CN1004291B - 燃气轮机叶片用的多室翼面冷却插入件 - Google Patents
燃气轮机叶片用的多室翼面冷却插入件 Download PDFInfo
- Publication number
- CN1004291B CN1004291B CN85108282.3A CN85108282A CN1004291B CN 1004291 B CN1004291 B CN 1004291B CN 85108282 A CN85108282 A CN 85108282A CN 1004291 B CN1004291 B CN 1004291B
- Authority
- CN
- China
- Prior art keywords
- mentioned
- chamber
- inserting member
- blade
- cup
- 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
- 238000001816 cooling Methods 0.000 title claims description 15
- 239000011148 porous material Substances 0.000 claims description 11
- 239000007921 spray Substances 0.000 claims description 3
- 230000035939 shock Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
一种翼面形状的燃气轮机叶片,它有一个单一整体的插入件22,插入件由多块径向延伸的肋板38、40、42分隔为一个前室30和接续的后室32、34、36,后室入口处装有节流装置48,而流入前塞的空气流46则不受限制,使前室的压力比后室高,因而通过冲击气孔56喷出的冲击气流其速度高于从低压后室通过冲击气孔58和60喷出的冲击气流的速度。
Description
本发明涉及一种燃气轮机,特别是涉及一种翼面形状的具有前沿壁的空心的燃气轮机叶片。此种燃气轮机翼面形叶片装有一个插入件,整体安排成提供叶片的空气冷却。
已知静叶片的不同段位需要不同的冷却程度。叶片结构是特征的,处于要求低的或中等冷却程度的段位,该冷却程度可以利用对准叶片内壁的冲击气流来达到。即使对于那些不需要高度冷却的叶片来说,叶片上不同部位所需的冷却程度也可能不同,叶片的前沿区通常具有较高的热负载,而在后边靠近叶片的后沿处,热负载可能相当低。
为了获得这样的不同冷却率,如美国专利第U.S.4,056,332号所示的燃气轮机叶片中有许多插入件,使得冷却气流到最需冷却的适当的内表面区域。但是,这些插入件必须分开插入并保持在适当的相对位置上,以便保证适宜的冷却空气的分配。
本发明的目的是提供一种叶片和插入件的结构,在这种结构中叶片具有单一的内腔,其中安装了一个单一的整体的空心插入件,插入件具有隔室和气流冲击气孔,它们都是为了使对叶片内壁的冲击冷却与外部热负载互相联系起来而特制的。
鉴于此目的,本发明属于一种具有翼面形状的空心的轮机叶片的燃气轮机;轮机叶片有前沿壁,带有空气出口槽缝的后沿部分,和两面耐压和耐抽吸的侧壁,两面侧壁构成一个与上述空气出口槽缝相连通的内腔;空心插入件的截面大体上与翼面形状互补,插入件置于上述空腔内,沿弦向延伸到大致充满整个上述空腔的程度,且与侧壁呈间隔关系,其特征在于:该插入件内有多块径向延伸的隔板,将内部分为一个位于上述叶片前沿部分内的前室和至少两个彼此相通的分开而接续的后室,在所有上述前室和后室的插入件侧壁上有许多冲击气孔,上述前室和后室的一个径向端部与一个冷却空气源相连通,插入件带有使流入上述后室的空气节流的装置,使上述前室中的压力相对地高于上述后室中的压力,因此,通过上述前室的气孔喷向上述前沿部分叶片内壁的冲击气流其速度要显著地高于从上述后室的气孔喷出的冲击气流的速度。
使流入后室的空气节流的装置,使得前室中的压力相对地高于上述后室中的压力。因此,通过上述前室的气孔喷向上述沿部分叶片内壁的冲击气流其速度要显著地高于从后室的气孔喷出的冲击气流的速度。整体的插入件是预先组装的,其气流冲击孔为预定尺寸,因此,相对的冷却空气流速度趋于保持在设计值。另外,整体构件便于插入空心的叶片,而无需相对于其他的孔洞调整位置。
下面作为例子参考附图描述本发明,附图中
图1是通过叶片和插入件的弦向截面图,它取自沿图2的Ⅰ-Ⅰ线截取的截面;
图2是叶片和插入件的部分正视图和部分截面图,对应于沿图1中Ⅱ-Ⅱ线截取的视图。
图1表示一个具有单一内腔的空心叶片,内腔由前沿部、凹形侧壁14、凸形侧壁16形成,后两个相对侧壁的下游部构成了一个带有槽缝20的后沿部分18。热气通过叶片的总方向如图1中虚线箭头所示。
单一的整体的空气冷却的空心插入件22的截面具有翼面形状,与叶片的翼面形状互补,它沿弦向延伸到大致充满整个叶片空腔的程度。虽然插入件具有翼面的全部形状,但从图1中可以见到,插入件在前沿部分24稍许鼓胀,在后沿部分26也同样地出现鼓胀。在前后鼓胀之间的中间部分28的壁,与叶片壁之间的距离基本均匀。
整体插入件22的内部由径向延伸的分隔件38、40和42分隔为前室30和依次向后排布的隔室32、34、36,分隔件38、40和42也起结构连结作用。
Claims (6)
1、一种带有翼面形状的燃气轮机空心轮机叶片,其轮机叶片(12)有一个前沿壁,一个带有空气出口槽缝(20)的后沿部分(18),和两面耐压和耐抽吸的侧壁(14,16),两面侧壁构成一个与上述出口槽缝相通的内腔,空心插入件(22)的截面大体上与翼面形状互补,插入件置于上述空腔内,沿弦向延伸到大致充满整个上述空腔的程度且与上述侧壁呈间隔开关系,其特征在于,上述插入件(22)是单一的整体构件,每个插入件内有多块径向延伸的隔板(38,40,42),将内部分为一个位于上述叶片(12)前沿部分内的前室(30)和至少两个彼此相通的分开而接续的后室(32,34,36),在所有上述前室和后室(30-36)的插入件侧壁上,开有许多冲击气孔(56,58,60),上述前室和后室(30,36)的一个径向端部与一个冷却空气源相连通,插入件带有使流入上述后室(32-36)的空气节流的装置(52,54),使上述前室(30)中的压力相对地高于上述后室中的压力,通过上述前室(30)的气孔(56)的气体喷向上述前沿部分叶片内壁(14,16)的冲击气流其速度要显著地高于从上述后室(32,34,36)的气孔(58,60)喷出的冲击气流的速度。
2、如权利要求1中所要求的燃气轮机叶片,其特征是在该轮机叶片中上述前室(30)中的冲击气孔(56)的行距比上述后室(32,34,36)中的大多数冲击气孔(58,60)的行距更宽。
3、如权利要求1或2中所要求的燃气轮机叶片,其特征是:在该轮机中叶片上述节流装置包括插入件(22)在上述后室(32,34,36)径向外端处的径向外延部分(48),以及上述插入件(22)径向外延部分(48)上的许多个节流孔(54)。
4、如权利要求1所要求的燃气轮机叶片,其特征是:在该轮机叶片中上述后室至少包括三个隔室(32,34,36)。
5、如权利要求1所要求的燃气轮机叶片,其特征是:在该轮机叶片中上述隔开件(38,40,42)由坚硬的延伸肋板构成,在使上述前室(30)与第一个接续的后室(32)相分开的第一块肋板(38)上不穿孔,而后面接续的两块肋板(40,42)上面有开孔(62)。
6、如权利要求5中所要求的燃气轮机叶片,其特征是:在该轮机叶片中上述后面两块肋板(40,42)径向向外延伸的长度小于上述第一块肋板(38),使得上述后室(32,34,36)在其径向外端部彼此敞开连通。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US67184684A | 1984-11-15 | 1984-11-15 | |
US671,846 | 1984-11-15 |
Publications (2)
Publication Number | Publication Date |
---|---|
CN85108282A CN85108282A (zh) | 1986-08-27 |
CN1004291B true CN1004291B (zh) | 1989-05-24 |
Family
ID=24696102
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN85108282.3A Expired CN1004291B (zh) | 1984-11-15 | 1985-11-14 | 燃气轮机叶片用的多室翼面冷却插入件 |
Country Status (9)
Country | Link |
---|---|
EP (1) | EP0182588B1 (zh) |
JP (1) | JPS61126302A (zh) |
KR (1) | KR860004224A (zh) |
CN (1) | CN1004291B (zh) |
CA (1) | CA1221915A (zh) |
DE (1) | DE3565298D1 (zh) |
IN (1) | IN163070B (zh) |
IT (1) | IT1186049B (zh) |
MX (1) | MX161444A (zh) |
Families Citing this family (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2189553B (en) * | 1986-04-25 | 1990-05-23 | Rolls Royce | Cooled vane |
US5212940A (en) * | 1991-04-16 | 1993-05-25 | General Electric Company | Tip clearance control apparatus and method |
US5207556A (en) * | 1992-04-27 | 1993-05-04 | General Electric Company | Airfoil having multi-passage baffle |
US6183192B1 (en) * | 1999-03-22 | 2001-02-06 | General Electric Company | Durable turbine nozzle |
DE10004128B4 (de) | 2000-01-31 | 2007-06-28 | Alstom Technology Ltd. | Luftgekühlte Turbinenschaufel |
US6609880B2 (en) * | 2001-11-15 | 2003-08-26 | General Electric Company | Methods and apparatus for cooling gas turbine nozzles |
US6652220B2 (en) * | 2001-11-15 | 2003-11-25 | General Electric Company | Methods and apparatus for cooling gas turbine nozzles |
US7008185B2 (en) * | 2003-02-27 | 2006-03-07 | General Electric Company | Gas turbine engine turbine nozzle bifurcated impingement baffle |
US7871246B2 (en) | 2007-02-15 | 2011-01-18 | Siemens Energy, Inc. | Airfoil for a gas turbine |
CN104088673B (zh) * | 2008-11-07 | 2016-03-09 | 三菱日立电力系统株式会社 | 涡轮用叶片 |
CN101825115B (zh) * | 2010-03-31 | 2011-09-28 | 北京航空航天大学 | 一种内置排骨架式气动阻尼的叶片 |
US20130104567A1 (en) * | 2011-10-31 | 2013-05-02 | Douglas Gerard Konitzer | Method and apparatus for cooling gas turbine rotor blades |
US9004866B2 (en) * | 2011-12-06 | 2015-04-14 | Siemens Aktiengesellschaft | Turbine blade incorporating trailing edge cooling design |
US9506351B2 (en) | 2012-04-27 | 2016-11-29 | General Electric Company | Durable turbine vane |
EP2706195A1 (en) * | 2012-09-05 | 2014-03-12 | Siemens Aktiengesellschaft | Impingement tube for gas turbine vane with a partition wall |
EP3189213A1 (en) * | 2014-09-04 | 2017-07-12 | Siemens Aktiengesellschaft | Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of a gas turbine airfoil |
GB201417476D0 (en) | 2014-10-03 | 2014-11-19 | Rolls Royce Plc | Internal cooling of engine components |
US10329932B2 (en) * | 2015-03-02 | 2019-06-25 | United Technologies Corporation | Baffle inserts |
US9849510B2 (en) | 2015-04-16 | 2017-12-26 | General Electric Company | Article and method of forming an article |
US9976441B2 (en) | 2015-05-29 | 2018-05-22 | General Electric Company | Article, component, and method of forming an article |
US9850763B2 (en) | 2015-07-29 | 2017-12-26 | General Electric Company | Article, airfoil component and method for forming article |
US10739087B2 (en) | 2015-09-08 | 2020-08-11 | General Electric Company | Article, component, and method of forming an article |
US10087776B2 (en) | 2015-09-08 | 2018-10-02 | General Electric Company | Article and method of forming an article |
US10253986B2 (en) | 2015-09-08 | 2019-04-09 | General Electric Company | Article and method of forming an article |
US10655477B2 (en) | 2016-07-26 | 2020-05-19 | General Electric Company | Turbine components and method for forming turbine components |
US10400608B2 (en) * | 2016-11-23 | 2019-09-03 | General Electric Company | Cooling structure for a turbine component |
US10260363B2 (en) | 2016-12-08 | 2019-04-16 | General Electric Company | Additive manufactured seal for insert compartmentalization |
US10494948B2 (en) * | 2017-05-09 | 2019-12-03 | General Electric Company | Impingement insert |
US10480347B2 (en) | 2018-01-18 | 2019-11-19 | United Technologies Corporation | Divided baffle for components of gas turbine engines |
US10697309B2 (en) | 2018-04-25 | 2020-06-30 | Raytheon Technologies Corporation | Platform cover plates for gas turbine engine components |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2873944A (en) * | 1952-09-10 | 1959-02-17 | Gen Motors Corp | Turbine blade cooling |
FR1177035A (fr) * | 1957-05-28 | 1959-04-20 | Snecma | Procédé et dispositif de refroidissement d'organes de machines |
US3540810A (en) * | 1966-03-17 | 1970-11-17 | Gen Electric | Slanted partition for hollow airfoil vane insert |
US3891348A (en) * | 1972-04-24 | 1975-06-24 | Gen Electric | Turbine blade with increased film cooling |
GB1587401A (en) * | 1973-11-15 | 1981-04-01 | Rolls Royce | Hollow cooled vane for a gas turbine engine |
CH584346A5 (zh) * | 1974-11-08 | 1977-01-31 | Bbc Sulzer Turbomaschinen | |
US4297077A (en) * | 1979-07-09 | 1981-10-27 | Westinghouse Electric Corp. | Cooled turbine vane |
-
1985
- 1985-10-22 IN IN755/CAL/85A patent/IN163070B/en unknown
- 1985-10-24 MX MX375A patent/MX161444A/es unknown
- 1985-11-07 JP JP60248171A patent/JPS61126302A/ja active Granted
- 1985-11-11 IT IT8522785A patent/IT1186049B/it active
- 1985-11-13 EP EP85308230A patent/EP0182588B1/en not_active Expired
- 1985-11-13 CA CA000495185A patent/CA1221915A/en not_active Expired
- 1985-11-13 DE DE8585308230T patent/DE3565298D1/de not_active Expired
- 1985-11-14 CN CN85108282.3A patent/CN1004291B/zh not_active Expired
- 1985-11-15 KR KR1019850008558A patent/KR860004224A/ko not_active Application Discontinuation
Also Published As
Publication number | Publication date |
---|---|
JPH0379522B2 (zh) | 1991-12-19 |
IT1186049B (it) | 1987-11-18 |
CA1221915A (en) | 1987-05-19 |
MX161444A (es) | 1990-09-27 |
JPS61126302A (ja) | 1986-06-13 |
CN85108282A (zh) | 1986-08-27 |
KR860004224A (ko) | 1986-06-18 |
IN163070B (zh) | 1988-08-06 |
IT8522785A0 (it) | 1985-11-11 |
EP0182588B1 (en) | 1988-09-28 |
EP0182588A1 (en) | 1986-05-28 |
DE3565298D1 (en) | 1988-11-03 |
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