置的内燃机的增压器的冷却装置
CN104595246A (zh) * 2015-01-05 2015-05-06 珠海格力电器股份有限公司 一种具有再冷却结构的离心压缩机
CN104595247A (zh) * 2015-01-05 2015-05-06 珠海格力电器股份有限公司 一种具有再冷却结构的离心压缩机
CN106286338A (zh) * 2015-06-02 2017-01-04 上海优耐特斯压缩机有限公司 对采用高速电机的离心压缩机泄漏空气进行冷却的结构
CN111720331B (zh) * 2020-05-22 2022-08-09 洛阳瑞华新能源技术发展有限公司 设置集排液流道分流隔板有至少2个排液口的单级离心泵

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191114702A (en) * 1910-06-22 1912-07-22 Hugo Junkers Improvements in or relating to Centrifugal or Turbo-compressors.
US2384251A (en) * 1943-01-14 1945-09-04 Wright Aeronautical Corp Liquid cooled supercharger
DE968742C (de) * 1944-09-22 1958-03-27 Daimler Benz Ag Mehrstufiges Radialgeblaese, vorzugsweise Ladegeblaese fuer Flugmotoren
US3966351A (en) * 1974-05-15 1976-06-29 Robert Stanley Sproule Drag reduction system in shrouded turbo machine
EP0518027A1 (fr) * 1991-06-14 1992-12-16 Mitsubishi Jukogyo Kabushiki Kaisha Compresseur centrifugal
DE19548852A1 (de) 1995-12-27 1997-07-03 Asea Brown Boveri Radialverdichter für Abgasturbolader
DE19652754A1 (de) 1996-12-18 1998-06-25 Asea Brown Boveri Abgasturbolader

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS61112737A (ja) * 1984-11-08 1986-05-30 Mitsubishi Heavy Ind Ltd 過給機
JPS6434435A (en) * 1987-07-06 1989-02-03 Agency Ind Science Techn Temperature sensitive gel and manufacture thereof
JPH0333431A (ja) * 1989-06-30 1991-02-13 Hitachi Ltd 内燃機関用過給機
JP2924363B2 (ja) * 1991-09-18 1999-07-26 石川島播磨重工業株式会社 過給機の水冷軸受ハウジング構造
JP2918773B2 (ja) * 1993-11-08 1999-07-12 株式会社日立製作所 遠心式圧縮機
JPH07208189A (ja) * 1994-01-10 1995-08-08 Hino Motors Ltd エンジンの過給機冷却装置
JP3606293B2 (ja) * 1996-02-14 2005-01-05 石川島播磨重工業株式会社 排気タービン過給機

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191114702A (en) * 1910-06-22 1912-07-22 Hugo Junkers Improvements in or relating to Centrifugal or Turbo-compressors.
US2384251A (en) * 1943-01-14 1945-09-04 Wright Aeronautical Corp Liquid cooled supercharger
DE968742C (de) * 1944-09-22 1958-03-27 Daimler Benz Ag Mehrstufiges Radialgeblaese, vorzugsweise Ladegeblaese fuer Flugmotoren
US3966351A (en) * 1974-05-15 1976-06-29 Robert Stanley Sproule Drag reduction system in shrouded turbo machine
EP0518027A1 (fr) * 1991-06-14 1992-12-16 Mitsubishi Jukogyo Kabushiki Kaisha Compresseur centrifugal
EP0518027B1 (fr) 1991-06-14 1995-07-05 Mitsubishi Jukogyo Kabushiki Kaisha Compresseur centrifugal
DE19548852A1 (de) 1995-12-27 1997-07-03 Asea Brown Boveri Radialverdichter für Abgasturbolader
DE19652754A1 (de) 1996-12-18 1998-06-25 Asea Brown Boveri Abgasturbolader

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007001487B4 (de) * 2007-01-10 2015-07-16 Caterpillar Energy Solutions Gmbh Verfahren und Vorrichtung zur Verdichterradkühlung eines Verdichters
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
WO2009071910A1 (fr) * 2007-12-06 2009-06-11 Napier Turbochargers Limited Turbine de turbocompresseur refroidie par liquide et procédé de refroidissement d'une turbine
EP2090788A1 (fr) 2008-02-14 2009-08-19 Napier Turbochargers Limited Rotor et turbocompresseur

Also Published As

Publication number Publication date
AU6075799A (en) 2001-04-30
KR100637643B1 (ko) 2006-10-23
KR20020041437A (ko) 2002-06-01
DE59906615D1 (de) 2003-09-18
EP1222399A1 (fr) 2002-07-17
EP1222399B1 (fr) 2003-08-13
CN1258648C (zh) 2006-06-07
JP2003515690A (ja) 2003-05-07
CN1375041A (zh) 2002-10-16

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