EP0984138A2 - Turbomachine avec arbre refroidie - Google Patents

Turbomachine avec arbre refroidie Download PDF

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Publication number
EP0984138A2
EP0984138A2 EP99810710A EP99810710A EP0984138A2 EP 0984138 A2 EP0984138 A2 EP 0984138A2 EP 99810710 A EP99810710 A EP 99810710A EP 99810710 A EP99810710 A EP 99810710A EP 0984138 A2 EP0984138 A2 EP 0984138A2
Authority
EP
European Patent Office
Prior art keywords
cooling
blades
machine according
blade
fluid machine
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
EP99810710A
Other languages
German (de)
English (en)
Other versions
EP0984138A3 (fr
EP0984138B1 (fr
Inventor
Bernhard Dr. Weigand
Conor Dr. Fitzsimons
Wolfgang Kappis
Hans Dr. Wettstein
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical Alstom Technology AG
Publication of EP0984138A2 publication Critical patent/EP0984138A2/fr
Publication of EP0984138A3 publication Critical patent/EP0984138A3/fr
Application granted granted Critical
Publication of EP0984138B1 publication Critical patent/EP0984138B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the invention relates to a turbomachine, in particular a compressor Gas turbine, according to the preamble of claim 1.
  • a first solution is to provide so-called heat shields prevent direct contact of the heated flow medium with the rotor shaft and thus their warming within the limits considered to be permissible should hold.
  • the disadvantage here is the increase in manufacturing costs and Complexity of the turbomachine due to the additional components.
  • the invention tries to avoid the disadvantages described. You are the Based on the task of specifying a turbomachine of the type mentioned at the outset, which allows the rotor shaft to be cooled locally with high efficiency, so that the life expectancy of the rotor shaft even at extremely high thermal Load is not significantly affected.
  • cooling blades which are from a cooling air supply are fed.
  • the cooling blades are designed such that they essentially are penetrated in the radial direction by air guide channels and in the area of the blade tips have blow-out openings that are aligned with the rotor shaft are.
  • heat shields can be used can be completely dispensed with because the rotor shaft is locally cooled in a targeted manner can.
  • the lifespan of the blading increases as a result of the cooling air caused lower temperature levels. This does not only concern that Cooling blades through which cooling air flows, but also the downstream, not refrigerated shovel rings.
  • the cooling air emerging at the blade tips also brings about an improvement the fluid mechanical properties. So on the one hand the boundary layer kinetic energy is locally supplied and influenced by the cooling air flow thereby positive. On the other hand, the emerging cooling air flow prevents the corresponding Design or arrangement of the blow-out openings a flow the guide vanes in the gap between the blade tips and the rotor shaft. Leakage losses in this area can therefore be avoided almost completely.
  • the Compressors By improving these aero-thermodynamic conditions, the Compressors also have improved operating behavior, which can also be seen in a clear Raising the surge limit is reflected.
  • the vibration behavior can be of the blades vary within wide limits. So it is possible to coordinate the natural frequency and flutter characteristics within limits so that critical vibration states no longer occur.
  • the attachment of the air duct to the guide vanes is in the Usually very easy and inexpensive, because cooling blades are especially thermal highly loaded rear stages of compressors and these Guide vanes are usually not or only slightly twisted.
  • the air ducts can therefore usually be carried out as simple holes that the Push through the respective guide vane completely radially or as in the axial direction branch at an angle from a central air duct.
  • the cooling device also has the advantage that it can be controlled very easily and precisely.
  • the cooling air can do this immediately upstream or downstream compressor stages are required
  • another preparation in such a way that it with higher pressure and is fed in at a lower temperature than the local state variables corresponds to the main flow. If a cooling air flow from a higher one than cooling air Compressor stage is removed, it must be cooled. If on the other hand a cooling air flow is taken from a lower compressor stage, it must first be further compressed externally and then cooled.
  • the cooling concept according to the invention can also be particularly advantageous for idlers can be applied with a cover tape.
  • the cover tape enables one even more uniform formation of the cooling film in the circumferential direction, because the emerging cooling air partial flows are not directly captured by the main flow and get carried away.
  • cooling blades are radial Direction slidably and are against the action of return springs shifted from their starting position by the pressure of the cooling air. This makes it possible to improve the compressor efficiency and in particular the Pumping limit raised significantly. This effect is with modern high pressure compressor stages clearly pronounced, because here for security reasons because of the slow response large gap widths must be provided to reliably prevent the blade tips from entering the rotor shaft.
  • the return springs are a safety measure in the event that the Cooling air supply should be interrupted.
  • the cooling blades sweep immediately back to their starting position and in this way enlarge the gap between the blade tips and the rotor, so that this also in the case of a then thermal radial expansion not in contact with the Blade tips can come.
  • the blade root of the cooling blades is provided with a piston-shaped section, the in a correspondingly shaped cylindrical housing section is sealed to form a work space.
  • the workspace is there in connection with the cooling air supply, so that when exposed to Cooling air is pushed out like a pneumatic cylinder, the cooling blades can.
  • the air ducts of the cooling air blades are preferably communicating Connection to the respective work area, which makes the airflow special simply designed.
  • the airflow fed by the cooling air supply first gets into the work area and causes the radial displacement the shovel.
  • the cooling air flow now enters directly from the work area the air guide channels and leaves the blade in the area of the blade tip through the blow-out openings.
  • the coordination of the geometry of the air duct Channel sections and the pressure conditions in the compressed air supply is such that the air jets emerging from the exhaust openings have a high speed own and at high speed on the opposite Impact arranged rotor shaft.
  • the impact cooling achieved in this way is guaranteed an optimal heat transfer and thus an optimal cooling effect for the rotor shaft.
  • two adjacent cooling blades are fixed to each other connected and slidably supported. This simplifies further the constructive structure of the bearing without the cooling effect disadvantageous to influence.
  • the air duct channels are preferred as bores, in particular as radial Through holes carried out, which minimizes the manufacturing effort can hold.
  • the cooling blades preferably each have several, in particular parallel to one another running air duct on, so that each of the cooling blades can form several partial cooling air jets. This allows cooling one Axial section of the rotor shaft corresponding to the axial width of the respective Diffuser.
  • rotor cooling on which the invention is based is particularly evident 1 and 2. It is a typical compressor stage of a high pressure compressor with an impeller and a stator, symbolized by a blade 11 and vane 12 shown. The blades 11 are in themselves known manner attached to a rotor shaft 18 which rotates in the direction of rotation D. is drivable.
  • the blades 11 are followed by the guide blades 12, which are known Way attached to a housing section 17 - and thus fixed are.
  • the guide blades 12 are designed as cooling blades. You point to this Purpose air guide channels 13 which are continuous in the radial direction within the cooling blade 12 and extend in the area of the blade tip 15 as Blow-out openings 14 open out.
  • the blow-out openings 14 are on the rotor shaft 18 aligned.
  • the air duct 13 are in a manner not shown with a Cooling air supply connected, which supplies cooling air.
  • the pressure is like this chosen that cooling air jets K at high speed from the exhaust openings 14 emerge and strike the immediately adjacent rotor shaft 18.
  • the cooling effect achieved in this way is enormous, since the heat transfer coefficient - and thus the transferable cooling energy - is very high.
  • the cooling air channels 13 do not have to necessarily have a circular cross section.
  • the cross-sectional shape optimally matches the profile cross-sectional shape of the guide vane 12 be adjusted so that a high and optimally distributed air flow can be realized leaves.
  • further advantages result from the fact that the guide vane 12 or the surface around which it flows, is cooled from the inside. So reduced the thermal stress on the guide vane 12 with the thus associated advantages of an extended service life or the possibility of allow a higher process temperature already at the time of design.
  • a rotor shaft 38 has a circumferential groove in the axial section to be cooled 39, into which a cooling blade 32 protrudes radially with its blade tip 35. Blow-out openings 34 are again provided, through which cooling air jets K emerge.
  • This configuration may have a. the advantage that the emerging cooling air K is not immediate is caught by the main flow H and carried away. This is the local cooling effect is more pronounced than, for example, that described above Configuration.
  • FIG. 4 has cooling blades 42 which are connected to a Shroud 46 are connected to one another in the area of the blade tips 45. Blow-out openings 44 are again arranged in the area of the blade tips 45, emerge through the cooling air jets K. These hit directly opposite on a rotor shaft 48 and cool it locally. Between the Shroud 46 and the rotor 48 is a continuous annular gap in the circumferential direction 49 available, so that a certain retention effect for the emerging cooling air jets K is given.
  • cooling blades 52 which Have blade tips 55 that extend radially in the direction of a rotor shaft 58 expand funnel-shaped. In turn, in the area of the blade tips 55 Blow-out openings 54 are provided, through which cooling air jets K are expelled become.
  • the funnel shape of the blade tips 55 enables the application of the rotor shaft 58 along a larger circumferential section than is the case with radial straight-ended blades would be possible.
  • cooling blades have 62 a blade root 67 in the manner of a piston-shaped radial section on that in a correspondingly shaped cylindrical housing section 78 is slidably mounted.
  • a working space 77 is created which a supply channel 76 opens. Through the supply channel 76 is off the cooling air supply, not shown here, cooling air to the working space 77 fed.
  • the blade root 67 is provided with sealing rings 73, so that in this way the working space 77 is sealed off from the cylindrical housing section 78 is.
  • cooling air is applied to the working space 77, there is a shift the cooling blade 62 towards the rotor shaft 68. Cooling air also occurs from the work space 77 into air guide channels 63 and leaves them through Blow-out openings 64.
  • the sliding movement of the cooling blade 62 takes place against the action of return springs 74 which between the blade root 67 and the housing section 78 act in the region of the working space 77.
  • the return springs 74 have the effect on the one hand that they the cooling blade 62 when switched off Withdraw cooling air supply and in this way a gap 70 between the blade tips 65 and the rotor shaft 68 is set to be as wide is dimensioned such that the blade tip 65 runs securely into the rotor shaft 68 is prevented.
  • the Gap 70 is reduced to such an extent that a cooling air stream K discharges Air cushion is formed in the gap 70, which not only cools the rotor shaft 68, but also a reliable flow around the cooling blade 62 in the area of the gap 70 prevented.
  • the compressor efficiency and the surge limit can be thereby increase optimally.
  • the width of the gap 70 can be appropriately controlled for the cooling air supply can be designed to be variably adjustable.
  • a particularly simple constructive Solution can also be achieved by not having a closer look here Shown stop is provided, the displacement of the cooling blade 62 limits and thus specifies the minimum width of the gap 70.
  • each of the cooling blades 62 of a guide vane ring is individually displaceable is stored.
  • This configuration includes an additional security aspect in the event that there is a local fault with a single cooling blade 62 - for example if the air duct 63 is blocked - the person concerned Cooling blade 62 returns to its original position.
  • One in a row due to the lack of internal cooling of the cooling blade 62 caused thermal expansion in radial Direction does not lead to the blade tip 65 entering the rotor shaft 68.
  • FIG. 8 shows a tandem arrangement of two cooling blades 82 on a common blade carrier 87.
  • a shroud 86 is provided in the area of blade tips 85.
  • cooling air jets K ejected from the cooling blades 82 via blow-out openings 84 and impact on a rotor shaft 88.
  • both are here Cooling blades 82 configured radially displaceable together.
  • a return spring 94 acts directly on the blade carrier 87.
  • a housing section is used 98 as a rear stop for the blade carrier 87.
  • the cooling air K each of the two cooling blades 82 is fed separately, with length compensation one bellows 95 each between a supply channel 96 and the blade carrier 87 is arranged.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP99810710A 1998-08-31 1999-08-09 Turbomachine avec arbre refroidie Expired - Lifetime EP0984138B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19839592A DE19839592A1 (de) 1998-08-31 1998-08-31 Strömungsmaschine mit gekühlter Rotorwelle
DE19839592 1998-08-31

Publications (3)

Publication Number Publication Date
EP0984138A2 true EP0984138A2 (fr) 2000-03-08
EP0984138A3 EP0984138A3 (fr) 2002-01-23
EP0984138B1 EP0984138B1 (fr) 2005-10-26

Family

ID=7879284

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99810710A Expired - Lifetime EP0984138B1 (fr) 1998-08-31 1999-08-09 Turbomachine avec arbre refroidie

Country Status (3)

Country Link
US (1) US6224328B1 (fr)
EP (1) EP0984138B1 (fr)
DE (2) DE19839592A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011054758A1 (fr) 2009-11-04 2011-05-12 Alstom Technology Ltd. Rotor soudé d'un compresseur de groupe motopropulseur de turbines à gaz
EP2551490A1 (fr) 2011-07-25 2013-01-30 Alstom Technology Ltd Compresseur axial avec dispositif d'injection permettant d'injecter un fluide
EP3205817A1 (fr) 2016-02-09 2017-08-16 Ansaldo Energia Switzerland AG Rotor refroidi par fluide pour une turbine à gaz

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002309903A (ja) * 2001-04-10 2002-10-23 Mitsubishi Heavy Ind Ltd ガスタービンの蒸気配管構造
US6974306B2 (en) * 2003-07-28 2005-12-13 Pratt & Whitney Canada Corp. Blade inlet cooling flow deflector apparatus and method
EP1691054A1 (fr) * 2005-02-12 2006-08-16 Hubert Antoine Turbine à gaz
RU2425982C2 (ru) * 2005-04-14 2011-08-10 Альстом Текнолоджи Лтд Лопатка газовой турбины
EP1895094B1 (fr) * 2006-08-25 2010-09-29 Siemens Aktiengesellschaft Rotor avec cordon de soudure refroidi par tourbillon
EP1923574B1 (fr) * 2006-11-20 2014-10-29 Siemens Aktiengesellschaft Compresseur, turbine et méthode d'alimentation de gaz chaud
EP2161411A1 (fr) * 2008-09-05 2010-03-10 Siemens Aktiengesellschaft Aube de turbine dotée d'une fréquence propre adaptée à l'aide d'un élément d'insertion
KR101906949B1 (ko) * 2012-02-29 2018-10-11 한화에어로스페이스 주식회사 터빈 시일 조립체 및 이를 구비한 터빈 장치
US9085982B2 (en) * 2012-03-19 2015-07-21 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine
US11022037B2 (en) 2018-01-04 2021-06-01 General Electric Company Gas turbine engine thermal management system
US10941706B2 (en) 2018-02-13 2021-03-09 General Electric Company Closed cycle heat engine for a gas turbine engine
US11143104B2 (en) 2018-02-20 2021-10-12 General Electric Company Thermal management system
US11015534B2 (en) 2018-11-28 2021-05-25 General Electric Company Thermal management system

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3635586A (en) * 1970-04-06 1972-01-18 Rolls Royce Method and apparatus for turbine blade cooling
US3703808A (en) * 1970-12-18 1972-11-28 Gen Electric Turbine blade tip cooling air expander
US4213296A (en) * 1977-12-21 1980-07-22 United Technologies Corporation Seal clearance control system for a gas turbine
JPS5848702A (ja) * 1981-09-18 1983-03-22 Hitachi Ltd ガスタ−ビン空冷翼
EP0790390A2 (fr) * 1996-02-13 1997-08-20 ROLLS-ROYCE plc Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4668162A (en) * 1985-09-16 1987-05-26 Solar Turbines Incorporated Changeable cooling control system for a turbine shroud and rotor
GB2210935B (en) * 1987-10-10 1992-05-27 Rolls Royce Plc Variable stator vane assembly
JP3260437B2 (ja) * 1992-09-03 2002-02-25 株式会社日立製作所 ガスタービン及びガスタービンの段落装置
DE4411616C2 (de) * 1994-04-02 2003-04-17 Alstom Verfahren zum Betreiben einer Strömungsmaschine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3635586A (en) * 1970-04-06 1972-01-18 Rolls Royce Method and apparatus for turbine blade cooling
US3703808A (en) * 1970-12-18 1972-11-28 Gen Electric Turbine blade tip cooling air expander
US4213296A (en) * 1977-12-21 1980-07-22 United Technologies Corporation Seal clearance control system for a gas turbine
JPS5848702A (ja) * 1981-09-18 1983-03-22 Hitachi Ltd ガスタ−ビン空冷翼
EP0790390A2 (fr) * 1996-02-13 1997-08-20 ROLLS-ROYCE plc Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 007, no. 133 (M-221), 10. Juni 1983 (1983-06-10) & JP 58 048702 A (HITACHI SEISAKUSHO KK), 22. März 1983 (1983-03-22) *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011054758A1 (fr) 2009-11-04 2011-05-12 Alstom Technology Ltd. Rotor soudé d'un compresseur de groupe motopropulseur de turbines à gaz
EP2551490A1 (fr) 2011-07-25 2013-01-30 Alstom Technology Ltd Compresseur axial avec dispositif d'injection permettant d'injecter un fluide
US9004853B2 (en) 2011-07-25 2015-04-14 Alstom Technology Ltd Axial compressor with an injection device for injecting a fluid
EP3205817A1 (fr) 2016-02-09 2017-08-16 Ansaldo Energia Switzerland AG Rotor refroidi par fluide pour une turbine à gaz

Also Published As

Publication number Publication date
EP0984138A3 (fr) 2002-01-23
DE19839592A1 (de) 2000-03-02
DE59912702D1 (de) 2005-12-01
EP0984138B1 (fr) 2005-10-26
US6224328B1 (en) 2001-05-01

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