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公开(公告)号：US5733102A
公开(公告)日：1998-03-31
申请号：US767905
申请日：1996-12-17
CPC分类号： F01D5/288 , F01D11/122 , F01D5/187 , F01D5/20 , F05D2230/90
摘要： A turbine blade includes an airfoil having an internal cooling circuit therein. The airfoil extends from a root to a tip cap, and includes laterally opposite pressure and suction sides extending between a leading edge and an opposite trailing edge over which is flowable a combustion gas. A pair of squealer tips extend radially upwardly from the tip cap along the pressure and suction sides, and are spaced apart between the leading and trailing edges to define an upwardly open tip cavity. At least one of the squealer tips includes a slot extending radially inwardly to the tip cap, with the slot also extending along the squealer tip between the leading and trailing edges. A plurality of spaced apart supply holes extend radially through the tip cap in the slot in flow communication with the cooling circuit for channeling the coolant into the slot for cooling the squealer tip. A thermal barrier coating may then be disposed on an outboard side of the squealer tip for providing insulation against the combustion gas flowable therealong.
摘要翻译： 涡轮叶片包括其中具有内部冷却回路的翼型件。 翼型件从根部延伸到尖端盖，并且包括在前缘和相对的后缘之间延伸的横向相对的压力和吸力侧，在该后缘上可燃燃烧气体。 一对尖叫尖端沿着压力和吸力侧从尖端径向向上延伸，并且在前缘和后缘之间间隔开以限定向上敞开的尖端腔。 至少一个尖叫尖端包括径向向内延伸到尖端盖的槽，槽也沿着尖端和前缘之间延伸。 多个间隔开的供应孔径向地延伸穿过狭缝中的尖端帽，与冷却回路流体连通，以将冷却剂引导到槽中以冷却鸣叫器尖端。 然后可以将热障涂层设置在发声器末端的外侧，以提供与可沿其流动的燃烧气体隔离。
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公开(公告)号：US5680767A
公开(公告)日：1997-10-28
申请号：US526471
申请日：1995-09-11
CPC分类号： F23R3/005 , F23R3/02 , Y02T50/675
摘要： A combustor, for a gas turbine engine, employing regenerative combustor cooling. The combustion gas flow direction extends generally longitudinally aft of the combustor fuel nozzle. A coolant flowpath between the combustor casing and the combustor liner has: 1) a longitudinally aft inlet in fluid communication with a source of compressor-derived cooling air, of lower temperature and higher pressure than diffused air from the combustor diffuser; and 2) a longitudinally forward outlet in fluid communication with the combustor fuel nozzle for "spent" cooling air to be used for combustion.
摘要翻译： 一种用于燃气涡轮发动机的燃烧器，其采用再生燃烧器冷却。 燃烧气体流动方向大致纵向延伸到燃烧器燃料喷嘴的后方。 在燃烧器壳体和燃烧器衬套之间的冷却剂流动路径具有：1）与来自燃烧器扩散器的扩散空气相比较，具有较低温度和较高压力的来自压缩机的冷却空气源流体连通的纵向后部入口; 和2）与燃烧器燃料喷嘴流体连通的用于燃烧的“已用”冷却空气的纵向前部出口。
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103.发明授权
公开(公告)号：US5660524A
公开(公告)日：1997-08-26
申请号：US912440
申请日：1992-07-13
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/182 , F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： An airfoil blade, such as a jet engine turbine rotor blade. An internal serpentine coolant circuit has a last downstream passageway bounded by four monolithic inner walls which are monolithic with at least a portion of the outer walls. Two of the inner walls are spaced from the outer walls and contain air impingement orifices creating two impingement chambers. Some coolant in the serpentine circuit exits the airfoil blade through a coolant exit in the blade tip. The remaining coolant in the circuit passes through the impingement orifices and exits the blade through film cooling holes in the outer walls.
摘要翻译： 翼型叶片，例如喷气发动机涡轮转子叶片。 内部蛇形冷却剂回路具有由四个整体内壁限定的最后一个下游通道，其与外壁的至少一部分是整体的。 两个内壁与外壁间隔开并且包含产生两个冲击室的空气冲击孔。 蛇形回路中的一些冷却剂通过叶片尖端中的冷却剂出口离开翼型叶片。 电路中剩余的冷却剂通过冲击孔，并通过外壁上的薄膜冷却孔离开叶片。
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公开(公告)号：US5653110A
公开(公告)日：1997-08-05
申请号：US733892
申请日：1991-07-22
申请人： Ching-Pang Lee , Nesim Abuaf , Paul Stuart Wilson
发明人： Ching-Pang Lee , Nesim Abuaf , Paul Stuart Wilson
CPC分类号： F01D5/186 , F05D2260/202 , F05D2260/2212 , Y02T50/676
摘要： A jet engine component, such as an aircraft gas turbine engine rotor blade or a scramjet engine fuel injector. The component has a wall portion including a first surface exposable to a cooler, higher static pressure fluid and a second surface exposable to a hotter, lower static pressure gas flow flowing across the second surface. The component further includes a generally straight film coolant passageway having an inlet on the first surface and an outlet on the second surface. The second surface has a seamless groove which is open substantially entirely along its longitudinal dimension extending from the outlet along the lower static pressure gas flow for improved film cooling of the second surface.
摘要翻译： 喷气发动机部件，例如飞机燃气涡轮发动机转子叶片或冲击式发动机燃料喷射器。 该部件具有壁部分，其包括可暴露于冷却器的第一表面，较高的静压流体和可暴露于流过第二表面的较热的较低静态气流的第二表面。 该部件还包括大致直的薄膜冷却剂通道，其具有在第一表面上的入口和在第二表面上的出口。 第二表面具有无缝槽，其基本上完全沿着其沿着下部静压气流从出口延伸的纵向尺寸敞开，以改善第二表面的膜冷却。
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公开(公告)号：US5591007A
公开(公告)日：1997-01-07
申请号：US455869
申请日：1995-05-31
CPC分类号： F01D5/187 , Y02T50/676
摘要： A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits arranged in part in different longitudinal tiers, with an outer tier circuit being disposed in part longitudinally above an inner tier circuit for differentially longitudinally cooling the airfoil.
摘要翻译： 涡轮机翼片包括限定至少两个独立的蛇形冷却回路的多个内部肋条，其部分地布置在不同的纵向层中，外层电路部分地纵向地设置在内层电路的上方，用于差异地纵向冷却翼型件。
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106.发明授权
公开(公告)号：US5326224A
公开(公告)日：1994-07-05
申请号：US801136
申请日：1991-12-02
CPC分类号： F01D5/20 , F01D5/186 , Y02T50/676
摘要： A jet engine component includes a body having a wall portion with an external surface exposed to hot gas flow and an internal surface exposed to a cooling air flow. The engine component incorporates an arrangement of cooling holes defined through the wall portion between the external and internal surfaces thereof to permit flow of cooling air from the hollow interior through the wall portion to the exterior of the component. Each cooling hole includes at least one flow inlet at the internal surface of the wall for receiving the cooling air flow, at least a pair of flow outlets at the external surface of the wall for discharging the cooling air flow, and at least a pair of flow branches extending through the wall portion and between the flow inlet and the flow outlets for permitting passage of the cooling air flow from the flow inlet to the flow outlets. In one V-shaped configuration, the flow branches merge and intersect with one another at the flow inlet. In another X-shaped configuration, there are a pair of flow inlets and the flow branches merge and intersect with one another at a location intermediate between and spaced from the flow inlets and outlets. The flow outlets are displaced preferably downstream of the flow inlet relative to the direction of gas flow past the external surface of the wall of the engine component.
摘要翻译： 喷气发动机部件包括具有暴露于热气流的外表面的壁部和暴露于冷却空气流的内表面的主体。 发动机部件包括在其外表面和内表面之间通过壁部分限定的冷却孔的布置，以允许冷却空气从中空内部流过壁部分到外部。 每个冷却孔包括用于接收冷却空气流的壁的内表面处的至少一个流入口，在壁的外表面处的至少一对流出口，用于排出冷却空气流，以及至少一对 流动分支延伸穿过壁部分并且在流入口和流出口之间，用于允许冷却空气流从流入口流到流出口。 在一个V形构造中，流动分支在流入口处相互合并并相互交叉。 在另一个X形构造中，存在一对流入口，并且流动分支在流入口和出口之间的中间和间隔开的位置处彼此合并和相交。 优选地，流动出口相对于通过发动机部件的壁的外表面的气流的方向在流入口的下游位移。
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公开(公告)号：US10787911B2
公开(公告)日：2020-09-29
申请号：US16005535
申请日：2018-06-11
申请人： Ching-Pang Lee , Benjamin Heneveld
发明人： Ching-Pang Lee , Benjamin Heneveld
IPC分类号： F01D5/18
摘要： A gas turbine engine airfoil includes an outer wall including a suction side, a pressure side, a leading edge, and a trailing edge, the outer wall defining an interior chamber of the airfoil. The airfoil further includes cooling structure provided in the interior chamber. The cooling structure defines an interior cooling cavity and includes a plurality of cooling fluid outlet holes, at least one of which is in communication with a pressure side cooling circuit and at least one of which is in communication with a suction side cooling circuit. At least one of the pressure and suction side cooling circuits includes: a plurality of rows of airfoils, wherein radially adjacent airfoils within a row define segments of cooling channels. Outlets of the segments in one row align aerodynamically with inlets of segments in an adjacent downstream row such that the cooling channels have a serpentine shape.
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108.发明授权Composite core die, methods of manufacture thereof and articles manufactured therefrom 有权复合芯模，其制造方法和由其制造的制品公开(公告)号：US09566642B2
公开(公告)日：2017-02-14
申请号：US13801483
申请日：2013-03-13
申请人： Ching-Pang Lee , Hsin-Pang Wang , Ram Kumar Upadhyay , Paul Richard Myers , Marc Thomas Edgar , Thomas Donald Martyn , Eric Alan Estill
发明人： Ching-Pang Lee , Hsin-Pang Wang , Ram Kumar Upadhyay , Paul Richard Myers , Marc Thomas Edgar , Thomas Donald Martyn , Eric Alan Estill
摘要： A composite core die includes a reusable core die; and a disposable core die. The disposable core die is in physical communication with the reusable core die and surfaces of communication between the disposable core die and the reusable core die serve as barriers to prevent the leakage of a slurry that is disposed in the composite core die.
摘要翻译： 复合芯模包括可重复使用的芯模; 和一次性芯片。 一次性芯模与可重复使用的芯模具物理连通，并且一次性芯模和可重复使用的芯模之间的连通表面用作屏障，以防止布置在复合芯模中的浆料的泄漏。
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公开(公告)号：US09186757B2
公开(公告)日：2015-11-17
申请号：US13467298
申请日：2012-05-09
CPC分类号： B23P6/002 , F01D5/005 , F01D5/18 , F01D5/186 , F01D5/187 , F01D5/20 , F01D11/14 , Y10T29/49318
摘要： A method of repairing a turbine blade having a radially extending outer wall defining an internal cavity width and a blade tip. The method comprises removing at least a portion of the blade tip to form a repair surface and providing a tip cap having a radially outer side with an outer width that may be less than the internal cavity width, and having a radially inner side with an inner width that is substantially equal to or greater than the internal cavity width. The tip cap is positioned at the repair surface, and the tip cap is welded to the repair surface using a ductile welding material. A cap peripheral portion is formed by build-up welding around the tip cap, and a squealer portion is formed by build-up welding on the cap peripheral portion.
摘要翻译： 一种修复具有限定内腔宽度的径向延伸的外壁和叶片尖端的涡轮叶片的方法。 该方法包括去除叶片尖端的至少一部分以形成修复表面并且提供具有径向外侧的顶端帽，其外部宽度可以小于内部空腔宽度，并且具有径向内侧，内侧具有内部 宽度基本上等于或大于内腔宽度。 顶盖位于修复表面，并且使用延性焊接材料将尖端焊接到修复表面。 通过围绕尖端盖进行堆积焊接而形成盖周边部分，并且通过在盖周边部分上堆积焊接形成尖叫部分。
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110.发明申请公开(公告)号：US20150184518A1
公开(公告)日：2015-07-02
申请号：US14140593
申请日：2013-12-26
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
CPC分类号： F01D5/186 , B22C7/02 , B22C9/04 , B22C9/043 , B22C9/10 , F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2250/184
摘要： A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel formed from a central trailing edge cooling channel and at least one trailing edge exit slot with a nonlinear longitudinal axis is disclosed. The trailing edge exit slot may be defined by ribs having wavy side edges that form a jagged edge As such, the nonlinear longitudinal axis of the trailing edge exit slot reduces the effective flow area, generates impingement and turbulence to increase heat transfer and provides sufficient mechanical strength for better casting yield without overflowing for better performance The nonlinear trailing edge exit slot may be formed using a ceramic core and investment casting.
摘要翻译： 公开了一种用于涡轮发动机的涡轮叶片的冷却系统，其具有由中央后缘冷却通道形成的后缘冷却通道和至少一个具有非线性纵向轴线的后缘出口槽。 后缘出口槽可以由具有形成锯齿状边缘的波浪形侧边缘的肋限定。因此，后缘出口槽的非线性纵向轴线减小有效流动面积，产生冲击和湍流以增加热传递并提供足够的机械 强度更好的铸造产量而不溢出以获得更好的性能非线性后缘出口槽可以使用陶瓷芯和熔模铸造形成。
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