GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS
摘要
A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing.
申请公布号
EP2938830(A1)
申请公布日期
2015.11.04
申请号
EP20130869557
申请日期
2013.12.06
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
GOELLER, TRAVIS;GRANSTRAND, ERIK R.;SINGER, IRWIN D.;MONGILLO, DOMINIC, J., JR.;PIETRASZKIEWICZ, EDWARD F.