公开(公告)号：DE3482915D1

公开(公告)日：1990-09-13

申请号：DE3482915

申请日：1984-04-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： STEVENS LEONARD W ,  SIWIK WILLIAMS S ,  MOORE WILLIAM A ,  BROWN WAYNE M ,  BARNARD ANDREW A

IPC: F02C7/06 ,  F01D11/00 ,  F01D25/12 ,  F01D25/18 ,  F02C7/18 ,  F02C7/28 ,  F01D25/16 ,  F04D29/12

公开(公告)号：CA1225334A

公开(公告)日：1987-08-11

申请号：CA497631

申请日：1985-12-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BROWN WAYNE M ,  NEAL WILLIAM F ,  SCHWARZ FREDERICK M

IPC: F02C7/06 ,  F01D3/00 ,  F02C7/18 ,  F02C7/28

Abstract: Rotor Thrust Bearing A turbine construction in which the axial loading on the rotor including the compressor and turbine resulting from cooling air pressure in the compartment between the compressor and turbine is balanced by making the compressor and turbine areas exposed to the cooling air of equal area as by having the seals at compressor and turbine ends of the compartment equal in radius with respect to the air of the rotor.

公开(公告)号：CA1050775A

公开(公告)日：1979-03-20

申请号：CA257254

申请日：1976-07-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BROWN WAYNE M ,  MANENTE JOSEPH C JR

IPC: F02C7/18 ,  F04D27/02 ,  F02K11/02

Abstract: COMPRESSOR BLEED SYSTEM Methods and apparatus for flowing cooling air from the compressor section to the turbine section of a gas turbine engine are disclosed. Cooling air from the compressor is flowed radially inward through the compressor drum cavity and thence axially rearward along the rotor shaft to the turbine. Vortex pressure losses in the drum cavity are diminished to enable effective utilization of a lower pressure, lower temperature cooling air source. The use of air from the lower pressure, lower temperature source improves the overall engine operating efficiency while maintaining turbine cooling rates which are consonant with durable operation of the engine.