Pilot flame tube

Claim 2

In an automotive gas turbine engine having fuel flow to a prechamber liner of a combustor for a prevaporization upstream of a combustor wall surrounded by a compressed air source and with the wall defining a primary combustion zone the improvement comprising: a continuously operated pilot flame tube assembly supported on the combustor wall to maintain a continuous ignition flame within the primary combustion zone during engine deceleration, said assembly including a dome located exteriorly of the wall and having an interior bulkhead defining an upstream air space therebetween in communication with said air chamber, a pilot air swirler on said bulkhead including a pilot nozzle for continuously directing fuel and air downstream of said bulkhead for ignition as a continuously burning pilot flame located within said combustor wall for continuously igniting air fuel mixtures within said primary combustion zone, a double-walled open end flame tube surrounding said pilot ignition flame, said flame tube located within said combustor wall and having an outer tubular member of porous material with holes therein and an inner tubular member of porous material with holes therein, said inner tubular member being telescoped within and located in spaced relationship to said outer tubular member to form an air passage therebetween upstream of holes in both said tubular members, said inner and outer tubular members having one end thereof sealed together at the open end of said flame tube to prevent air flow axially therefrom into said primary combustion zone, cooling air entrance means to direct compressed air from said air source to the surfaces of said inner and outer tubular members which define said air passage therebetween, said inner tubular member holes receiving air from said air passage for redistributing air as a sheath radially inwardly of said inner tubular member to continuously shield it from said pilot flame, said outer tubular member holes receiving air from said air passage for redistributing air as a sheath radially outwardly through said outer tubular member to shield it against a flame within said combustor primary combustion zone thereby to maintain a continuous pilot flame within said primary combustion zone to prevent flameout therein during engine decelerations wherein air and fuel flows are reduced to the primary combustion zone.

Claim 3

In an automotive gas turbine engine having fuel flow to a prechamber liner of a combustor for a prevaporization upstream of a combustor wall surrounded by a compressed air source and with the wall defining a primary combustion zone, the improvement comprising: a continuously operated pilot flame tube assembly supported on the combustor wall to maintain a continuous ignition flame within the primary combustion zone during engine deceleration, said assembly including a dome located exteriorly of the wall and having an interior bulkhead defining an upstream air space therebetween in communication with said air chamber, a pilot air swirler on said bulkhead including a pilot nozzle for continuously directing air and fuel downstream of said bulkhead for ignition as a continuously burning pilot flame located within said combustor wall for continuously igniting air fuel mixtures within said primary combustion zone, a double-walled open end flame tube surrounding said pilot ignition flame, said flame tube located with said combustor wall and having an outer tubular member of porous material with holes therein and an inner tubular member of porous material with holes therein, said inner tubular member being telescoped within and located in spaced relationship to said outer tubular member to form an air passage therebetween upstream of holes in both said tubular members, said porous material including at least two joined metal sheets, each of said joined metal sheets having performations therein to define a coolant passage between opposite sides of the joined metal sheets, said inner and outer tubular members having one end thereof sealed together at the open end of said flame tube to prevent air flow axially therefrom into said primary combustion zone, cooling air entrance means to direct compressed air from said air source to the surfaces of said inner and outer tubular members which define said air passage therebetween, said inner tubular member holes receiving air from said air passage for redistributing air as a sheath radially inwardly of said inner tubular member to continuously shield it from said pilot flame, said outer tubular member redistributing cooling air as a sheath radially outwardly through said outer tubular member to shield it against a flame within said combustor primary combustion zone thereby to maintain a continuous pilot flame within said primary combustion zone to prevent flameout therein during engine decelerations wherein air and fuel flows are reduced to the primary combustion zone.

Claim 4

In an automotive gas turbine engine having fuel flow to a prechamber liner of a combustor for a prevaporization upstream of a combustor wall surrounded by a compressed air source and with the wall defining a primary combustion zone, the improvement comprising: a continuously operated pilot flame tube assembly supported on the combustor wall to maintain a continuous ignition flame within the primary combustion zone during engine deceleration, said assembly including a dome located exteriorly of the wall and having an interior bulkhead defining an upstream air space therebetween in communication with said air chamber, a pilot air swirler on said bulkhead including a pilot nozzle for continuously directing air and fuel downstream of said bulkhead for ignition as a continuously burning pilot flame located within said combustor wall for continuously igniting air fuel mixtures within said primary combustion zone, a double-walled open end flame tube surrounding said pilot ignition flame, said flame tube located with said combustor wall and having an outer tubular member of porous material with holes therein and an inner tubular member of porous material with holes therein, said inner tubular member being telescoped within and located in spaced relationship to said outer tubular member to form an air passage therebetween upstream of holes in both said tubular members, said porous material including at least two joined metal sheets, each of said joined metal sheets having performations therein to define a coolant passage between opposite sides of the joined metal sheets, said inner and outer tubular members having one end thereof sealed together at the open end of said flame tube to prevent air flow axially therefrom into said primary combustion zone, cooling air entrance means to direct compressed air from said air source to the surfaces of said inner and outer tubular members which define said air passage therebetween, said inner tubular member holes receiving air from said air passage for redistributing air as a sheath radially inwardly of said inner tubular member to continuously shield it from said pilot flame, said outer tubular member redistributing cooling air as a sheath radially outwardly through said outer tubular member to shield it against a flame within said combustor primary combustion zone thereby to maintain a continuous pilot flame within said primary combustion zone to prevent flameout therein during engine decelerations wherein air and fuel flows are reduced to the primary combustion zone.

Claim 5

A flame tube assembly for continuously igniting a combustor with a wall surrounded by a compressed air source, said assembly comprising an imperforate dome and an interior bulkhead defining an upstream pressurizable space therebetween, means for directing compressed air from the source into said space, a pilot air swirler on said bulkhead including a pilot nozzle for continuously directing air/fuel downstream of said bulkhead for forming a continuous pilot flame for ignition as a continuously burning pilot flame located within said combustor wall for continuously igniting air fuel mixtures within said primary combustion zone, an outer tubular member of porous material with holes and an inner tubular member of porous material with holes, said inner tubular member telescoped within and located in spaced relationship to said outer tubular member to form an air passage therebetween, said inner tubular member surrounding the continuous pilot flame, said inner and outer tubular members having one end thereof sealed together to prevent air flow axially therefrom, cooling air entrance means for directing compressed air from said air source to the surfaces of said inner and outer tubular members which define said air passage therebetween, said inner tubular member holes receiving air from said air passage for redistributing air as a sheath for distribution radially inwardly of said inner tubular member to continuously shield it from the pilot flame therein, said outer tubular member redistributing cooling air as a sheath radially outwardly through said outer tubular member holes to shield the outer tubular member from a flame within said combustor thereby to maintain a continuous pilot flame within the combustor to prevent flameout therein during periods of reduced air and fuel flow to the combustor.

Claim 6

A flame tube assembly for continuously igniting a combustor with a wall surrounded by a compressed air source, said assembly comprising an imperforate dome and an interior bulkhead defining an upstream pressurizable space therebetween, means for directing compressed air from the source into said space, a pilot air swirler on said bulkhead including a pilot nozzle for continuously directing air/fuel downstream of said bulkhead for forming a continuous pilot flame for ignition as a continuously burning pilot flame located within said combustor wall for continuously igniting air fuel mixtures within said primary combustion zone, an outer tubular member of porous material with holes and an inner tubular member of porous material with holes, said inner tubular member telescoped within and located in spaced relationship to said outer tubular member to form an air passage therebetween, said inner tubular member surrounding the continuous pilot flame, said inner and outer tubular members having one end thereof sealed together to prevent air flow axially therefrom, cooling air entrance means for directing compressed air from said air source to the surfaces of said inner and outer tubular members which define said air passage therebetween, said inner tubular member holes receiving air from said air passage for redistributing air as a sheath for distribution radially inwardly of said inner tubular member to continuously shield it from the pilot flame therein, said outer tubular member redistributing cooling air as a sheath radially outwardly through said outer tubular member holes to shield the outer tubular member from a flame within said combustor thereby to maintain a continuous pilot flame within the combustor to prevent flameout therein during periods of reduced air and fuel flow to the combustor.

Claim 7

A flame tube assembly for continuously igniting a combustor with a wall surrounded by a compressed air source comprising an imperforate dome and an interior bulkhead defining an upstream pressurizable air space therebetween, means for directing compressed air from the source into said space, a pilot air swirler on said bulkhead including a pilot nozzle for continuously directing air/fuel downstream of said bulkhead for forming a continuous pilot flame for ignition as a continuously burning pilot flame located within said combustor wall for continuously igniting air fuel mixtures within said primary combustion zone, an outer tubular member of porous material with holes and an inner tubular member of porous material with holes, said inner tubular member telescoped within and located in spaced relationship to said outer tubular member to form an air passage therebetween, said inner tubular member surrounding the continuous pilot flame, said porous material including at least two joined metal sheets, each having holes therein to define a coolant passage between opposite sides of the joined sheets, said inner and outer tubular members each having one end thereof sealed together to prevent air flow axially therefrom, cooling air entrance means for directing compressed air from said air source to the surfaces of said inner and outer tubular members which define said air passage therebetween, said inner tubular member holes receiving air from said air passage for redistributing air as a sheath for distribution radially inwardly of said inner tubular member to continuously shield it from the pilot flame therein, said outer tubular member redistributing cooling air as a sheath radially outwardly through said outer tubular member holes to shield the outer tubular member against a flame within said combustor thereby to maintain a continuous pilot flame within the combustor to prevent flameout therein during periods of reduced air and fuel flow to the combustor.

Claim 8

A flame tube assembly for continuously igniting a combustor with a wall surrounded by a compressed air source comprising an imperforate dome and an interior bulkhead defining an upstream pressurizable air space therebetween, means for directing compressed air from the source into said space, a pilot air swirler on said bulkhead including a pilot nozzle for continuously directing air/fuel downstream of said bulkhead for forming a continuous pilot flame for ignition as a continuously burning pilot flame located within said combustor wall for continuously igniting air fuel mixtures within said primary combustion zone, an outer tubular member of porous material with holes and an inner tubular member of porous material with holes, said inner tubular member telescoped within and located in spaced relationship to said outer tubular member to form an air passage therebetween, said inner tubular member surrounding the continuous pilot flame, said porous material including at least two joined metal sheets, each having holes therein to define a coolant passage between opposite sides of the joined sheets, said inner and outer tubular members each having one end thereof sealed together to prevent air flow axially therefrom, cooling air entrance means for directing compressed air from said air source to the surfaces of said inner and outer tubular members which define said air passage therebetween, said inner tubular member holes receiving air from said air passage for redistributing air as a sheath for distribution radially inwardly of said inner tubular member to continuously shield it from the pilot flame therein, said outer tubular member redistributing cooling air as a sheath radially outwardly through said outer tubular member holes to shield the outer tubular member against a flame within said combustor thereby to maintain a continuous pilot flame within the combustor to prevent flameout therein during periods of reduced air and fuel flow to the combustor.