US 12,111,054 B2
Gas turbine combustor structure
Hiroki Kasuya, Yokohama Kanagawa (JP); Masao Itoh, Yokohama Kanagawa (JP); Yasunori Iwai, Yokohama Kanagawa (JP); Yuichi Morisawa, Yokohama Kanagawa (JP); and Takashi Sasaki, Yokohama Kanagawa (JP)
Assigned to TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION, Kawasaki (JP)
Filed by TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION, Kawasaki (JP)
Filed on Sep. 11, 2023, as Appl. No. 18/464,565.
Application 18/464,565 is a continuation of application No. PCT/JP2022/017993, filed on Apr. 18, 2022.
Claims priority of application No. 2021-077479 (JP), filed on Apr. 30, 2021.
Prior Publication US 2023/0417413 A1, Dec. 28, 2023
Int. Cl. F23R 3/12 (2006.01); F23R 3/46 (2006.01); F23R 3/20 (2006.01); F23R 3/28 (2006.01)
CPC F23R 3/12 (2013.01) [F23R 3/46 (2013.01); F23R 3/20 (2013.01); F23R 3/28 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A gas turbine combustor structure disposed to penetrate a casing of a gas turbine from a direction perpendicular to an axial direction of a turbine rotor of the gas turbine, the gas turbine combustor structure comprising:
a plurality of combustors;
a rear liner which is constituted by a cylinder body provided in a direction perpendicular to the axial direction of the turbine rotor on a downstream side of the plurality of combustors, and gathers a combustion gas discharged from the plurality of combustors and guides the combustion gas to a downstream side; and
a scroll which is connected to a downstream end of the rear liner, and guides the combustion gas discharged from the rear liner in the axial direction of the turbine rotor and guides the combustion gas in a circumferential direction of the turbine rotor, wherein:
each combustor of the plurality of combustors comprises:
a combustor liner in a cylindrical shape, which combusts fuel and an oxidant;
a fuel supply part which is provided at an upstream end of the combustor liner, and supplies the fuel into the combustor liner; and
an oxidant supply part which is provided in an annular shape around the fuel supply part, and supplies a swirling flow of the oxidant into the combustor liner; and
the plurality of combustors comprise:
the combustor in which a swirling direction of the swirling flow of the oxidant is clockwise when seen from a downstream side of the oxidant supply part; and
the combustor in which a swirling direction of the swirling flow of the oxidant is counterclockwise when seen from the downstream side of the oxidant supply part.