US 12,480,655 B2
Combustor for gas turbine engine
Yasuharu Kamoi, Saitama (JP); Toshiyuki Tsuji, Saitama (JP); and Tomomitsu Karube, Saitama (JP)
Assigned to HONDA MOTOR CO., LTD., Tokyo (JP)
Filed by HONDA MOTOR CO., LTD., Tokyo (JP)
Filed on Jan. 15, 2025, as Appl. No. 19/022,184.
Claims priority of application No. 2024-011892 (JP), filed on Jan. 30, 2024.
Prior Publication US 2025/0244014 A1, Jul. 31, 2025
Int. Cl. F23R 3/00 (2006.01); F23R 3/06 (2006.01)
CPC F23R 3/002 (2013.01) [F23R 3/06 (2013.01); F23R 2900/03042 (2013.01)] 7 Claims
OG exemplary drawing
 
1. A combustor for a gas turbine engine that is placed in a compressed air chamber of the gas turbine engine to generate combustion gas, the combustor being provided with a liner that defines a combustion chamber therein around a prescribed central axis, the liner comprising:
a plurality of raised wall portions that extends in a circumferential direction at an angle with respect to the central axis and are arranged at predetermined intervals along the central axis;
a plurality of cooling air holes passed through each of the raised wall portions at a predetermined interval in the circumferential direction; and
thick wall portions provided in parts of each of the raised wall portions at ends of the cooling air holes such that each thick wall portion is formed around an outer periphery of an end of a corresponding one of the cooling air holes,
wherein the thick wall portions are provided at inlets and/or outlets of the cooling air holes, and
the thick wall portions are individually formed in an arcuate shape at the inlets and/or outlets of the cooling air holes such that a recess is defined between each pair of the thick wall portions adjacent to each other in the circumferential direction.