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Patent Searching and Data


Title:
AIRCRAFT GAS TURBINE ENGINE
Document Type and Number:
WIPO Patent Application WO/2022/091275
Kind Code:
A1
Abstract:
The present invention comprises: a core engine having a core casing that covers a low-pressure rotation part and a high-pressure rotation part and forms a flow path of air passing through the low-pressure rotation part and the high-pressure rotation part; a fan located in front of the core engine; an inner cowl forming an inner periphery surface of a bypass flow path that passes through the fan and bypasses the core engine; an accessory gearbox that extracts power from the low-pressure rotation part and the high-pressure rotation part and supplies the extracted power to various auxiliary devices; an auxiliary compressor that is attached to the accessory gearbox, is driven by a driving force of the accessory gearbox, and boosts the compressed air extracted from the core engine; and a compressed air piping that passes through an inside of a strut connecting the core engine and an aircraft and supplies the compressed air boosted by the auxiliary compressor to the aircraft, wherein the accessory gearbox and the auxiliary compressor are arranged inside an inner space formed between the core casing and the inner cowl.

Inventors:
TAKAMI HIROAKI
SEKOGUCHI NAOYA
ISHIDA KATSUHIKO
UMEZAKI KENTA
SAKAMOTO HIROSHI
GOI TATSUHIKO
Application Number:
PCT/JP2020/040542
Publication Date:
May 05, 2022
Filing Date:
October 28, 2020
Export Citation:
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Assignee:
KAWASAKI HEAVY IND LTD (JP)
International Classes:
F02C7/32; B64D41/00
Domestic Patent References:
WO2012137843A12012-10-11
Foreign References:
US20110203293A12011-08-25
US20170268423A12017-09-21
US20190112060A12019-04-18
US20140165589A12014-06-19
US20160010561A12016-01-14
US20100242496A12010-09-30
JP2008298069A2008-12-11
JPH04231291A1992-08-20
US20190316482A12019-10-17
US20190292989A12019-09-26
US20170037783A12017-02-09
US20120117981A12012-05-17
Attorney, Agent or Firm:
ARCO PATENT & TRADEMARK ATTORNEYS (JP)
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