Low emissions combustor

Claim 2

A combustor for a gas turbine engine comprising: a first liner having an upstream end and a downstream end; a second liner having an upstream end and a downstream end and spaced from said first liner to define a combustor primary zone adjacent to said upstream end, a dilution zone adjacent to said downstream end, and an annular center region disposed between said first and second liners; an annular dome jointed to said first and second liner upstream ends and including a plurality of circumferentially spaced apertures; a plurality of carburetors disposed in respective ones of said dome apertures for providing a fuel/air mixture into said primary zone, each of said carburetors including: a swirler disposed in a respective one of said dome apertures for swirling and channeling air; and a fuel injector disposed in said swirler for channeling fuel into said swirler for mixing with said swirler air for providing said fuel/air mixture into said primary zone; said first and second liners having inner surfaces facing each other to define said primary zone, said inner surfaces being characterized by the absence of film cooling; and means for distributing fuel for obtaining a fuel distribution from each of said carburetors extending radially from said first liner upstream end through said center region to said second liner upstream end and having values of said fuel distribution at said center region generally no greater than about values of said fuel distribution adjacent to at least one of said first and second liners.

Claim 3

A combustor according to claim 1 wherein said first and second liners each include an upstream portion defining said primary zone and a downstream portion defining said dilution zone, and said upstream liner portions are imperforate.

Claim 4

A combustor according to claim 2 wherein said inner surfaces of said upstream liner portions include a thermal barrier coating.

Claim 5

A combustor according to claim 2 wherein said first and second liner upstream portions include outer surfaces facing away from said inner surfaces, and further including means for impingement cooling said outer surfaces of said first and second liner upstream portions.

Claim 6

A combustor according to claim 1 wherein said fuel distribution means comprises said fuel injector including: a spin chamber for providing fuel into said swirler; and a spin chamber for providing fuel into said swirler; and an annular shroud spaced from said spin chamber to define a shroud chamber having an outlet, and including a plurality of circumferentially spaced inlets extending through said shroud for channeling air into said shroud chamber, said inlets and said outlet being sized for reducing an axial component of velocity of said air channeled through said shroud chamber outlet for increasing radially outward dispersion of said fuel discharged from said injector into said swirler.

Claim 7

A combustor according to claim 5 wherein said swirler is a counter-rotational swirler.

Claim 8

A combustor according to claim 5 wherein said shroud inlets are sized for throttling said air channeled therethrough and said air channeled through said shroud chamber is metered by said shroud inlets only.

Claim 9

A combustor according to claim 5 wherein said fuel injector has an axial centerline axis, and each of said shroud inlets is inclined relative to a radial axis extending from said injector centerline axis for spinning said air channeled through said shroud chamber for reducing said air axial component of velocity.

Claim 10

A combustor according to claim 8 wherein said shroud inlets are inclined at about 20°-30° from said radial axis.

Claim 11

A combustor according to claim 9 wherein each of said shroud inlets has an oblong cross section with a maximum dimension disposed parallel to said injector centerline axis.

Claim 12

A combustor according to claim 1 wherein said fuel distributing means comprises: said swirler including: a tubular ferrule; a primary venturi; a plurality of circumferentially spaced swirler primary vanes extending between said ferrule and said primary venturi; a secondary venturi; a plurality of circumferentially spaced swirler secondary vanes extending between said primary and secondary venturis; and said secondary venturi being spaced radially outwardly of said primary venturi; said fuel injector including a spin chamber, and a cone extending therefrom for providing fuel into said swirler, and an imperforate annular shroud, having no air inlets, disposed around said spin chamber and positioned slideably in said swirler ferrule so that no air flows through said shroud and substantially no air is channeled between said shroud and said ferrule; and said injector and said swirler being sized and configured for dispersing fuel form said injector cone toward said primary venturi, and said primary and secondary venturis being effective for swirling said fuel with said air form said primary and secondary vanes for dispersing said fuel radially outwardly.

Claim 13

A combustor according to claim 11 wherein said primary and secondary vanes extend radially for channeling and swirling said air radially inwardly.

Claim 14

A combustor according to claim 12 wherein said primary vanes are configured for swirling said air in an opposite direction to said air swirled by said secondary vanes.

Claim 15

A combustor according to claim 12 wherein said fuel injector has an axial centerline axis and said primary and secondary venturis are disposed generally parallel to said injector centerline axis.

Claim 16

A combustor according to claim 12 wherein said injector and swirler are sized and configured for obtaining a generally uniform fuel distribution.

Claim 17

A combustor according to claim 12 wherein said first and second liners each include an upstream portion defining said primary zone and a downstream portion defining said dilution zone and said upstream liner portions are imperforate.

Claim 18

A combustor according to claim 16 wherein said first and second liner upstream portions include outer surfaces facing away from said inner surfaces, and further including means for impingement cooling said outer surfaces of said first and second liner upstream portions, and said inner surfaces of said upstream portions include a thermal barrier coating.

Claim 19

A combustor for a gas turbine engine comprising: a first liner having an upstream end and a downstream end; a second liner having an upstream end and a downstream end and spaced from said first liner to define a combustion primary zone adjacent to said upstream end, a dilution zone adjacent to said downstream end, and an annular center region disposed between said first and second liners; an annular dome joined to said first and second liner upstream ends and including a plurality of circumferentially spaced apertures; a plurality of carburetors disposed in respective ones of said dome apertures for providing an fuel/air mixture into said primary zone, each of said carburetors including: a swirler disposed in a respective one of said dome apertures for swirling and channeling air; and a fuel injector disposed in said swirler for channeling fuel into said swirler for mixing with said swirler air for providing said fuel/air mixture into said primary zone; said first and second liners having inner surfaces facing each other to define said primary zone, said inner surfaces being characterized by the absence of film cooling; and means for distributing fuel for obtaining a fuel distribution from each of said carburetors extending radially from said first liner upstream end through said center region to said second liner upstream end and having values of said fuel distribution at said center region generally no greater than about values of said fuel distribution adjacent to at least one of said first and second liners, said fuel distribution means comprising said fuel injector including: a spin chamber for providing fuel into said swirler; and an annular shroud spaced from said spin chamber to define a shroud chamber having an outlet, and including a plurality of circumferentially spaced inlets extending through said shroud for channeling air into said shroud chamber, said inlets and said outlet being sized for reducing an axial component of velocity of said air channeled through said shroud chamber outlet for increasing radially outward dispersion of said fuel discharged form said injector into said swirler.

Claim 20

A combustor for a gas turbine engine comprising: a first liner having an upstream end and a downstream end; a second liner having an upstream end and a downstream end and spaced from said first liner to define a combustion primary zone adjacent to said upstream end, a dilution zone adjacent to said downstream end, and an annular center region disposed between said first and second liners; an annular dome joined to said first and second liner upstream ends and including a plurality of circumferentially spaced apertures; a plurality of carburetors disposed in respective ones of said dome apertures for providing an fuel/air mixture into said primary zone, each of said carburetors including: a swirler disposed in a respective one of said dome apertures for swirling and channeling air; and a fuel injector disposed in said swirler for channeling fuel into said swirler for mixing with said swirler air for providing said fuel/air mixture into said primary zone; said first and second liners having inner surfaces facing each other to define said primary zone, said inner surfaces being characterized by the absence of film cooling; and means for distributing fuel for obtaining a fuel distribution from each of said carburetors extending radially from said first liner upstream end through said center region to said second liner upstream end and having values of said fuel distribution at said center region generally no greater than about values of said fuel distribution adjacent to at least one of said first and second liners, said fuel distribution means comprising said fuel injector including: a spin chamber for providing fuel into said swirler; and an annular shroud spaced from said spin chamber to define a shroud chamber having an outlet, and including a plurality of circumferentially spaced inlets extending through said shroud for channeling air into said shroud chamber, said inlets and said outlet being sized for reducing an axial component of velocity of said air channeled through said shroud chamber outlet for increasing radially outward dispersion of said fuel discharged form said injector into said swirler.

Claim 21

A combustor according to claim 18 wherein said shroud inlets are sized for throttling said air channeled therethrough; said air channeled through said shroud chamber is metered by said shroud inlets only; and wherein said shroud inlets are disposed in a radial direction.

Claim 22

A combustor for a gas turbine engine comprising: a first liner having an upstream end and a downstream end; a second liner having an upstream end and a downstream end and spaced from said first liner to define a combustion primary zone adjacent to said upstream end, a dilution zone adjacent to said downstream end, and an annular center region disposed between said first and second liners; an annular dome joined to said first and second liner upstream ends and including a plurality of circumferentially spaced apertures; a plurality of carburetors disposed in respective ones of said dome apertures for providing an fuel/air mixture into said primary zone, each of said carburetors including: a swirler disposed in a respective one of said dome apertures for swirling and channeling air; and a fuel injector disposed in said swirler for channeling fuel into said swirler for mixing with said swirler air for providing said fuel/air mixture into said primary; said first and second liners having inner surfaces facing each other to define said primary zone, said inner surfaces being characterized by the absence of film cooling; and means for distributing fuel for obtaining a fuel distribution from each of said carburetors extending radially from said first liner upstream end through said center region to said second liner upstream end and having values of said fuel distribution at said center region generally no greater than about values of said fuel distribution adjacent to at least one of said first and second liners, said fuel distribution means comprising said fuel injector including: a spin chamber for providing fuel into said swirler; and an annular shroud spaced from said spin chamber to define a shroud chamber having an outlet, and including a plurality of circumferentially spaced inlets extending through said shroud for channeling air into said shroud chamber; said fuel injector having an axial centerline axis, and each of said shroud inlets inclined relative to a radial axis extending from said injector centerline axis for spinning said air channeled through said shroud chamber; said inlets and said outlet being sized for reducing an axial component of velocity of said air channeled through said shroud chamber outlet for increasing radially outward dispersion of said fuel discharged from said injector into said swirler.

Claim 23

A combustor for a gas turbine engine comprising: a first liner having an upstream end and a downstream end; a second liner having an upstream end and a downstream end and spaced from said first liner to define a combustion primary zone adjacent to said upstream end, a dilution zone adjacent to said downstream end, and an annular center region disposed between said first and second liners; an annular dome joined to said first and second liner upstream ends and including a plurality of circumferentially spaced apertures; a plurality of carburetors disposed in respective ones of said dome apertures for providing an fuel/air mixture into said primary zone, each of said carburetors including: a swirler disposed in a respective one of said dome apertures for swirling and channeling air; and a fuel injector disposed in said swirler for channeling fuel into said swirler for mixing with said swirler air for providing said fuel/air mixture into said primary; said first and second liners having inner surfaces facing each other to define said primary zone, said inner surfaces being characterized by the absence of film cooling; and means for distributing fuel for obtaining a fuel distribution from each of said carburetors extending radially from said first liner upstream end through said center region to said second liner upstream end and having values of said fuel distribution at said center region generally no greater than about values of said fuel distribution adjacent to at least one of said first and second liners, said fuel distribution means comprising said fuel injector including: a spin chamber for providing fuel into said swirler; and an annular shroud spaced from said spin chamber to define a shroud chamber having an outlet, and including a plurality of circumferentially spaced inlets extending through said shroud for channeling air into said shroud chamber; said fuel injector having an axial centerline axis, and each of said shroud inlets inclined relative to a radial axis extending from said injector centerline axis for spinning said air channeled through said shroud chamber; said inlets and said outlet being sized for reducing an axial component of velocity of said air channeled through said shroud chamber outlet for increasing radially outward dispersion of said fuel discharged from said injector into said swirler.

Claim 24

A combustor according to claim 20 wherein said shroud inlets are inclined at about 20°-30° from said radial axis.

Claim 25

A combustor according to claim 21 wherein each of said shroud inlets has an oblong cross section with a maximum dimension disposed parallel to said injector centerline axis.

Claim 26

A combustor for a gas turbine engine comprising: a first liner having an upstream end and a downstream end; a second liner having an upstream end and a downstream end and spaced from said first liner to define a combustion primary zone adjacent to said upstream end, a dilution zone adjacent to said downstream end, and an annular center region disposed between said first and second liners; an annular dome joined to said first and second liner upstream ends and including a plurality of circumferentially spaced apertures; a plurality of carburetors disposed in respective ones of said dome apertures for providing an fuel/air mixture into said primary zone, each of said carburetors including: a swirler disposed in a respective one of said dome apertures for swirling and channeling air; and a fuel injector disposed in said swirler for channeling fuel into said swirler for mixing with said swirler air for providing said fuel/air mixture into said primary zone; said first and second liners having inner surfaces facing each other to define said primary zone, said inner surfaces being characterized by the absence of film cooling; and means for distributing fuel for obtaining a fuel distribution from each of said carburetors extending radially from said first liner upstream end through said center region to said second liner upstream end and having values of said fuel distribution at said center region generally no greater than about values of said fuel distribution adjacent to at least one of said first and second liners, said fuel distribution means comprises: said swirler including: a tubular ferrule; a primary venturi; a plurality of circumferentially spaced swirler primary vanes extending between said ferrule and said primary venturi; a secondary venturi; a plurality of circumferentially spaced swirler secondary vanes extending between said primary and secondary venturis; and said secondary venturi being spaced radially outwardly of said primary venturi; said fuel injector including a spin chamber, and a cone extending therefrom for providing fuel into said swirler, and an imperforate annular shroud, having no air inlets, disposed around said spin chamber and positioned slideably in said swirler ferrule so that no air flows through said shroud and substantially no air is channeled between said shroud and said ferrule; and said injector and said swirler being sized and configured for dispersing fuel form said injector cone toward said primary venturi, and said primary and secondary venturis being effective for swirling said fuel with said air from said primary and secondary vanes for dispersing said fuel radially outwardly.

Claim 27

A combustor for a gas turbine engine comprising: a first liner having an upstream end and a downstream end; a second liner having an upstream end and a downstream end and spaced from said first liner to define a combustion primary zone adjacent to said upstream end, a dilution zone adjacent to said downstream end, and an annular center region disposed between said first and second liners; an annular dome joined to said first and second liner upstream ends and including a plurality of circumferentially spaced apertures; a plurality of carburetors disposed in respective ones of said dome apertures for providing an fuel/air mixture into said primary zone, each of said carburetors including: a swirler disposed in a respective one of said dome apertures for swirling and channeling air; and a fuel injector disposed in said swirler for channeling fuel into said swirler for mixing with said swirler air for providing said fuel/air mixture into said primary zone; said first and second liners having inner surfaces facing each other to define said primary zone, said inner surfaces being characterized by the absence of film cooling; and means for distributing fuel for obtaining a fuel distribution from each of said carburetors extending radially from said first liner upstream end through said center region to said second liner upstream end and having values of said fuel distribution at said center region generally no greater than about values of said fuel distribution adjacent to at least one of said first and second liners, said fuel distribution means comprises: said swirler including: a tubular ferrule; a primary venturi; a plurality of circumferentially spaced swirler primary vanes extending between said ferrule and said primary venturi; a secondary venturi; a plurality of circumferentially spaced swirler secondary vanes extending between said primary and secondary venturis; and said secondary venturi being spaced radially outwardly of said primary venturi; said fuel injector including a spin chamber, and a cone extending therefrom for providing fuel into said swirler, and an imperforate annular shroud, having no air inlets, disposed around said spin chamber and positioned slideably in said swirler ferrule so that no air flows through said shroud and substantially no air is channeled between said shroud and said ferrule; and said injector and said swirler being sized and configured for dispersing fuel form said injector cone toward said primary venturi, and said primary and secondary venturis being effective for swirling said fuel with said air from said primary and secondary vanes for dispersing said fuel radially outwardly.

Claim 28

A combustor according to claim 23 wherein said primary and secondary vanes extend radially for channeling and swirling said air radially inwardly, said primary vanes are configured for swirling said air in an opposite direction to said air swirled by said secondary vanes, and said fuel injector has an axial centerline axis, and said primary and secondary venturis are disposed generally parallel to said injector centerline axis.

Claim 29

A combustor according to claim 24 wherein said injector and swirler are sized and configured for obtaining a generally uniform fuel distribution.