CN102537441A - 气轮机的自致动泄放阀 - Google Patents

气轮机的自致动泄放阀 Download PDF

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CN102537441A
CN102537441A CN2011104150080A CN201110415008A CN102537441A CN 102537441 A CN102537441 A CN 102537441A CN 2011104150080 A CN2011104150080 A CN 2011104150080A CN 201110415008 A CN201110415008 A CN 201110415008A CN 102537441 A CN102537441 A CN 102537441A
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valve
bleeder
poppet
bleeder valve
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CN102537441B (zh
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R·古德曼
M·M·库恩斯
J·S·埃尔德
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Hamilton Sundstrand Corp
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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/105—Final actuators by passing part of the fluid
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/145—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path by means of valves, e.g. for steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/13—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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
    • F05D2260/85—Starting
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49298—Poppet or I.C. engine valve or valve seat making
    • Y10T29/49314—Poppet or I.C. engine valve or valve seat making with assembly or composite article making

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
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  • Fluid Mechanics (AREA)
  • Safety Valves (AREA)
  • Control Of Turbines (AREA)
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Abstract

本发明涉及气轮机的自致动泄放阀。用于正压空气室的泄放阀包括阀体，其限定阀座。提升阀相对于阀座可在打开位置和关闭位置之间移动。弹簧朝着正压空气室将提升阀偏压到打开位置。

Description

气轮机的自致动泄放阀
技术领域
本发明涉及辅助气轮机起动的自致动泄放阀。
背景技术
气轮机设置有数个功能段，包括风扇段、压缩机段、燃烧段和涡轮机段。在起动时，气轮机的涡轮机段还没有开始完全提供动力。因此，驱动压缩机，作为示例，比在稳态条件下更具挑战性，并且通常使用泄放阀来在起动过程中从压缩机段泄放空气，以减少压缩机段上的负载。
发明内容
根据本发明的示例性方面的用于正压空气室的泄放阀包括阀体，该阀体限定阀座。提升阀可相对于阀座在打开位置和关闭位置之间移动。弹簧将提升阀朝向正压空气室地偏压到打开位置。
根据本发明的示例性方面的气轮机包括与压缩机段连通的正压空气室。泄放阀包括限定阀座的阀体、可相对于阀座移动的提升阀和弹簧，该弹簧可操作以在泄放阀处于打开位置时朝向正压空气室地将提升阀偏压远离阀座。
根据本发明示例性方面的将泄放阀安装到气轮机上的方法，包括将泄放阀定位成与正压空气室连通。根据压缩机段内的压力，在打开位置和关闭位置之间移动泄放阀内的提升阀，并且在泄放阀处于打开位置时朝向正压空气室地将提升阀偏压远离阀座。
附图说明
各种特征将从下面的对所公开的非限制性实施例的具体描述中变得为本领域技术人员所明了。具体描述的附图可简要地描述如下：
图1是气轮机的示意图；
图2是气轮机的压缩机段的一部分的局部剖视图；
图3是处于打开位置的泄放阀的透视图；
图4是处于打开位置的泄放阀的剖视图；
图5是处于打开位置的泄放阀的示意剖视图；
图6是处于关闭位置的泄放阀的示意剖视图；
图7是提升阀力相对于横过提升阀的PSID的曲线表示；
图8是提升阀位置和deltaP相对于时间的曲线表示，示出了卡合动作；
图9是提升阀位置相对于压力的曲线表示，示出了错开的打开和关闭瞬间；和
图10是主动受控的泄放阀的另一非限制性实施例的示意剖视图。
具体实施方式
图1示意性地示出了气轮机20，其大体包括沿着轴线A的风扇段22、压缩机段24、燃烧段26和涡轮机段28。图1是高度示意图，不过，它仍然示出了气轮机的主要各段。而且，虽然示出了特定类型的气轮机，但是应当理解的是，其他类型的气轮机也可以从本发明受益。
参照图2，压缩机段24包括沿着压缩机燃气路径C的多个旋转压缩机叶片30和固定叶片32。称为中心空气流的空气流沿着压缩机燃气路径C被传输进下游涡轮机段28(图1)。正压空气室34通常定位在压缩机燃气路径C的外部，从而压缩空气从压缩机燃气路径C经过开口36流入正压空气室34，以用于例如泄放流***中。
泄放阀40包括阀体42，阀体42带有选择性地从正压空气室34排放空气的开口(也示出在图3中)。泄放阀40在起动状态时处于打开位置，以将泄放空气通入例如短舱(未示出)，并且因此减少了压缩机段24上的载荷。因此，在起动且低压的条件下，泄放阀40减少了驱动压缩机段24所要求的载荷，然后在压缩机段24达到运行压力时泄放阀40就关闭，从而气轮机将按设计运行。
参照图4，泄放阀40大体包括阀体42、盖44、弹簧46、活塞48和提升阀50。阀体42形成导引件52，提升阀轴54在导引件52中延伸。提升阀轴54将提升阀50安装到活塞48上，使得提升阀50随着活塞48沿由导引件52限定的轴线X移动。提升阀50在打开位置(图5)和关闭位置(图6)之间移动，打开位置允许所要求的泄放流通过，而关闭位置阻止盖流动。
提升阀50被安装到提升阀轴54的轴向端部56处，使得提升阀50的延伸部58可至少部分地围绕导引件52。轴向端部56可带有螺纹以接收紧固件60从而保持提升阀50。延伸部58有助于提升阀50相对于阀体42的对准和轴向移动，阀体42限定阀座62。延伸部58还遮蔽导引件52的开口端52A，从而防止了压缩机空气中的任何潜在的污染物流过提升阀轴54和导引件52之间的间隙进而可能阻碍泄放阀40的移动。
提升阀50限定了下游阀面64(也示出在图3中)，下游阀面64也在关闭位置(图6)中抵靠在阀座62上。提升阀50限定了下游大体凸形面66，下游大体凸形面66将延伸部58与阀面64结合。上游大体凹形面68与凸形面66相对，向着上游朝向来自压缩机段24的正压空气室34的泄放流。
弹簧46加载活塞48并由此加载提升阀50使其到打开位置(图5)。当气轮机逐渐加快旋转时，在起动过程中，在提升阀50上的级压力(P0)施加关闭力(F0)。在提升阀50的下游侧，存在施加打开力的背压分布(P1)。弹簧力Fs1将克服净关闭力，直到压力差开始超过预定值。提升阀50此时将开始朝向关闭位置(图6)移动。当提升阀50向关闭位置移动时，下游大体凸形面66上的压力减小，因为流动被节流，因而净关闭力增加。这个动作导致阀“卡合”关闭到图6中示出的位置(见图7、8和9)。
参照图7，卡合动作效果的实质被示出为各种阀提升的阀关闭力与阀位置对比。在这个绘图上还叠加了作为提升阀提升的函数的弹簧力。通过绘制提升阀提升路径，其中弹簧力与压力相交，可以看到在初始关闭移动发生后不久，压力克服弹簧力以产生卡合动作效果(也在图8和9中示出)。如果增加弹簧常数，那么在发动机加速旋转时会有更多的比例正在关闭。卡合动作效果是期望的，从而确保泄放阀40关闭时进口压力的例如从次怠速到怠速状态时的变化最小，同时保证泄放阀40不会逆转地打开。即，泄放阀40在比泄放阀40关闭时的压力更低的压力下打开。由此泄放阀40在最小压力至少“故障地关闭着”以避免使短舱过热(未示出)。
参照图10，泄放阀40’的另一非限制性实施例满足了主动操作的需要。虽然大体上与上述的泄放阀40相当，但是泄放阀40’将活塞环70定位在活塞48和盖44之间，从而通过诸如螺线管控制器(示意性示出)的外部源72改变盖44内的压力以控制其中的活塞48的移动。当例如在起动以及诸如滑行、起飞、爬升、巡航和下降的其他状态中检测到可能的喘振状态时，外部源72响应于控制器74和传感器***76选择性地控制盖44内的压力以选择性地控制泄放阀40’。外部源72可例如降低由盖44限定的腔内的压力，以借此克服弹簧46的弹簧力并关闭提升阀50。
应当理解的是，诸如“前”、“后”、“上”、“下”、“高于”、“低于”等的相对位置术语是参照交通工具的正常运行姿态，并且不应当被认为具有其他的限定性。
应当理解，在所有这些附图中，相同的附图标记表示相应或相似的元件。还应当理解的是，虽然在图示的实施例中公开了特定的部件布置，但其他布置也可从本文受益。
虽然示出了、描述了并要求了特定的布置顺序，应当理解的是，这些步骤可以以任意顺序被执行，可被分离或组合，除非有相反的指示，并且将从本发明受益。
前面的描述是示例性的而非由其中的限制所限定。各种不同的非限制性实施例在本文中公开，但是，本领域技术人员将认识到，根据上述教导的各种修改和变形都将落入所附权利要求的范围。因此应当理解，在所附权利要求的范围内，本发明可以不按说明书所描述的被实践。因此应当研究所附的权利要求以确定真实的范围和内容。

Claims (16)

1.一种用于正压空气室的泄放阀，包括：
阀体，其限定阀座；
提升阀，其可相对于所述阀座在打开位置和关闭位置之间移动；和
弹簧，其可操作以朝着所述正压空气室将所述提升阀偏压至所述打开位置。
2.如权利要求1所述的泄放阀，其中所述阀体限定凹形阀座，该凹形阀座面向正压空气室。
3.如权利要求1所述的泄放阀，其中所述阀体限定导引件，从所述提升阀延伸的提升阀轴可移动通过该导引件。
4.如权利要求3所述的泄放阀，其中所述提升阀限定延伸部，该延伸部至少部分地围绕所述导引件。
5.如权利要求3所述的泄放阀，还包括安装到所述提升阀轴的活塞。
6.如权利要求3所述的泄放阀，还包括安装到所述提升阀轴的活塞，所述活塞支撑活塞环。
7.如权利要求6所述的泄放阀，其中所述活塞环与盖接触。
8.如权利要求7所述的泄放阀，还包括外部压力源，其与所述盖连通以选择性地改变所述盖内的压力。
9.一种气轮机，包括：
压缩机段；
与所述压缩机段连通的正压空气室；和
与所述正压空气室连通的泄放阀，所述泄放阀根据所述压缩机段内的压力可在打开位置和关闭位置之间移动，所述泄放阀包括：
阀体，其限定阀座；
提升阀，其可相对于所述阀座移动；和
弹簧，其可操作以在所述泄放阀处于所述打开位置时朝着所述正压空气室将所述提升阀偏压远离所述阀座。
10.如权利要求9所述的气轮机，其中所述正压空气室围绕所述压缩机段。
11.如权利要求9所述的气轮机，还包括：
安装在所述提升阀轴的活塞，所述活塞接触盖以限定压力腔；和
外部压力源，其与所述盖连通以选择性地减少所述盖内的压力从而克服所述弹簧并将所述提升阀移动至所述关闭位置。
12.一种将泄放阀安装在气轮机上的方法，包括：
将泄放阀定位成与和压缩机段连通的正压空气室连通；
根据所述压缩机段内的压力在打开位置和关闭位置之间移动泄放阀内的提升阀；和
当所述泄放阀处于打开位置时将所述提升阀朝着正压空气室偏压远离阀座。
13.如权利要求12所述的方法，还包括：
当所述泄放阀处于打开位置时，排放由所述压缩机段压缩的空气。
14.如权利要求12所述的方法，还包括：
当所述泄放阀处于关闭位置时，阻挡由所述压缩机段压缩的空气。
15.如权利要求12所述的方法，还包括：
将所述提升阀卡合到关闭位置，其中当所述提升阀向着所述关闭位置移动时，所述提升阀的下游侧上的压力被减小以节流流动，由此增加净关闭力。
16.如权利要求12所述的方法，还包括：
主动地控制所述提升阀。
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* Cited by examiner, † Cited by third party
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CN104089025A (zh) * 2014-07-01 2014-10-08 中国船舶重工集团公司第七�三研究所 用于燃气轮机装置的快速排放阀
CN112361061A (zh) * 2020-11-30 2021-02-12 中国船舶重工集团公司第七0三研究所 一种应用于燃气轮机的带位置反馈的放气阀

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8814499B2 (en) * 2010-04-19 2014-08-26 Korea Fluid Machinery Co., Ltd. Centrifugal compressor
US9513010B2 (en) 2013-08-07 2016-12-06 Honeywell International Inc. Gas turbine engine combustor with fluidic control of swirlers
EP2977590B1 (en) * 2014-07-25 2018-01-31 Ansaldo Energia Switzerland AG Compressor assembly for gas turbine
US10330019B2 (en) 2015-02-25 2019-06-25 Hamilton Sundstrand Corporation Self-actuating and dual pivot flapper valve
US9784184B2 (en) 2015-03-16 2017-10-10 Hamilton Sundstrand Corporation Self-actuated, in-line bleed valve
US20160341130A1 (en) * 2015-05-20 2016-11-24 United Technologies Corporation Pneumatic porting via self-actuated dual pivot flapper valve
US9964223B2 (en) * 2015-07-13 2018-05-08 Hamilton Sundstrand Corporation Bleed valves for gas turbine engines
US10302019B2 (en) 2016-03-03 2019-05-28 General Electric Company High pressure compressor augmented bleed with autonomously actuated valve
US10273884B2 (en) * 2016-06-09 2019-04-30 Hamilton Sundstrand Corporation Altitude compensating bleed valve
JP2018080767A (ja) * 2016-11-17 2018-05-24 株式会社日邦バルブ 逆止弁
US11193427B2 (en) 2018-04-27 2021-12-07 Hamilton Sundstrand Corporation Passive active poppet-type bleed valves
US10859178B2 (en) * 2018-05-25 2020-12-08 Hamilton Sundstrand Corporation Bleed valves
US11053949B2 (en) 2018-08-03 2021-07-06 Hamilton Sundstrand Corporation Passively controlled inline bleed valves
US10975875B2 (en) 2018-08-03 2021-04-13 Hamilton Sundstrand Corporation Passive bleed valves with adjustable pressure threshold
US10626802B2 (en) 2018-09-21 2020-04-21 United Technologies Corporation Ducted gas turbine engine stability bleed valve with passive and active shutoff
US11105219B2 (en) * 2019-07-03 2021-08-31 Raytheon Technologies Corporation Vane angle system accuracy improvement
US11174757B2 (en) 2020-01-20 2021-11-16 Raytheon Technologies Corporation Externally replaceable valve assembly for a turbine engine
US11906071B1 (en) 2022-08-26 2024-02-20 Hamilton Sundstrand Corporation Remote passively and actively actuated valve systems

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2509880A (en) * 1948-05-04 1950-05-30 Robert L Pelton Air pressure mechanism
US4280678A (en) * 1978-11-29 1981-07-28 Pratt & Whitney Aircraft Of Canada, Limited Bleed valve
CN1408990A (zh) * 2002-09-08 2003-04-09 章国标 ***
DE202004001877U1 (de) * 2004-02-07 2004-04-15 Judo Wasseraufbereitung Gmbh Druckminderer
US20040103666A1 (en) * 2001-04-06 2004-06-03 Volvo Aero Corporation Method and arrangement for proving a gas turbine, and engine-braking therefore
US20070044848A1 (en) * 2005-09-01 2007-03-01 Jamie Norman Check valve
US20070089429A1 (en) * 2005-10-21 2007-04-26 Pratt & Whitney Canada Corp. Bleed valve for a gas turbine engine
US20090208321A1 (en) * 2008-02-20 2009-08-20 O'leary Mark Turbine blade tip clearance system

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3360189A (en) 1965-10-11 1967-12-26 United Aircraft Canada Bleed arrangement for gas turbine engines
GB1115968A (en) 1966-10-17 1968-06-06 Rolls Royce Device for controlling the bleed of air from a gas turbine engine compressor
US4574585A (en) 1985-02-08 1986-03-11 General Motors Corporation Compressor bleed valve
US5477673A (en) 1994-08-10 1995-12-26 Pratt & Whitney Canada Inc. Handling bleed valve
US6122905A (en) 1998-02-13 2000-09-26 Pratt & Whitney Canada Corp. Compressor bleed valve
US6446657B1 (en) 2000-12-15 2002-09-10 Fairchild Controls Corporation Aircraft air control valve apparatus
GB2376515B (en) 2001-06-13 2004-09-29 Rolls Royce Plc Bleed valve assembly
US6981842B2 (en) 2003-07-22 2006-01-03 Honeywell International, Inc. Bleed valve system
US7555905B2 (en) 2006-03-28 2009-07-07 United Technologies Corporation Self-actuating bleed valve for gas turbine engine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2509880A (en) * 1948-05-04 1950-05-30 Robert L Pelton Air pressure mechanism
US4280678A (en) * 1978-11-29 1981-07-28 Pratt & Whitney Aircraft Of Canada, Limited Bleed valve
US20040103666A1 (en) * 2001-04-06 2004-06-03 Volvo Aero Corporation Method and arrangement for proving a gas turbine, and engine-braking therefore
CN1408990A (zh) * 2002-09-08 2003-04-09 章国标 ***
DE202004001877U1 (de) * 2004-02-07 2004-04-15 Judo Wasseraufbereitung Gmbh Druckminderer
US20070044848A1 (en) * 2005-09-01 2007-03-01 Jamie Norman Check valve
US20070089429A1 (en) * 2005-10-21 2007-04-26 Pratt & Whitney Canada Corp. Bleed valve for a gas turbine engine
US20090208321A1 (en) * 2008-02-20 2009-08-20 O'leary Mark Turbine blade tip clearance system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104089025A (zh) * 2014-07-01 2014-10-08 中国船舶重工集团公司第七�三研究所 用于燃气轮机装置的快速排放阀
CN112361061A (zh) * 2020-11-30 2021-02-12 中国船舶重工集团公司第七0三研究所 一种应用于燃气轮机的带位置反馈的放气阀

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