CN1012833B - 喷管调节片后缘冷却装置 - Google Patents

喷管调节片后缘冷却装置

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Publication number
CN1012833B
CN1012833B CN88102318A CN88102318A CN1012833B CN 1012833 B CN1012833 B CN 1012833B CN 88102318 A CN88102318 A CN 88102318A CN 88102318 A CN88102318 A CN 88102318A CN 1012833 B CN1012833 B CN 1012833B
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CN
China
Prior art keywords
trailing edge
baffle plate
support plate
edge liner
liner
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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.)
Expired
Application number
CN88102318A
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English (en)
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CN88102318A (zh
Inventor
阿尔弗雷多·奇雷斯
乔治·D·李
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Raytheon Technologies Corp
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United Technologies Corp
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Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of CN88102318A publication Critical patent/CN88102318A/zh
Publication of CN1012833B publication Critical patent/CN1012833B/zh
Expired legal-status Critical Current

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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; Infra-red 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装置。
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，因为不需这种冷却，而空气走涡轮机旁路，结果使功率下降，美国专利US4544098公开了一种这种类型的活动调节片喷管。
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。
本发明的目的在于提供一种燃气轮机喷管调节片后缘冷却装置，它可克服先有技术中冷却装置的缺点，不仅可降低衬套的温度，而且可阻挡后缘衬套的辐射。
本发明的一种喷管调节片后缘冷却装置，包括一个结构蜂窝式平面支承板;和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;一个喷管后缘衬套固定在该喷管衬套上，从上面向外伸，覆盖该冷却剂增压室的边缘和该支承板;一个挡板支持在一个该衬套上，并被密封地偏压在该支承板上，该挡板形成挡板和该后缘衬套间的冷却腔;若干在该挡板上的冲击孔，引导冷却剂通过该挡板进入冷却腔，冲撞该后缘衬 套，若干通过该后缘衬套的孔，用于排放来自冷却腔的冷却剂。
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后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纵向剖视图。
图3为图2所示调节片顶端的密封装置的第一实施方案。
图4为图2所示调节片顶端的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，形成挡板和后缘衬套30之间的一个冷却腔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。该后缘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，抵抗暴露的后缘衬套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，冲撞后缘衬套30。后缘衬套也有若干较小的通孔40，使冷却空气穿过后缘衬套。
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 (3)

1、一种喷管调节片后缘冷却装置，包括一个结构蜂窝式平面支承板；和
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；
其特征在于：
一个喷管后缘衬套固定在该喷管衬套上，从上面向外伸，覆盖该冷却剂增压室的边缘和该支承板；
一个挡板支持在一个该衬套上，并被密封地偏压在该支承板上，该挡板形成挡板和该后缘衬套间的冷却腔；
若干在该挡板上的冲击孔，引导冷却剂通过该挡板进入冷却腔，冲撞该后缘衬套，
若干通过该后缘衬套的孔，用于排放来自冷却腔的冷却剂。
2、一种喷管调节片后缘冷却装置，包括一个结构蜂窝式平面支承板;和
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;
其特征在于：
一个喷管后缘衬套固定在该喷管衬套上，从上面向外伸，覆盖该冷却剂增压室的边缘和该支承板;
一个挡板支持在一个该衬套上，并被密封地偏压在该支承板上，该挡板形成挡板和该后缘衬套间的冷却腔;
若干在该挡板上的冲击孔，引导冷却剂通过该挡板进入冷却腔，冲撞该后缘衬套，
一个在该后缘衬套和该支承板之间的开孔，用以排放来自冷却腔的冷却剂。
3、如权利要求2中之冷却装置，其特征在于该喷管衬套在远离该后缘衬套的一个位置上，和该支承板固定;
在该后缘衬套和该支承板之间有一个贴靠密封件;
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

Publications (2)

Publication Number Publication Date
CN88102318A CN88102318A (zh) 1988-11-02
CN1012833B true 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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JPH0660740B2 (ja) * 1985-04-05 1994-08-10 工業技術院長 ガスタービンの燃焼器

Also Published As

Publication number Publication date
EP0287499A3 (en) 1990-08-16
EP0287499A2 (en) 1988-10-19
US4747542A (en) 1988-05-31
DE3885495T2 (de) 1994-02-24
KR880012883A (ko) 1988-11-29
CN88102318A (zh) 1988-11-02
JP2617761B2 (ja) 1997-06-04
DE3885495D1 (de) 1993-12-16
EP0287499B1 (en) 1993-11-10
JPS63263251A (ja) 1988-10-31
KR950003751B1 (ko) 1995-04-18

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