EP0899425A2 - Aube pour une turbine à gaz - Google Patents

Aube pour une turbine à gaz Download PDF

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Publication number
EP0899425A2
EP0899425A2 EP98810770A EP98810770A EP0899425A2 EP 0899425 A2 EP0899425 A2 EP 0899425A2 EP 98810770 A EP98810770 A EP 98810770A EP 98810770 A EP98810770 A EP 98810770A EP 0899425 A2 EP0899425 A2 EP 0899425A2
Authority
EP
European Patent Office
Prior art keywords
cooling
blade
turbine blade
steam
cooling system
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
EP98810770A
Other languages
German (de)
English (en)
Other versions
EP0899425B1 (fr
EP0899425A3 (fr
Inventor
Wilhelm Dr. Endres
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
ABB Schweiz 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 Schweiz AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Schweiz AG
Publication of EP0899425A2 publication Critical patent/EP0899425A2/fr
Publication of EP0899425A3 publication Critical patent/EP0899425A3/fr
Application granted granted Critical
Publication of EP0899425B1 publication Critical patent/EP0899425B1/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
    • 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

Definitions

  • the invention relates to a turbine blade of a gas turbine, according to the preamble of claim 1.
  • gas turbine plants are caused by an increase in temperatures achieved.
  • temperature resistance of the material of the gas turbine is limited components exposed to the highest temperatures must be cooled. This particularly affects the guide and rotor blades of the gas turbine.
  • the turbine blades are at least partially hollow in their interior and have one or more cooling channels.
  • the latter are made by one Cooling fluid flows through, the cooling effect through convective heat transfer arises inside the blade body.
  • An additional film cooling is possible by placing parts of the cooling fluid through openings in the blade body on the Be guided outside of the turbine blade. A film of cooling fluid forms there, which the outside of the turbine blade from the hot working medium shields the turbine (see DE 36 42 789 C2).
  • cooling fluid are from the compressor the gas turbine plant or from an external source and under Overpressurized air or also appropriately treated water vapor are known.
  • Closed steam cooling systems have opposite and also opposite procedural advantages of the hybrid steam cooling systems mentioned.
  • the range of uses such systems are increasing today particularly because of their higher Efficiency.
  • a closed steam cooling system can penetrate of foreign bodies in the cooling channel adjacent to the blade leading edge be severely damaged.
  • a lot of cooling steam escapes that downstream of the impact point is not sufficient Bucket cooling takes place more. This causes the material to overheat, which is why serious consequential damage can occur.
  • the invention tries to avoid all of these disadvantages. You have the task based on creating turbine blades with increased functional reliability.
  • the interior of the blade body in the area the suction side wall, the pressure side wall and the blade exit edge has a closed cooling system with at least one cooling channel.
  • the blade leading edge has a separate, open cooling system at least one cooling channel and several penetrating the blade body Film cooling holes formed.
  • the open cooling system particularly advantageously consists of two parallel to one another arranged and connected to one another via several feed openings Cooling channels.
  • the cooling can also downstream of a leak of the first cooling channel by supplying the cooling medium from the second Cooling channel can be maintained.
  • Adjacent cooling duct is at least approximately circular.
  • the film cooling holes are arranged tangentially starting from this first cooling channel, while the feed openings extend tangentially from the second cooling channel and also lead tangentially into the first cooling channel.
  • This is the cooling medium A rotating movement is impressed in the first cooling channel. This vortex of the cooling medium ensures improved convective cooling in the interior as well as for effective film cooling of the blade body.
  • the film cooling holes face the suction wall and at least approximately in the flow direction of the working fluid of the gas turbine are aligned.
  • the one emerging from the film cooling holes at high speed The desired flow direction is thus already the cooling medium given. This can have a better effect on the suction side Wall of the turbine blade spreading cooling film and thus an improved Film cooling can be achieved.
  • the closed Steam cooling system also consists of at least two arranged parallel to each other Cooling channels, which are connected to each other via connection openings. After foreign objects have been struck, the cooling medium flows through the connection openings to the corresponding impact points, so that the cooling side downstream cooling sections can be filled with cooling medium. On in this way the functional reliability of the turbine blades can be further increased become.
  • the gas turbine system for example, does not show the compressor, the combustion chamber and the guide vanes of the gas turbine.
  • the flow direction the work equipment is marked with arrows.
  • the gas turbine has several rows of rotor and guide blades.
  • one of the blades 1 is shown. It consists of one Blade root 2 and a blade body 3.
  • the blade body 3 of the moving blade 1 has a suction-side wall 4, one opposite, pressure-side Wall 5, a blade leading edge 6 and a blade leading edge 7 on. It has a hollow interior 8 which is in the area of the suction side Wall 4, the pressure side wall 5 and the blade trailing edge 7 a closed Steam cooling system 9, with a cooling channel 10 (Fig. 2).
  • an open cooling system 11 with two in parallel mutually arranged cooling channels 14, 15 are formed.
  • Between the closed Steam cooling system 9 and the open cooling system 11 is a partition 16 arranged.
  • the first cooling channel 14 of the open cooling system 11 is the blade leading edge 6 adjacent, circular and with the second cooling channel 15 over several feed openings 18 arranged in an intermediate wall 17 are connected.
  • the first cooling channel 14 can also have other suitable shapes, such as, for example approximately circular, elliptical or potato-shaped Have training (not shown).
  • the intermediate wall 17 is in the area of Blade root 2 connected to the suction-side wall 4 via a connecting piece 19, wherein in the connector 19 a plurality of cooling holes 20 for local cooling the suction-side wall 4 are arranged.
  • the feed openings 18 arranged in the intermediate wall 17 close tangentially to the two cooling channels 14, 15.
  • a film hole row 21 with each several tangential to the suction side wall 4 and approximately in the flow direction 12 of the working fluid 13 of the gas turbine aligned film cooling holes 22 educated.
  • a plurality of rows of film holes 21 can also be arranged in the blade body 3 be what in Figure 3 by a second, dashed line of film holes 21 is indicated.
  • Air is used as the cooling medium 23.
  • the air 23 is in the blade root 2 arranged supply channel 24 introduced into the second cooling channel 15 and serves there the convective cooling of the blade body 3 Air 23 through the supply openings 18 in the first cooling channel 14, where they Blade body 3 also cools convectively.
  • the air 23 experiences the first cooling channel 14 and its tangential injection a rotating movement, which significantly improves the cooling effect.
  • the air 23 passes from the first cooling duct 14 through the tangential ones Film cooling holes 22 on the suction side wall 4. There it forms a thin Cooling film from which the outer surface of the blade body 3 from shields hot working fluid 13 of the gas turbine. By aligning the film cooling holes 22 the air 23 is already approximately in the direction of flow 12 of the working fluid 13 of the gas turbine, which further improves film cooling.
  • appropriately prepared water vapor can also be used as the cooling medium 23 Find use.
  • both the closed and the open cooling system 9, 11 operated with the same cooling medium 23, 26. Therefore no separate coolant supply is required, so that the partition between the two cooling systems 9, 11 shortened in the area of the blade root 2 can be trained (not shown).
  • the cooling medium that got into the working fluid 13 of the gas turbine during the cooling process 23 of the open cooling system 11 is in the downstream part of the turbine blading relaxed.
  • that in the closed steam cooling system 9 recycled steam used as cooling medium 26 and for example relaxed in the steam circuit of a steam turbine connected to the gas turbine (not shown).
  • the closed steam cooling system 9 designed as a serpentine cooling system. It consists of two parallel to each other arranged cooling channels 27, 28 which extend in the longitudinal direction of the blade from the blade root 2 extend to the tip of the blade 29.
  • the cooling channels 27, 28 are on of the blade tip 29 is deflected in the direction of the blade root 2 of the moving blade 1 (Fig. 3).
  • rib walls 30 Between the two parallel and in the same direction from steam 26 through which cooling channels 27, 28 are arranged are rib walls 30 which have a plurality of connection openings 31.
  • connection openings 31 FIG. 4
  • holes 25 can also be made in the area of the closed steam cooling system 9 can be compensated. It comes to Impact of foreign bodies in this area of the blade 1 flows the cooling medium from the cooling channel 27, 28 not affected by the Connection openings 31 to the corresponding holes 25, so that the Cooling section downstream of the cooling side can again be filled with steam 26.
  • the the Open cooling system 11 related procedures are analogous to the first Embodiment specified.
  • guide vanes can refer to a gas turbine their cooling are formed analog.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98810770A 1997-09-01 1998-08-11 Aube pour une turbine à gaz Expired - Lifetime EP0899425B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19738065A DE19738065A1 (de) 1997-09-01 1997-09-01 Turbinenschaufel einer Gasturbine
DE19738065 1997-09-01

Publications (3)

Publication Number Publication Date
EP0899425A2 true EP0899425A2 (fr) 1999-03-03
EP0899425A3 EP0899425A3 (fr) 2000-07-05
EP0899425B1 EP0899425B1 (fr) 2003-12-03

Family

ID=7840791

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810770A Expired - Lifetime EP0899425B1 (fr) 1997-09-01 1998-08-11 Aube pour une turbine à gaz

Country Status (5)

Country Link
US (1) US6033181A (fr)
EP (1) EP0899425B1 (fr)
JP (1) JPH11132003A (fr)
CN (1) CN1120287C (fr)
DE (2) DE19738065A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1162355A2 (fr) 2000-06-05 2001-12-12 ALSTOM Power N.V. Méthode de refroidissement d'une turbine à gaz
EP1605136A2 (fr) 2004-05-27 2005-12-14 United Technologies Corporation Aube de rotor refroidie
US7263834B2 (en) 2000-06-05 2007-09-04 Alstom Technology Ltd Method for cooling a gas turbine system and a gas turbine system for performing this method
EP1600605A3 (fr) * 2004-05-27 2007-10-03 United Technologies Corporation Aube de turbine refroidie
DE102012011294A1 (de) 2011-06-16 2012-12-20 Alstom Technology Ltd. Verfahren zum Kühlen einer Gasturbinenanlage sowie Gasturbinenanlage zur Durchführung des Verfahrens
CN103806951A (zh) * 2014-01-20 2014-05-21 北京航空航天大学 一种缝气膜冷却加扰流柱的组合式涡轮叶片
EP3425165A1 (fr) * 2017-07-05 2019-01-09 General Electric Technology GmbH Composant mécanique
EP2828484B1 (fr) 2012-03-22 2019-05-08 Ansaldo Energia IP UK Limited Aube de turbine

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EP1342882B1 (fr) * 1998-12-10 2006-05-17 ALSTOM Technology Ltd Procédé de fabrication d'un rotor soudé de turbomachine
DE19902437C5 (de) 1999-01-22 2017-01-12 General Electric Technology Gmbh Verfahren und Vorrichtung zum schnellen Anfahren und zur schnellen Leistungssteigerung einer Gasturbinenanlage
GB0025012D0 (en) * 2000-10-12 2000-11-29 Rolls Royce Plc Cooling of gas turbine engine aerofoils
DE10053356A1 (de) * 2000-10-27 2002-05-08 Alstom Switzerland Ltd Gekühltes Bauteil, Gusskern für die Herstellung eines solchen Bauteils, sowie Verfahren zum Herstellen eines solchen Bauteils
EP1321627A1 (fr) * 2001-12-21 2003-06-25 Siemens Aktiengesellschaft Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement
JP2003200936A (ja) * 2001-12-28 2003-07-15 Toyo Roki Mfg Co Ltd 容器の水抜き穴形状
US6932573B2 (en) * 2003-04-30 2005-08-23 Siemens Westinghouse Power Corporation Turbine blade having a vortex forming cooling system for a trailing edge
US7198468B2 (en) * 2004-07-15 2007-04-03 Pratt & Whitney Canada Corp. Internally cooled turbine blade
US7097419B2 (en) * 2004-07-26 2006-08-29 General Electric Company Common tip chamber blade
EP1621730B1 (fr) 2004-07-26 2008-10-08 Siemens Aktiengesellschaft Element refroidi d'une turbomachine et procédé pour le moulage de cet élement
GB0418914D0 (en) * 2004-08-25 2004-09-29 Rolls Royce Plc Turbine component
US7128533B2 (en) * 2004-09-10 2006-10-31 Siemens Power Generation, Inc. Vortex cooling system for a turbine blade
US7217097B2 (en) * 2005-01-07 2007-05-15 Siemens Power Generation, Inc. Cooling system with internal flow guide within a turbine blade of a turbine engine
US7189060B2 (en) * 2005-01-07 2007-03-13 Siemens Power Generation, Inc. Cooling system including mini channels within a turbine blade of a turbine engine
US7632071B2 (en) * 2005-12-15 2009-12-15 United Technologies Corporation Cooled turbine blade
WO2009016744A1 (fr) * 2007-07-31 2009-02-05 Mitsubishi Heavy Industries, Ltd. Pale pour turbine
US8376706B2 (en) * 2007-09-28 2013-02-19 General Electric Company Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method
US10286407B2 (en) 2007-11-29 2019-05-14 General Electric Company Inertial separator
US8393157B2 (en) * 2008-01-18 2013-03-12 General Electric Company Swozzle design for gas turbine combustor
US8511968B2 (en) * 2009-08-13 2013-08-20 Siemens Energy, Inc. Turbine vane for a gas turbine engine having serpentine cooling channels with internal flow blockers
DE102010046331A1 (de) * 2010-09-23 2012-03-29 Rolls-Royce Deutschland Ltd & Co Kg Gekühlte Turbinenschaufeln für ein Gasturbinentriebwerk
US8840370B2 (en) 2011-11-04 2014-09-23 General Electric Company Bucket assembly for turbine system
US9915176B2 (en) 2014-05-29 2018-03-13 General Electric Company Shroud assembly for turbine engine
EP3149310A2 (fr) 2014-05-29 2017-04-05 General Electric Company Moteur à turbine, composants et leurs procédés de refroidissement
US11033845B2 (en) 2014-05-29 2021-06-15 General Electric Company Turbine engine and particle separators therefore
CA2949547A1 (fr) 2014-05-29 2016-02-18 General Electric Company Moteur de turbine, et epurateurs de particules pour celui-ci
US10167725B2 (en) 2014-10-31 2019-01-01 General Electric Company Engine component for a turbine engine
US10036319B2 (en) 2014-10-31 2018-07-31 General Electric Company Separator assembly for a gas turbine engine
CN104696018B (zh) * 2015-02-15 2016-02-17 德清透平机械制造有限公司 一种高效汽轮机叶片
US10174620B2 (en) 2015-10-15 2019-01-08 General Electric Company Turbine blade
US9988936B2 (en) 2015-10-15 2018-06-05 General Electric Company Shroud assembly for a gas turbine engine
US10428664B2 (en) 2015-10-15 2019-10-01 General Electric Company Nozzle for a gas turbine engine
CN105840315B (zh) * 2016-03-15 2017-10-31 哈尔滨工程大学 一种应用于气膜冷却技术的旋流冷气腔结构
CN105909318B (zh) * 2016-04-26 2017-09-26 西北工业大学 一种用于涡轮叶片气膜冷却出口上游扩张孔结构
US10704425B2 (en) 2016-07-14 2020-07-07 General Electric Company Assembly for a gas turbine engine
FR3062675B1 (fr) * 2017-02-07 2021-01-15 Safran Helicopter Engines Aube haute pression ventilee de turbine d'helicoptere comprenant un conduit amont et une cavite centrale de refroidissement
US10801724B2 (en) * 2017-06-14 2020-10-13 General Electric Company Method and apparatus for minimizing cross-flow across an engine cooling hole
CN109812301A (zh) * 2019-03-06 2019-05-28 上海交通大学 一种具有横向通气孔的涡轮叶片双层壁冷却结构
CN112483191B (zh) * 2020-11-30 2022-07-19 日照黎阳工业装备有限公司 一种适用于燃气轮机具备对流换热功能的涡轮叶片
CN115234306A (zh) * 2022-09-21 2022-10-25 中国航发燃气轮机有限公司 一种燃气轮机透平气冷叶片

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DE3642789A1 (de) 1985-12-23 1987-06-25 United Technologies Corp Filmgekuehlte turbinenlauf- oder -leitschaufel fuer ein gasturbinentriebwerk
EP0698723A2 (fr) 1994-08-23 1996-02-28 General Electric Company Circuit de refroidissement fermé pour aube distributeur de turbine

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DE3642789A1 (de) 1985-12-23 1987-06-25 United Technologies Corp Filmgekuehlte turbinenlauf- oder -leitschaufel fuer ein gasturbinentriebwerk
EP0698723A2 (fr) 1994-08-23 1996-02-28 General Electric Company Circuit de refroidissement fermé pour aube distributeur de turbine

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1162355A2 (fr) 2000-06-05 2001-12-12 ALSTOM Power N.V. Méthode de refroidissement d'une turbine à gaz
US6532744B1 (en) 2000-06-05 2003-03-18 Alstom (Switzerland) Ltd Method for cooling a gas turbine system and a gas turbine system for performing this method
US7263834B2 (en) 2000-06-05 2007-09-04 Alstom Technology Ltd Method for cooling a gas turbine system and a gas turbine system for performing this method
EP1605136A2 (fr) 2004-05-27 2005-12-14 United Technologies Corporation Aube de rotor refroidie
EP1600605A3 (fr) * 2004-05-27 2007-10-03 United Technologies Corporation Aube de turbine refroidie
EP1605136A3 (fr) * 2004-05-27 2009-01-21 United Technologies Corporation Aube de rotor refroidie
DE102012011294A1 (de) 2011-06-16 2012-12-20 Alstom Technology Ltd. Verfahren zum Kühlen einer Gasturbinenanlage sowie Gasturbinenanlage zur Durchführung des Verfahrens
US9145774B2 (en) 2011-06-16 2015-09-29 Alstom Technology Ltd. Method for cooling a gas turbine plant and gas turbine plant for implementing the method
DE102012011294B4 (de) 2011-06-16 2019-03-14 Ansaldo Energia Switzerland AG Verfahren zum Kühlen einer Gasturbinenanlage sowie Gasturbinenanlage zur Durchführung des Verfahrens
EP2828484B1 (fr) 2012-03-22 2019-05-08 Ansaldo Energia IP UK Limited Aube de turbine
EP2828484B2 (fr) † 2012-03-22 2024-10-09 Ansaldo Energia IP UK Limited Aube de turbine
CN103806951A (zh) * 2014-01-20 2014-05-21 北京航空航天大学 一种缝气膜冷却加扰流柱的组合式涡轮叶片
EP3425165A1 (fr) * 2017-07-05 2019-01-09 General Electric Technology GmbH Composant mécanique
US10612396B2 (en) 2017-07-05 2020-04-07 General Electric Technology Gmbh Mechanical component

Also Published As

Publication number Publication date
EP0899425B1 (fr) 2003-12-03
CN1211667A (zh) 1999-03-24
JPH11132003A (ja) 1999-05-18
US6033181A (en) 2000-03-07
CN1120287C (zh) 2003-09-03
DE19738065A1 (de) 1999-03-04
EP0899425A3 (fr) 2000-07-05
DE59810315D1 (de) 2004-01-15

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