US 12,366,359 B2
Combustor and gas turbine
Shinichi Fukuba, Tokyo (JP); Zhi Zhang, Tokyo (JP); Keisuke Miura, Tokyo (JP); Tomo Kawakami, Tokyo (JP); Kiyoshi Fujimoto, Tokyo (JP); Taku Egawa, Tokyo (JP); Kenta Taniguchi, Tokyo (JP); and Keijiro Saito, Tokyo (JP)
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Appl. No. 18/850,333
Filed by MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
PCT Filed Feb. 17, 2023, PCT No. PCT/JP2023/005867
§ 371(c)(1), (2) Date Sep. 24, 2024,
PCT Pub. No. WO2023/188984, PCT Pub. Date Oct. 5, 2023.
Claims priority of application No. 2022-056000 (JP), filed on Mar. 30, 2022.
Prior Publication US 2025/0207781 A1, Jun. 26, 2025
Int. Cl. F23R 3/28 (2006.01); F02C 7/22 (2006.01)
CPC F23R 3/286 (2013.01) [F02C 7/22 (2013.01); F05D 2240/35 (2013.01)] 11 Claims
OG exemplary drawing
 
11. A combustor comprising:
a combustor plate configured to have a downstream end face intersected to a combustor axis;
a nozzle segment configured such that a plurality of first nozzles that inject a premixed gas of air and fuel from a side of the downstream end face are collectively disposed; and
a plurality of second nozzles configured to inject the fuel from the downstream end face,
wherein a plurality of the nozzle segments are provided at intervals in a direction perpendicular to the combustor axis,
the combustor plate is configured of a plurality of divided bodies divided as viewed from a direction of the combustor axis, the nozzle segment is provided in each of the divided bodies, and each of the second nozzles injects the fuel from a dividing region between the nozzle segments on the downstream end face, and
the dividing region is a region including a dividing line between the divided bodies.