GAS TURBINE - MITSUBISHI HEAVY IND AERO ENGINES LTD

Title:

GAS TURBINE

Document Type and Number:

WIPO Patent Application WO/2017/110104

Kind Code:

A1

Abstract:

The present invention reduces the thermal stress of flanges which join a combustor casing and a turbine casing together. This gas turbine (10) is provided with a compressor (14), a combustor (15), and a turbine (16) along the extension direction of a rotary shaft (axis R), wherein a combustor casing (12A) for encasing the combustor (15) and a turbine casing (12B) for encasing the turbine (16) are joined by their respective flanges (12Aa, 12Ba) protruding outward. The inner surface of the combustor casing (12A) is equipped with a protrusion (1) protruding radially inward in at least part of the region in the extension direction of the rotary shaft between flange (12Aa) and the compressor (14)-side end of a combustion cylinder (inner cylinder 15B) in the combustor (15) .

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Inventors:

OKABE YOSHIYUKI (JP)
HORIE SHIGENARI (JP)
HANADA TADAYUKI (JP)

Application Number:

PCT/JP2016/060920

Publication Date:

June 29, 2017

Filing Date:

April 01, 2016

Export Citation:

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Assignee:

MITSUBISHI HEAVY IND AERO ENGINES LTD (JP)

International Classes:

F23R3/42; F02C7/20; F23R3/26

Foreign References:

US20130291544A1	2013-11-07
JP2003083088A	2003-03-19
JP2004169655A	2004-06-17

Other References: