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。

公开(公告)号：US5326224A

公开(公告)日：1994-07-05

申请号：US801136

申请日：1991-12-02

Applicant: Ching-Pang Lee ,  Theodore T. Thomas, Jr. ,  Anne M. Isburgh

Inventor： Ching-Pang Lee ,  Theodore T. Thomas, Jr. ,  Anne M. Isburgh

IPC: F01D5/18 ,  F01D9/02 ,  F02C7/18

CPC classification number: F01D5/20 ,  F01D5/186 ,  Y02T50/676

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20180318919A1

公开(公告)日：2018-11-08

申请号：US16036611

申请日：2018-07-16

Applicant: Ching-Pang Lee ,  Nan Jiang

Inventor： Ching-Pang Lee ,  Nan Jiang

IPC: B22D25/02 ,  F01D5/18 ,  B22C9/04 ,  B22C9/10 ,  B22C7/02 ,  B22D29/00 ,  B22C21/14 ,  B22C9/24

CPC classification number: B22D25/02 ,  B22C7/02 ,  B22C9/04 ,  B22C9/043 ,  B22C9/10 ,  B22C9/108 ,  B22C9/24 ,  B22C21/14 ,  B22D29/001 ,  F01D5/186 ,  F05D2220/32 ,  F05D2230/211

Abstract: A method of forming an airfoil (12), including: abutting end faces (72) of cantilevered film hole protrusions (64) extending from a ceramic core (50) against an inner surface (80) of a wax die (68) to hold the ceramic core in a fixed positional relationship with the wax die; casting an airfoil including a superalloy around the ceramic core; and machining film cooling holes (34) in the airfoil after the casting step to form an pattern of film cooling holes comprising the film cooling holes formed by the machining step and the cast film cooling holes (102) formed by the film hole protrusions during the casting step.

公开(公告)号：US09091495B2

公开(公告)日：2015-07-28

申请号：US13893392

申请日：2013-05-14

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F28F13/12 ,  F01D5/18 ,  F04D29/38

CPC classification number: F28F13/12 ,  F01D5/187 ,  F05D2260/22141

Abstract: A cooling passage defined between first and second spaced apart sidewalls of a turbine engine component includes a turbulator system including a plurality of rows of turbulator members. Each row includes a first side turbulator member extending from the first sidewall, and a second side turbulator member extending from the second sidewall. The first and second side turbulator members are arranged such that a space is defined therebetween. The first and second side turbulator members are staggered with respect to one another such that respective forward and aft ends thereof are offset from one another. Each row further includes at least one elongate intermediate turbulator member located at least partially in the space between the respective first and second side turbulator members.

Abstract translation: 限定在涡轮发动机部件的第一和第二间隔开的侧壁之间的冷却通道包括包括多排湍流器构件的湍流器系统。 每排包括从第一侧壁延伸的第一侧湍流器构件和从第二侧壁延伸的第二侧湍流构件。 第一和第二侧面紊流器构件被布置成使得在它们之间限定空间。 第一和第二侧面紊流器构件相对于彼此交错，使得其相应的前端和后端彼此偏移。 每列还包括至少一个至少部分地位于相应的第一和第二侧面湍流器构件之间的空间中的细长的中间湍流器构件。

公开(公告)号：US09085981B2

公开(公告)日：2015-07-21

申请号：US13655675

申请日：2012-10-19

Applicant: Ching-Pang Lee ,  Jay A. Morrison

Inventor： Ching-Pang Lee ,  Jay A. Morrison

IPC: F01D9/06 ,  F23R3/02 ,  F23R3/06 ,  F23R3/54 ,  F01D9/02 ,  F23R3/00

CPC classification number: F01D9/023 ,  F05D2260/20 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R3/54 ,  F23R2900/03045

Abstract: A ducting arrangement (10) for a can annular gas turbine engine, including: a duct (12, 14) disposed between a combustor (16) and a first row of turbine blades and defining a hot gas path (30) therein, the duct (12, 14) having raised geometric features (54) incorporated into an outer surface (80); and a flow sleeve (72) defining a cooling flow path (84) between an inner surface (78) of the flow sleeve (72) and the duct outer surface (80). After a cooling fluid (86) traverses a relatively upstream raised geometric feature (90), the inner surface (78) of the flow sleeve (72) is effective to direct the cooling fluid (86) toward a landing (94) separating the relatively upstream raised geometric feature (90) from a relatively downstream raised geometric feature (94).

Abstract translation: 一种用于罐式环形燃气涡轮发动机的管道装置（10），包括：设置在燃烧器（16）和第一排涡轮叶片之间并在其中限定热气体通道（30）的管道（12,14），所述管道 （12,14），其具有结合到外表面（80）中的凸起的几何特征（54）; 以及流动套筒（72），其限定在所述流动套筒（72）的内表面（78）和所述管道外表面（80）之间的冷却流动路径（84）。 在冷却流体（86）穿过相对上游的凸起的几何特征（90）之后，流动套筒（72）的内表面（78）有效地将冷却流体（86）引导到将相对 上游凸起几何特征（90）从相对下游凸起的几何特征（94）。

公开(公告)号：US09039357B2

公开(公告)日：2015-05-26

申请号：US14043958

申请日：2013-10-02

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F04D29/08 ,  F01D11/00 ,  F01D11/02

CPC classification number: F01D11/001 ,  F01D11/02 ,  F05D2240/80 ,  F05D2250/37 ,  F05D2250/38 ,  F05D2250/71 ,  F05D2260/14

Abstract: A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface. The grooves are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Abstract translation: 在盘腔和涡轮部分热气路径之间的密封组件包括固定叶片组件和在叶片组件下游的旋转叶片组件，并且包括支撑在平台上并与涡轮转子和平台一起旋转的多个叶片 在发动机运行期间。 平台包括径向向外的第一表面，径向向内的第二表面，第三表面和延伸到第三表面中的多个凹槽。 凹槽被布置成使得在相邻凹槽之间限定空间。 在发动机操作期间，凹槽将吹扫空气从盘腔朝向热气路径引导，使得净化空气相对于热气流通过热气路径的方向在所需方向上流动。

公开(公告)号：US20150122450A1

公开(公告)日：2015-05-07

申请号：US13998541

申请日：2013-11-07

Applicant: Ching-Pang Lee ,  Gerald L. Hillier ,  Jae Y. UM ,  Gm Salam Azad

Inventor： Ching-Pang Lee ,  Gerald L. Hillier ,  Jae Y. UM ,  Gm Salam Azad

IPC: B22C9/24 ,  B22C9/10

CPC classification number: B22C9/24 ,  B22C7/06 ,  B22C9/04 ,  B22C9/10 ,  F01D5/188 ,  F01D9/041 ,  F05D2260/201

Abstract: A cast ceramic core (110), including: an airfoil portion (116) shaped to define an inner surface (56) of an airfoil (52) of a vane segment (50); and a shell portion (122) having a backside-shaping surface (120) shaped to define a backside surface (68) of a shroud (62) of the vane segment. The backside-shaping surface has a higher elevation (132) and a lower elevation (134). The higher elevation is set apart from a nearest point (138) on the airfoil portion by the lower elevation. The airfoil portion and the shell portion are cast as a monolithic body during a single casting pour.

Abstract translation: 一种铸造陶瓷芯（110），包括：形成为限定叶片段（50）的翼型件（52）的内表面（56）的翼型部分（116） 以及壳体部分（122），其具有形成为限定叶片段的护罩（62）的后侧表面（68）的后侧成形表面（120）。 后侧成形表面具有较高的仰角（132）和较低的高度（134）。 较高的高度与翼面部分的最近点（138）分开，较低的高度。 翼型部分和壳体部分在单次铸造过程中作为整体式铸造。