A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.
申请公布号
WO2014149108(A1)
申请公布日期
2014.09.25
申请号
WO2013US76696
申请日期
2013.12.19
申请人
GRAVES, CHARLES B.;CUMMINGS, WILLIAM, G., III;BENNETT, RUSSELL N.;SHI, JUN
发明人
GRAVES, CHARLES B.;CUMMINGS, WILLIAM, G., III;BENNETT, RUSSELL N.;SHI, JUN