发明名称 |
COATED COOLING PASSAGE |
摘要 |
A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery. |
申请公布号 |
EP3066322(A4) |
申请公布日期 |
2016.11.30 |
申请号 |
EP20140857449 |
申请日期 |
2014.09.04 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
BURD, STEVEN W.;BRDAR, CHRISTOPHER R.;PHILIPPONA, DERK S. |
分类号 |
F02C7/24;F01D25/12;F01D25/30;F02C7/12;F02K1/82 |
主分类号 |
F02C7/24 |
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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