Combustor liner joints

In a combustor for a gas turbine engine including a compressor discharging into a combustor diffuser directing discharge flow from the compressor for uniform distribution to a dome plenum the improvement comprising:

• an annular porous liner wall segment, said liner wall segment defining a combustion zone downstream of said dome, said porous liner wall segment directing compressed air radially inwardly of the combustor at a point downstream of the dome plenum to cool the inner surfaces thereof by transpiration cooling, said wall segment having an inlet end thereon and an outlet end thereon, a solid metal joint ring welded to said inlet end to define a sealed joint, said solid metal joint ring including a plurality of small diameter effusion holes sized to direct cooling air from the plenum through said solid metal joint ring at a rate to cool the mass of said ring without producing a tangential wall stream on the inner surface of said porous liner wall segment thereby to direct heat from the sealed joint and said porous liner wall segment to maintain structural integrity therebetween without excessive diversion of total engine air flow from the plenum, said solid metal ring having offset ends thereon, one of said offset ends being welded to said wall segment, another porous liner wall segment joined to the other offset end, said solid metal ring having a convexly curved inner surface flush with the inner surfaces of said wall segment and the inner surfaces of said outer wall segment and wherein said effusion holes are directed through said solid metal ring to intersect said convexly curved surface for dispersion therefrom into the combustion zone without formation of a two dimensional tangential wall film on the inner surface of said other porous liner wall segment.

In a combustor for a gas turbine engine including a compressor discharging into a combustor diffuser directing discharge flow from the compressor for uniform distribution to a dome plenum the improvement comprising:

• an annular porous liner wall segment, said liner wall segment defining a combustion zone downstream of said dome, said porous liner wall segment directing compressed air radially inwardly of the combustor at a point downstream of the dome plenum to cool the inner surfaces thereof by transpiration cooling, said wall segment having an inlet end thereon and an outlet end thereon, a solid metal joint ring welded to said inlet end to define a sealed joint, said solid metal joint ring including a plurality of small diameter effusion holes sized to direct cooling air from the plenum through said solid metal joint ring at a rate to cool the mass of said ring without producing a tangential wall stream on the inner surface of said porous liner wall segment thereby to direct heat from the sealed joint and said porous liner wall segment to maintain structural integrity therebetween without excessive diversion of total engine air flow from the plenum, said solid metal ring having offset ends thereon, one of said offset ends being welded to said wall segment, another porous liner wall segment joined to the other offset end, said solid metal ring having a convexly curved inner surface flush with the inner surfaces of said wall segment and the inner surfaces of said outer wall segment and wherein said effusion holes are directed through said solid metal ring to intersect said convexly curved surface for dispersion therefrom into the combustion zone without formation of a two dimensional tangential wall film on the inner surface of said other porous liner wall segment, said annular porous liner wall segment forming a transition duct from the combustor, a support ring for said duct including a conically configured, axially extending beam member welded to said outlet end of said porous liner wall segment and having a resilient deflection to accommodate thermal expansion of said duct with respect to said support ring, an upstream surface on said beam member in communication with compressor discharge air, and effusion holes in said beam member at its weld connection to said outlet end, said holes sized to produce a coolant flow across said weld connection for cooling it without excessive diversion of total engine airflow.

A combustor for a gas turbine engine including a compressor discharging into an annular combustor diffuser with a flow director therein including an annular snout dividing discharge flow from the compressor for uniform distribution to an outer annular combustor plenum, a domed chamber and an inner annular combustor plenum comprising:

• a porous laminated annular dome, first inner and an outer annular porous wall segments, said inner and outer segments and dome defining a combustion zone downstream of said laminated dome and also directing compressed air from the annular inner and outer diffuser plenums radially inwardly of the combustor at a point immediately downstream of the laminated annular dome member to cool the inner surfaces thereof by transpiration cooling, each of said inner and outer wall segments having an inlet end thereon and an outlet end thereon, a solid metal joint ring welded to each of said inlet ends and to said laminated dome to define a sealed joint between said porous laminated dome and said inner and outer wall segments, each of said solid metal joint rings including a plurality of small diameter effusion holes sized to direct cooling air from the domed chamber through each of said solid metal joint rings at a rate to cool the ring mass without producing a tangential wall stream on the inner surface of the first wall segment thereby to direct heat from the connection between said joint ring and adjacent laminated segments of said dome and said inner and outer wall segments to maintain structural integrity therebetween, a second solid metal joint ring connected by welds to each of said first inner and outer segments at the downstream end thereof, each of said second solid metal joint rings including a rebent end thereon to define a scoop for directing compressor discharge air to a selected area of the outer surface of each of said first and second annular porous wall segments for flow into the combustion zone, a second outer annular porous wall segment and a second inner annular porous wall segment on said combustor each weld connected to one of said second solid metal joint rings, said second solid joint ring having a plurality of effusion cooling holes therein for directing coolant from the scoop through the second solid metal ring at a flow rate to cool it and adjacent weld connections to said second inner and outer wall segments without excessive diversion of engine airflow or formation of a tangential wall stream of the inner surface of the second inner and outer wall segments and thereby to maintain a high strength structural connection at the weld without excessive diversion of total engine airflow for tangential airflow across the last mentioned inner surfaces.

A combustor for a gas turbine engine including an axial flow compressor discharging into an annular combustor diffuser with a flow director therein including an annular snout dividing discharge flow from the axial compressor for uniform distribution to an outer annular combustor plenum and a domed chamber comprising:

• a porous laminated dome, an annular porous liner wall segment, said liner wall segment and dome defining a combustion zone downstream of said laminated dome and also directing compressed air from the outer diffuser plenum radially inwardly of the combustor at a point immediately downstream of the laminated annular dome member, said dome having an opening therethrough, a support ring having a thin walled tubular extension with an end welded to said dome at the hole therein, a flange on said support ring spaced upstream of the outer surface of said dome to form an annular opening to supply air from said domed chamber for directing coolant air flow axially through said dome completely around the outer surface of said extension, a nozzle support ferrule axially slidably supported within said thin walled extension, said ferrule including a radially outwardly directed flange thereon, a fuel supply nozzle supported within said ferrule for directing fuel into said combustion zone, and means for supporting said ferrule flange for free radial movement with respect to said support ring without blockage of said annular opening whereby coolant airflow is maintained through said dome through all the fuel surface extent thereof while said dome is free to both axially and radially expand with respect to said nozzle during combustor operation.