公开(公告)号：US06790005B2

公开(公告)日：2004-09-14

申请号：US10334091

申请日：2002-12-30

Applicant: Ching-Pang Lee ,  David Glenn Cherry ,  Chander Prakash ,  Aspi Rustom Wadia

Inventor： Ching-Pang Lee ,  David Glenn Cherry ,  Chander Prakash ,  Aspi Rustom Wadia

IPC: F01D516

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/13 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine blade includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The pressure sidewall includes an inclined tip rib offset therein by a ramp defining a tip notch having compound inclinations.

Abstract translation: 燃气涡轮发动机叶片包括在前缘和后缘之间从根部到尖端延伸的压力和吸力侧壁。 压力侧壁包括通过限定具有复合倾斜的尖端凹口的斜面偏置在其中的倾斜尖端肋。

公开(公告)号：US06422821B1

公开(公告)日：2002-07-23

申请号：US09756902

申请日：2001-01-09

Applicant: Ching-Pang Lee ,  Chander Prakash ,  Monty Lee Shelton ,  John Howard Starkweather ,  Hardev Singh ,  Gerard Anthony Rinck

Inventor： Ching-Pang Lee ,  Chander Prakash ,  Monty Lee Shelton ,  John Howard Starkweather ,  Hardev Singh ,  Gerard Anthony Rinck

IPC: F01D518

CPC classification number: F01D5/20 ,  F01D5/186 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/70 ,  F05D2260/202

Abstract: A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.

Abstract translation: 描述了一种用于燃气涡轮发动机的转子叶片，其包括有助于降低转子叶片的操作温度的尖端区域。 尖端区域包括从翼型件的顶板径向向外延伸的第一顶端壁和第二顶端壁。 尖端壁从翼型的前缘相邻延伸，以在翼型的后缘连接。 在翼型件前缘处的第一和第二尖端壁之间限定了切口。 第二末端壁的至少一部分被凹入以限定尖端架。

公开(公告)号：US5503527A

公开(公告)日：1996-04-02

申请号：US329750

申请日：1994-12-19

Applicant: Ching-Pang Lee ,  Edward F. Pietraszkiewicz ,  Chander Prakash ,  Ronald D. Zerkle

Inventor： Ching-Pang Lee ,  Edward F. Pietraszkiewicz ,  Chander Prakash ,  Ronald D. Zerkle

IPC: F01D5/20 ,  F01D5/18

CPC classification number: F01D5/20 ,  Y02T50/673

Abstract: A gas turbine engine rotor blade includes an airfoil having first and second sidewalls joined together at leading and trailing edges. First and second tip walls extend from adjacent the leading edge along the respective first and second sidewalls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A first notch is disposed in the first tip wall adjacent to the leading edge for channeling into the tip cavity a portion of combustion gases flowable over the airfoil for reducing the heating effect of the gases on the blade tip. In a preferred embodiment, a second notch is disposed adjacent to the trailing edge for promoting flow through the tip cavity from the first notch.

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第一和第二侧壁的翼型件。 第一和第二尖端壁沿着相应的第一和第二侧壁的相邻前缘延伸到邻近的后缘并且间隔开以限定其间的尖端腔。 第一凹口设置在与前缘相邻的第一末端壁中，用于将一部分可在翼型上流动的燃烧气体引导到尖端腔中，以减少气体在叶片尖端上的加热效应。 在优选实施例中，第二凹口设置成与后缘相邻，用于促进从第一凹口流过尖端空腔。

公开(公告)号：US5458461A

公开(公告)日：1995-10-17

申请号：US354194

申请日：1994-12-12

Applicant: Ching-Pang Lee ,  Chander Prakash ,  John H. Starkweather ,  Ronald D. Zerkle

Inventor： Ching-Pang Lee ,  Chander Prakash ,  John H. Starkweather ,  Ronald D. Zerkle

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2260/202

Abstract: A wall adapted for use in a gas turbine engine between a first fluid and a second hotter fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends partly inwardly and perpendicularly from the second side toward the first side and is provided with the first fluid through a plurality of longitudinally spaced apart holes. The holes are aligned coplanar with the slot and longitudinally inclined to effect longitudinal overlapping of the first fluid inside the slot prior to discharge therefrom as a substantially continuous film.

Abstract translation: 适于在第一流体和第二热流体之间的燃气涡轮发动机中使用的壁包括可流过第一流体的第一侧和可流动第二流体的相对的第二侧。 细长槽从第二侧向第一侧部分地向内并垂直延伸，并且通过多个纵向间隔开的孔设置有第一流体。 孔与槽对齐并且纵向倾斜以在将槽排出之前的第一流体作为基本上连续的膜进行纵向重叠。