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ANGLED COMBUSTOR LINER COOLING HOLES THROUGH TRANSVERSE STRUCTURE WITHIN A GAS TURBINE ENGINE COMBUSTOR
ANGLED COMBUSTOR LINER COOLING HOLES THROUGH TRANSVERSE STRUCTURE WITHIN A GAS TURBINE ENGINE COMBUSTOR
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机译:燃气轮机燃烧室中横向结构的倾斜燃烧室冷却孔
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摘要
A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.
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