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公开(公告)号：EP1496204B1
公开(公告)日：2006-04-12
申请号：EP04252650.9
申请日：2004-05-06
CPC分类号： F01D5/20 , F01D5/184 , F01D5/186 , Y02T50/673 , Y02T50/676
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公开(公告)号：EP1496204A1
公开(公告)日：2005-01-12
申请号：EP04252650.9
申请日：2004-05-06
CPC分类号： F01D5/20 , F01D5/184 , F01D5/186 , Y02T50/673 , Y02T50/676
摘要： A turbine blade (10) includes a hollow airfoil (12) integrally joined to a dovetail (14). The airfoil (12) includes a perforate first bridge (30) defining a flow channel (32) behind the airfoil leading edge (22). A second bridge (40) is spaced behind the first bridge (30) and extends from a pressure sidewall (18) of the airfoil short of the airfoil trailing edge (24). A third bridge (44) has opposite ends joined to the pressure sidewall (18) and the second bridge (40) to define with the first bridge a supply channel (46) for the leading edge channel (32), and defines with the second bridge a louver channel (48) extending aft along the second bridge to its distal end at the pressure sidewall (18).
摘要翻译： 涡轮机叶片（10）包括与燕尾榫（14）一体连接的中空翼型件（12）。 翼型件（12）包括限定翼型件前缘（22）后面的流动通道（32）的多孔第一桥（30）。 第二桥（40）在第一桥（30）的后面间隔开并且从翼型的压力侧壁（18）延伸到翼型后缘（24）之外。 第三桥（44）具有连接到压力侧壁（18）和第二桥（40）的相对端以与第一桥限定用于前缘通道（32）的供应通道（46），并且与第二桥 在所述压力侧壁（18）处桥接沿着所述第二桥向后延伸到其远端的百叶窗通道（48）。
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公开(公告)号：EP0486133B1
公开(公告)日：1996-12-18
申请号：EP91306338.4
申请日：1991-07-12
CPC分类号： F23R3/002 , B23K26/389 , F02K1/822 , F05D2260/202 , Y02T50/67 , Y02T50/671 , Y02T50/676
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公开(公告)号：EP0534586A1
公开(公告)日：1993-03-31
申请号：EP92303636.2
申请日：1992-04-23
CPC分类号： F01D5/147 , F01D5/187 , F05D2260/201
摘要： An impingement-cooled gas turbine blade includes an impingement baffle (13) which, during engine operation, is subject only to shear loading. A tubular baffle body (14) is provided with a pair of mounting flanges (27) which are bonded between a forward portion (12) of the turbine blade and an aft portion (12a) of the turbine blade. The bond extends from the blade dovetail to the blade tip.
摘要翻译： 冲击冷却的燃气轮机叶片包括冲击挡板（13），其在发动机操作期间仅经受剪切载荷。 管状挡板体（14）设置有一对安装凸缘（27），其连接在涡轮叶片的前部（12）和涡轮叶片的后部（12a）之间。 接合处从叶片燕尾榫延伸到叶片尖端。
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公开(公告)号：EP1471243A3
公开(公告)日：2007-09-05
申请号：EP04252347.2
申请日：2004-04-21
发明人： Venkataramani, Kattalaicheri Srinivasan , Butler, Lawrence , Lee, Ching-Pang , Maclin, Harvey Michael
IPC分类号： F02K7/075 , F02K7/02 , F02K7/00 , F02K3/06 , F02C5/04 , F02C5/06 , F01D1/32 , F02C3/16 , F02C7/22 , F23R3/56 , F23R7/00
摘要： A pulse detonation system (40) for a gas turbine engine (10) having a longitudinal centerline axis (12) extending therethrough includes a rotatable cylindrical member (42) having a forward surface (44), an aft surface (46), and an outer circumferential surface (48), where a plurality of spaced detonation passages (52) are disposed therethrough. Each detonation passage (52) includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis (12). The pulse detonation system (40) further includes a shaft (36) rotatably connected to the cylindrical member (42) and a stator (62) configured in spaced arrangement with the forward surface (44) of the cylindrical member (42) and a portion of the shaft (36). The stator (62) has at least one group of ports formed therein alignable with the detonation passages (52) as the cylindrical member (42) rotates. In this way, detonation cycles are performed in the detonation passages (52) so that combustion gases exit the aft surface (46) of the cylindrical member (42) to create a torque which causes the cylindrical member (42) to rotate.
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公开(公告)号：EP1533473B1
公开(公告)日：2007-06-13
申请号：EP04257129.9
申请日：2004-11-17
CPC分类号： F01D25/12 , F01D5/082 , F01D5/084 , F01D5/085 , F02C7/18 , Y02T50/673 , Y02T50/676
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公开(公告)号：EP1533473A1
公开(公告)日：2005-05-25
申请号：EP04257129.9
申请日：2004-11-17
CPC分类号： F01D25/12 , F01D5/082 , F01D5/084 , F01D5/085 , F02C7/18 , Y02T50/673 , Y02T50/676
摘要： A turbofan engine (10) includes in serial flow communication a first fan (12), second fan (14), multistage compressor (16), combustor (20), first turbine (26), second turbine (30), and third turbine (34). The first turbine (26) is joined to the compressor by a first shaft (28). The second turbine (30) is joined to the second fan (14) by a second shaft (32). And, the third turbine (34) is joined to the first fan (12) by a third shaft (36). First, second, and third cooling circuits (40,42,44) are joined to different stages of the compressor (16) for cooling the forward and aft sides and center bore of the first turbine (26) with different pressure air.
摘要翻译： 涡轮风扇发动机（10）包括串联流动连通的第一风扇（12），第二风扇（14），多级压缩机（16），燃烧器（20），第一涡轮机（26），第二涡轮机（30） （34）。 第一涡轮（26）通过第一轴（28）连接到压缩机。 第二涡轮（30）通过第二轴（32）连接到第二风扇（14）。 并且，第三涡轮（34）通过第三轴（36）连接到第一风扇（12）。 第一，第二和第三冷却回路（40,42,44）连接到压缩机（16）的不同级，以用不同的压力空气冷却第一涡轮（26）的前后侧和中心孔。
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公开(公告)号：EP1655454B1
公开(公告)日：2011-06-15
申请号：EP05256817.7
申请日：2005-11-03
CPC分类号： F23R3/002 , F01D5/183 , F01D5/186 , F01D5/288 , F05D2230/90 , F05D2300/611 , F23R2900/03041
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公开(公告)号：EP1655454A1
公开(公告)日：2006-05-10
申请号：EP05256817.7
申请日：2005-11-03
CPC分类号： F23R3/002 , F01D5/183 , F01D5/186 , F01D5/288 , F05D2230/90 , F05D2300/611 , F23R2900/03041
摘要： A gas turbine engine component (40) includes a substrate wall (50) including a first surface (52) and an opposite second surface (54), and a plurality of pores (56) extending through the wall. The component also includes a thermal barrier coating (TBC) (74) extending over the wall first surface, wherein the TBC substantially seals the pores at the first surface. The component also includes a plurality of film cooling holes (58) extending through the wall and the TBC, wherein the plurality of film cooling holes and the plurality of pores extend substantially perpendicularly through the wall and the TBC.
摘要翻译： 一种燃气涡轮发动机部件（40）包括：衬底壁（50），包括第一表面（52）和相对的第二表面（54）;以及多个孔（56）延伸穿过壁。 所述部件还包括在所述壁第一表面上延伸的热障涂层（TBC）（74），其中所述TBC基本上密封所述第一表面处的孔。 所述部件还包括延伸穿过所述壁和所述TBC的多个薄膜冷却孔（58），其中所述多个薄膜冷却孔和所述多个孔基本垂直地穿过所述壁和所述TBC延伸。
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公开(公告)号：EP1471243A2
公开(公告)日：2004-10-27
申请号：EP04252347.2
申请日：2004-04-21
发明人： Venkataramani, Kattalaicheri Srinivasan , Butler, Lawrence , Lee, Ching-Pang , Maclin, Harvey Michael
摘要： A pulse detonation system (40) for a gas turbine engine (10) having a longitudinal centerline axis (12) extending therethrough includes a rotatable cylindrical member (42) having a forward surface (44), an aft surface (46), and an outer circumferential surface (48), where a plurality of spaced detonation passages (52) are disposed therethrough. Each detonation passage (52) includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis (12). The pulse detonation system (40) further includes a shaft (36) rotatably connected to the cylindrical member (42) and a stator (62) configured in spaced arrangement with the forward surface (44) of the cylindrical member (42) and a portion of the shaft (36). The stator (62) has at least one group of ports formed therein alignable with the detonation passages (52) as the cylindrical member (42) rotates. In this way, detonation cycles are performed in the detonation passages (52) so that combustion gases exit the aft surface (46) of the cylindrical member (42) to create a torque which causes the cylindrical member (42) to rotate.
摘要翻译： 可旋转的圆柱形构件（42）具有间隔开的引爆通道，在其中进行爆震循环，使得燃烧气体离开构件的后表面以产生使构件旋转的扭矩。
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