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    Tip leakage flow directionality control
    1.
    发明授权
    Tip leakage flow directionality control 有权
    尖端泄漏流动方向性控制

    公开(公告)号：US09260972B2

    公开(公告)日：2016-02-16

    申请号：US13540752

    申请日：2012-07-03

    申请人： Mark F. Zelesky ,  Andrew S. Aggarwala

    发明人： Mark F. Zelesky ,  Andrew S. Aggarwala

    IPC分类号： F01D5/20 ,  F01D5/18 ,  F01D5/14

    CPC分类号： F01D5/18 ,  F01D5/146 ,  F01D5/20 ,  F05D2240/307 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.

    摘要翻译： 涡轮机翼片包括抽吸侧壁，压力侧壁，尖端壁和尖端泄漏控制通道。 每个侧壁从翼型基座向翼展方向延伸，并且在前缘和后缘之间并排。 尖端壁从前缘延伸到后缘，并且连接吸力和压力侧壁的相应的外翼展端。 尖端泄漏控制通道具有凹入到顶端壁的外表面中的入口和出口。 通道的入口在翼型压力侧壁和尖端壁的接合点附近开始。 通道的出口终止于尖端壁和抽吸侧壁的接合处的凹陷部分。

    Coolable vane or blade for a turbomachine
    5.
    发明授权
    Coolable vane or blade for a turbomachine 有权
    用于涡轮机的可冷却叶片或叶片

    公开(公告)号：US06283708B1

    公开(公告)日：2001-09-04

    申请号：US09453649

    申请日：1999-12-03

    申请人： Mark F. Zelesky

    发明人： Mark F. Zelesky

    IPC分类号： B63H114

    CPC分类号： F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/676

    摘要： A coolable vane (12) for a turbomachine includes an airfoil (16) with a pair of imperforate ribs (42, 44) that extend laterally across the airfoil. The ribs have suction side termini (52, 56) and pressure side termini (54, 58). The suction side termini chordwisely delimit a segment SS of the airfoil suction wall (28) so that the ribs and the suction wall segment bound an internal plenum (48) for distributing a pressurized coolant spanwisely through the interior of the airfoil. An array of film cooling holes (84) penetrates the suction wall segment and is the exclusive avenue for conveying coolant from the plenum to a working medium fluid flowpath. Accordingly, relatively low pressure coolant may be supplied to the plenum without the risk of backflow or spanwise discontinuities in the surface cooling film. In one specific embodiment of the invention, the suction side rib termini (52, 56) straddle a point of minimum fluid pressure along the suction surface (38) so that positive coolant flow and spanwise continuity of the cooling film can be realized with coolant of the lowest possible pressure and without exposing the suction wall segment SS to excessive stress.

    摘要翻译： 用于涡轮机的可冷却叶片（12）包括翼型件（16），其具有横跨翼型延伸的一对无孔肋条（42,44）。 肋具有吸入侧端部（52,56）和压力侧端子（54,58）。 吸入侧端部弦向地限定翼型件抽吸壁（28）的段SS，使得肋和抽吸壁段结合内部增压室（48），用于将加压的冷却剂分流穿过翼型件的内部。 一组薄膜冷却孔（84）穿透吸壁部分，是将冷却剂从气室输送到工作介质流体流路的专用通道。 因此，可以将相对低压的冷却剂供应到集气室，而不会在表面冷却膜中产生回流或翼展方向不连续的风险。 在本发明的一个具体实施例中，吸入侧肋端部（52,56）沿着吸力表面（38）跨过最小流体压力点，使得冷却剂流的正向冷却剂流动和翼展方向连续性可以通过 压力尽可能低，并且不会使吸力壁段SS暴露于过度的压力。

    Cooled rotor assembly for a turbine engine
    6.
    发明授权
    Cooled rotor assembly for a turbine engine 失效
    用于涡轮发动机的冷却转子组件

    公开(公告)号：US5800124A

    公开(公告)日：1998-09-01

    申请号：US631506

    申请日：1996-04-12

    申请人： Mark F. Zelesky

    发明人： Mark F. Zelesky

    IPC分类号： F01D5/06 ,  F01D5/08 ,  F01D5/30 ,  F01D11/00 ,  F02B77/02 ,  F02C7/18

    CPC分类号： F01D5/081 ,  F01D11/006 ,  F01D5/3015 ,  F05D2240/81 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    摘要： A cooled rotor assembly for a gas turbine engine includes rotor blades (48) and a plurality of cover plates (86a) retained in the blade attachment slots (34) of a rotor disk (30). Each blade has a platform (46) with a trailing edge (58), and each cover plate includes at least one conduit (120, 126) for drawing leakage air from a plenum (102) in front of the disk and impinging that air against the platform trailing edges (58) to cool the tailing edges. In the preferred embodiment, each conduit (120) is defined by the rear face of a blade root (40) and a groove (122) cast into the cover plate. The invention makes productive use of leakage air by using that air to cool the platform trailing edges rather than allowing it to flow unbeneficially into the engine gaspath (24) in the vicinity of the platform leading edges (56).

    摘要翻译： 用于燃气涡轮发动机的冷却转子组件包括转子叶片（48）和保持在转子盘（30）的叶片附接槽（34）中的多个盖板（86a）。 每个叶片具有具有后缘（58）的平台（46），并且每个盖板包括至少一个导管（120,126），用于从盘前面的压力室（102）吸取泄漏的空气，并使空气抵抗 平台后缘（58）以冷却后缘。 在优选实施例中，每个导管（120）由叶片根部（40）的后表面和浇注到盖板中的凹槽（122）限定。 本发明通过使用该空气来冷却平台后缘，而不是使其不受益地流动到平台前缘附近的发动机气路（24）中，从而有效利用泄漏空气。

    Tip leakage flow directionality control
    9.
    发明授权
    Tip leakage flow directionality control 有权

    公开(公告)号：US09951629B2

    公开(公告)日：2018-04-24

    申请号：US14143102

    申请日：2013-12-30

    申请人： Mark F. Zelesky ,  Andrew S. Aggarwala

    发明人： Mark F. Zelesky ,  Andrew S. Aggarwala

    IPC分类号： F01D5/18 ,  F01D11/10 ,  F01D5/14 ,  F01D5/20

    CPC分类号： F01D5/187 ,  F01D5/146 ,  F01D5/18 ,  F01D5/186 ,  F01D5/20 ,  F01D11/10 ,  F05D2240/307 ,  Y02T50/673 ,  Y02T50/676

    摘要： An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control channel is recessed into the tip wall, the tip leakage control channel including a control channel floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. An internal cooling cavity is disposed between the suction sidewall and the pressure sidewall and a channel cooling aperture feeds airflow from the internal cooling cavity to the tip leakage control channel.