Gas turbine with forced vortex fuel injection

Claim 2

A small scale turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes, with at least two of said tubes being of substantially uniform cross section along the axial length thereof, the outermost tube having a diameter of not more than about one-half inch and being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex about the ends of said innermost and intermediate tubes to prevent stream separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube.

Claim 3

The small scale turbine of claim 1 wherein said forcing means comprise swirler blades between said intermediate and said outermost tubes.

Claim 4

A small scale turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes, the outermost tube having a diameter of not more than about one-half inch and being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex about the ends of said innermost and intermediate tubes to prevent stress separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube, wherein said forcing means comprise swirler blades between said intermediate and said outermost tubes, wherein said swirler blades are relatively straight at their radially inner edges and relatively curved at their radially outer edges.

Claim 5

A small scale turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes, the outermost tube having a diameter of not more than about one-half inch and being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex about the ends of said innermost and intermediate tubes to prevent stress separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube, wherein said forcing means comprise swirler blades between said intermediate and said outermost tubes, wherein said swirler blades are relatively straight at their radially inner edges and relatively curved at their radially outer edges.

Claim 6

A small scale turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes with at least two of said tubes being of substantially uniform cross-section along the axis lengths and at the outlet ends thereof, the outermost tube having a diameter of not more than about one-half inch and being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex near the ends off said innermost and intermediate tubes at a point where oxidant from said intermediate tube and fuel from said innermost tube meet and mix to prevent stream separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube.

Claim 7

A small scale turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes with at least two of said tubes being of substantially uniform cross-section along the axis lengths and at the outlet ends thereof, the outermost tube having a diameter of not more than about one-half inch and being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex near the ends off said innermost and intermediate tubes at a point where oxidant from said intermediate tube and fuel from said innermost tube meet and mix to prevent stream separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube.

Claim 8

The small scale turbine of claim 1 wherein said forcing means comprise swirler blades between said intermediate and said outermost tubes.

Claim 9

A small scale turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes, the outermost tube having a diameter of not more than about one-half inch and being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex near the ends off said innermost and intermediate tubes at a point where oxidant from said intermediate tube and fuel from said innermost tube meet and mix to prevent stream separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube. wherein said forcing means comprise swirler blades between said intermediate and said outermost tubes, wherein said swirler blades extend relatively axially at their radially inner edges and relatively nonaxially at their radially outer edges.

Claim 10

A small scale turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes, the outermost tube having a diameter of not more than about one-half inch and being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex near the ends off said innermost and intermediate tubes at a point where oxidant from said intermediate tube and fuel from said innermost tube meet and mix to prevent stream separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube. wherein said forcing means comprise swirler blades between said intermediate and said outermost tubes, wherein said swirler blades extend relatively axially at their radially inner edges and relatively nonaxially at their radially outer edges.

Claim 11

A turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes, the outermost tube being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex about the ends of said innermost and intermediate tubes to prevent stream separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube, said forcing means comprising swirler blades between said intermediate and said outermost tubes and being relatively axially at their radially inner edges and relatively curved at their radially outer edges.

Claim 12

A turbine comprising: a rotary compressor; a turbine wheel coupled to said compressor; a nozzle for directing combustion gas at said turbine wheel; a combustor wherein fuel may be combusted and directed to said nozzle; and at least one injector for said combustor and including three substantially concentric tubes, the outermost tube being connected to said compressor to receive compressed air therefrom, the innermost tube having a diameter no more than half the diameter of said outermost tube and being connected to a source of fuel, and the intermediate tube being connected to a source of concentrated oxidant for the fuel; and means for forcing compressed air into a vortex about the ends of said innermost and intermediate tubes to prevent stream separation and resulting eddies or backflows of burning fuel in damaging close proximity to the end of at least said innermost tube, said forcing means comprising swirler blades between said intermediate and said outermost tubes and being relatively axially at their radially inner edges and relatively curved at their radially outer edges.