Title:
【発明の名称】ガスタービン機関の分流装置
Document Type and Number:
Japanese Patent JPH06102992
Kind Code:
B2
Abstract:
The present invention provides a gas turbine engine with a circumferentially disposed plurality of pivotal flow splitters between compressor sections to bleed off flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine engine, by pivoting the leading edge of the splitter into the compressor flow thereby using the total pressure Q of the flow to drive bleed flows overboard and remove particles. In the preferred embodiment the pivotal flow splitter is integral with a booster variable bleed valve (VBV) door, and includes a booster bleed duct means having a bellmouth shaped inducer type inlet to enhance the capture of compressor flow and particle removal
Inventors:
Shin-Tsang Liu
William Ronald Heinz
William Ronald Heinz
Application Number:
JP23552492A
Publication Date:
December 14, 1994
Filing Date:
September 03, 1992
Export Citation:
Assignee:
GENERAL ELECTRIC COMPANY
International Classes:
F02C7/05; F02C7/052; F02C9/18; F04D27/02; F04D29/70; (IPC1-7): F02C9/18; F02C7/05
Domestic Patent References:
| JP4228838A |
Attorney, Agent or Firm:
Tokunji Ikunuma