EP2083147B1 - Filmkühlstruktur - Google Patents

Filmkühlstruktur Download PDF

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Publication number
EP2083147B1
EP2083147B1 EP07738382.6A EP07738382A EP2083147B1 EP 2083147 B1 EP2083147 B1 EP 2083147B1 EP 07738382 A EP07738382 A EP 07738382A EP 2083147 B1 EP2083147 B1 EP 2083147B1
Authority
EP
European Patent Office
Prior art keywords
film cooling
hole
combustion gas
structural wall
flow direction
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.)
Active
Application number
EP07738382.6A
Other languages
English (en)
French (fr)
Other versions
EP2083147A1 (de
EP2083147A4 (de
Inventor
Yoji Ohkita
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.)
IHI Corp
Original Assignee
IHI Corp
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 IHI Corp filed Critical IHI Corp
Publication of EP2083147A1 publication Critical patent/EP2083147A1/de
Publication of EP2083147A4 publication Critical patent/EP2083147A4/de
Application granted granted Critical
Publication of EP2083147B1 publication Critical patent/EP2083147B1/de
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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
    • F01D5/186—Film 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to a film cooling structure that is suitable for film cooling of the surface of a component (turbine blade or the like) of a gas turbine engine.
  • a film cooling structure according to the preamble of claim 1 is known from GB 2 409 243 A .
  • a gas turbine engine The efficiency of a gas turbine engine is increased as combustion gas temperature rises.
  • the combustion gas heats a structural wall of a component (a combustor liner, a turbine blade, a turbine shroud, or the like), that is disposed on a flow passage for combustion gas, to high temperature.
  • a film cooling structure In the cooling structure, a cooling passage is formed therein, convection cooling is performed by making cooling air flow through the cooling passage, and film cooling is performed by making the cooling air be ejected from film cooling holes onto a surface, which is exposed to high-temperature combustion gas, in the shape of a film (for example, see the following Patent Documents 1 to 5).
  • Figs. 1A to 1C show an example of a film cooling structure 30 of the related art.
  • Fig. 1B is a cross-sectional view taken along a line 1B-1B of Fig. 1A
  • Fig. 1C is a cross-sectional view taken along a line 1C-1C of Fig. 1B .
  • a structural wall 31 has an outer surface 32 that is exposed to combustion gas 1, and an inner surface 33 that is positioned opposite to the outer surface 32.
  • Film cooling holes 34 are formed at the structural wall 31 so as to be inclined with respect to the outer surface 32 by a predetermined angle, and introduce cooling air 5 from the inner surface 33 toward the outer surface 32 in order to perform the film cooling of the outer surface 32.
  • the film cooling hole 34 includes an introducing portion 34a that extends to a middle position in the structural wall 31 from the inner surface 33 toward the outer surface 32, and an enlarged portion 34b (diffuser) of which the cross-sectional area is gradually increased toward the outer surface 32 from an end of the introducing portion 34a facing the outer surface 32 and which is opened at the outer surface 32.
  • a wall surface 35 of the enlarged portion 34b facing an upstream side in the flow direction of the combustion gas 1 is formed in a linear shape.
  • both wall surfaces 36 and 36 of the enlarged portion 34b in a direction perpendicular to the flow direction of the combustion gas 1 are formed in a linear shape.
  • cooling air 5 As for film cooling, it is preferable to spread the cooling air 5 on the outer surface 32, which is to be cooled, as thinly and broadly as possible, and to attach the cooling air to the outer surface 32 as close as possible. Accordingly, in order to spread the cooling air 5 thinly and broadly on the outer surface 32, it is effective to increase an enlarged angle of the enlarged portion 34b as much as possible.
  • the cross-sectional area of the hole is linearly increased at the enlarged portion 34b of the above-mentioned film cooling structure 30 in the related art. Accordingly, if an enlarged angle of the enlarged portion 34b is excessively large, the separation of the cooling air 5 occurs in the hole. For this reason, there have been problems that the cooling air 5 is not effectively diffused and it is difficult to improve average film cooling efficiency.
  • the invention has been made in consideration of the above-mentioned problems, and an object of the invention is to provide a film cooling structure that can increase an enlarged angle of an enlarged portion and improve average film cooling efficiency.
  • the invention provides a film cooling structure according to claim 1.
  • a film cooling structure that includes a structural wall that has an outer surface exposed to combustion gas and an inner surface positioned opposite to the outer surface, and film cooling holes are formed at the structural wall and introduce cooling air from the inner surface toward the outer surface in order to perform film cooling of the outer surface.
  • the film cooling hole includes an introducing portion that extends to a middle position in the structural wall from the inner surface toward the outer surface, an enlarged portion of which the cross-sectional area is gradually increased toward the outer surface from an end of an outer surface side of the introducing portion and which is opened at the outer surface, and a partition portion that partitions the inside of the enlarged portion into a plurality of spaces in a width direction of the hole perpendicular to a flow direction of the combustion gas.
  • the film cooling hole includes the partition portion that has been formed as described above, an effective area expansion ratio may be reduced. Accordingly, even though the enlarged angle of the enlarged portion in a transverse direction is large, the separation of the cooling air is suppressed. Therefore, since it is possible to effectively diffuse cooling air as compared to the related art, the enlarged angle of the enlarged portion in the transverse direction can be made large. As a result, it is possible to spread the cooling air thinly and broadly on the outer surface of the structural wall, and to improve average film cooling efficiency. Meanwhile, the definition of the average film cooling efficiency will be described below.
  • the number of film cooling holes formed at the structural wall may be reduced. Accordingly, the number of processes for manufacturing the film cooling structure can be reduced. Furthermore, as the number of film cooling holes is reduced, the amount of cooling air extracted from the compressor of the gas turbine engine can be decreased. Therefore, engine efficiency can be improved.
  • the partition portion is formed at a middle position of the inside of the film cooling hole in the width direction of the hole perpendicular to the flow direction of the combustion gas, protrudes from one of the wall surfaces facing upstream and downstream sides in the flow direction of the combustion gas toward the other thereof, and extends over the entire inside of the hole from the inner surface of the structural wall toward the outer surface.
  • the partition portion does not completely partition the film cooling hole in the transverse direction, and extends over the entire structural wall in a thickness direction. Therefore, it is easy to form the film cooling hole.
  • a film cooling structure according to the invention is applied to a component that is disposed on a flow passage for combustion gas in a gas turbine engine.
  • this component include a combustor liner, a turbine nozzle vane, a turbine nozzle band, a turbine rotating blade, a turbine stator blade, a turbine shroud, and a turbine outlet liner.
  • Fig. 2 is a perspective view of a turbine rotating blade 2 to which the film cooling structure 10 according to the invention is applied.
  • the turbine rotating blade 2 includes a blade portion 3 that serves as a structural wall having an outer surface 12 exposed to combustion gas 1, and a base portion 4 that is used to mount the blade portion 3 on a rotor of an engine.
  • a cooling circuit (not shown) through which cooling air flows is formed in the blade portion 3. This cooling air is extracted from a compressor of a gas turbine engine, and flows into the cooling circuit through a flow passage (not shown) that is formed in the base portion 4.
  • the cooling air which has flown into the cooling circuit, is ejected from a plurality of film cooling holes 14 that is formed on an outer surface 12 of the blade portion 3, and performs film cooling on the outer surface 12 of the blade portion 3.
  • the film cooling structure 10 according to an embodiment of the invention will be described below.
  • Figs. 3A to 3C show the film cooling structure 10 according to the invention.
  • Fig. 3A is a plan view of the film cooling structure 10.
  • Fig. 3B is a cross-sectional view taken along a line 3B-3B of Fig. 3A.
  • Fig. 3C is a cross-sectional view taken along a line 3C-3C of Fig. 3B .
  • Fig. 4 is a perspective view showing the shape of the film cooling hole 14 of the film cooling structure 10 according to the embodiment of the invention.
  • the film cooling structure 10 is applied to a component such as a turbine rotating blade that is disposed on a flow passage for combustion gas 1 in a gas turbine engine.
  • the film cooling structure 10 includes a structural wall 11 that has the outer surface 12 exposed to the combustion gas 1 and an inner surface 13 positioned opposite to the outer surface 12. If the component of the gas turbine is, for example, a turbine rotating blade, a wall forming the blade portion of the turbine rotating blade is the structural wall 11. Cooling air 5 flows into the inner surface 13 of the structural wall 11.
  • the film cooling hole 14, which introduces the cooling air 5 from the inner surface 13 to the outer surface 12 in order to perform the film cooling of the outer surface 12, is formed in the structural wall 11. As shown in Fig. 3B , an axis of the film cooling hole 14 is inclined with respect to the outer surface 12 of the structural wall 11 by a predetermined angle so that the cooling air 5 is blown from the film cooling hole 14 in a direction corresponding to the flow of the combustion gas 1.
  • the film cooling hole 14 includes an introducing portion 14a that extends to a middle position in the structural wall 11 from the inner surface 13 toward the outer surface 12, and an enlarged portion 14b of which the cross-sectional area is gradually increased toward the outer surface 12 from an end of an outer surface side of the introducing portion 14a and which is opened at the outer surface 12.
  • the film cooling hole 14 further includes a partition portion 16 that partitions the inside of the enlarged portion 14b into a plurality of spaces in a width direction of the hole perpendicular to the flow direction of the combustion gas 1.
  • the "width direction of the hole perpendicular to the flow direction of the combustion gas 1" is a direction perpendicular to the plane of in Fig. 3B , and is a horizontal direction in Fig. 3C .
  • the partition portion 16 is formed at a middle position of the inside of the film cooling hole 14 in the width direction of the hole perpendicular to the flow direction of the combustion gas 1, protrudes from the wall surface facing an upstream side in the flow direction of the combustion gas 1 toward the upstream side in the flow direction of the combustion gas 1, and extends over the entire inside of the hole from the inner surface 13 of the structural wall 11 toward the outer surface 12.
  • a gap is formed between the partition portion 16 and a wall surface facing a downstream side in the flow direction of the combustion gas 1.
  • One partition portion 16 has been formed in the embodiment shown in Figs. 3A to 3C and 4 , but a plurality of partition portions may be formed at intervals in the width direction of the hole.
  • the partition portion 16 has protruded from the wall surface facing the upstream side in the flow direction of the combustion gas 1 toward the upstream side in the flow direction of the combustion gas 1.
  • the partition portion may protrude from the wall surface facing a downstream side in the flow direction of the combustion gas 1 toward the downstream side in the flow direction of the combustion gas 1.
  • a gap is formed between the partition portion 16 and a wall surface facing the upstream side in the flow direction of the combustion gas 1.
  • Fig. 5 is a graph where a length ratio is represented on a horizontal axis in logarithmic scale, a value obtained by subtracting 1 from an inlet-outlet area ratio is represented on a vertical axis in logarithmic scale, and a pressure recovery rate (reduction rate) Cp is used as a parameter, as for a diffuser.
  • a pressure recovery rate reduction rate
  • a straight line of Cp * is a line where the maximum pressure recovery rate is obtained when a length ratio is constant. Accordingly, it is found out that if an inlet-outlet area ratio is constant, when an enlarged angle is small, a pressure recovery rate is high and separation hardly does occur. If a passage of the diffuser is divided into two or three equal parts, an enlarged angle of each of the small passages becomes a half or a third and becomes smaller than an enlarged angle determined by Cp * . For this reason, a high pressure recovery rate is obtained over the entire passage.
  • the film cooling hole 14 includes the partition portion 16 formed as described above, an effective area expansion ratio is suppressed. Therefore, even though an enlarged angle of the enlarged portion 14b is increased in a transverse direction, the separation of the cooling air 5 is suppressed. For this reason, since it is possible to effectively diffuse the cooling air 5 as compared to the related art, the enlarged angle of the enlarged portion 14b in the transverse direction can be increased. Accordingly, it is possible to spread the cooling air 5 thinly and broadly on the outer surface 12 of the structural wall 11, and to improve average film cooling efficiency. In this case, the average film cooling efficiency is given by (fuel gas temperature-surface temperature of structural wall)/(combustion gas temperature-cooling air temperature).
  • the number of film cooling holes 14 formed at the structural wall 11 can be reduced. For this reason, the number of processes for manufacturing the film cooling structure 10 can be reduced. Further, as the number of film cooling holes 14 is reduced, the amount of cooling air extracted from the compressor of the gas turbine engine can be decreased. Therefore, engine efficiency can be improved.
  • the film cooling holes 14 are formed using a method such as electric discharge machining, an electric discharge machining electrode needs to be inserted into each of the divided holes in order to form holes if the partition portion 16 completely partitions the film cooling hole 14 in a transverse direction. Further, if the partition portion 16 is formed in a shape that is broken at a position in a thickness direction of the structural wall 11, a plurality of processes is required to form one film cooling hole 14 (for example, electric discharge machining electrodes need to be inserted from the outer surface 12 and the inner surface 13 in order to form the hole.) Furthermore, even though other machining means is used, forming processes are complicated likewise.
  • the partition portion 16 does not completely partition the film cooling hole 14 in the transverse direction, and extends over the entire structural wall 11 in the thickness direction. Accordingly, if an electric discharge machining electrode, which is formed to form the film cooling hole 14 shown in Figs. 3A to 3C and 4 , is inserted from the outer surface 12, it is possible to form the film cooling hole 14 by a single process. Therefore, it is easy to form the film cooling hole 14.
  • the embodiment of the invention has been described above.
  • the above-mentioned embodiment of the invention is only illustrative, and the scope of the invention is not limited to the embodiment of the invention.
  • the invention has been applied to the turbine rotating blade 2 in the above-mentioned embodiment, but may be applied to other components, such as a combustor liner, a turbine nozzle vane, a turbine nozzle band, a stationary turbine blade, a turbine shroud, and a turbine outlet liner, which are disposed on a flow passage for combustion gas in a gas turbine engine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)

Claims (1)

  1. Filmkühlungs-Struktur (10), die umfasst:
    eine strukturelle Wand (11), die eine Außenfläche (12), die Verbrennungsgas (1) ausgesetzt ist, und eine Innenfläche (13) aufweist, die der Außenfläche (12) gegenüberliegend angeordnet ist,
    wobei Filmkühlungs-Löcher (14) in der strukturellen Wand (11) ausgebildet sind und Kühlluft (5) von der Innenfläche (13) in Richtung der Außenfläche (12) leiten, um Filmkühlung der Außenfläche (12) durchzuführen,
    das Filmkühlungs-Loch (14) einen Einleitabschnitt (14a), der sich zu einer mittleren Position in der strukturellen Wand (11) von der Innenfläche (13) auf die Außenfläche (12) zu erstreckt, einen aufgeweiteten Abschnitt (14b), dessen Querschnittsfläche von einer Seite am Ende einer Außenfläche (12) des Einleitabschnitts (14a) auf die Außenfläche (12) zu allmählich größer wird und der sich an der Außenfläche (12) öffnet, sowie einen Trennabschnitt (16) enthält, der den Innenraum des aufgeweiteten Abschnitts (14b) in eine Vielzahl" von Räumen in einer Breitenrichtung des Lochs (14) senkrecht zu einer Strömungsrichtung des Verbrennungsgases (1) trennt,
    wobei der Trennabschnitt (16) an einer mittleren Position des Innenraums des Filmkühlungs-Lochs (14) in der Breitenrichtung des Lochs (14) senkrecht zu der Strömungsrichtung des Verbrennungsgases (1) ausgebildet ist,
    dadurch gekennzeichnet, dass
    der Trennabschnitt (16) von einer der Wandflächen, die stromauf und stromab liegenden Seiten in der Strömungsrichtung des Verbrennungsgases (1) zugewandt sind, auf die andere derselben zu vorsteht, jedoch das Filmkühlungs-Loch (14) in der Breitenrichtung nicht vollständig trennt, und
    sich der Trennabschnitt (16) über den gesamten Innenraum des Lochs (14) von der Innenfläche (13) der strukturellen Wand (11) auf die Außenfläche (12) zu erstreckt.
EP07738382.6A 2006-11-13 2007-03-13 Filmkühlstruktur Active EP2083147B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2006306538A JP4941891B2 (ja) 2006-11-13 2006-11-13 フィルム冷却構造
PCT/JP2007/054910 WO2008059620A1 (en) 2006-11-13 2007-03-13 Film cooling structure

Publications (3)

Publication Number Publication Date
EP2083147A1 EP2083147A1 (de) 2009-07-29
EP2083147A4 EP2083147A4 (de) 2014-05-14
EP2083147B1 true EP2083147B1 (de) 2015-10-07

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EP07738382.6A Active EP2083147B1 (de) 2006-11-13 2007-03-13 Filmkühlstruktur

Country Status (5)

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US (1) US20100040459A1 (de)
EP (1) EP2083147B1 (de)
JP (1) JP4941891B2 (de)
CA (1) CA2668750C (de)
WO (1) WO2008059620A1 (de)

Families Citing this family (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8371814B2 (en) * 2009-06-24 2013-02-12 Honeywell International Inc. Turbine engine components
US8529193B2 (en) * 2009-11-25 2013-09-10 Honeywell International Inc. Gas turbine engine components with improved film cooling
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US8672613B2 (en) * 2010-08-31 2014-03-18 General Electric Company Components with conformal curved film holes and methods of manufacture
US8858175B2 (en) * 2011-11-09 2014-10-14 General Electric Company Film hole trench
JP5982807B2 (ja) * 2011-12-15 2016-08-31 株式会社Ihi タービン翼
US9284844B2 (en) * 2012-02-15 2016-03-15 United Technologies Corporation Gas turbine engine component with cusped cooling hole
US10422230B2 (en) 2012-02-15 2019-09-24 United Technologies Corporation Cooling hole with curved metering section
US9273560B2 (en) * 2012-02-15 2016-03-01 United Technologies Corporation Gas turbine engine component with multi-lobed cooling hole
US8689568B2 (en) 2012-02-15 2014-04-08 United Technologies Corporation Cooling hole with thermo-mechanical fatigue resistance
US8850828B2 (en) 2012-02-15 2014-10-07 United Technologies Corporation Cooling hole with curved metering section
US8763402B2 (en) * 2012-02-15 2014-07-01 United Technologies Corporation Multi-lobed cooling hole and method of manufacture
US8683813B2 (en) * 2012-02-15 2014-04-01 United Technologies Corporation Multi-lobed cooling hole and method of manufacture
US9024226B2 (en) * 2012-02-15 2015-05-05 United Technologies Corporation EDM method for multi-lobed cooling hole
US8683814B2 (en) 2012-02-15 2014-04-01 United Technologies Corporation Gas turbine engine component with impingement and lobed cooling hole
US20130209235A1 (en) * 2012-02-15 2013-08-15 United Technologies Corporation Gas turbine engine component with cusped, lobed cooling hole
US8584470B2 (en) * 2012-02-15 2013-11-19 United Technologies Corporation Tri-lobed cooling hole and method of manufacture
US9422815B2 (en) 2012-02-15 2016-08-23 United Technologies Corporation Gas turbine engine component with compound cusp cooling configuration
US9650900B2 (en) 2012-05-07 2017-05-16 Honeywell International Inc. Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
JP2015520322A (ja) * 2012-06-13 2015-07-16 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジンの壁
US10113433B2 (en) * 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
JP6348965B2 (ja) 2013-03-15 2018-06-27 ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ 冷却孔内に構造物を付加するための付加製造方法
US10030524B2 (en) * 2013-12-20 2018-07-24 Rolls-Royce Corporation Machined film holes
JP6222876B2 (ja) 2014-04-03 2017-11-01 三菱日立パワーシステムズ株式会社 翼列、ガスタービン
US11313235B2 (en) * 2015-03-17 2022-04-26 General Electric Company Engine component with film hole
US10208602B2 (en) * 2015-04-27 2019-02-19 United Technologies Corporation Asymmetric diffuser opening for film cooling holes
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US10605092B2 (en) * 2016-07-11 2020-03-31 United Technologies Corporation Cooling hole with shaped meter
KR101853550B1 (ko) 2016-08-22 2018-04-30 두산중공업 주식회사 가스 터빈 블레이드
JP2019535987A (ja) * 2016-09-01 2019-12-12 アッディティブ ロケット コーポレーション 構造的熱交換器
EP3354849A1 (de) * 2017-01-31 2018-08-01 Siemens Aktiengesellschaft Wand für heissgasbauteil und zugehöriges heissgasbauteil für eine gasturbine
MX2020001518A (es) 2017-08-11 2020-03-20 Archroma Ip Gmbh Metodos para fabricar soluciones de sal de leucoindigo con muy bajo contenido de anilina.
US10933481B2 (en) * 2018-01-05 2021-03-02 General Electric Company Method of forming cooling passage for turbine component with cap element
US11286792B2 (en) * 2019-07-30 2022-03-29 Rolls-Royce Plc Ceramic matrix composite vane with cooling holes and methods of making the same

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3936223A (en) * 1974-09-23 1976-02-03 General Motors Corporation Compressor diffuser
US4529358A (en) * 1984-02-15 1985-07-16 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Vortex generating flow passage design for increased film cooling effectiveness
JPH0693802A (ja) * 1992-09-14 1994-04-05 Hitachi Ltd ガスタ−ビン静翼
JP2810023B2 (ja) * 1996-09-18 1998-10-15 株式会社東芝 高温部材冷却装置
JP2001012204A (ja) * 1999-06-30 2001-01-16 Toshiba Corp ガスタービン翼
US6234755B1 (en) 1999-10-04 2001-05-22 General Electric Company Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture
JP2002221005A (ja) * 2001-01-26 2002-08-09 Ishikawajima Harima Heavy Ind Co Ltd 冷却タービン翼
US6629817B2 (en) 2001-07-05 2003-10-07 General Electric Company System and method for airfoil film cooling
US7008186B2 (en) 2003-09-17 2006-03-07 General Electric Company Teardrop film cooled blade
JP3997986B2 (ja) * 2003-12-19 2007-10-24 株式会社Ｉｈｉ 冷却タービン部品、及び冷却タービン翼
US7328580B2 (en) 2004-06-23 2008-02-12 General Electric Company Chevron film cooled wall
JP4898253B2 (ja) * 2005-03-30 2012-03-14 三菱重工業株式会社 ガスタービン用高温部材

Also Published As

Publication number Publication date
US20100040459A1 (en) 2010-02-18
WO2008059620A1 (en) 2008-05-22
EP2083147A1 (de) 2009-07-29
CA2668750C (en) 2012-06-19
JP2008121561A (ja) 2008-05-29
CA2668750A1 (en) 2008-05-22
JP4941891B2 (ja) 2012-05-30
EP2083147A4 (de) 2014-05-14

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