Ring connection for porous combustor wall panels

Claim 2

A gas turbine engine combustor assembly comprising: an annular wall forming a combustion chamber, said annular wall having a plurality of axially directed panels, each of said panels including at least two or more laminated layers of porous material for directing fluid air flow from outside said liner to produce transpiration cooling of the inner surface of said segments in surrounding relationship to said combustion chamber, said panels each having axially spaced ends thereon, a combustor connector ring located in surrounding relationship to said ends on the outer surface of said panels, said ring including a locater tang thereon interposed between said ends in engagement therewith to maintain a controlled weld gap therebetween, a weld annulus of weld metal filling said weld gap to interconnect said ends, said weld annulus having an axial extent within the axial confines of said ring to minimize weld joint width and consequent reduction of flow of transpiration cooling air through said two or more laminated layers on either side of said annulus of weld metal, said weld annulus serving as a heat conductor for transfer of heat to said ring and thence exteriorly of said combustor so as to prevent hot spots in said weld annulus.

Claim 3

A gas turbine engine combustor assembly comprising: an annular wall forming a combustion chamber, said annular wall having a plurality of axially directed panels, each of said panels including at least two or more laminated layers of porous material for directing fluid air flow from outside said liner to produce transpiration cooling of the inner surface of said segments in surrounding relationship to said combustion chamber, said panels each having axially spaced ends thereon, a combustor connector ring located in surrounding relationship to said ends on the outer surface of said panels, said ring including a locater tang thereon interposed between said ends in engagement therewith to maintain a controlled weld gap therebetween, a weld annulus of weld metal filling said weld gap to interconnect said ends, said weld annulus having an axial extent within the axial confines of said ring to minimize weld joint width and consequent reduction of flow of transpiration cooling air through said two or more laminated layers on either side of said annulus of weld metal, said weld annulus having a smooth internal surface substantially flush with the internal surface of said segments to maintain a smooth inner combustor wall surface for minimal cooling film change, and said weld annulus serving as a heat conductor for transfer of heat to said ring and thence exteriorly of said combustor so as to prevent hot spots in said weld annulus.

Claim 4

A gas turbine engine combustor assembly comprising: an annular wall forming a combustion chamber, said annular wall having a plurality of axially directed panels, each of said panels including at least two or more laminated layers of porous material for directing fluid air flow from outside said liner to produce transpiration cooling of the inner surface of said segments in surrounding relationship to said combustion chamber, said panels each having axially spaced ends thereon, a combustor connector ring located in surrounding relationship to said ends on the outer surface of said panels, said ring including a locater tang thereon interposed between said ends in engagement therewith to maintain a controlled weld gap therebetween, a weld annulus of weld metal filling said weld gap to interconnect said ends, said weld annulus having an axial extent within the axial confines of said ring to minimize weld joint width and consequent reduction of flow of transpiration cooling air through said two or more laminated layers on either side of said annulus of weld metal, said weld annulus having a smooth internal surface substantially flush with the internal surface of said segments to maintain a smooth inner combustor wall surface for minimal cooling film change, and said weld annulus serving as a heat conductor for transfer of heat to said ring and thence exteriorly of said combustor so as to prevent hot spots in said weld annulus.

Claim 5

A gas turbine engine combustor assembly comprising: an outer axial wall and an inner axial wall forming a combustion chamber therebetween, said outer axial wall having a plurality of axially directed panels, each of said panels including at least two or more laminated layers of porous material for directing fluid air flow from outside said liner to produce transpiration cooling of the inner surface of said segments in surrounding relationship to said combustion chamber, said panels each having axially spaced ends thereon, a combustor connector ring located in surrounding relationship to said ends on the outer surface of said panels, said ring including a locater tang thereon interposed between said ends in engagement therewith to maintain a controlled weld gap therebetween, a weld annulus of weld metal filling said weld gap to interconnect said ends, said weld annulus having an axial extent within the axial confines of said ring to minimize weld joint width and consequent reduction of flow of transpiration cooling air through said two or more laminated layers on either side of said annulus of weld metal, said weld annulus having a smooth internal surface substantially flush with the internal surface of said segments to maintain a smooth inner combustor wall surface for minimal cooling film change, and said weld annulus serving as a heat conductor for transfer of heat to said ring and thence exteriorly of said combustor so as to prevent hot spots in said weld annulus.

Claim 6

A gas turbine engine combustor assembly comprising: an outer axial wall and an inner axial wall forming a combustion chamber therebetween, said outer axial wall having a plurality of axially directed panels, each of said panels including at least two or more laminated layers of porous material for directing fluid air flow from outside said liner to produce transpiration cooling of the inner surface of said segments in surrounding relationship to said combustion chamber, said panels each having axially spaced ends thereon, a combustor connector ring located in surrounding relationship to said ends on the outer surface of said panels, said ring including a locater tang thereon interposed between said ends in engagement therewith to maintain a controlled weld gap therebetween, a weld annulus of weld metal filling said weld gap to interconnect said ends, said weld annulus having an axial extent within the axial confines of said ring to minimize weld joint width and consequent reduction of flow of transpiration cooling air through said two or more laminated layers on either side of said annulus of weld metal, said weld annulus having a smooth internal surface substantially flush with the internal surface of said segments to maintain a smooth inner combustor wall surface for minimal cooling film change, and said weld annulus serving as a heat conductor for transfer of heat to said ring and thence exteriorly of said combustor so as to prevent hot spots in said weld annulus.

Claim 7

A gas turbine engine cannular combustor assembly comprising: an outer axial wall and an inner axial wall forming a combustion chamber therebetween, said outer annular wall and said inner axial wall each having a plurality of axially directed panels, each of said panels including at least two or more laminated layers of porous material for directing fluid air flow from outside said liner to produce transpiration cooling of the inner surface of said segments in surrounding relationship to said combustion chamber, said panels each having axially spaced ends thereon, a combustor connector ring located in surrounding relationship to said ends on the outer surface of each of said panels, said ring including a locater tang thereon interposed between said ends in engagement therewith to maintain a controlled weld gap therebetween, a weld annulus of weld metal filling said weld gap to interconnect said ends, said weld annulus having an axial extent within the axial confines of said ring to minimize weld joint width and consequent reduction of flow of transpiration cooling air through said two or more laminated layers on either side of said annulus of weld metal, said weld annulus serving as a heat conductor for transfer of heat to said ring and thence exteriorly of said combustor so as to prevent hot spots in said weld annulus.

Claim 8

A gas turbine engine cannular combustor assembly comprising: an outer axial wall and an inner axial wall forming a combustion chamber therebetween, said outer annular wall and said inner axial wall each having a plurality of axially directed panels, each of said panels including at least two or more laminated layers of porous material for directing fluid air flow from outside said liner to produce transpiration cooling of the inner surface of said segments in surrounding relationship to said combustion chamber, said panels each having axially spaced ends thereon, a combustor connector ring located in surrounding relationship to said ends on the outer surface of each of said panels, said ring including a locater tang thereon interposed between said ends in engagement therewith to maintain a controlled weld gap therebetween, a weld annulus of weld metal filling said weld gap to interconnect said ends, said weld annulus having an axial extent within the axial confines of said ring to minimize weld joint width and consequent reduction of flow of transpiration cooling air through said two or more laminated layers on either side of said annulus of weld metal, said weld annulus serving as a heat conductor for transfer of heat to said ring and thence exteriorly of said combustor so as to prevent hot spots in said weld annulus.