公开(公告)号：US3907458A

公开(公告)日：1975-09-23

申请号：US50403474

申请日：1974-09-09

Applicant: GEN MOTORS CORP

Inventor： LIDDLE SIDNEY G

IPC: F01D11/08 ,  F01D25/12 ,  F01D5/08

CPC classification number: F01D25/12 ,  F01D11/08

Abstract: In a turbomachine, a turbine shroud surrounding a rotor has an inner wall adjacent the rotor blade tips and additional walls defining an annular chamber. A generally T-shaped baffle with a base portion extending from one of the additional walls and a top portion parallel to the inner wall divides the annular chamber into an annular cooling passage between the top portion and inner wall and a pair of annular manifolds separated from each other by the base portion and open to the annular cooling passage around each axial edge of the top portion. An air inlet is provided into one of the manifolds from a source of air at a high pressure; and an air outlet is provided from the other manifold at a point diametrically opposite the air inlet to a source of air at a lower pressure. The cooling air passes from the first manifold through the cooling passage to the second manifold, and therefore cools the annular wall of the turbine shroud, at all points around the circumference.

Abstract translation: 在涡轮机中，围绕转子的涡轮罩具有邻近转子叶片尖端的内壁和限定环形室的附加壁。 具有从附加壁中的一个延伸并且平行于内壁的顶部的基部的大致T形挡板将环形室分成在顶部和内壁之间的环形冷却通道，以及一对环形歧管， 彼此通过基座部分，并且围绕顶部的每个轴向边缘的环形冷却通道开口。 空气入口从高压空气源提供到歧管之一; 并且在与较低压力的空气源的空气入口径向相对的点处，从另一个歧管提供空气出口。 冷却空气从第一歧管通过冷却通道流到第二歧管，因此在围绕圆周的所有点处冷却涡轮机罩的环形壁。

公开(公告)号：US3625003A

公开(公告)日：1971-12-07

申请号：US3625003D

申请日：1970-09-08

Applicant: GEN MOTORS CORP

Inventor： LIDDLE SIDNEY G ,  YU MASON K

IPC: F02C7/057 ,  F02C9/54 ,  F04D29/46 ,  F02C9/14 ,  F02G3/00

CPC classification number: F02C9/54 ,  F02C7/057 ,  F04D29/464

Abstract: A GAS TURBINE ENGINE HAS A DOBULE-ENTRY CENTRIFUGAL COMPRESSOR, COMBUSTION APPARATUS SUPPLIED BY THE COMPRESSOR, AND A TURBINE HAVING VARIABLE NOZZLE AREA SUPPLIED FROM THE COMBUSTION APPARATUS AND DRIVING THE COMPRESSOR. THE TURBINE MAY DRIVE THE LOAD OR A SECOND POWER TURBINE IN SERIES WITH THE COMPRESSOR DRIVING TURBINE MAY BE PROVIDED. A REGENATOR TO EXCHANGE HEAT BETWEEN TURBINE EXHAUST AND COMPRESSED AIR IS PREFERABLY PROVIDED. ONE SIDE OF THE DOUBLE-ENTRY COMPRESSOR IS PROVIDED WITH A SHUT OFF VALVE WHICH CLOSES THE ENTRANCE TO THIS SIDE FOR OPERATION AT IDLING AND UNDER LIGHT LOADS. THE VALVE IS OPENED COMPLETELY FOR HIGHER POWER OUTPUT OF THE ENGINE.

公开(公告)号：US3893292A

公开(公告)日：1975-07-08

申请号：US38595173

申请日：1973-08-06

Applicant: GEN MOTORS CORP

Inventor： AMANN CHARLES A ,  LIDDLE SIDNEY G

IPC: F02C9/18 ,  F02C9/08

CPC classification number: F02C9/18

Abstract: A gas turbine engine connected to drive a motor vehicle includes valving to by-pass the regenerator of the engine when it is desired to decelerate the vehicle so that heat stored in the regenerator is not effective to provide positive power output from the turbine. The cold gas path of the heat exchanger only may be by-passed; or, compressed air may be diverted to atmosphere, by-passing the combustion apparatus, turbine and the entire heat exchanger. Opening of the by-pass is responsive to a request for zero or idling power output from the engine and to turbine rpm above a particular level.

Abstract translation: 连接以驱动机动车辆的燃气涡轮发动机包括阀，以在需要使车辆减速时绕过发动机的再生器，使得存储在再生器中的热量不能有效地提供来自涡轮机的正功率输出。 热交换器的冷气路径只能被旁路; 或者压缩空气可以转移到大气中，绕过燃烧装置，涡轮机和整个热交换器。 旁路的打开响应于从发动机输出的零或空转功率的请求以及高于特定水平的涡轮转速。