GAS TURBINE ENGINE WALL ASSEMBLY WITH SUPPORT SHELL CONTOUR REGIONS
摘要
A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.
申请公布号
WO2015031816(A1)
申请公布日期
2015.03.05
申请号
WO2014US53514
申请日期
2014.08.29
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
BANGERTER, JAMES, P.;LOW, KEVIN, J.;HANSON, RUSSELL, B.;ERBAS-SEN, NURHAK;CUNHA, FRANK, J.