Combustor liner construction

Claim 1

A liner for a combustor for a gas turbine engine comprising an outer wall generally configured in the shape of the combustor, a plurality of circumferentially mounted inner walls facing the combustion products radially disposed from said outer wall, interconnecting elements between said inner and outer walls defining generally longitudinal open ended channels aligned substantially with the flow of combustion products in the combustor, said inner and outer walls and the included interconnecting elements defining a liner segment, and each segment being axially spaced defining a transition zone, opening means formed in said outer wall intermediate the ends of each liner segment for leading compressor cooler air from the space surrounding said liner admitting air internally of said open ended channels so that a portion of the cooler air flows counter to and the remaining portion flow in the direction of the combustion products, the cooler air discharging in the upstream end of the open ended panels merging with the flow of cooler air discharging from the downstream end of the open ended channels of the next adjacent upstream segment, the flow of cooler air in said channels convectively cooling said liner walls and the flow of cooler air discharging from said open ended channels film cooling the outer wall at said transition zone and then the inner wall by flowing along the outside surface thereof.