EP0518027A1 - Centrifugal compressor - Google Patents
Centrifugal compressor Download PDFInfo
- Publication number
- EP0518027A1 EP0518027A1 EP92106288A EP92106288A EP0518027A1 EP 0518027 A1 EP0518027 A1 EP 0518027A1 EP 92106288 A EP92106288 A EP 92106288A EP 92106288 A EP92106288 A EP 92106288A EP 0518027 A1 EP0518027 A1 EP 0518027A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- impeller
- centrifugal compressor
- exit
- 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.)
- Granted
Links
Images
Classifications
-
- 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
- F04D29/08—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
- 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)
Abstract
Description
- 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, and Fig. 4 is a section for explaining the operations of the same. At the back of an
impeller 1 of the centrifugal compressor and acasing 12, as shown, there is sandwiched alabyrinth packing 5 which seals up aseal space 7 between the exit and back of theimpeller 1. Theseal space 7 is vented to the outside through aventilation hole 8 for releasing a slight amount of air, which comes into theseal space 7 along the labyrinth packing 5, to the outside thereby to drop the pressure in theseal space 7. As a result, the pressurized air at the exit of theimpeller 1 is prevented from leaking to the back of theimpeller 1 and accordingly from establishing a thrust pushing arotor shaft 2 toward the entrance of theimpeller 1. Thus, the facial pressure upon a main thrust bearing 3 is lowered to lighten a load upon the main thrust bearing 3.Reference numerals - In the existing centrifugal compressor described above, 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 theimpeller 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 theimpeller 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 theimpeller 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 theimpeller 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.
- According to the present invention, there is provided 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.
- In the centrifugal compressor according to the present invention, 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.
- Other objects, features and advantages of the present invention will become apparent from the following description to be made with reference to the accompanying drawings, in which:
- Fig. 1 is a longitudinal section showing a centrifugal compressor according to one embodiment of the present invention;
- Fig. 2 is a section for explaining the operations of the same;
- Fig. 3 is a longitudinal section showing the centrifugal compressor of the prior art; and
- Fig. 4 is a section for explaining the operations of the same.
- Fig. 1 shows the structure of a centrifugal compressor according to one embodiment of the present invention, and Fig. 2 illustrates the operations of the centrifugal compressor. As shown, the centrifugal compressor according to the present embodiment is used as a supercharger of an engine. Between the back of an
impeller 1 and acasing 12, as shown in Fig. 1, there is sandwiched a labyrinth packing 15 for sealing up aseal space 7 between the exit and back of theimpeller 1. Theseal space 7 is vented to the outside through aventilation hole 8 for releasing a slight amount of air, which comes into theseal space 7 along the labyrinth packing 5, to the outside thereby to drop the pressure in theseal space 7. As a result, the pressurized air at the exit of theimpeller 1 is prevented from leaking to the back of theimpeller 1 and accordingly from establishing a thrust pushing arotor shaft 2 toward the entrance of theimpeller 1. Thus, the facial pressure upon a main thrust bearing 3 is lowered to reduce a load upon the main thrust bearing 3.Reference numerals - 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 theimpeller 1 if the pressure ratio is about 4.0. In order that the back of theimpeller 1 may be prevented from being heated by that hot temperature, the labyrinth packing 15 of the present centrifugal compressor has its fines classified into two outer and inner groups, which form anannular space 6 inbetween. Thisannular space 6 is fed, as better seen from Fig. 2, through anair passage 9 from the outside with the cold air which has a higher pressure P₂ than a pressure P₁ at the exit of theimpeller 1. Generally speaking, the air having left the centrifugal compressor has a higher pressure than that P₁ at the exit of theimpeller 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. Thus, this cooled air may be guided to the labyrinth packing 15 at the back of theimpeller 1. - At the labyrinth packing at the back of the impeller of the existing centrifugal compressor, the air in the inside seal space is released to have its pressure dropped so that the air at the impeller exit will pass in a small amount through the labyrinth packing. On the contrary, 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 theimpeller 1. Thus, the air thus fed has the higher pressure P₂ so that the air at the exit of theimpeller 1 will not flow along the labyrinth packing 15 into theannular space 6. To the contrary, a small amount of air fed to theannular space 6 will flow toward the exit of theimpeller 1. As a result, the back of theimpeller 1 is not exposed to and accordingly heated by the air, which might otherwise flow from the exit of theimpeller 1, but is cooled by the cold air fed from the outside via theair passage 9. Thus, theimpeller 1 can have its temperature rise suppressed so that its strength can be prevented from being degraded by the temperature rise. Incidentally, since theseal space 7 at the back of theimpeller 1 and theannular space 6 are sealed up by the labyrinth packing 15, the air flow, if any to theseal space 7, is released from theventilation hole 8 to drop a pressure P₃ in theseal space 7. Thus, the load upon the main thrust bearing 3 is not increased by the balanced thrust unlike the centrifugal compressor of the prior art. - According to the aforementioned structure of the centrifugal compressor of the present invention, the impeller back is not heated by the gas at the impeller exit but is cooled down by the cold gas. As a result, 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.
Claims (3)
- A centrifugal compressor characterized in comprising: an impeller (1); a seal member (15) arranged annularly and multiplexly at the back of said impeller for sealing up a gap between the exit of said impeller and a space (7) at the back of said impeller and for forming an annular space (6); and a passage (9) for feeding a cold gas under a higher pressure than that at the exit of said impeller into said annular space.
- A centrifugal compressor according to Claim 1, wherein said cold gas under a high pressure is the air at the exit of an engine air cooler.
- A centrifugal compressor according to Claim 1, wherein said seal member (15) is disposed at both the outer and inner circumferences of said annular space (6).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP143231/91 | 1991-06-14 | ||
JP3143231A JP2934530B2 (en) | 1991-06-14 | 1991-06-14 | Centrifugal compressor |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0518027A1 true EP0518027A1 (en) | 1992-12-16 |
EP0518027B1 EP0518027B1 (en) | 1995-07-05 |
Family
ID=15333954
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP92106288A Expired - Lifetime EP0518027B1 (en) | 1991-06-14 | 1992-04-10 | Centrifugal compressor |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP0518027B1 (en) |
JP (1) | JP2934530B2 (en) |
KR (1) | KR950006873B1 (en) |
DE (1) | DE69203293T2 (en) |
FI (1) | FI921758A (en) |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0961034A1 (en) * | 1998-05-25 | 1999-12-01 | Asea Brown Boveri Ag | Radial compressor |
EP0961033A1 (en) | 1998-05-25 | 1999-12-01 | Asea Brown Boveri Ag | Radial compressor |
WO2001029426A1 (en) * | 1999-10-20 | 2001-04-26 | Abb Turbo Systems Ag | Method and device for the indirect cooling of a flow regime in radial slits formed between the rotors and stators of turbomachines |
WO2001029425A1 (en) * | 1999-10-20 | 2001-04-26 | Abb Turbo Systems Ag | Method and device for cooling the flow in the radial gaps formed between rotors and stators of turbine-type machines |
WO2005028813A1 (en) * | 2003-09-12 | 2005-03-31 | Mes International, Inc. | Sealing arrangement in a compressor |
WO2007035699A2 (en) * | 2005-09-19 | 2007-03-29 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
WO2007035698A3 (en) * | 2005-09-19 | 2007-05-18 | Ingersoll Rand Co | Centrifugal compressor including a seal system |
WO2014163702A3 (en) * | 2013-03-08 | 2014-11-20 | Lunsford Patrick L | Multi-piece impeller |
ITFI20130237A1 (en) * | 2013-10-14 | 2015-04-15 | Nuovo Pignone Srl | "SEALING CLEARANCE CONTROL IN TURBOMACHINES" |
CN104712380A (en) * | 2013-12-16 | 2015-06-17 | 霍尼韦尔国际公司 | Compressor or turbine with back-disk seal and vent |
DE102016102923A1 (en) | 2016-02-19 | 2017-08-24 | Abb Turbo Systems Ag | Compressor wheel back radial turbine |
EP3343044A1 (en) * | 2016-12-28 | 2018-07-04 | Nidec Corporation | Fan device and vaccum cleaner including the same |
EP3456980A1 (en) * | 2017-09-15 | 2019-03-20 | Mitsubishi Heavy Industries Compressor Corporation | Compressor with axial thrust balancing by pressure on the impeller backplate |
CN112628162A (en) * | 2020-12-23 | 2021-04-09 | 苏州苏磁智能科技有限公司 | Flow channel structure and method for preventing high-temperature and high-pressure gas of centrifugal compressor from flowing back and centrifugal compressor |
US11002291B2 (en) | 2016-03-30 | 2021-05-11 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Compressor impeller |
WO2021105047A1 (en) * | 2019-11-25 | 2021-06-03 | Robert Bosch Gmbh | Turbomachine |
CN115450950A (en) * | 2022-11-08 | 2022-12-09 | 中国核动力研究设计院 | Gas compressor and supercritical carbon dioxide power generation system |
WO2023273232A1 (en) * | 2021-07-02 | 2023-01-05 | 鑫磊压缩机股份有限公司 | Assembly accuracy self-correcting compressor |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4810599A (en) | 1987-03-27 | 1989-03-07 | Japan Synthetic Rubber Co., Ltd. | Structure suitable for solid electrochemical elements |
DE59709283D1 (en) * | 1997-12-23 | 2003-03-13 | Abb Turbo Systems Ag Baden | Method and device for contactless sealing of a separation gap formed between a rotor and a stator |
DE19845375A1 (en) | 1998-10-02 | 2000-04-06 | Asea Brown Boveri | Indirect cooling process for flow in gap between turbine rotor and stator, involving use of water to cool stator part adjacent to gap |
KR100414103B1 (en) * | 2001-08-17 | 2004-01-07 | 엘지전자 주식회사 | Structure for engaging diffuser in turbo compressor |
EP1926915B1 (en) * | 2005-09-19 | 2016-12-28 | Ingersoll-Rand Company | Stationary seal ring for a centrifugal compressor |
US7402020B2 (en) * | 2005-12-14 | 2008-07-22 | Hamilton Sundstrand Corporation | ACM cooling flow path and thrust load design |
JP5135981B2 (en) * | 2007-10-05 | 2013-02-06 | 株式会社Ihi | Centrifugal compressor |
JP2010168968A (en) * | 2009-01-21 | 2010-08-05 | Toyota Motor Corp | Turbocharger |
DE102010037356B8 (en) * | 2010-09-06 | 2014-05-22 | Kompressorenbau Bannewitz Gmbh | Verdichterradkühlung |
JP5700999B2 (en) * | 2010-10-06 | 2015-04-15 | 三菱重工業株式会社 | Centrifugal compressor |
US9228497B2 (en) * | 2010-12-30 | 2016-01-05 | Rolls-Royce Corporation | Gas turbine engine with secondary air flow circuit |
JP2014111905A (en) | 2012-12-05 | 2014-06-19 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor and supercharger with the same, and operation method for centrifugal compressor |
CN105143636B (en) * | 2013-02-21 | 2018-01-09 | 丰田自动车株式会社 | Possesses the cooling device of the booster of the internal combustion engine of blow-by gas circulating device |
JP6225092B2 (en) * | 2014-10-17 | 2017-11-01 | 三菱重工業株式会社 | Labyrinth seal, centrifugal compressor and turbocharger |
CN105240280A (en) * | 2015-10-30 | 2016-01-13 | 江苏大学 | Centrifugal pump with rectangular gear pump front cavity structure |
Citations (3)
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---|---|---|---|---|
DE249336C (en) * | 1900-01-01 | |||
FR379125A (en) * | 1907-06-21 | 1907-10-25 | Wilhelm Heinrich Eyermann | axial pressure balancing in turbines, rotary pumps and compressors |
US3650634A (en) * | 1970-11-06 | 1972-03-21 | Carrier Corp | Centrifugal refrigeration compressor |
-
1991
- 1991-06-14 JP JP3143231A patent/JP2934530B2/en not_active Expired - Lifetime
-
1992
- 1992-04-10 DE DE69203293T patent/DE69203293T2/en not_active Expired - Fee Related
- 1992-04-10 EP EP92106288A patent/EP0518027B1/en not_active Expired - Lifetime
- 1992-04-21 FI FI921758A patent/FI921758A/en not_active Application Discontinuation
- 1992-06-12 KR KR1019920010196A patent/KR950006873B1/en not_active IP Right Cessation
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE249336C (en) * | 1900-01-01 | |||
FR379125A (en) * | 1907-06-21 | 1907-10-25 | Wilhelm Heinrich Eyermann | axial pressure balancing in turbines, rotary pumps and compressors |
US3650634A (en) * | 1970-11-06 | 1972-03-21 | Carrier Corp | Centrifugal refrigeration compressor |
Cited By (34)
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---|---|---|---|---|
EP0961034A1 (en) * | 1998-05-25 | 1999-12-01 | Asea Brown Boveri Ag | Radial compressor |
EP0961033A1 (en) | 1998-05-25 | 1999-12-01 | Asea Brown Boveri Ag | Radial compressor |
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 |
WO2001029426A1 (en) * | 1999-10-20 | 2001-04-26 | Abb Turbo Systems Ag | Method and device for the indirect cooling of a flow regime in radial slits formed between the rotors and stators of turbomachines |
WO2001029425A1 (en) * | 1999-10-20 | 2001-04-26 | Abb Turbo Systems Ag | Method and device for cooling the flow in the radial gaps formed between rotors and stators of turbine-type machines |
WO2005028813A1 (en) * | 2003-09-12 | 2005-03-31 | Mes International, Inc. | Sealing arrangement in a compressor |
US7252474B2 (en) | 2003-09-12 | 2007-08-07 | Mes International, Inc. | Sealing arrangement in a compressor |
WO2007035699A2 (en) * | 2005-09-19 | 2007-03-29 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
WO2007035698A3 (en) * | 2005-09-19 | 2007-05-18 | Ingersoll Rand Co | Centrifugal compressor including a seal system |
WO2007035699A3 (en) * | 2005-09-19 | 2007-05-31 | Ingersoll Rand Co | Impeller for a centrifugal compressor |
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US10527055B2 (en) | 2013-03-08 | 2020-01-07 | Rolls-Royce Corporation | Multi-piece impeller |
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CN105814284B (en) * | 2013-10-14 | 2019-04-23 | 诺沃皮尼奥内股份有限公司 | Seal clearance control in turbine |
US10280932B2 (en) | 2013-10-14 | 2019-05-07 | Nuovo Pignone Srl | Sealing clearance control in turbomachines |
ITFI20130237A1 (en) * | 2013-10-14 | 2015-04-15 | Nuovo Pignone Srl | "SEALING CLEARANCE CONTROL IN TURBOMACHINES" |
CN104712380A (en) * | 2013-12-16 | 2015-06-17 | 霍尼韦尔国际公司 | Compressor or turbine with back-disk seal and vent |
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CN104712380B (en) * | 2013-12-16 | 2018-11-02 | 盖瑞特交通一公司 | Compressor or turbine with back of the body disk sealing element and outlet |
US11377954B2 (en) | 2013-12-16 | 2022-07-05 | Garrett Transportation I Inc. | Compressor or turbine with back-disk seal and vent |
EP3553275A1 (en) * | 2013-12-16 | 2019-10-16 | Garrett Transportation I Inc. | Compressor or turbine with back-disk seal and vent |
DE102016102923A1 (en) | 2016-02-19 | 2017-08-24 | Abb Turbo Systems Ag | Compressor wheel back radial turbine |
US11002291B2 (en) | 2016-03-30 | 2021-05-11 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Compressor impeller |
EP3343044A1 (en) * | 2016-12-28 | 2018-07-04 | Nidec Corporation | Fan device and vaccum cleaner including the same |
US10876535B2 (en) | 2017-09-15 | 2020-12-29 | Mitsubishi Heavy Industries Compressor Corporation | Compressor |
EP3456980A1 (en) * | 2017-09-15 | 2019-03-20 | Mitsubishi Heavy Industries Compressor Corporation | Compressor with axial thrust balancing by pressure on the impeller backplate |
WO2021105047A1 (en) * | 2019-11-25 | 2021-06-03 | Robert Bosch Gmbh | Turbomachine |
CN112628162A (en) * | 2020-12-23 | 2021-04-09 | 苏州苏磁智能科技有限公司 | Flow channel structure and method for preventing high-temperature and high-pressure gas of centrifugal compressor from flowing back and centrifugal compressor |
WO2023273232A1 (en) * | 2021-07-02 | 2023-01-05 | 鑫磊压缩机股份有限公司 | Assembly accuracy self-correcting compressor |
CN115450950A (en) * | 2022-11-08 | 2022-12-09 | 中国核动力研究设计院 | Gas compressor and supercritical carbon dioxide power generation system |
CN115450950B (en) * | 2022-11-08 | 2023-03-03 | 中国核动力研究设计院 | Gas compressor and supercritical carbon dioxide power generation system |
Also Published As
Publication number | Publication date |
---|---|
JP2934530B2 (en) | 1999-08-16 |
DE69203293T2 (en) | 1996-01-25 |
JPH04365997A (en) | 1992-12-17 |
EP0518027B1 (en) | 1995-07-05 |
FI921758A (en) | 1992-12-15 |
KR950006873B1 (en) | 1995-06-23 |
KR930000807A (en) | 1993-01-15 |
FI921758A0 (en) | 1992-04-21 |
DE69203293D1 (en) | 1995-08-10 |
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