Combustor support structure

Claim 2

A combustor support structure in an air duct for supplying combustion products to the turbine nozzle of a gas turbine engine having a combustor support wall comprising in combination: multi-layered porous metal combustor having an inlet end and an outlet end and an internal combustion chamber for receiving maximized combustion and dilution air flow through said porous metal wall, a dome of porous metal material secured to said combustor, said dome including a radially outwardly contoured ring segment forming a maximized air fuel mixing volume within said dome, a rigid support ring having a radial flange connected to said ring segment, said support ring further including an axial extension outboard of said dome, an air-blast nozzle on said extension defining an axial air inlet, an inlet diffuser member for axially directing primary air flow into the inlet of said dome, said inlet diffuser member having a low profile inlet snout to direct compressor air flow toward said axial air inlet, said diffuser member further including an outlet end with a flared cone in axial alignment with said porous dome and including a circular lip on said cone spaced axially of said dome to accommodate axial movement between said dome and said diffuser member, a support secured to one side of said inlet diffuser member including means thereon for fixedly securing the inlet diffuser member to the combustor support wall and means for axially slidably supporting said lip on said rigid support ring to permit free thermal expansion of said dome relative to said fixed inlet diffuser member for preventing excessive stress build-up in the porous metal material of said dome.

Claim 3

A support assembly for a canister type combustor in an annular air duct for supplying combustion products to the turbine nozzle of a gas turbine engine with an axial compressor including a combustor support wall internally thereof comprising in combination: a tubular, multi-layered porous metal wall having an inlet end and an outlet end and an internal combustion chamber therein for receiving combustion and dilution air flow through said porous wall, a dome of porous metal material secured to said inlet end having a radially outwardly contoured ring segment forming a maximized air fuel mixing volume within said dome, a rigid support ring having a radial flange connected to said ring segment, said support ring further including an axial extension outboard of said dome defining an axial air inlet, an inlet diffuser member for axially directing primary air flow into the inlet of said dome, said inlet diffuser member having a low profile inlet snout to direct compressor air flow toward said axial air inlet, said diffuser member further including an outlet end with a flared cone in axial alignment with said porous dome and including a circular lip on said cone spaced axially of said dome to accommodate axial movement between said dome and said diffuser member, a flow divider secured to one side of said inlet difuser member including means thereon for fixedly securing the inlet diffuser member to the combustor support wall and means for axially slidably supporting said lip on said rigid support ring to permit free thermal expansion of said dome relative to said fixed inlet diffuser member for preventing excessive stress build-up in the porous metal material of said dome.

Claim 4

A support assembly for a canister type combustor in an annular air duct for supplying combustion products to the turbine nozzle of a gas turbine engine with an axial compressor including a combustor support wall internally thereof comprising in combination: a tubular, multi-layered porous metal wall having an inlet end and an outlet end and an internal combustion chamber therein for receiving combustion and dilution air flow through said porous wall, a dome of porous metal material secured to said inlet end having a radially outwardly contoured ring segment forming a maximized air fuel mixing volume within said dome, a rigid support ring having a radial flange connected to said ring segment, said support ring further including an axial extension outboard of said dome defining an axial air inlet, an inlet diffuser member for axially directing primary air flow into the inlet of said dome, said inlet diffuser member having a low profile inlet snout to direct compressor air flow toward said axial air inlet, said diffuser member further including an outlet end with a flared cone in axial alignment with said porous dome and including a circular lip on said cone spaced axially of said dome to accommodate axial movement between said dome and said diffuser member, a flow divider secured to one side of said inlet difuser member including means thereon for fixedly securing the inlet diffuser member to the combustor support wall and means for axially slidably supporting said lip on said rigid support ring to permit free thermal expansion of said dome relative to said fixed inlet diffuser member for preventing excessive stress build-up in the porous metal material of said dome.