发明名称 |
ANGLED COMBUSTOR LINER COOLING HOLES THROUGH TRANSVERSE STRUCTURE WITHIN A GAS TURBINE ENGINE COMBUSTOR |
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. |
申请公布号 |
WO2015039075(A1) |
申请公布日期 |
2015.03.19 |
申请号 |
WO2014US55791 |
申请日期 |
2014.09.16 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
BOULDIN, LEE E.;MOURA, DENNIS M.;EASTWOOD, JONATHAN J.;PACHECO-TOUGAS, MONICA |
分类号 |
F02C7/12;F02C7/18;F23M5/04;F23R3/42 |
主分类号 |
F02C7/12 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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