CN88102318A - 喷管调节片边缘冷却 - Google Patents

喷管调节片边缘冷却 Download PDF

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Publication number
CN88102318A
CN88102318A CN88102318.3A CN88102318A CN88102318A CN 88102318 A CN88102318 A CN 88102318A CN 88102318 A CN88102318 A CN 88102318A CN 88102318 A CN88102318 A CN 88102318A
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edge
support plate
bush
baffle plate
freezing mixture
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CN88102318.3A
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CN1012833B (zh
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阿尔弗雷多·奇雷斯
乔治·D·李
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RTX Corp
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United Technologies Corp
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Publication of CN88102318A publication Critical patent/CN88102318A/zh
Publication of CN1012833B publication Critical patent/CN1012833B/zh
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Continuous Casting (AREA)

Abstract

喷管调节片12，14后缘的冷却装置有后缘衬套30和挡板32。来自冷却剂增压室22的空气通过开孔38，将后缘衬套30冷却。

Description

本发明涉及燃气轮机活动调节片喷管，特别是调节片后缘的冷却。
燃气轮机排气喷管可有变截面积和/或变方向调节片。这种调节片基本为平面形，在喷管的相对平行侧壁之间旋转。
在大功率运转中，调节片必须能耐受约1500°F的高温，但在其他条件下都仅耐受较低的温度。传统上都向在喷管中各位置上的调节片的暴露表面供给冷却空气。大功率要求的冷却空气的量，在其他条件下都属于浪费和不必需，因为不需要这种冷却，而空气走涡轮机旁路，结果使功率下降。
主燃气流通过喷管时，并非全部调节片的后缘都对气流暴露。然而当热主燃气流离开喷管又重依附喷管的下游边缘时涡旋，便造成过热。这种过热不仅使衬套表面本身损坏，而且热表面的辐射会损坏不能耐受这种高温的内结构件。
燃气轮机的一种活动喷管调节片有一个结构蜂窝支承板和与之有间距的喷管衬套。一个喷管下游端的后缘衬套和喷管衬套固定，从上面向外伸展，覆盖支承板的边缘和位于支承板及喷管衬套间的冷却剂增压室。一个和该边缘衬套近距离间隔的挡板，支撑在喷管衬套上或边缘衬套上，向支承板作密封偏压。这样便形成挡板和边缘衬套之间的冷却剂体积。冷却剂从增压室通过挡板使边缘衬套冷却，不仅降低衬套的温度，并且挡板可阻挡边缘衬套向结构支承板的辐射。
喷管衬套在一个上游位置上和支承板固定，从而从上游边缘作相对的膨胀。一个贴靠的密封件位于边缘衬套和支承板之间，从而喷管衬套相对支承板变热而膨胀时，贴靠的密封件开放，因而仅在有高温时，才有较大的冷却空气流量。
图1为燃气轮机一个喷管活动调节片装置的透视。
图2为通过一个调节片的剖视。
图3为密封装置的第一实施方案。
图4为密封装置的第二实施方案。
图1表示燃气轮机一个喷管组合件10，其中有一个上活动调节片12和一个下活动调节片14。这些喷管可向上或向下旋转，靠在侧壁16上密封。喷管的向通过的热气体暴露的部分，由与蜂窝式支承结构20有间隔的衬套18覆盖，形成二者间的一个冷却剂增压室22。
衬套18由外衬套24和冲击衬套26组成。
在后缘上，也就是在一个下游位置上，有一个后缘衬套30，附在喷管衬套18上。一个挡板32在喷管衬套上固定，形成挡板和边缘衬套30之间的一个空气体积34。在这挡板上安装一个弹性密封件36，被偏压在结构蜂窝支承板20上密封。衬套用耐高温材料制造，诸如耐高热镍基合金，而结构蜂窝式平面支承板20，则用钛之类的高强度材料，其耐热性较差。挡板32保护支承板20，抵抗暴露的衬套板30的辐射，从而防止过热。
挡板32有若干贯通的冲击孔38，引导增压室22的冷却空气，冲撞边缘衬套30。边缘衬套也有若干较小的通孔40，使冷却空气穿过边缘板衬。
冲击衬套26有若干开孔27贯通，使增压室22的冷却气流可冲撞衬套24。这衬套有通孔25，与垂线倾斜45度，使通过的冷却空气形成喷管中的冷却膜。
参看图2，喷管衬套18在一个上游位置42上和蜂窝式支承结构20固定。因此衬套从这上游位置42上，相对于支承结构膨胀，膨胀量和二者之间的温差成正比。因此，当喷管中有高温时，高载荷运转中有相当大的差胀。这使图4中的边缘衬套50向右移动，使贴靠密封件52作相对于支承板20的开放。这实施方案中的冷却空气，从增压室22通过挡板55的开孔54，冲撞衬板50，然后向下经过密封件52排出。这样便可在喷管要求受保护的温度中，按温度比例调节冷却流的量。低功率时可安排为基本无冷却流，从而使燃气轮机的冷却气流免走旁路。

Claims (5)

1、喷管调节片后缘冷却装置有一个结构蜂窝式平面支承板；
一个喷管衬套和该支承板有间距，形成其间的冷却剂增压室；
一个喷管后缘衬套在该喷管衬套上固定，从上面向外伸，覆盖该冷却剂增压室的边缘和该支承板；
将一个挡板支持在一个该衬套上，被偏压在该支承板上作密封，该挡板形成挡板和该边缘衬套间的冷却体积；
将冷却剂从该冷却剂增压室通过和该边缘衬套接触的该冷却剂体积的输送装置，使该边缘衬套冷却。
2、如权利要求1中之冷却装置;该输送冷却剂的装置中有若干在该挡板上的冲击孔，引导冷却剂通过该挡板，冲撞该边缘衬套。
3、如权利要求2中之冷却装置，该冷却剂输送装置还有若干通过该边缘衬套的孔。
4、如权利要求2中之冷却装置，该冷却剂输送装置还有一个在该边缘衬套和该支承板之间的开孔。
5、如权利要求1中之冷却装置，该喷管衬套在远离该边缘衬套的一个位置上，和该支承板固定;
一个贴靠密封件在该边缘衬套和该支承板之间;
该密封件在平行于该喷管衬套从固定支承板上膨胀的方向贴靠，因而衬套相对于支承结构的膨胀将该贴靠密封件开放，使冷却空气可从其中通过。
CN88102318A 1987-04-14 1988-04-14 喷管调节片后缘冷却装置 Expired CN1012833B (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US038,074 1987-04-14
US07/038,074 US4747542A (en) 1987-04-14 1987-04-14 Nozzle flap edge cooling

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CN88102318A true CN88102318A (zh) 1988-11-02
CN1012833B CN1012833B (zh) 1991-06-12

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US (1) US4747542A (zh)
EP (1) EP0287499B1 (zh)
JP (1) JP2617761B2 (zh)
KR (1) KR950003751B1 (zh)
CN (1) CN1012833B (zh)
DE (1) DE3885495T2 (zh)

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FR2637016A1 (fr) * 1988-09-28 1990-03-30 Snecma Tuyere d'ejection bidimensionnelle de turboreacteur et son systeme de commande
US4934600A (en) * 1988-12-14 1990-06-19 General Electric Company Exhaust nozzle thermal distortion control device
US5101624A (en) * 1989-09-07 1992-04-07 General Electric Company Exhaust nozzle hinge
US5079912A (en) * 1990-06-12 1992-01-14 United Technologies Corporation Convergent side disk cooling system for a two-dimensional nozzle
US5080284A (en) * 1990-06-25 1992-01-14 United Technologies Corporation Cooling system for the trailing edge of a liner
US5131222A (en) * 1990-11-28 1992-07-21 The United States Of Americas As Represented By The Secretary Of The Air Force Thermally valved cooling system for exhaust nozzle systems
US5720434A (en) * 1991-11-05 1998-02-24 General Electric Company Cooling apparatus for aircraft gas turbine engine exhaust nozzles
DE4138784A1 (de) * 1991-11-26 1993-05-27 Mtu Muenchen Gmbh Einrichtung zur abdichtung eines spaltes
US6000635A (en) * 1995-10-02 1999-12-14 Lockheed Martin Corporation Exhaust nozzle for a turbojet engine
DE10303088B4 (de) 2002-02-09 2015-08-20 Alstom Technology Ltd. Abgasgehäuse einer Wärmekraftmaschine
US7188477B2 (en) * 2004-04-21 2007-03-13 United Technologies Corporation High temperature dynamic seal for scramjet variable geometry
US7624567B2 (en) * 2005-09-20 2009-12-01 United Technologies Corporation Convergent divergent nozzle with interlocking divergent flaps
US8205454B2 (en) * 2007-02-06 2012-06-26 United Technologies Corporation Convergent divergent nozzle with edge cooled divergent seals
US7757477B2 (en) * 2007-02-20 2010-07-20 United Technologies Corporation Convergent divergent nozzle with slot cooled nozzle liner
US8051663B2 (en) * 2007-11-09 2011-11-08 United Technologies Corp. Gas turbine engine systems involving cooling of combustion section liners
CN105067988B (zh) 2015-07-02 2018-03-30 英特尔公司 集成电路、集成电路测试装置以及方法

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US4575006A (en) * 1983-06-13 1986-03-11 United Technologies Corporation Nozzle flap edge seal
JPH0660740B2 (ja) * 1985-04-05 1994-08-10 工業技術院長 ガスタービンの燃焼器

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Publication number Publication date
JPS63263251A (ja) 1988-10-31
US4747542A (en) 1988-05-31
CN1012833B (zh) 1991-06-12
KR950003751B1 (ko) 1995-04-18
EP0287499B1 (en) 1993-11-10
EP0287499A3 (en) 1990-08-16
DE3885495T2 (de) 1994-02-24
KR880012883A (ko) 1988-11-29
EP0287499A2 (en) 1988-10-19
DE3885495D1 (de) 1993-12-16
JP2617761B2 (ja) 1997-06-04

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