Title:
遷音速ガスタービンの衝撃波誘起境界層の抽気
Document Type and Number:
Japanese Patent JP2007536459
Kind Code:
A
Abstract:
An apparatus and method is provided for improving efficiency of a transonic gas turbine engine compressor by bleeding off a shockwave-induced boundary layer from the gas flow passage of the compressor using an array of bleed holes having a downstream edge aligned with a foot of an oblique shock wave which originates on the leading edge of an adjacent transonic rotor blade tip.
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Inventors:
Wellet, Gilbert
Le Blanc, Andre
Le Blanc, Andre
Application Number:
JP2007511810A
Publication Date:
December 13, 2007
Filing Date:
May 06, 2005
Export Citation:
Assignee:
Pratt & Whitney Canada Corp.
International Classes:
F04D29/54; F01D1/00; F01D5/14; F01D5/18; F02C3/06; F02C9/18; F04D21/00; F04D29/66; F04D29/68
Domestic Patent References:
| JPH08326505A | 1996-12-10 | |||
| JP2003065299A | 2003-03-05 | |||
| JPS63183204A | 1988-07-28 | |||
| JP2001304194A | 2001-10-31 | |||
| JPH08219094A | 1996-08-27 | |||
| JPH0712098A | 1995-01-17 |
Attorney, Agent or Firm:
Tsuyoshi Hashimoto
Tomioka Kiyoshi
Tomioka Kiyoshi