CN1003879B - 燃烧室/定叶片界面冷却方案 - Google Patents
燃烧室/定叶片界面冷却方案 Download PDFInfo
- Publication number
- CN1003879B CN1003879B CN85105913.9A CN85105913A CN1003879B CN 1003879 B CN1003879 B CN 1003879B CN 85105913 A CN85105913 A CN 85105913A CN 1003879 B CN1003879 B CN 1003879B
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- China
- Prior art keywords
- those
- fixed blades
- fixed blade
- listrium
- cooling air
- 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.)
- Expired
Links
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
把冷却空气合理地引向轮叶前缘(30),轮叶翼形部份和缘板(32)交接处前方的驻点,便可以保持燃气涡轮发动机燃烧室的直接下游处的涡轮轮叶(22)有较低温度。见图2A。
Description
本发明关于燃气轮机,它有燃烧室、定叶片以及和该些定叶片相近但又轴向地隔开的转子,该些定叶片各包括一个翼形部分和一个位于该翼形部分根部的缘板部分,该燃烧室包括导流衬片,其结构形式可以形成一条环形通道以把燃烧产物引向该些定叶片以进入它们之间,一个支撑结构包括一个薄片元件和该些导流衬片之一隔开着,在两者之间形成一条通道把冷却空气引向该些定叶片并吹遍该处的缘板部分,形成靠近该些缘板部分的较冷的边界层。
如众所周知,传递到第一级转子的燃烧产物在发动机中温度最高。同样为人所共知的是发动机的效率和这温度直接相关,温度越高,发动机的效率也越高。显然,在技术上要求温度能达到组成部件的最高容许限度,而自耐高温的合金问世以来,这种温度已达极高地步。
在某些发动机型中,由于提高温度,转子/燃烧室附近的组件经历局部高温造成烧蚀、挠曲和裂缝等问题。现在参照图1a来进行解释,图1a所示为双转子轴流型涡轮动力装置环形燃烧室的局部示意,这种型式的举例有如美国联合技术公司的pratt & Whitney公司出品的型号JT9D,PW203和PW4000。该公司为本发明申请案的受让人。
如从图1a(先有技术)可见,内和外导流衬片10和12都和定叶片支架14和16适当连接,它们最后以熟知的方式连接在内套18和外套20上。从这个结构可以明确看到,内外导流衬片在喷气端被喇叭形物体,形成一个通道,把发动机的工作流体引入一列定叶片22(图中仅示一片)去对动叶片24冲击。在这种结构中以及如图1b明显表示的,图1b是图1A的一个投影图,图中箭头表示把发动机空气压缩机(图中未示)通过环形腔26供给的冷却空气送到定叶片部件的关键部位上去以保证这些部件能耐受酷劣的环境。
但是如图1A中箭头所示,和字母A所表示的过热点,这种设计上的问题是由定叶片前缘30排送的工作流体的高温高速造成的,结果转移到定叶片缘板32和34和燃烧室的后缘36上(箭头B所指的附近)。
美国专利4264272中公开的先有技术燃气轮机发动机具有上述的缺点,其中的冷却空气是通过一个环形通道排出,流过翼型缘板部分的。在先有技术燃气轮机发动机中的由高温、高速工作流体造成的过热点由定叶片的前缘转移到缘板。
本发明的目的是减少或消除在定叶片缘板和燃烧室后缘中的所述过热点。
为了达到此目的,按照本发明的燃气轮机发动机,其特征在于在该通道中放置着一个波纹形元件,它有交替隔开的封闭部分和开口通道,以把该冷却空气引过该些缘板部分,该些开口通道被放置成使冷却空气只直接冲击该些定叶片的前缘和该些缘板的交接处。
上述的问题的排除是通过把这些开口通道合适地放在导流片后缘以接受冷却空气,并使它分散地冲击相邻定叶片的前缘。这种冲击可以被引向定叶片的外侧或内侧,但一定要在定叶片前缘的工作流体的驻点上。把这高速空气直接喷射在定叶片前缘和定叶片缘板的交接处,定叶片前缘向燃气路径边缘排送的热燃气大量减少,甚至完全消灭,这样便可减少图中箭头B表示的涡流的形成。显然,这造成边界层有更低的燃气温度。此外,这些通道提供额外的热传递表面,提高热传递的对流系数,进一步冷却导流片后缘。
在实际试验中发现,在定叶片缘板和燃烧室后缘,过热点有相当大的减少。
燃气轮机发动机的一个实施例现参照附图来进行说明。
图1A是一个涡轮式动力装置的局部剖视图,表示燃烧室/定叶片组合的现有技术结构示例。
图1B是一个定叶片和燃烧室后缘的局部投影图,表示现有技术结构的问题。
图2A是和图1A相同的局部视图,但加入了本发明。
图2B是图2A的局部投影图。
图3是图2A中导流衬片后缘上的各通道的立体图。
现在来介绍实施本发明的最佳实施例。虽然对本发明的最佳实施例的说明使用的是上面提出的发动机型式,但内行人可以明显看出本发明也可应用于其他类型的发动机。明显可见,本发明的课题是保证燃气轮机发动机的关键部件不致发生事故,特别是在导流片后缘附近的区域,和在第一级涡轮前面的第一列定叶片的前缘附近区域(就是基本属于发动机温度最高的区域)。
为了方便和简化起见,仅对为了解本发明所必须知道的部分作说明如下,但应参看图1A和1B,该二图为上述型号发动机未结合本发明的同一结构,附于本文作参考用。
从图2A和2B中可以看出,最后导流片40和后缘已按本发明作了修改。和定叶片缘板32连接的金属薄板安装件44,支撑着导流片支撑件42,支撑件41形成一个环形冷却室46,空气压缩机排出的空气从腔26通过孔48(图中仅示一个)送入环形冷却室46。如已所述,导流片40的后缘和导流片支撑件42之间有距离,以形成一条环形开口通道。支撑件42的排气端被做成正弦曲线形,所形成的交替的各封闭部分对准着定叶片22之间的空间,各开口通道50对准着各定叶片前缘30。
从上文可见,开口通道50都有相对于定叶片22的适当位置(见图2B),因而相当高速的冷却空气仅指向定叶片22的翼型部分的前缘30和定叶片22的缘板的交接处形成的区域。如上所述,这用于容纳热燃气(流体工质)路经边缘的温度,以减少甚至有时可以消灭先有技术设计的定叶片所引起的涡流。增加通道有助于提供高“后部”对流传热系统,进一步冷却导流衬片的后缘。
应能理解本发明并不局限于本文所透露及叙述的特定实施方案,尚可作出各种变化或修改而并不脱离下列权利要求中设定的新颖性概念的精神和范围。
Claims (3)
1、一种燃气轮机发动机有一个燃烧室,多个定叶片(22)和与上述定叶片(22)轴向隔开但又相靠近的转子,该些定叶片(22)各包括一个翼型部分和一个位于该翼型部分根部的缘板部分(32),该燃烧室包括多个导流衬片(10,12)其结构形式可以形成一条环形通道以把燃烧产物引向该些定叶片(22)以进入它们之间,一个支撑结构包括一个薄片元件(44),它和该些导流衬片(10,12)之一隔开着,在两者之间形成一条通道(46)把冷却空气引向该些定叶片(22)并吹遍该处的缘板部分(32)形成靠近该些缘板部分(32)的较冷的边界层,
本发明的特征是在该通道(46)中放置着一个波纹形元件(42),它有交替隔开的封闭部分和开口通道(50),以把该冷却空气引导吹遍该些缘板部分(32),该些开口通道(50)被放置成使冷却空气只直接冲击该些定叶片(22)的前缘(30)和该些缘板(32)的交接处。
2、如权利要求1中的燃气轮机发动机,其特征是波纹形元件(42)有对准各定叶片(22)之间的各空间的封闭部分,而该些开口通道(50)对准着那些定叶片的前缘(30)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
USSN659,748 | 1984-10-11 | ||
US06/659,748 US4739621A (en) | 1984-10-11 | 1984-10-11 | Cooling scheme for combustor vane interface |
US659,748 | 1991-02-21 |
Publications (2)
Publication Number | Publication Date |
---|---|
CN85105913A CN85105913A (zh) | 1986-08-06 |
CN1003879B true CN1003879B (zh) | 1989-04-12 |
Family
ID=24646666
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN85105913.9A Expired CN1003879B (zh) | 1984-10-11 | 1985-08-05 | 燃烧室/定叶片界面冷却方案 |
Country Status (7)
Country | Link |
---|---|
US (1) | US4739621A (zh) |
EP (1) | EP0178242B1 (zh) |
JP (1) | JPS6196140A (zh) |
CN (1) | CN1003879B (zh) |
CA (1) | CA1245869A (zh) |
DE (2) | DE3566010D1 (zh) |
IL (1) | IL75780A (zh) |
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US5083422A (en) * | 1988-03-25 | 1992-01-28 | General Electric Company | Method of breach cooling |
US4916906A (en) * | 1988-03-25 | 1990-04-17 | General Electric Company | Breach-cooled structure |
US5101620A (en) * | 1988-12-28 | 1992-04-07 | Sundstrand Corporation | Annular combustor for a turbine engine without film cooling |
US5303543A (en) * | 1990-02-08 | 1994-04-19 | Sundstrand Corporation | Annular combustor for a turbine engine with tangential passages sized to provide only combustion air |
DE9203776U1 (zh) * | 1992-03-20 | 1992-05-21 | Schreckling, Kurt, 5090 Leverkusen, De | |
GB9304994D0 (en) * | 1993-03-11 | 1993-04-28 | Rolls Royce Plc | Improvements in or relating to gas turbine engines |
GB9305010D0 (en) * | 1993-03-11 | 1993-04-28 | Rolls Royce Plc | A cooled turbine nozzle assembly and a method of calculating the diameters of cooling holes for use in such an assembly |
GB9305012D0 (en) * | 1993-03-11 | 1993-04-28 | Rolls Royce Plc | Sealing structures for gas turbine engines |
US5394687A (en) * | 1993-12-03 | 1995-03-07 | The United States Of America As Represented By The Department Of Energy | Gas turbine vane cooling system |
DE19813779B4 (de) * | 1998-03-27 | 2005-04-14 | Rolls-Royce Deutschland Ltd & Co Kg | Anordnung zur Kühlung der Plattformen von Leitschaufeln einer Gasturbine |
DE19856199A1 (de) | 1998-12-05 | 2000-06-08 | Abb Alstom Power Ch Ag | Kühlung in Gasturbinen |
US6419446B1 (en) * | 1999-08-05 | 2002-07-16 | United Technologies Corporation | Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine |
FR2825787B1 (fr) * | 2001-06-06 | 2004-08-27 | Snecma Moteurs | Montage de chambre de combustion cmc de turbomachine par viroles de liaison souples |
US6884029B2 (en) * | 2002-09-26 | 2005-04-26 | Siemens Westinghouse Power Corporation | Heat-tolerated vortex-disrupting fluid guide component |
US6969232B2 (en) | 2002-10-23 | 2005-11-29 | United Technologies Corporation | Flow directing device |
US7234304B2 (en) | 2002-10-23 | 2007-06-26 | Pratt & Whitney Canada Corp | Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine |
EP1731711A1 (de) * | 2005-06-10 | 2006-12-13 | Siemens Aktiengesellschaft | Übergang zwischen Brennkammer und Turbineneinheit, Hitzeschild und Turbinenleitschaufel für eine Gasturbine |
US7862291B2 (en) * | 2007-02-08 | 2011-01-04 | United Technologies Corporation | Gas turbine engine component cooling scheme |
EP2229507B1 (de) * | 2007-12-29 | 2017-02-08 | General Electric Technology GmbH | Gasturbine |
US20100054922A1 (en) * | 2008-09-04 | 2010-03-04 | General Electric Company | Turbine airfoil clocking |
US8087253B2 (en) * | 2008-11-20 | 2012-01-03 | General Electric Company | Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath |
JP5180807B2 (ja) | 2008-12-24 | 2013-04-10 | 三菱重工業株式会社 | 1段静翼の冷却構造、及びガスタービン |
US8439626B2 (en) * | 2008-12-29 | 2013-05-14 | General Electric Company | Turbine airfoil clocking |
JP5479058B2 (ja) | 2009-12-07 | 2014-04-23 | 三菱重工業株式会社 | 燃焼器とタービン部との連通構造、および、ガスタービン |
CN102146844A (zh) * | 2010-02-10 | 2011-08-10 | 中国科学院工程热物理研究所 | 航空发动机涡轮叶片的零冷气消耗超强度冷却装置 |
JP5031110B2 (ja) * | 2011-01-21 | 2012-09-19 | 三菱重工業株式会社 | ガスタービン |
US9157331B2 (en) * | 2011-12-08 | 2015-10-13 | Siemens Aktiengesellschaft | Radial active clearance control for a gas turbine engine |
US8905714B2 (en) * | 2011-12-30 | 2014-12-09 | General Electric Company | Turbine rotor blade platform cooling |
JP5506834B2 (ja) * | 2012-01-27 | 2014-05-28 | 三菱重工業株式会社 | ガスタービン |
JP2012107628A (ja) * | 2012-01-27 | 2012-06-07 | Mitsubishi Heavy Ind Ltd | ガスタービン |
US9752447B2 (en) * | 2014-04-04 | 2017-09-05 | United Technologies Corporation | Angled rail holes |
CN108442985B (zh) * | 2018-04-11 | 2020-10-27 | 西安交通大学 | 一种具有提高静叶通道端壁冷却效率的槽缝冷却结构 |
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US3126705A (en) * | 1956-03-26 | 1964-03-31 | Combustion system | |
FR1248821A (fr) * | 1960-02-17 | 1960-12-23 | Entwicklungsbau Pirna Veb | Chambre de combustion annulaire pour turbines à gaz, notamment pour avions et turbine équipée de ladite chambre ou d'une chambre similaire |
GB980363A (en) * | 1961-12-04 | 1965-01-13 | Jan Jerie | Improvements in or relating to gas turbines |
GB1010338A (en) * | 1962-09-11 | 1965-11-17 | Lucas Industries Ltd | Means for supporting the downstream end of a combustion chamber in a gas turbine engine |
US3307354A (en) * | 1965-10-01 | 1967-03-07 | Gen Electric | Cooling structure for overlapped panels |
US3608310A (en) * | 1966-06-27 | 1971-09-28 | Gen Motors Corp | Turbine stator-combustor structure |
US3527053A (en) * | 1968-12-11 | 1970-09-08 | Gen Electric | Gas turbine engine with improved gas seal |
US3565545A (en) * | 1969-01-29 | 1971-02-23 | Melvin Bobo | Cooling of turbine rotors in gas turbine engines |
US3670497A (en) * | 1970-09-02 | 1972-06-20 | United Aircraft Corp | Combustion chamber support |
US3965066A (en) * | 1974-03-15 | 1976-06-22 | General Electric Company | Combustor-turbine nozzle interconnection |
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-
1984
- 1984-10-11 US US06/659,748 patent/US4739621A/en not_active Expired - Lifetime
-
1985
- 1985-06-28 CA CA000486033A patent/CA1245869A/en not_active Expired
- 1985-07-11 DE DE8585630109T patent/DE3566010D1/de not_active Expired
- 1985-07-11 EP EP85630109A patent/EP0178242B1/en not_active Expired
- 1985-07-11 DE DE198585630109T patent/DE178242T1/de active Pending
- 1985-07-12 IL IL75780A patent/IL75780A/xx not_active IP Right Cessation
- 1985-07-30 JP JP60168448A patent/JPS6196140A/ja active Pending
- 1985-08-05 CN CN85105913.9A patent/CN1003879B/zh not_active Expired
Also Published As
Publication number | Publication date |
---|---|
IL75780A (en) | 1991-04-15 |
CA1245869A (en) | 1988-12-06 |
EP0178242A1 (en) | 1986-04-16 |
CN85105913A (zh) | 1986-08-06 |
IL75780A0 (en) | 1985-11-29 |
DE178242T1 (de) | 1986-10-16 |
DE3566010D1 (en) | 1988-12-08 |
US4739621A (en) | 1988-04-26 |
JPS6196140A (ja) | 1986-05-14 |
EP0178242B1 (en) | 1988-11-02 |
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