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1. 发明授权

EP3667167B1 COMBUSTOR LINER FOR GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3667167B1
公开(公告)日：2023-01-25
申请号：EP19215043.1
申请日：2019-12-10
发明人： Khoun, Laengheng , Pietraszkiewicz, Edward F , Kinnaman, Joshua E.
IPC分类号： F23R3/08 , F23R3/26 , F23R3/50

2. 发明授权

EP3076078B1 COMBUSTOR CONFIGURATIONS FOR A GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3076078B1
公开(公告)日：2019-10-16
申请号：EP16162430.9
申请日：2016-03-24
申请人： United Technologies Corporation
发明人： KWOKA, David , REZVANI, Reza , EASTWOOD, Jonathan Jeffery
IPC分类号： F23R3/08 , F23R3/00

3. 发明公开

EP3312508A1 GAS TURBINE COMBUSTOR 有权转让
标题翻译：燃气轮机燃烧器
公开(公告)号：EP3312508A1
公开(公告)日：2018-04-25
申请号：EP17197585.7
申请日：2017-10-20
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： MIURA, Keisuke , AKIYAMA, Yasuhiro , ASAI, Tomohiro , ABE, Kazuki , KARISHUKU, Mitsuhiro , DODO, Satoshi , HAYASHI, Akinori , HIRATA, Yoshitaka , OKUYAMA, Noboru
IPC分类号： F23R3/00 , F23R3/08 , F23R3/60 , F23R3/28
CPC分类号： F23R3/286 , F02C3/05 , F02C7/222 , F02C7/28 , F23D14/64 , F23R3/002 , F23R3/08 , F23R3/12 , F23R3/20 , F23R3/58 , F23R3/60 , F23R2900/00005 , F23R2900/00012 , F24H3/0488 , Y02B30/28
摘要： A highly reliable gas turbine combustor with a multi-cluster burner structure which prevents deformation/damage of a swirler lip on an air hole plate periphery by cooling the periphery effectively. The gas turbine combustor includes a swirler lip on the air hole plate periphery, protruding toward a chamber, and a spring seal in an area for fitting the liner and the plate/lip . The spring seal has an air hole for passage of part of the combustion air introduced in the gap between the outer periphery of the air hole plate and the liner. The swirler lip has an air hole which introduces part of the combustion air passing through the spring seal air hole into the chamber. The liner has an air hole facing the spring seal air hole, to introduce part of air from outside the liner into the gap between the outer periphery of the air hole plate and the liner. A turn guide for rectifying a combustion air flow is provided at the liner end portion on the side for fitting the liner and air hole plate.
摘要翻译：具有多簇式燃烧器结构的高度可靠的燃气轮机燃烧器，其通过有效地冷却周边来防止气孔板周边上的旋流器唇缘变形/损坏。燃气轮机燃烧器包括在气孔板周边上朝向腔室突出的旋流器唇缘以及在用于装配衬管和板/唇缘的区域中的弹簧密封件。弹簧密封件具有气孔，用于使引入到气孔板的外周与衬套之间的间隙中的燃烧空气的一部分通过。旋流器唇部具有气孔，该气孔将通过弹簧密封空气孔的部分燃烧空气引入腔室中。衬套具有面对弹簧密封空气孔的空气孔，以将来自衬套外部的部分空气引入空气孔板的外周与衬套之间的间隙中。用于整流燃烧空气流的转向引导件设置在用于装配衬里和空气孔板的一侧的衬里端部处。

4. 发明公开

EP3106755A3 COMBUSTION DUCT ASSEMBLY FOR GAS TURBINE 有权
标题翻译： VERBRENNUNGSKANALANORDNUNGFÜREINE GASTURBINE
公开(公告)号：EP3106755A3
公开(公告)日：2017-02-08
申请号：EP16174803.3
申请日：2016-06-16
申请人： Doosan Heavy Industries & Construction Co., Ltd.
发明人： JIN, Heon Seop
IPC分类号： F23R3/08 , F01D9/02
CPC分类号： F23R3/002 , F01D9/023 , F02C7/18 , F02C7/28 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F23R3/08 , F23R3/42 , F23R2900/00012
摘要： A combustion duct assembly for a gas turbine includes a liner, an annular spring seal and a transition piece. The annular spring seal is outwardly convex and coupled to an outer face of the downstream side of the liner. The transition piece has includes an inner wall and an outer wall that surrounds the inner wall. The convex part of annular spring seal is operable to elastically engage the inner wall of the transition piece. An end portion of the downstream side of the annular spring seal is fixed to the line. The annular spring seal includes a plurality of through holes formed in an upstream side of a point where the annular spring seal comes into contact with the inner wall. The liner includes a plurality of vent holes formed in an inner area surrounded by the spring seal.
摘要翻译：用于燃气涡轮机的燃烧管道组件包括衬套，环形弹簧密封件和过渡件。环形弹簧密封件向外凸出并且联接到衬套的下游侧的外表面。过渡件包括内壁和围绕内壁的外壁。环形弹簧密封件的凸形部分可操作以弹性地接合过渡件的内壁。环形弹簧密封件的下游侧的端部固定在该线上。环形弹簧密封件包括形成在环形弹簧密封件与内壁接触的点的上游侧的多个通孔。衬套包括形成在由弹簧密封件包围的内部区域中的多个通气孔。

5. 发明公开

EP2148140A3 Flow sleeve impingement cooling baffles 审中-公开
标题翻译：套筒状的具有挡板的冲击冷却
公开(公告)号：EP2148140A3
公开(公告)日：2013-03-20
申请号：EP09251001.5
申请日：2009-03-31
申请人： United Technologies Corporation
发明人： Chokshi, Jaisukhlal V. , Smith, Craig F. , Figueroa, Carlos G. , George, Larry C.
IPC分类号： F23R3/06 , F23R3/08
CPC分类号： F23R3/08 , F23R3/06 , F23R2900/03044
摘要： A combustor assembly (10) for a turbine engine includes a combustor liner (12), a flow sleeve (14) and a baffle ring (36). The flow sleeve surrounds the combustor liner. An annulus (26) is formed between the flow sleeve and the combustor liner. A plurality of rows of cooling holes (24) are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.

6. 发明公开

EP1882822A3 Cooled exhaust liner assembly for a gas turbine 有权转让
标题翻译：冷却插入涡轮发动机的排气喷管
公开(公告)号：EP1882822A3
公开(公告)日：2011-02-23
申请号：EP07252042.2
申请日：2007-05-18
申请人： United Technologies Corporation
发明人： Lavin, Jeffrey R. , Murphy, Michael J.
IPC分类号： F01D11/00 , F01D25/12 , F01D25/30 , F02K1/82 , F23R3/08
CPC分类号： F01D25/30 , F01D11/005 , F01D25/12 , F02K1/822 , Y02T50/675
摘要： An exhaust liner assembly (24) including an interface (30) between moveable parts (50, 52) includes a seal liner (35) having a plurality of slots (42). The size of each slot (42) varies with the circumferential position of the liner assembly (24) to provide a stable cavity pressure within the interface (30) to create a stable barrier about the entire circumference of the exhaust liner assembly (24).

7. 发明公开

EP2261565A1 Gasturbinenbrennkammer und Gasturbine 审中-公开
标题翻译： Gasturbinenbrennkammer和Gurburbine
公开(公告)号：EP2261565A1
公开(公告)日：2010-12-15
申请号：EP09162297.7
申请日：2009-06-09
申请人： Siemens Aktiengesellschaft
发明人： Burbach, Björn , Buse, Christoph , Casu, Alessandro , Colmegna, Giacomo , Gruschka, Uwe , Grüger, Birgit , Heilos, Andreas , Schneider, Thomas Alexis , Stamm, Werner , Völker, Stefan , Wörz, Ulrich , Zimmermann, Adam , auf dem Kampe, Tilman , van Kampen, Jaap
IPC分类号： F23R3/08 , F23M5/08 , F23R3/00
CPC分类号： F23R3/44 , F23M5/085 , F23M2900/05004 , F23R3/08 , F23R2900/03042
摘要： Es wird eine Gasturbinenbrennkammer (25) mit im Wesentlichen rotationssymmetrischem Querschnitt zur Verfügung gestellt. Sie weist eine innere Wand (39) mit einer Außenseite und eine äußere Wand (37) mit einer der Außenseite der inneren Wand zugewandten und von dieser beabstandeten Innenseite auf, so dass zwischen der Außenseite der inneren Wand (39) und der Innenseite der äußeren Wand (37) ein wenigstens einen Kühlfluidkanal bildender Zwischenraum (41) vorhanden ist und wobei die Außenwand (37) zum Zwischenraum (41) führende Eintrittsöffnungen (49) für ein Kühlfluid aufweist. Erfindungsgemäß ist im Zwischenraum (41) zumindest partiell eine poröse, metallische Struktur vorgesehen.
摘要翻译：所述腔室（25）具有包括外侧的内壁（39A-39C）和外壁（37），所述外壁（37）包括内壁，所述内侧与所述内壁的外侧距离一定距离，使得间隙（41A-41C ）形成在内壁的外侧和外壁的内侧之间的冷却通道。外壁具有用于冷却流体的通孔（49），并且在间隙中形成多孔金属结构（30），并由invar（RTM：镍钢合金）制成。内壁和外壁在室的轴向方向上形成为单件。

8. 发明公开

EP1231435A3 Slot cooled combustor liner 有权
标题翻译：槽冷却燃烧室壁
公开(公告)号：EP1231435A3
公开(公告)日：2004-01-14
申请号：EP02250778.4
申请日：2002-02-05
申请人： GENERAL ELECTRIC COMPANY
发明人： Young, Craig Douglas , Kutter, Ella Christine
IPC分类号： F23R3/08 , F23R3/52
CPC分类号： F23R3/50 , F23R3/08 , Y02T50/675
摘要： A combustor liner (12) for use in a gas turbine engine includes a first annular panel section (42) having a forward end, an aft end and a first cooling nugget (48) located at the forward end thereof, and a second annular panel section (43) having a forward end, an aft end and a second cooling nugget (56) located at the forward end thereof. The second panel section (43) is joined at its forward end to the aft end of the first panel section (42). A first row of cooling holes (54) is located in the first cooling nugget (48), and a second row of cooling holes (54) is located in the second cooling nugget (56). A group of dilution holes (84) is located in the first panel section (42). The dilution holes (84) are located at the aft end of the first panel section (42), immediately upstream of the second cooling nugget (56). Furthermore, each one of the dilution holes (84) defines an aftmost edge, and all of the aftmost edges are axially aligned, even if the dilution holes (84) have different hole diameters.

9. 发明公开

EP1249663A3 Gas turbine combustor, particularly for an aircraft engine 有权
标题翻译： Gasturbinenverbrennungsanlage，insbesonderefüreinen Flugzeugmotor
公开(公告)号：EP1249663A3
公开(公告)日：2002-11-20
申请号：EP02007907.5
申请日：2002-04-09
申请人： FIATAVIO S.p.A.
发明人： Coutandin, Daniele
IPC分类号： F23R3/00 , F23R3/06 , F23R3/08 , F23R3/26
CPC分类号： F23R3/54 , F23R3/08 , F23R3/26 , Y02T50/675
摘要： A gas turbine combustor (5), in particular for an aircraft engine (1), has at least one chamber (14), through which combustion gas flows in use, and which is defined by a lateral wall (15) with channeling (60) for feeding cooling air into the chamber (14) and cooling the lateral wall (15); part of the channeling (60) is defined by at least one double wall (31, 32, 36) for guiding a relative stream (F1, F2) of cooling air into the chamber (14) in a tangential direction with respect to the lateral wall (15).
摘要翻译：特别是用于飞行器发动机（1）的燃气涡轮机燃烧器（5）具有至少一个腔室（14），燃烧气体在其中流动使用，并且由具有通道（60）的侧壁（15）限定，），用于将冷却空气送入室（14）并冷却侧壁（15）; 通道（60）的一部分由至少一个双壁（31,32,36）限定，用于将冷却空气的相对流（F1，F2）沿相对于侧面的切线方向引导到室（14）中墙（15）。

10. 发明公开

EP1156280A2 Gas turbine engine liner 有权
标题翻译：燃气轮机发动机缸套
公开(公告)号：EP1156280A2
公开(公告)日：2001-11-21
申请号：EP01304302.1
申请日：2001-05-15
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Narcus, Andrew , Pechette, Thomas F. , Brewer, Keith
IPC分类号： F23R3/08
CPC分类号： F23R3/26
摘要： A liner for a gas turbine engine is provided that includes a first liner section 30 and a second liner section 32. The first liner section 30 includes a first flange 34 having a first contact surface 36. The second liner section 32 includes a second flange 47 having a second contact surface 44 and a plurality of apertures 46. The first and second flanges 36,42 axially overlap one another, and in a circumferential liner the second flange 42 is disposed radially outside of the first flange 34. A channel 48 is formed by the two liner sections that is open to the core gas path. In a first position, the first flange 34 axially overlaps the second flange 42 by a first distance and the apertures 46 are misaligned with the first flange 34 and disposed within the channel 48. Cooling air entering apertures 46 within the second flange 42 subsequently passes into the channel 48. In a second position, the first flange 34 axially overlaps the second flange 42 by a second distance. The second distance is greater than the first distance and in the second position the apertures 46 in the second flange 42 are substantially aligned with the first flange 34. Cooling air entering the second flange apertures 46 subsequently impinges on the first flange 34.
摘要翻译：提供了用于燃气涡轮发动机的衬套，其包括第一衬套部分30和第二衬套部分32.第一衬套部分30包括具有第一接触表面36的第一凸缘34.第二衬套部分32包括第二凸缘47 具有第二接触表面44和多个孔46.第一和第二凸缘36,42彼此轴向重叠，并且在周向衬里中，第二凸缘42设置在第一凸缘34的径向外侧。形成通道48 通过对核心气体通道开放的两个衬管部分。在第一位置，第一凸缘34与第二凸缘42轴向重叠第一距离，并且孔46与第一凸缘34未对准并且设置在通道48内。进入第二凸缘42内的孔46的冷却空气随后进入在第二位置中，第一凸缘34与第二凸缘42轴向重叠第二距离。第二距离大于第一距离，并且在第二位置中，第二凸缘42中的孔46与第一凸缘34基本对齐。进入第二凸缘孔46的冷却空气随后撞击在第一凸缘34上。

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