CN101161997B - 用于重型燃气涡轮机的涡轮机壳体冲击冷却 - Google Patents

用于重型燃气涡轮机的涡轮机壳体冲击冷却 Download PDF

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CN101161997B
CN101161997B CN2007101807840A CN200710180784A CN101161997B CN 101161997 B CN101161997 B CN 101161997B CN 2007101807840 A CN2007101807840 A CN 2007101807840A CN 200710180784 A CN200710180784 A CN 200710180784A CN 101161997 B CN101161997 B CN 101161997B
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impingement cooling
cooling manifold
manifold
holes
turbine
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CN101161997A (zh
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D·M·埃里克森
张华�
J·西尔
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General Electric Co PLC
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    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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

Abstract

用于重型涡轮机的冲击冷却系统，其包括附接到重型涡轮机的壳体的冲击冷却歧管，其中冲击冷却歧管在冲击冷却歧管的表面中包括多个冲击孔，和鼓风机，其提供通过冲击冷却歧管的多个冲击孔以冷却重型涡轮机的壳体的空气流，以控制涡轮机叶片尖端和重型涡轮机的罩之间的间隙。

Description

用于重型燃气涡轮机的涡轮机壳体冲击冷却
背景技术
空气冲击冷却已经用于控制小燃气涡轮机的壳体温度且用于减少并维持旋转叶片和附随的内部壳体表面之间的间隙。在重型燃气涡轮机上的空气冲击冷却系统的一个问题是获得通过大的非一致非标准的壳体表面的一致的传热系数的能力。在小燃气涡轮机上，通常应用小的冲击孔和短的喷嘴到表面距离。这些因素产生壳体上要求的更高的传热系数。应用小的冲击冷却孔的一个有害影响为需要操作在通过孔的高差压降下。这导致不希望的高冷却空气供应压力的要求，其负面地影响净效率。
作为一种涡轮机间隙控制方法，冲击冷却已经应用于飞行器发动机。然而，在飞行器发动机上使用的冲击系统不能在重型涡轮机应用中使用。应用到飞行器发动机的系统采用从压缩机排出的空气作为冷却媒介。由于设计传热系数要求更冷的空气温度，在重型燃气涡轮机上使用压缩机排出空气是不可行的。重型燃气涡轮机具有显著大的、非一致的壳体表面，与飞行器发动机相比其要求复杂的歧管设计。同样，壳体厚度和壳体厚度变化在重型燃气涡轮机上相当大。
目前，本领域中要求能够在重型燃气涡轮机上提供间隙控制的冲击冷却系统。这种系统将要求的传热系数合适地提供到目标壳体表面，且合适地控制空气到壳体的流动是基本的。
附图说明
图1为依据本发明的实施例的重型燃气涡轮机的截面图；
图2为依据本发明的实施例的涡轮机叶片到罩间隙的特写图；
图3为依据本发明的实施例的冲击冷却系统；
图4为依据本发明的实施例的冲击冷却歧管的透视图；
图5为依据本发明的实施例的冲击冷却歧管的截面图；
图6为依据本发明的实施例的在涡轮机壳体上安装的冲击冷却歧管的透视图。
具体实施方式
现在，本发明将参见附图在下文中更全面地描述，其中显示本发明的示范性的实施例。然而，本发明可以以许多不同的形式实施且不应该解释为限于在此陈列的实施例；相反，提供这些实施例使得本披露详尽和完整，且将本发明的范围传达给本领域中的技术人员。
图1图示重型涡轮机110的示范性实施例。重型涡轮发动机包括压缩机段112、燃烧器段114和涡轮机段116。涡轮机110也包括压缩机壳体118和涡轮机壳体120。涡轮机和压缩机壳体118、120包围重型涡轮机的主要部件。涡轮机段116包括轴和多组旋转和静止涡轮机叶片。
参见图1，涡轮机壳体120可以包括附接到壳体120的内部表面的罩126。罩126可以定位为接近旋转涡轮机叶片122的尖端，以最小化通过叶片尖端123的空气泄漏。叶片尖端123和罩126之间的距离称为间隙128。需要注意的是，由于叶片和壳体的不同热增长特性，每个涡轮机级的间隙128不一致。
重型燃气涡轮机效率的关键贡献者为通过叶片尖端123到壳体间隙128的空气/排出气体泄漏数量。图2图示涡轮机叶片尖端123和涡轮机壳体120中罩126之间的间隙128的示范性实施例。由于涡轮机叶片尖端123和涡轮机壳体120的不同的热增长特性，当涡轮机通过从点火到基本载荷稳定状态条件的瞬态过渡时，间隙128显著地改变。间隙控制系统，包括其操作顺序，可以实施以解决在全操作条件期间的特定的间隙特性问题。控制系统的不正确的设计和/或者定序可以导致涡轮机叶片尖端123与壳体罩126的过大的摩擦，其能够导致增加的间隙和减少的性能。
如在图3的示范性的实施例中图示的，冲击空气冷却系统200可以用于减少并维持在涡轮机罩126和附随的叶片尖端123之间的间隙。参见图3，冲击空气冷却系统200可以包括鼓风机130、流动控制阻尼器132、互连管道134、分配集管136、流动计量阀或者孔口138和一系列冲击冷却歧管140。冲击冷却歧管附接到涡轮机壳体。在图3示范性的实施例中，多个冲击歧管140围绕涡轮机壳体120的周边附接。冲击冷却鼓风机130从环境空气抽吸且将空气鼓风通过流动控制阻尼器132、互连管道134、分配集管136、流动计量阀或者孔口138且进入冲击冷却歧管140。鼓风机130可以为包括风扇或者喷射器的任何鼓凤设备。冲击冷却歧管140确保将一致的传热系数提供到涡轮机壳体120。需要理解的是，冲击空气冷却系统不限于在此披露的元件，而可以包括使空气能够沿冲击冷却歧管通过的任何元件。
参见在图4和5中图示的示范性的实施例，冲击冷却歧管140可以设计为涡轮机壳体120的目标区域的轮廓。每个冲击冷却歧管140可以包括带有进给管144的上部板142、带有多冲击孔148的下部板146、侧部件、支撑腿150和压紧支撑件152。冲击孔148允许空气从冲击冷却歧管流动到涡轮机壳体，以选择性地冷却涡轮机壳体。
冲击孔148以阵列形式定位。在示范性的实施例中，冲击孔148可以1.25-2.5英寸范围间隔。在示范性的实施例中，单独冲击孔148可以定尺寸在0.12-0.2英寸之间。要求不同的孔尺寸和间隔以补偿涡轮机壳体几何形状的非一致性。在下部板146上的冲击孔148的尺寸和定位产生由冲击空气冷却系统确定目标的通过壳体的一致的传热系数。然而，冲击孔不限于这些尺寸或者间隔。上部板142和下部板146之间的距离也可以定尺度以最小化内部压力变化，其导致一致的冷却孔压力比。
冲击冷却歧管下部板146和涡轮机壳体120之间的间距距离影响传热系数。过大的间距能够导致非最优的传热系数。过小的间距能够导致非最优和非一致的传热系数。在示范性的实施例中，0.5-1.0英寸之间的间距提供合适的传热系数。然而，间距并不限于这个范围且可以为提供合适的传热系数的任何距离。
如图6中图示的，多冲击冷却歧管140在目标冷却区域直接上方附接到涡轮机的壳体120。冲击冷却歧管140定位为使得在其边缘和壳体的任何凸出之间有充足的间隙。这提供空气通过冲击孔148以从冲击冷却歧管140下排出到环境的自由路径。在示范性的实施例中，两个相邻冲击冷却歧管之间的间隙可以为1-30英寸之间且取决于壳体凸出和带凸缘接合处。间隙并不限于这些尺度且可以间隔任何合适的距离。冲击冷却歧管140也可以将冲击冷却提供到任何轴向凸缘，包括水平拼接处。
受益于前文说明书和相关附图中提出的教示，本发明所属领域技术人员将想到本发明的许多修改和其他实施例。因此，需要理解的是，本发明不限于披露的特定实施例，且修改和其他实施例意欲包括在附上的权利要求书的范围内。尽管在此采用特定的术语，他们仅用于一般的和描述的意义而不为限制的目的。
零件列表
重型涡轮机110
压缩机段112
燃烧器段114
涡轮机段116
压缩机壳体118
涡轮机壳体120
涡轮机叶片122
叶片尖端123
罩126
间隙128
鼓风机130
流动控制阻尼器132
互连管道134
分配集管136
孔口138
冲击冷却歧管140
上部板142
进给管144
下部板146
冲击孔148
支撑腿150
压紧支撑件152
冲击空气冷却系统200

Claims (9)

1.一种用于重型涡轮机(110)的冲击冷却系统(200)，其包括：
附接到所述重型涡轮机(110)的壳体(120)的冲击冷却歧管(140)，其中所述冲击冷却歧管(140)在该冲击冷却歧管(140)的表面中包括多个冲击孔(148)；和
鼓风机(130)，其提供通过所述冲击冷却歧管(140)的所述多个冲击孔(148)以冷却所述重型涡轮机(110)的壳体(120)的空气流，以控制涡轮机叶片尖端(123)和所述重型涡轮机(110)的罩(126)之间的间隙(128)；且
所述冲击冷却歧管(140)包括以一距离定位的上部板(142)和下部板(146)，以提供通过所述多个孔(148)的大致一致的压力比。
2.根据权利要求1所述的系统，其中所述多个冲击孔(148)位于所述冲击冷却歧管(140)的下部板(146)上。
3.根据权利要求1所述的系统，其中所述多个孔(148)定位为通过所述冲击冷却歧管(140)的一致的阵列。
4.根据权利要求1所述的系统，其中所述多个孔(148)定位为通过所述冲击冷却歧管(140)的非一致的阵列。
5.根据权利要求1所述的系统，其中所述多个孔(148)直径一致。
6.根据权利要求1所述的系统，其中所述多个孔(148)直径不一致。
7.根据权利要求1所述的系统，其中所述多个孔(148)从包括大致圆形、卵形、椭圆形、方形、三角形和长方形的形状选择。
8.根据权利要求1所述的系统，其中涡轮机叶片(122)包括旋转叶片。
9.根据权利要求1所述的系统，其中所述冲击冷却歧管(140)包括围绕所述重型涡轮机(110)的壳体(120)的周边定位的多个冲击冷却歧管(140)。
CN2007101807840A 2006-10-12 2007-10-12 用于重型燃气涡轮机的涡轮机壳体冲击冷却 Active CN101161997B (zh)

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US11/548,791 US8801370B2 (en) 2006-10-12 2006-10-12 Turbine case impingement cooling for heavy duty gas turbines

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004017008B4 (de) * 2004-04-02 2009-10-22 Aloys Wobben Verfahren zum Errichten eines Turmes
DE102004017006B4 (de) * 2004-04-02 2012-03-29 Aloys Wobben Verfahren zum Errichten eines Turmes
US8801370B2 (en) * 2006-10-12 2014-08-12 General Electric Company Turbine case impingement cooling for heavy duty gas turbines
US7837429B2 (en) * 2006-10-12 2010-11-23 General Electric Company Predictive model based control system for heavy duty gas turbines
US8251637B2 (en) * 2008-05-16 2012-08-28 General Electric Company Systems and methods for modifying modal vibration associated with a turbine
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US8061971B2 (en) * 2008-09-12 2011-11-22 General Electric Company Apparatus and method for cooling a turbine
US8123406B2 (en) * 2008-11-10 2012-02-28 General Electric Company Externally adjustable impingement cooling manifold mount and thermocouple housing
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JP5478576B2 (ja) * 2011-09-20 2014-04-23 株式会社日立製作所 ガスタービン
US9011079B2 (en) 2012-01-09 2015-04-21 General Electric Company Turbine nozzle compartmentalized cooling system
US9039350B2 (en) 2012-01-09 2015-05-26 General Electric Company Impingement cooling system for use with contoured surfaces
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US9011078B2 (en) 2012-01-09 2015-04-21 General Electric Company Turbine vane seal carrier with slots for cooling and assembly
US8944751B2 (en) 2012-01-09 2015-02-03 General Electric Company Turbine nozzle cooling assembly
US9133724B2 (en) 2012-01-09 2015-09-15 General Electric Company Turbomachine component including a cover plate
US9115595B2 (en) * 2012-04-09 2015-08-25 General Electric Company Clearance control system for a gas turbine
US9422824B2 (en) 2012-10-18 2016-08-23 General Electric Company Gas turbine thermal control and related method
US9238971B2 (en) 2012-10-18 2016-01-19 General Electric Company Gas turbine casing thermal control device
CA2949539A1 (en) * 2014-05-29 2016-02-18 General Electric Company Engine components with impingement cooling features
CN105089719B (zh) * 2015-06-11 2017-03-01 中国石油天然气股份有限公司 冷却分布器和汽轮机
FR3040429B1 (fr) * 2015-08-27 2019-06-07 Safran Aircraft Engines Dispositif de fixation des rampes de refroidissement par jets d'air du carter d'une turbine de turbomachine
CN106555619B (zh) * 2015-09-30 2018-07-24 中国航发商用航空发动机有限责任公司 燃气轮机叶尖间隙的控制装置和方法
US10502137B2 (en) * 2015-10-19 2019-12-10 General Electric Company Gas turbine with a valve cooling system
CN107795383B (zh) * 2016-08-29 2019-08-06 中国航发商用航空发动机有限责任公司 一种燃气轮机冷却气分配系统
US10428676B2 (en) 2017-06-13 2019-10-01 Rolls-Royce Corporation Tip clearance control with variable speed blower
FR3073007B1 (fr) * 2017-10-27 2019-09-27 Safran Aircraft Engines Dispositif de maintien d'un tube de refroidissement pour carter de turbomachine
FR3082872B1 (fr) * 2018-06-25 2021-06-04 Safran Aircraft Engines Dispositif de refroidissement d'un carter de turbomachine
FR3085719B1 (fr) * 2018-09-06 2021-04-16 Safran Aircraft Engines Boitier d'alimentation en air sous pression d'un dispositif de refroidissement par jets d'air
CN114198153B (zh) * 2020-09-17 2024-05-03 中国航发商用航空发动机有限责任公司 涡轮叶片冷却系统及航空发动机
DE102020007518A1 (de) 2020-12-09 2022-06-09 Svetlana Beck Verfahren zum Erreichen von hohen Gastemperaturen unter Verwendung von Zentrifugalkraft
JP2023100250A (ja) 2022-01-05 2023-07-18 ゼネラル・エレクトリック・カンパニイ 排気フレーム差動冷却システム

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2650753A (en) * 1947-06-11 1953-09-01 Gen Electric Turbomachine stator casing
US4251185A (en) * 1978-05-01 1981-02-17 Caterpillar Tractor Co. Expansion control ring for a turbine shroud assembly
US5399066A (en) * 1993-09-30 1995-03-21 General Electric Company Integral clearance control impingement manifold and environmental shield
US6615588B2 (en) * 2000-12-22 2003-09-09 Alstom (Switzerland) Ltd Arrangement for using a plate shaped element with through-openings for cooling a component

Family Cites Families (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966354A (en) * 1974-12-19 1976-06-29 General Electric Company Thermal actuated valve for clearance control
US4279123A (en) * 1978-12-20 1981-07-21 United Technologies Corporation External gas turbine engine cooling for clearance control
US4337016A (en) * 1979-12-13 1982-06-29 United Technologies Corporation Dual wall seal means
US4338061A (en) * 1980-06-26 1982-07-06 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Control means for a gas turbine engine
JPS59173527A (ja) 1983-03-22 1984-10-01 Hitachi Ltd ガスタ−ビン排気フレ−ム冷却空気系統
US4467134A (en) * 1983-06-30 1984-08-21 General Electric Company Thermocouple with out-of-line aspiration holes
US4573806A (en) * 1985-05-02 1986-03-04 Semco Instruments, Inc. Thermocouple isolation block system
JPS63154806A (ja) 1986-12-19 1988-06-28 Mitsubishi Heavy Ind Ltd 回転機械の翼端間隙調節装置
US4928240A (en) * 1988-02-24 1990-05-22 General Electric Company Active clearance control
US5012420A (en) * 1988-03-31 1991-04-30 General Electric Company Active clearance control for gas turbine engine
US4826397A (en) * 1988-06-29 1989-05-02 United Technologies Corporation Stator assembly for a gas turbine engine
US5100291A (en) * 1990-03-28 1992-03-31 General Electric Company Impingement manifold
US5116199A (en) * 1990-12-20 1992-05-26 General Electric Company Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion
US5281085A (en) 1990-12-21 1994-01-25 General Electric Company Clearance control system for separately expanding or contracting individual portions of an annular shroud
US5160241A (en) * 1991-09-09 1992-11-03 General Electric Company Multi-port air channeling assembly
US5205115A (en) * 1991-11-04 1993-04-27 General Electric Company Gas turbine engine case counterflow thermal control
US5205708A (en) * 1992-02-07 1993-04-27 General Electric Company High pressure turbine component interference fit up
US5478214A (en) * 1994-02-09 1995-12-26 Illinois Blower, Inc. Compact redundant cooling module and method
US5540547A (en) * 1994-06-23 1996-07-30 General Electric Company Method and apparatus for damping vibrations of external tubing of a gas turbine engine
US5685693A (en) * 1995-03-31 1997-11-11 General Electric Co. Removable inner turbine shell with bucket tip clearance control
JPH08334034A (ja) 1995-06-07 1996-12-17 Mitsubishi Heavy Ind Ltd ガスタービンの冷却装置
FR2751694B1 (fr) 1996-07-25 1998-09-04 Snecma Agencement et procede de reglage de diametre d'anneau de stator
FR2766232B1 (fr) * 1997-07-18 1999-08-20 Snecma Dispositif de refroidissement ou d'echauffement d'un carter circulaire
JP3073468B2 (ja) 1997-08-26 2000-08-07 三菱重工業株式会社 蒸気冷却式ガスタービン複合プラント及びその運転制御方法
US6431824B2 (en) * 1999-10-01 2002-08-13 General Electric Company Turbine nozzle stage having thermocouple guide tube
FR2804882B1 (fr) * 2000-02-11 2002-05-10 Air Liquide Procede de compression d'air atmospherique
US6389793B1 (en) 2000-04-19 2002-05-21 General Electric Company Combustion turbine cooling media supply system and related method
US6357221B1 (en) * 2000-07-21 2002-03-19 General Electric Company Ventilation for an enclosure of a gas turbine and related method
US6379108B1 (en) 2000-08-08 2002-04-30 General Electric Company Controlling a rabbet load and air/oil seal temperatures in a turbine
US6435823B1 (en) * 2000-12-08 2002-08-20 General Electric Company Bucket tip clearance control system
US6454529B1 (en) * 2001-03-23 2002-09-24 General Electric Company Methods and apparatus for maintaining rotor assembly tip clearances
US6487491B1 (en) * 2001-11-21 2002-11-26 United Technologies Corporation System and method of controlling clearance between turbine engine blades and case based on engine components thermal growth model
JP4040556B2 (ja) 2003-09-04 2008-01-30 株式会社日立製作所 ガスタービン設備及び冷却空気供給方法
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly
US7293953B2 (en) * 2005-11-15 2007-11-13 General Electric Company Integrated turbine sealing air and active clearance control system and method
US7837429B2 (en) * 2006-10-12 2010-11-23 General Electric Company Predictive model based control system for heavy duty gas turbines
US8801370B2 (en) * 2006-10-12 2014-08-12 General Electric Company Turbine case impingement cooling for heavy duty gas turbines
US7914254B2 (en) * 2007-02-13 2011-03-29 General Electric Company Integrated support/thermocouple housing for impingement cooling manifolds and cooling method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2650753A (en) * 1947-06-11 1953-09-01 Gen Electric Turbomachine stator casing
US4251185A (en) * 1978-05-01 1981-02-17 Caterpillar Tractor Co. Expansion control ring for a turbine shroud assembly
US5399066A (en) * 1993-09-30 1995-03-21 General Electric Company Integral clearance control impingement manifold and environmental shield
US6615588B2 (en) * 2000-12-22 2003-09-09 Alstom (Switzerland) Ltd Arrangement for using a plate shaped element with through-openings for cooling a component

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JP5328130B2 (ja) 2013-10-30
EP1914392A3 (en) 2013-01-02
KR20080033869A (ko) 2008-04-17
US20080089780A1 (en) 2008-04-17
EP1914392A2 (en) 2008-04-23
US20090068007A1 (en) 2009-03-12
US8801370B2 (en) 2014-08-12
KR101410570B1 (ko) 2014-06-23
EP1914392B1 (en) 2017-12-13
JP2008095687A (ja) 2008-04-24
CN101161997A (zh) 2008-04-16

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