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Patent Searching and Data


Title:
GAS TURBINE FOR AIRCRAFT
Document Type and Number:
WIPO Patent Application WO/2019/187435
Kind Code:
A1
Abstract:
This gas turbine for an aircraft comprises: a moving blade (24) having a moving blade body (41) extending diametrally outward from a rotor that rotates about an axis, and a fin (43) protruding from an outer peripheral surface (42a) of a moving blade shroud (42) provided to the tip of the moving blade body (41); a casing (22) forming a gap (Cr) with the fin (43); and a stationary blade (26) having a stationary blade shroud (51) of which at least an axially upstream-side front end (51F) is positioned farther diametrally outward than an extended line (Ex) of an inner peripheral surface (22cb) of the casing (22).

Inventors:
FUJIMURA Daigo (16-5, Konan 2-chome, Minato-k, Tokyo 15, 〒1088215, JP)
WATANABE Hiroshi (16-5, Konan 2-chome, Minato-k, Tokyo 15, 〒1088215, JP)
HANADA Tadayuki (1200, Higashitanaka, Komaki-sh, Aichi 26, 〒4850826, JP)
HASE Takaaki (1200, Higashitanaka, Komaki-sh, Aichi 26, 〒4850826, JP)
Application Number:
JP2018/047810
Publication Date:
October 03, 2019
Filing Date:
December 26, 2018
Export Citation:
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Assignee:
MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD. (1200, Higashitanaka Komaki-sh, Aichi 26, 〒4850826, JP)
International Classes:
F01D9/02; F01D5/20; F01D11/12; F01D25/00; F02C7/00; F02C7/28
Domestic Patent References:
WO2017195782A12017-11-16
Foreign References:
JPH05240066A1993-09-17
US20090010758A12009-01-08
JP2013221512A2013-10-28
Attorney, Agent or Firm:
MATSUNUMA Yasushi et al. (1-9-2, Marunouchi Chiyoda-k, Tokyo 20, 〒1006620, JP)
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