COMBUSTOR FOR GAS TURBINE, GAS TURBINE, AND GAS TURBINE ASSEMBLY METHOD

WIPO Patent Application WO/2022/202516

A1

A combustor for a gas turbine according to one embodiment of the present invention includes an acoustic device that is located on the downstream side of a combustion pipe and has: a first region that lies in at least any one of a pair of positions spanning the combustion pipe in the radial direction of the combustion pipe; a pair of second regions having positions in the axial direction of the combustion pipe that at least partially overlap the pair of positions, having different positions in the circumferential direction of the combustion pipe than the pair of positions, and lying in positions spanning the combustion pipe in the radial direction; and a third region located on the upstream side of the combustion pipe relative to the first and second regions. The radial thickness of the acoustic device in the pair of second regions is less than the radial thickness of the acoustic device in the first region, and the radial thickness of the acoustic device in the third region is greater than the radial thickness of the acoustic device in the pair of second regions.

TOKUYAMA KENTARO (JP)
KINOSHITA TAIKI (JP)
TANIGUCHI KENTA (JP)
HASHIMOTO KENICHI (JP)
TAKIGUCHI SATOSHI (JP)
TOMINAGA KAZUHIRO (JP)

PCT/JP2022/011809

September 29, 2022

March 16, 2022

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MITSUBISHI HEAVY IND LTD (JP)
MITSUBISHI POWER LTD (JP)

F02C3/16; F23L1/00; F23R3/00; F23R3/42

JP2017020682A	2017-01-26
JP2013117231A	2013-06-13

SSIP PATENT ATTORNEY CORPORATION (JP)

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