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公开(公告)号：US5134844A
公开(公告)日：1992-08-04
申请号：US560538
申请日：1990-07-30
申请人： Ching-Pang Lee , Clay K. Carlson , Monty L. Shelton , Harold P. Rieck, Jr. , Harvey W. Mason , Ambrose A. Hauser
发明人： Ching-Pang Lee , Clay K. Carlson , Monty L. Shelton , Harold P. Rieck, Jr. , Harvey W. Mason , Ambrose A. Hauser
CPC分类号： F01D5/08 , Y02T50/673 , Y02T50/676
摘要： An aft entry system in a gas turbine engine is provided for cooling selected one or more of aft high and low pressure turbine stages of the engine. The aft entry system includes an air flow circuit for routing low pressure cooling air radially outward from an interstage region of a multi-stage compressor of a core engine of the gas turbine engine and axially in an aft direction to a plurality of radial passages, such as provided by stationary stator and outlet guide vanes, which provide an aft entry region to the selected high and low pressure turbine stages. The pressure of the cooling air routed by the air flow circuit of the aft entry system can be lower than the pressure of air at a discharge end of the compressor but higher than the pressure of the gas stream discharging from the selected turbine stage.
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2.发明授权Turbine blade squealer tip having air cooling holes contiguous with tip interior wall surface 失效涡轮叶片尖头尖端具有与尖端内壁表面相邻的空气冷却孔
公开(公告)号：US5183385A
公开(公告)日：1993-02-02
申请号：US830975
申请日：1992-02-10
摘要： A turbine blade squealer tip has a plurality of holes defined through the end cap of the blade tip portion and located contiguous with an interior surface of the squealer tip wall along at least one of the turbine blade pressure and suction sides of the tip cap for providing effective cooling air on the squealer tip wall. Each tip hole has an inner portion which communicates with the interior of the blade and an outer portion which communicates with a cavity defined by the blade end cap and the peripheral wall of the squealer tip. The cross-section of the inner hole portion is circular and the inner hole portion overall defines a right cylinder. The cross-section of the outer hole portion is rectangular and the outer hole portion overall defines a rectangular trapezoid.
摘要翻译： 涡轮叶片尖叫尖端具有多个孔，其限定穿过叶片尖端部分的端盖并且沿尖端盖的涡轮叶片压力和吸力侧中的至少一个定位成与鼓风机顶端壁的内表面相邻，以提供 有效的冷却空气在鸣叫器顶端壁上。 每个尖端孔具有与叶片内部连通的内部部分和与由叶片端盖和鼓风机尖端的周壁限定的空腔连通的外部部分。 内孔部分的横截面为圆形，内孔部分整体形成右圆柱体。 外孔部分的横截面是矩形的，外孔部分总体上限定了矩形梯形。
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公开(公告)号：US5472313A
公开(公告)日：1995-12-05
申请号：US264743
申请日：1994-06-23
申请人： Armando J. Quinones , Harold P. Rieck, Jr. , Richard W. Albrecht , Michael A. Sullivan , Robert H. Weisgerber , Larry W. Plemmons
发明人： Armando J. Quinones , Harold P. Rieck, Jr. , Richard W. Albrecht , Michael A. Sullivan , Robert H. Weisgerber , Larry W. Plemmons
CPC分类号： F04D29/582 , F01D5/082 , F04D29/321 , Y02T50/676
摘要： A turbine disk cooling system for a gas turbine engine of a type having a compressor section including first and second disks connected by a seal and defining a compressor interstage volume, a turbine section including first and second stage disks connected by a seal and defining a turbine inner stage volume, and a compressor shaft interconnecting the compressor disks with the turbine disks including orifices located in the compressor seal for allowing air in the compressor section to enter the compressor interstage volume, and a radial inflow impeller for guiding the compressor air towards the compressor shaft. The impeller including a plurality of radially-extending conduits suspended in the compressor interstage volume, the conduits having a plurality of interior, radially-extending passages for conveying the compressor air from the orifice to the compressor shaft. The cooling system further including ducts concentric with the engine centerline for conveying air from the compressor interstage volume to the turbine section, wherein the first stage turbine disk includes an aft shaft having a plurality of openings therethrough allowing the flow of air from the ducts into the turbine interstage volume. The tubular conduit elements having a radially outer portion divided into a plurality of spaced longitudinal segments and a radially inner portion protruding from the conduit element and including a peripheral flange shaped to engage the peripheral flange of the conduit elements.
摘要翻译： 一种用于具有压缩机部分的燃气涡轮发动机的涡轮盘冷却系统，所述压缩机部分包括通过密封件连接并限定压缩机级间容积的第一和第二盘，涡轮部分，包括通过密封件连接的第一和第二级盘， 以及压缩机轴，其将压缩机盘与包括位于压缩机密封件中的孔的涡轮盘相互连接，以允许压缩机部分中的空气进入压缩机级间容积;以及径向流入叶轮，用于将压缩机空气引导到压缩机 轴。 叶轮包括悬挂在压缩机级间体积中的多个径向延伸的管道，该管道具有多个内部径向延伸的通道，用于将压缩机空气从孔口输送到压缩机轴。 所述冷却系统还包括与所述发动机中心线同心的管道，用于将空气从所述压缩机级间容积输送到所述涡轮部分，其中所述第一级涡轮盘包括具有多个开口的后轴，所述后轴允许从所述管道进入的空气流入 涡轮级间体积。 所述管状导管元件具有分成多个间隔的纵向段的径向外部部分和从所述导管元件突出的径向内部，并且包括成形为接合所述导管元件的周边凸缘的外围凸缘。
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公开(公告)号：US5245821A
公开(公告)日：1993-09-21
申请号：US779753
申请日：1991-10-21
摘要： An aerodynamically efficient flow transfer device having a means to transfer flow from a static element to a rotor element such that the end of the exit flow is substantially parallel to an exit plane that is perpendicular to the axis of rotation of the rotor and substantially tangential to the operational rotational direction of the rotor. The preferred embodiment provides a cooling air flow transfer apparatus, between a stationary compressor and turbine rotor, having an inducer which includes cooling air flow holes or passages that are acutely angled in a tangential manner to the rotational direction of the rotor. The passages include a cylindrical section leading to a downstream flared outlet in the form of an open channel that has a back wall with a portion that curves to be parallel to the exit plane of the inducer at the channel's end.
摘要翻译： 一种空气动力学有效的流动传递装置，其具有将流动从静态元件传递到转子元件的装置，使得出口流的端部基本上平行于垂直于转子的旋转轴线的出口平面，并且基本上与 转子的操作旋转方向。 优选实施例提供了一种在固定式压缩机和涡轮机转子之间的冷却空气流传输装置，其具有导流器，该导流器包括冷却空气流动孔或与转子的旋转方向相切地锐角地形成的通道。 通道包括通向开口通道形式的下游扩口出口的圆柱形部分，该开口通道的后壁具有在通道末端处平行于诱导器的出口平面弯曲的部分。
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公开(公告)号：US6065928A
公开(公告)日：2000-05-23
申请号：US119914
申请日：1998-07-22
CPC分类号： F01D5/189 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： A turbine nozzle includes radially outer and inner bands between which extend a plurality of vanes. The vanes include impingement baffles having impingement holes for impinging cooling air inside the vane for cooling thereof. An air circuit is disposed in the inner band and includes a plurality of outlet holes. A transfer tube is disposed in flow communication between respective ones of the baffles and the air circuit for channeling thereto a portion of the cooling air from inside the baffles as pre-impingement air for discharge through the outlet holes.
摘要翻译： 涡轮喷嘴包括径向外部和内部带，其间延伸有多个叶片。 叶片包括冲击挡板，其具有用于冲击叶片内部的冷却空气的冲击孔以进行冷却。 空气回路设置在内带中并且包括多个出口孔。 传送管被设置成在相应的挡板和空气回路之间流动连通，用于将来自挡板内部的冷却空气的一部分作为预冲击空气引导，以便通过出口孔排出。
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公开(公告)号：US5351478A
公开(公告)日：1994-10-04
申请号：US891494
申请日：1992-05-29
CPC分类号： F01D25/26 , F04D29/522 , F04D29/584 , F05D2240/126 , F05D2260/201 , F05D2260/941 , Y02T50/676
摘要： An apparatus and method for minimizing compressor casing distortion due to bleed air extraction wherein the compressor casing includes an annular outer casing having at least one outlet duct, an annular inner casing disposed co-axially with the outer casing and spaced radially inwardly therefrom to define a plenum, two radial discs extending inwardly from the outer casing defining a plenum, a plurality of small area bleed openings located in the inner casing for imparting a radial velocity to the bleed air greater than the circumferential velocity entering the plenum, an air tube located over each bleed opening, and a baffle plate located on top of the air tubes and communicating with the radial discs for supporting the casings, whereby the bleed air impinges on the outer casing and controls distortion by sufficiently reducing the circumferential temperature gradient forming at the outer casing.
摘要翻译： 一种用于使压缩机壳体由于排气提取引起的变形最小化的装置和方法，其中所述压缩机壳体包括具有至少一个出口管道的环形外壳，与所述外壳同轴并与所述外壳径向向内间隔开的环形外壳， 气室，从限定集气室的外壳向内延伸的两个径向盘，位于内壳中的多个小区域排放口，用于使放气速度大于进入气室的圆周速度，空气管位于 每个排气口和位于空气管顶部的挡板，并与用于支撑壳体的径向盘连通，由此泄放空气冲击外壳并通过充分降低在外壳处形成的周向温度梯度来控制变形 。
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