公开(公告)号：US06243948B1

公开(公告)日：2001-06-12

申请号：US09443132

申请日：1999-11-18

Applicant: Ching-Pang Lee ,  Robert A. Johnson ,  Nesim Abuaf

Inventor： Ching-Pang Lee ,  Robert A. Johnson ,  Nesim Abuaf

IPC: B23P1500

CPC classification number: F01D5/186 ,  B23K26/389 ,  B23P6/002 ,  B23P2700/06 ,  F01D5/005 ,  F05D2230/10 ,  F05D2230/80 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T29/49318 ,  Y10T29/49341 ,  Y10T29/49725 ,  Y10T29/49726

Abstract: A method for modifying cooling holes in a gas turbine engine film-cooled component by machining cooling hole outlets to enlarge the outlets and remove any portion of the cooling hole walls which might exhibit cracks.

Abstract translation: 一种用于通过加工冷却孔出口来改变燃气涡轮发动机膜冷却部件中的冷却孔的方法，以扩大出口并去除可能发生裂纹的冷却孔壁的任何部分。

公开(公告)号：US06220817B1

公开(公告)日：2001-04-24

申请号：US08971305

申请日：1997-11-17

Applicant: George A. Durgin ,  Ching-Pang Lee

Inventor： George A. Durgin ,  Ching-Pang Lee

IPC: F01D508

CPC classification number: F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits having outer and inner serpentine portions, respectively, in different longitudinal tiers with the outer serpentine position being disposed longitudinally above the inner tier serpentine position for differentially longitudinally cooling the airfoil. The outer and inner serpentine portions include outer and inner exits and entrances wherein the outer and inner exits are positioned aft of the outer and inner entrances, respectively, so as to have a chordal flow direction aftwards from the leading edge to the trailing edge within the serpentine portions.

Abstract translation: 涡轮机翼片包括多个内部肋条，其限定至少两个独立的蛇形冷却回路，分别在不同的纵向层中具有外部和内部蛇形部分，其中外部蛇形位置纵向设置在内部蛇形位置上方，用于差异地纵向冷却翼型件 。 外部和内部蛇形部分包括外部和外部出口和入口，其中外部出口和内部出口分别位于外部入口和内部入口的后方，以便在内部出口和内部出口之间具有从前缘到后缘的弦向流动方向 蛇纹石部分。

公开(公告)号：US6086328A

公开(公告)日：2000-07-11

申请号：US217105

申请日：1998-12-21

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  F01D5/20 ,  F01D11/08 ,  F01D5/28

CPC classification number: F01D5/18 ,  F01D5/20 ,  F05D2250/292

Abstract: A turbine blade includes a hollow airfoil extending from an integral dovetail. The airfoil includes sidewalls extending between leading and trailing edges and longitudinally between a root and a tip. The sidewalls are spaced apart to define a flow channel for channeling cooling air through the airfoil. The tip is tapered longitudinally above at least one of the sidewalls and decreases in thickness.

Abstract translation: 涡轮机叶片包括从整体燕尾形延伸的中空翼型件。 翼型件包括在前缘和后缘之间延伸的侧壁，并且在根部和尖端之间纵向延伸。 侧壁间隔开以限定用于将冷却空气引导通过翼型的流动通道。 尖端在纵向上至少一个侧壁上倾斜并且厚度减小。

公开(公告)号：US5927946A

公开(公告)日：1999-07-27

申请号：US939761

申请日：1997-09-29

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  F01D5/20

CPC classification number: F01D5/187 ,  F01D5/20

Abstract: A gas turbine engine rotor blade includes an airfoil having a concave side wall and a convex side wall joined together at leading and trailing edges. Concave and convex tip walls extend from adjacent the leading edge along the respective concave and convex side walls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A hole or channel is disposed in a trailing edge tip region connecting the tip cavity to the trailing edge for channeling cooling fluid through the trailing edge tip region.

Abstract translation: 燃气涡轮发动机转子叶片包括具有在前缘和后缘处连接在一起的凹侧壁和凸侧壁的翼型件。 凹凸尖端壁从相邻的凹凸侧壁的前缘相邻延伸，与后缘相邻并且间隔开以在其间限定尖端腔。 孔或通道设置在将尖端空腔连接到后缘的后缘尖端区域中，用于将冷却流体引导通过后缘尖端区域。

公开(公告)号：US5738489A

公开(公告)日：1998-04-14

申请号：US778565

申请日：1997-01-03

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  F01D25/14

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/221

Abstract: A turbine blade includes a dovetail, shank, platform, and airfoil. A cooling circuit extends radially therethrough for circulating a coolant. A thermal conductor is disposed on a lower surface of the platform for conducting heat from the platform to the shank for removal by the coolant in the cooling circuit.

Abstract translation: 涡轮叶片包括燕尾，柄，平台和翼型件。 冷却回路径向延伸穿过其中以使冷却剂循环。 热导体设置在平台的下表面上，用于将热量从平台传导到柄部，以便由冷却回路中的冷却剂除去。

公开(公告)号：US5733102A

公开(公告)日：1998-03-31

申请号：US767905

申请日：1996-12-17

Applicant: Ching-Pang Lee ,  Gulcharan S. Brainch ,  Anne M. Isburgh

Inventor： Ching-Pang Lee ,  Gulcharan S. Brainch ,  Anne M. Isburgh

IPC: F01D5/18 ,  F01D5/20 ,  F01D5/28 ,  F01D11/12 ,  F02C7/18

CPC classification number: F01D5/288 ,  F01D11/122 ,  F01D5/187 ,  F01D5/20 ,  F05D2230/90

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US5680767A

公开(公告)日：1997-10-28

申请号：US526471

申请日：1995-09-11

Applicant: Ching-Pang Lee ,  Gary L. Leonard ,  George A. Coffinberry

Inventor： Ching-Pang Lee ,  Gary L. Leonard ,  George A. Coffinberry

IPC: F23R3/00 ,  F23R3/02 ,  F02C1/00

CPC classification number: F23R3/005 ,  F23R3/02 ,  Y02T50/675

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US5660524A

公开(公告)日：1997-08-26

申请号：US912440

申请日：1992-07-13

Applicant: Ching-Pang Lee ,  Anne Marie Isburgh ,  Donald George La Chapelle ,  Paul Stuart Wilson

Inventor： Ching-Pang Lee ,  Anne Marie Isburgh ,  Donald George La Chapelle ,  Paul Stuart Wilson

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/182 ,  F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US5653110A

公开(公告)日：1997-08-05

申请号：US733892

申请日：1991-07-22

Applicant: Ching-Pang Lee ,  Nesim Abuaf ,  Paul Stuart Wilson

Inventor： Ching-Pang Lee ,  Nesim Abuaf ,  Paul Stuart Wilson

IPC: F01D5/18 ,  F02C1/00 ,  B63H1/14

CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2260/2212 ,  Y02T50/676

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US5591007A

公开(公告)日：1997-01-07

申请号：US455869

申请日：1995-05-31

Applicant: Ching-Pang Lee ,  Sundaresa V. Subramanian ,  George A. Durgin

Inventor： Ching-Pang Lee ,  Sundaresa V. Subramanian ,  George A. Durgin

IPC: F01D5/18 ,  F01D5/08

CPC classification number: F01D5/187 ,  Y02T50/676

Abstract: 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.

Abstract translation: 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。