公开(公告)号：GB2219046A

公开(公告)日：1989-11-29

申请号：GB8909977

申请日：1989-05-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DENNISON WILLIAM T ,  BRODELL ROBERT F ,  MONSARRAT WILLIAM G

IPC: F02C7/20

Abstract: A gas turbine fan engine with improved maintainability features is disclosed. Forward and rearward sections of the core of the engine are joined one to the other, and each are independently separable from the pylon on which the engine is mounted without the necessity of removing the other from the airplane.

公开(公告)号：US3904307A

公开(公告)日：1975-09-09

申请号：US45984474

申请日：1974-04-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DENNISON WILLIAM T

IPC: F01D5/08 ,  F02C7/12

CPC classification number: F02C7/12 ,  F01D5/081

Abstract: An arrangement for cooling the high and low pressure rotors of a gas turbine, the rotors being independently rotatable on concentric axes, in which cooling air is supplied from a source downstream of the rotors through the low pressure rotor to the space between them and from this space to the blades thereon, and also to a space upstream of the high pressure rotor for cooling the face thereof.

Abstract translation: 一种用于冷却燃气轮机的高压和低压转子的装置，转子可以在同心轴上独立地旋转，其中冷却空气从转子下游的源通过低压转子供应到它们之间的空间，并且由此 空间到其上的叶片，并且还到达高压转子的上游的空间，用于冷却其表面。

公开(公告)号：DE3871973D1

公开(公告)日：1992-07-23

申请号：DE3871973

申请日：1988-02-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DENNISON WILLIAM T

IPC: F02C7/00 ,  B32B5/08 ,  F01D5/02 ,  F01D5/28 ,  F01D7/00 ,  F16C35/077

Abstract: The composite support disc or ring (10) for a row of fan blades (62) in a bypass turbine engine is made up of plies of high strength fibers so oriented as to carry the loading developed on the ring (10) by the fan blades (62) and with the fan blades (62) mounted to minimize the loading on the composite disc (10). The orientation of the fibers are different in selected areas of the disc to provide a high strength disc (10) with a minimum weight.

公开(公告)号：FR2631385A1

公开(公告)日：1989-11-17

申请号：FR8906303

申请日：1989-05-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DENNISON WILLIAM T ,  BRODELL ROBERT F ,  MONSARRAT WILLIAM G

IPC: F02C7/20

Abstract: A gas turbine fan engine with improved maintainability features is disclosed. Forward and rearward sections of the core of the engine are joined one to the other, and each are independently separable from the pylon on which the engine is mounted without the necessity of removing the other from the airplane.

公开(公告)号：DE3862695D1

公开(公告)日：1991-06-13

申请号：DE3862695

申请日：1988-06-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DENNISON WILLIAM T ,  BRODELL ROBERT F

IPC: F02C7/06 ,  A61M1/10 ,  F02C7/14 ,  F01D25/20

Abstract: An oil lubricating and cooling system is positioned in the engine cowl (2) and includes a heat exchanger (84), a compressor (50) for delivering air from air inlets (65) in the surface of the cowl (2) through the heat exchanger (84) and hence to air outlets (104) also in the cowl surface and oil pumps (74,76) also located within the cowl (2) for circulating oil from the sump (42) in the cowl (2) to the heat exchanger (84) to the reduction gear (14,16,20) within the cowl (2) that serve to drive a fan also supported within the cowl (2) and having the blades (32) extending outwardly therefrom. The reduction gear (14,16,20), compressor (50) and pumps (74,76) are all driven from the engine shaft (19), the end of which is located in the cowl (2).

公开(公告)号：DE3862652D1

公开(公告)日：1991-06-13

申请号：DE3862652

申请日：1988-02-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DENNISON WILLIAM T

IPC: B64C11/38 ,  F01D7/00

Abstract: A non-rotating actuating system for pitch control of a fan in a bypass turbine engine in which the actuating ring (20), that rotates with the fan and is moved axially to change the pitch of the fan blades (2), is supported by a part of the fixed structure (12) thereby to minimize loading of the disc supporting structure.

公开(公告)号：DE3871973T2

公开(公告)日：1993-02-18

申请号：DE3871973

申请日：1988-02-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DENNISON WILLIAM T

IPC: F02C7/00 ,  B32B5/08 ,  F01D5/02 ,  F01D5/28 ,  F01D7/00 ,  F16C35/077

Abstract: The composite support disc or ring (10) for a row of fan blades (62) in a bypass turbine engine is made up of plies of high strength fibers so oriented as to carry the loading developed on the ring (10) by the fan blades (62) and with the fan blades (62) mounted to minimize the loading on the composite disc (10). The orientation of the fibers are different in selected areas of the disc to provide a high strength disc (10) with a minimum weight.