US 11,754,285 B2
Combustor for gas turbine engine including plurality of projections extending toward a compressed air chamber
Yasuharu Kamoi, Saitama (JP); Shinichi Kobayashi, Saitama (JP); and Hideaki Nakano, Saitama (JP)
Assigned to HONDA MOTOR CO., LTD., Tokyo (JP)
Filed by HONDA MOTOR CO., LTD., Tokyo (JP)
Filed on Mar. 8, 2022, as Appl. No. 17/689,307.
Claims priority of application No. 2021-053778 (JP), filed on Mar. 26, 2021.
Prior Publication US 2022/0307693 A1, Sep. 29, 2022
Int. Cl. F23R 3/06 (2006.01); F23R 3/00 (2006.01)
CPC F23R 3/002 (2013.01) [F23R 3/06 (2013.01); F23R 2900/03042 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A combustor configured to be placed in a compressed air chamber of a gas turbine engine and formed around an axial line to define a combustion chamber for generating combusted gas therein, the combustor including a liner having a liner outer surface facing the compressed air chamber and a liner inner surface facing the combustion chamber,
wherein the liner is provided with a projection region provided with a plurality of projections each projecting toward the compressed air chamber from the liner outer surface and having a vertical wall portion extending substantially orthogonally to a flow direction of compressed air flowing in the compressed air chamber, and a plurality of cooling holes passed through the liner from the liner outer surface to the liner inner surface such that an end of each cooling hole on a side of the compressed air chamber is more downstream than an end of each cooling hole on a side of the combustion chamber with respect to the flow direction of the compressed air in the compressed air chamber, at least a part of the plurality of cooling holes being formed in the projection region,
wherein each projection is provided with a parallel wall portion extending from the vertical wall portion to a downstream side with respect to the flow direction of the compressed air flowing in the compressed air chamber in parallel with the liner outer surface, and an inclined wall portion extending from a downstream end of the parallel wall portion to the liner outer surface in an inclined direction with respect to the flow direction of the compressed air flowing in the compressed air chamber,
wherein each cooling hole is inclined so as to approach the liner outer surface toward the downstream side with respect to the flow direction of the compressed air flowing in the compressed air chamber, the end of each cooling hole on the side of the compressed air chamber opens at the inclined wall portion, and the end of each cooling hole on the side of the combustion chamber reaches more upstream than the vertical wall portion with respect to the flow direction of the compressed air flowing in the compressed air chamber,
wherein each cooling hole follows a linear path from the end of the cooling hole on the side of the compressed air chamber to the end of the cooling hole on the side of the combustion chamber.