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公开(公告)号：US5555721A
公开(公告)日：1996-09-17
申请号：US313951
申请日：1994-09-28
CPC分类号： F02C7/18
摘要： A turbine cooling supply circuit for a gas turbine engine is disclosed in which the flow of coolant through the engine is directed to minimize temperature rise prior to discharge into the turbine. Bleed air from an impeller stage of a compressor is channeled along a backwall thereof into a cavity disposed radially inwardly of a combustor casing. The cavity is divided by a lightweight tubular member having a circumferentially uniform contour into a non-flow zone proximate the casing and a flow zone proximate a rotor. Maintenance of a high tangential flow component in the bleed flow in the flow zone facilitates discharge of the flow through apertures in a rotor into a bore portion thereof, minimizing work input and temperature rise of the coolant. Further, the coolant is isolated from the hot casing wall and nonuniform structures disposed thereon, thereby reducing heat flux and temperature rise associated with aerodynamic drag caused by increased surface area, nonuniform interruptions in the stationary surface or any combination thereof. Features are incorporated in the tubular member to provide margin against buckling.
摘要翻译： 公开了一种用于燃气涡轮发动机的涡轮冷却供应回路，其中通过发动机的冷却剂流被引导以在排放到涡轮机之前使温度上升最小化。 来自压缩机的叶轮级的排出空气沿其后壁被引导到设置在燃烧器壳体的径向内侧的空腔中。 空腔由具有周向均匀轮廓的轻质管状构件分隔成靠近壳体的非流动区域和靠近转子的流动区域。 在流动区域中的排出流中维持高切向流动分量有助于将流过转子中的孔的流体排放到其孔部分中，从而最小化冷却剂的工作输入和温度上升。 此外，冷却剂与热套管壁和设置在其上的不均匀结构隔离，从而减少与由增加的表面积，固定表面的不均匀中断或其任何组合引起的空气动力学阻力相关联的热通量和温度升高。 特征被并入管状构件以提供抵抗屈曲的边缘。
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公开(公告)号：US6036441A
公开(公告)日：2000-03-14
申请号：US192225
申请日：1998-11-16
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and extending longitudinally from a root to a tip. The sidewalls are spaced apart from each other to define in part first and second adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding first and second partitions disposed between the sidewalls. The second partition is common to both chambers, and both partitions include respective pluralities of first and second inlet holes sized to meter cooling air therethrough in series between the chambers.
摘要翻译： 燃气涡轮发动机翼型件包括在相对的前缘和后缘处连接在一起的第一和第二侧壁，并且从根部到纵向延伸到尖端。 侧壁彼此间隔开，以限定在其中纵向延伸的第一和第二毗邻流动室，并且由另一部分由设置在侧壁之间的对应的第一和第二隔板限定。 第二分隔件对两个腔室是共同的，并且两个分隔件包括相应的多个第一入口孔和第二入口孔，其尺寸设计成用于计量串联在腔室之间的冷却空气。
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公开(公告)号：US06183198B2
公开(公告)日：2001-02-06
申请号：US09192229
申请日：1998-11-16
IPC分类号： F01D518
CPC分类号： F01D5/186 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and spaced apart from each other therebetween to define a leading edge channel extending longitudinally from a root to a tip of the airfoil. A plurality of film cooling holes extend through the leading edge and are disposed in flow communication with the leading edge channel. An isolation plenum extends along the first sidewall and adjacent the leading edge channel, and is separated therefrom by a partition having a plurality of inlet holes. A plurality of film cooling gill holes extend through the first sidewall, and are disposed in flow communication with the isolation plenum. Cooling air is channeled from the leading edge channel to the isolation plenum for feeding the gill holes with reduced pressure air.
摘要翻译： 燃气涡轮发动机翼型件包括在相对的前缘和后缘处连接在一起并且彼此间隔开的第一和第二侧壁，以限定从叶片纵向延伸到翼型的尖端的前缘通道。 多个膜冷却孔延伸穿过前缘并且与前缘通道流体连通地设置。 隔离通风室沿着第一侧壁延伸并且邻近前缘通道，并且通过具有多个入口孔的隔板与其隔开。 多个薄膜冷却鳃孔延伸穿过第一侧壁，并且与隔离气室成流动连通地设置。 冷却空气从前缘通道引导到隔离气室，用于通过减压空气供给鳃孔。
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公开(公告)号：US06227798B1
公开(公告)日：2001-05-08
申请号：US09451279
申请日：1999-11-30
IPC分类号： F01D514
CPC分类号： F01D25/12 , F01D5/18 , F01D9/041 , F05D2230/21 , F05D2240/128 , F05D2260/201 , Y02T50/676
摘要： A gas turbine engine nozzle segment includes at least two circumferentially adjacent vanes joined together along an interface between the vanes. Each of the vanes includes a hollow airfoil disposed between radially inner and outer band panels and a cooling air intake duct leading to a hollow interior of the airfoil for directing cooling air into the hollow interior. The intake duct has a duct wall protruding radially outward from the outer band panel and at least one impingement cooling hole disposed through the intake duct wall and circumferentially and radially inwardly angled. A flange portion extends circumferentially along the outer band panel and an opening in the flange portion is in fluid communication with the intake duct. The hollow airfoil, radially inner and outer band panels, intake duct wall, and flange portion are integrally formed and, preferably, integrally cast such that the vane is a single piece integrally cast vane.
摘要翻译： 燃气涡轮发动机喷嘴段包括沿叶片之间的界面连接在一起的至少两个周向相邻的叶片。 每个叶片包括设置在径向内部和外部带状面板之间的中空翼型件和通向翼型件的中空内部的冷却空气进气管道，用于将冷却空气引导到中空内部。 进气管具有从外带板径向向外突出的导管壁和至少一个冲击冷却孔，该冲击冷却孔设置成穿过进气管壁并沿周向和径向向内成角度。 凸缘部分沿着外带板沿周向延伸，并且凸缘部分中的开口与进气管道流体连通。 中空翼片，径向内外带板，进气管壁和凸缘部分一体地形成，并且优选地整体铸造，使得叶片是单件整体铸造叶片。
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公开(公告)号：US6099252A
公开(公告)日：2000-08-08
申请号：US192227
申请日：1998-11-16
CPC分类号： F01D5/187
摘要： A gas turbine engine airfoil includes an axial serpentine cooling circuit therein. A plurality of the serpentine circuits are preferably stacked in a radial row along the airfoil trailing edge for cooling thereof.
摘要翻译： 燃气涡轮发动机翼型件包括其中的轴向蛇形冷却回路。 多个蛇形回路优选地沿翼型后缘沿径向排堆叠以进行冷却。
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公开(公告)号：US4297077A
公开(公告)日：1981-10-27
申请号：US55833
申请日：1979-07-09
申请人： George A. Durgin , Daniel E. Demers
发明人： George A. Durgin , Daniel E. Demers
CPC分类号： F01D5/189 , F05D2260/201
摘要： A hollow gas turbine vane is shown enclosing, in spaced relation, a vane insert for receiving cooling air. The insert has a plurality of apertures for selectively directing jets of the cooling air against the internal walls of the vane. A portion of the air is discharged from within the vane chamber through a slit in the trailing edge which contains cooling pins extending transversely thereacross to maintain the slit dimensionally stable and also induce turbulence in the exhausting cooling air to improve its cooling effectiveness. Certain apertures in the insert adjacent the trailing edge are selectively directed to cause jets of the cooling air to impinge at the base of certain of the pins in the inlet area of the slit to promote turbulence in the air entering the slit and adjacent the internal face, thereby maximizing heat transfer from the slit walls to the air.
摘要翻译： 中空燃气涡轮机叶片被示出为间隔开地封闭用于接收冷却空气的叶片插入件。 插入件具有多个孔，用于选择性地将冷却空气的喷射限制在叶片的内壁上。 空气的一部分通过后缘的狭缝从叶片室内排出，其中包含横向横向延伸的冷却销，以保持狭缝的尺寸稳定性，并且还引起排气冷却空气中的湍流以提高其冷却效果。 与后缘相邻的插入件中的某些孔被选择性地导向，使得冷却空气的喷嘴在狭缝的入口区域中的某些销的基部处撞击，以促进进入狭缝的空气和邻近内表面的湍流 从而使从狭缝壁到空气的热传递最大化。
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