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公开(公告)号：US11754285B2
公开(公告)日：2023-09-12
申请号：US17689307
申请日：2022-03-08
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03042
摘要： The liner of a combustor (100) for a gas turbine engine is provided with a projection region (111) provided with a plurality of projections (110) each projecting toward the compressed air chamber (56) from the liner outer surface and having a vertical wall portion (114) extending substantially orthogonally to a flow direction of compressed air flowing in the compressed air chamber, and a plurality of cooling holes (118) 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 the cooling hole on a side of the combustion chamber (52) with respect to the flow direction of the compressed air in the compressed air chamber, at least a part of the cooling holes being formed in the projection region.
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公开(公告)号：US11725821B2
公开(公告)日：2023-08-15
申请号：US17692273
申请日：2022-03-11
摘要： A fuel nozzle device (100) for injecting liquid fuel into a combustion chamber (52) of a gas turbine engine (10) includes an outer tube (101), a rear end wall (102) closing a base end of the outer tube, a tapered conical tube (104) defining a first air passage (112) therein, and a second air passage (114) having an annular cross section jointly with the outer tube, a fuel passage (108) axially passed through the rear end wall, and leading to a fuel ejection port (109) directed toward an inner circumferential surface of a base end of the conical tube, a first air introduction passage (111) passed through the outer tube to communicate with the first air passage, and a second air introduction passage (113) passed through the outer tube to communicate with the second air passage.
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