Title:
ガスタービンエンジン用の混流式および遠心式の圧縮機
Document Type and Number:
Japanese Patent JP2004516401
Kind Code:
A
Abstract:
A two stage compressor for a gas turbine engine with a mixed flow first stage, a centrifugal second stage, and an intermediate duct. The mixed flow stage has a mixed rotor rotatable about the central compressor axis with a circumferential array of mixed flow blades between the mixed flow hub and an associated mixed flow shroud. The downstream centrifugal stage has a centrifugal rotor rotatable about the same compressor axis. The centrifugal rotor has a circumferential array of radially extending centrifugal flow blades between the centrifugal flow hub and an associated centrifugal flow shroud. An intermediate duct has an inner duct wall defining an axially curvilinear transition surface of revolution between an outlet end of the mixed flow hub and an inlet end of the centrifugal flow hub and an outer duct wall defining an axially curvilinear transition surface of revolution between an outlet end of the mixed flow shroud and an inlet end of the centrifugal flow shroud. Preferably, the intermediate duct has a median inlet radius greater than an intermediate duct median outlet radius whereby air flow from the mixed rotor is directed radially inwardly and axially rearwardly toward the centrifugal rotor.
Inventors:
Youssef, Nashed
Clothing, gully
Clothing, gully
Application Number:
JP2002532798A
Publication Date:
June 03, 2004
Filing Date:
September 21, 2001
Export Citation:
Assignee:
Pratt & Whitney Canada, Inc.
International Classes:
F02C3/08; F02K3/06; F04D17/02; F04D17/06; F04D17/12; F04D23/00; F04D29/44; (IPC1-7): F02C3/08; F02K3/06; F04D17/02; F04D23/00
Attorney, Agent or Firm:
Tsuyoshi Hashimoto
Tomioka Kiyoshi
Tomioka Kiyoshi