COOLING CHANNELS FOR GAS TURBINE ENGINE COMPONENTS
摘要
A gas turbine engine component (72) includes a wall portion and a leading edge cooling channel (82; 82') that extends through the wall portion. The leading edge cooling channel (82; 82') includes at least one first cooling passage (110; 210) separated from at least one serpentine cooling passage (114; 214).
申请公布号
EP3133254(A1)
申请公布日期
2017.02.22
申请号
EP20160185200
申请日期
2016.08.22
申请人
United Technologies Corporation
发明人
ROMANOV, Dmitriy A.;MONGILLO Jr., Dominic J.;DEVORE, Matthew A.
