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An auxiliary power unit (APU) includes a rotary fuel slinger, and a single-spool, two-stage turbine. The rotary fuel slinger receives a rotational drive force from the turbine, and a supply of fuel from a fuel source. The rotary fuel slinger injects the fuel into a combustor as a continuous "fuel sh

An auxiliary power unit (APU) includes a rotary fuel slinger, and a single-spool, two-stage turbine. The rotary fuel slinger receives a rotational drive force from the turbine, and a supply of fuel from a fuel source. The rotary fuel slinger injects the fuel into a combustor as a continuous "fuel sheet." As a result, fuel mixing and atomization inside the combustor is improved, which reduces emissions and pattern factor, which in turn increases turbine life.

대표청구항 ▼

We claim: 1. An auxiliary power unit, comprising: a compressor having an air inlet and a compressed air outlet, and operable to supply a flow of compressed air; a radial-annular combustor including at least a forward radial liner and an aft radial liner spaced apart from one another to form a combu

We claim: 1. An auxiliary power unit, comprising: a compressor having an air inlet and a compressed air outlet, and operable to supply a flow of compressed air; a radial-annular combustor including at least a forward radial liner and an aft radial liner spaced apart from one another to form a combustion chamber therebetween, the forward and aft radial liners each including a plurality of openings in fluid communication with the compressed air outlet, to thereby receive at least a portion of the flow of compressed air therefrom, the plurality of openings configured to generate a single toroidal recirculation air flow pattern in the combustion chamber; a rotary fuel slinger including a coupler shaft, a vertical shoulder, and a slinger, the coupler shaft adapted to receive a rotational drive force, the vertical shoulder coupled to, and extending substatially perpendicular from, the coupler shaft, the slinger extending substantially perpendicular from the vertical shoulder and including a plurality of evenly spaced openings extending therethrough, the rotary fuel slinger further adapted to receive a flow of fuel from a fuel source and configured, upon receipt of the rotational drive force, to centrifuge the received fuel into the combustion chamber; a vertical shoulder coupled to, and extending substantially perpendicularly from, the coupler shaft; a slinger extending substantially perpendicularly from the vertical shoulder, the slinger including a plurality of evenly spaced openings extending therethrough; an igniter extending through the aft radial liner and at least partially into the combustion chamber, the igniter adapted to receive an ignition command and operable, in response thereto, to ignite the fuel and compressed air in the combustion chamber, to thereby generate combusted gas; a turbine coupled to receive the combusted gas from the combustion chamber and configured, in response thereto, to supply at least the rotational drive force to the rotary fuel slinger; and a turbine inlet nozzle disposed between the radial combustor and the turbine inlet, the turbine nozzle configured to change a flow direction of the combusted gas from a radial flow direction to an axial flow direction. 2. The auxiliary power unit of claim 1, further comprising: a fuel housing adapted to receive a flow of fuel and configured to supply the flow of fuel to the rotary fuel slinger. 3. The auxiliary power unit of claim 2, further comprising: a fuel tube having an inlet and an outlet, the fuel tube inlet adapted to receive a flow of fuel, the fuel tube outlet in fluid communication with the fuel housing to supply the flow of fuel thereto. 4. The auxiliary power unit of claim 1, wherein the turbine is a two-stage turbine. 5. The auxiliary power unit of claim 1, wherein the igniter extends through at least a portion of the turbine nozzle. 6. The auxiliary power unit of claim 1, wherein the turbine inlet nozzle includes a plurality of hollow vanes configured to fluidly communicate the aft radial liner with the compressed air outlet. 7. The auxiliary power unit of claim 6, wherein the igniter extends through one of the hollow vanes. 8. The auxiliary power unit of claim 1, wherein the slinger has a substantially cup-shaped radial cross section. 9. The auxiliary power unit of claim 1, wherein the fuel supplied to the rotary fuel slinger impinges on the vertical shoulder and is centrifuged into the slinger. 10. An auxiliary power unit, comprising: a compressor having an air inlet and a compressed air outlet, the compressor coupled to receive a rotational drive force and operable, in response thereto, to supply a flow of compressed air; a radial-annular combustor including at least a forward radial liner and an aft radial liner spaced apart from one another to form a combustion chamber therebetween, the forward and aft radial liners each including a plurality of openings in fluid communication with the compressed air outlet, to thereby receive at least a portion of the flow of compressed air therefrom, the plurality of openings configured to generate a single toroidal recirculation air flow pattern in the combustion chamber; a rotary fuel slinger adapted to receive a rotational drive force, the rotary fuel slinger further adapted to receive a flow of fuel from a fuel source and configured, upon receipt of the rotational drive force, to centrifuge the received fuel into the combustion chamber; an igniter extending through the aft radial liner and at least partially into the combustion chamber, the igniter adapted to receive an ignition command and operable, in response thereto, to ignite the fuel and compressed air in the combustion chamber, to thereby generate combusted gas; a turbine coupled to receive the combusted gas from the combustion chamber and configured, in response thereto, to supply the rotational drive force to at least the compressor and the rotary fuel slinger; and a turbine inlet nozzle disposed between the radial combustor and the turbine inlet, the turbine inlet nozzle configured to change a flow direction of the combusted gas from a radial flow direction to an axial flow direction, and including a plurality hollow vanes configured to fluidly communicate the aft radial liner with the compressed air outlet. 11. The auxiliary power unit of claim 10, further comprising: a fuel housing adapted to receive a flow of fuel and configured to supply the flow of fuel to the rotary fuel slinger. 12. The auxiliary power unit of claim 11, further comprising: a fuel tube having an inlet and an outlet, the fuel tube inlet adapted to receive a flow of fuel, the fuel tube outlet in fluid communication with the fuel housing to supply the flow of fuel thereto. 13. The auxiliary power unit of claim 10, wherein the igniter extends through at least a portion of the turbine nozzle. 14. The auxiliary power unit of claim 10, wherein the igniter extends through one of the hollow vanes. 15. The auxiliary power unit of claim 10, wherein the rotary fuel slinger comprises: a coupler shaft coupled to receive the rotational drive force from the turbine; a vertical shoulder coupled to, and extending substantially perpendicularly from, the coupler shaft; and a slinger extending substantially perpendicularly from the vertical shoulder, the slinger including a plurality of evenly spaced openings extending therethrough. 16. The auxiliary power unit of claim 15, wherein the slinger has a substantially cup-shaped radial cross section. 17. The auxiliary power unit of claim 15, wherein the fuel supplied to the rotary fuel slinger impinges on the vertical shoulder and is centrifuged into the slinger. 18. The auxiliary power unit of claim 10, wherein the turbine is a two-stage turbine. 19. An auxiliary power unit, comprising: a compressor having an air inlet and a compressed air outlet, the compressor coupled to receive a rotational drive force and operable, in response thereto, to supply a flow of compressed air; a radial-annular combustor including at least a forward radial liner and an aft radial liner spaced apart from one another to form a combustion chamber therebetween, the forward and aft radial liners each including a plurality of openings in fluid communication with the compressed air outlet, to thereby receive at least a portion of the flow of compressed air therefrom, the plurality of openings configured to generate a single toroidal recirculation air flow pattern in the combustion chamber; a fuel housing adapted to receive a flow of fuel from a fuel source; a rotary fuel slinger adapted to receive a rotational drive force, the rotary fuel slinger further adapted to receive a flow of fuel from the fuel housing and configured, upon receipt of the rotational drive force, to centrifuge the received fuel into the combustion chamber; an igniter extending through the aft radial liner and at least partially into the combustion chamber, the igniter adapted to receive an ignition command and operable, in response thereto, to ignite the fuel and compressed air in the combustion chamber, to thereby generate combusted gas; a single-spool, two-stage turbine coupled to receive the combusted gas from the combustion chamber and configured, in response thereto, to supply the rotational drive force to at least the compressor and the rotary fuel slinger; and a turbine inlet nozzle disposed between the radial combustor and the turbine inlet, the turbine nozzle configured to change a flow direction of the combusted gas from a radial flow direction to an axial flow direction, the turbine inlet nozzle including a plurality of hollow vanes configured to fluidly communicate the aft radial liner with the compressed air outlet, and wherein the igniter extends through one of the hollow vanes.