Combustor construction

Claim 2

A gas turbine engine combustor assembly located in an inlet air plenum comprising: an outer annular porous laminated wall, an inner annular porous laminated wall aligned with said outer wall to define a fuel combustion zone therebetween having opposite open ends, an annular porous laminated wall dome plate closing one of said open ends, an extension of porous laminated wall on the inlet end of each of said inner and outer annular walls, said extension being directed outwardly of the combustion zone to define a flame isolated connection surface on both the inner and outer laminated walls of the combustor at a point exposed to inlet plenum air, said dome plate having spaced, bent porous flanges thereon, and connection weld means connecting said dome plate flanges to said connection surfaces to define an annular sealed weld joint at said connection surfaces to close said one open end whereby coolant flow from exteriorly of the combustor assembly is free to flow across the full flamed exposed inner wall surfaces of the inner and outer wall and dome exposed to the combustion zone and wherein the connection means between said inner and outer walls and dome plate flanges is maintained out of direct flame exposed relationship with the combustion zone and in direct coolant flow relationship with inlet plenum air for maintenance of a secure, cool, thermal fatigue resistant connection between the annular dome plate and the inner and outer walls of the combustor assembly.

Claim 3

A gas turbine engine combustor assembly located in an inlet air plenum comprising: an outer annular porous laminated wall, an inner annular porous laminated wall aligned with said outer wall to define a fuel combustion zone therebetween having opposite open ends, an annular porous laminated wall dome plate closing one of said open ends, a porous flange on the inlet end of each of said inner and outer annular walls, said porous flanges being flared outwardly of the combustion zone to define extended length flame isolated connection surfaces on the inner and outer laminated walls of the combustor at a point exposed to inlet plenum air, said connection surfaces being arranged parallel to one another, said dome plate having spaced, bent porous flanges thereon, and connection weld means connecting said dome plate flanges to said connection surfaces to define annular weld sealed joints at the outer end of said connection surfaces to close said one open end and wherein the connection means between said inner and outer walls and dome plate flanges is maintained out of direct flame exposed relationship with the combustion zone and in direct coolant flow relationship with inlet plenum air for maintenance of a secure, cool, thermal fatigue resistant connection between the dome plate and the inner and outer walls of the combustor assembly.

Claim 4

A gas turbine engine combustor assembly located in an inlet air plenum comprising: an outer annular porous laminated wall, an inner annular porous laminated wall aligned with said outer wall to define a fuel combustion zone therebetween having opposite open ends, an annular porous laminated wall dome plate closing one of said open ends, a porous flange on the inlet end of each of said inner and outer annular walls, said porous flanges being flared outwardly of the combustion zone to define extended length flame isolated connection surfaces on the inner and outer laminated walls of the combustor at a point exposed to inlet plenum air, said connection surfaces being arranged parallel to one another, said dome plate having spaced, bent porous flanges thereon, and connection weld means connecting said dome plate flanges to said connection surfaces to define annular weld sealed joints at the outer end of said connection surfaces to close said one open end and wherein the connection means between said inner and outer walls and dome plate flanges is maintained out of direct flame exposed relationship with the combustion zone and in direct coolant flow relationship with inlet plenum air for maintenance of a secure, cool, thermal fatigue resistant connection between the dome plate and the inner and outer walls of the combustor assembly.

Claim 5

A gas turbine engine combustor assembly located in an inlet air plenum, comprising: an outer annular porous laminated wall, an inner annular porous laminated wall aligned with said outer wall to define a fuel combustion zone therebetween having opposite open ends, an annular porous laminated wall dome plate closing one of said open ends, a porous flange on the inlet end of each of said inner and outer annular walls, said porous flanges being flared outwardly of the combustion zone to define a flame isolated connection surface on both the inner and outer laminated walls of the combustor at a point exposed to inlet plenum air, said connection surfaces being divergently formed to one another outboard of said dome plate, said dome plate having spaced, bent porous flanges thereon, and connection weld means connecting said dome plate flanges to said connection surfaces to define annular weld sealed joints at the outer end of said connection surfaces to close said one open end whereby coolant flow from exteriorly of the combustor assembly is free to flow across the full flamed exposed inner wall surfaces of the inner and outer wall and dome exposed to the combustion zone and wherein the connection means between said inner and outer walls and dome plate flanges is maintained out of direct flame exposed relationship with the combustion zone for maintenance of a secure, cool thermal fatigue resistant connection between the dome plate and the inner and outer walls of the combustor assembly.

Claim 6

A gas turbine engine combustor assembly located in an inlet air plenum, comprising: an outer annular porous laminated wall, an inner annular porous laminated wall aligned with said outer wall to define a fuel combustion zone therebetween having opposite open ends, an annular porous laminated wall dome plate closing one of said open ends, a porous flange on the inlet end of each of said inner and outer annular walls, said porous flanges being flared outwardly of the combustion zone to define a flame isolated connection surface on both the inner and outer laminated walls of the combustor at a point exposed to inlet plenum air, said connection surfaces being divergently formed to one another outboard of said dome plate, said dome plate having spaced, bent porous flanges thereon, and connection weld means connecting said dome plate flanges to said connection surfaces to define annular weld sealed joints at the outer end of said connection surfaces to close said one open end whereby coolant flow from exteriorly of the combustor assembly is free to flow across the full flamed exposed inner wall surfaces of the inner and outer wall and dome exposed to the combustion zone and wherein the connection means between said inner and outer walls and dome plate flanges is maintained out of direct flame exposed relationship with the combustion zone for maintenance of a secure, cool thermal fatigue resistant connection between the dome plate and the inner and outer walls of the combustor assembly.

Claim 7

A gas turbine engine combustor assembly located in an inlet air plenum comprising: an outer case, an outer annular porous laminated wall, an inner annular porous laminted wall aligned with said outer wall to define a fuel combustion zone therebetween having opposite open ends, an annular, load support dome closing one of said open ends, said dome being a porous laminated wall, a porous flange on the inlet end of each of said inner and outer annular walls, said porous flanges being flared outwardly of the combustion zone to define a flame isolated connection surface on both the inner and outer laminated walls of the combustor at a point exposed to inlet plenum air, said dome plate having spaced, bent porous flanges thereon, and connection weld means connecting said dome plate flanges to said connection surfaces to define annular weld sealed joints at said connection surfaces to close said one open end whereby coolant flow from exteriorly of the combustor assembly is free to flow across the full flame exposed inner wall surfaces of the inner and outer wall and dome exposed to the combustion zone and wherein the connection means between said inner and outer walls and dome plate is maintained out of direct flame exposed relationship with the combustion zone for maintenance of a secure, thermal fatigue resistant connection between the load support dome plate and the inner and outer walls of the combustor assembly, and a dome support bracket including a brace secured to the outer surface of said dome and an axial support member secured at one end to said brace and at the opposite end to said outer case.

Claim 8

A gas turbine engine combustor assembly located in an inlet air plenum comprising: an outer case, an outer annular porous laminated wall, an inner annular porous laminted wall aligned with said outer wall to define a fuel combustion zone therebetween having opposite open ends, an annular, load support dome closing one of said open ends, said dome being a porous laminated wall, a porous flange on the inlet end of each of said inner and outer annular walls, said porous flanges being flared outwardly of the combustion zone to define a flame isolated connection surface on both the inner and outer laminated walls of the combustor at a point exposed to inlet plenum air, said dome plate having spaced, bent porous flanges thereon, and connection weld means connecting said dome plate flanges to said connection surfaces to define annular weld sealed joints at said connection surfaces to close said one open end whereby coolant flow from exteriorly of the combustor assembly is free to flow across the full flame exposed inner wall surfaces of the inner and outer wall and dome exposed to the combustion zone and wherein the connection means between said inner and outer walls and dome plate is maintained out of direct flame exposed relationship with the combustion zone for maintenance of a secure, thermal fatigue resistant connection between the load support dome plate and the inner and outer walls of the combustor assembly, and a dome support bracket including a brace secured to the outer surface of said dome and an axial support member secured at one end to said brace and at the opposite end to said outer case.