MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS
摘要
A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed.
申请公布号
WO2014077909(A3)
申请公布日期
2014.07.03
申请号
WO2013US49036
申请日期
2013.07.02
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
XU, JINQUAN;PIETRASZKIEWICZ, EDWARD, F.;ZELESKY, MARK, F.;LEVASSEUR, GLENN;MONGILLO, DOMINIC, J.