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Apparatus for reducing air mass flow through the compressor in a single shaft gas turbine engine having an extended operating range including part load conditions, to provide low emissions combustion. The apparatus includes one or more nozzles positioned for injecting compressed air into the inlet r

Apparatus for reducing air mass flow through the compressor in a single shaft gas turbine engine having an extended operating range including part load conditions, to provide low emissions combustion. The apparatus includes one or more nozzles positioned for injecting compressed air into the inlet region of the compressor. The nozzles are oriented to direct the compressed air tangentially to, and in the same angular direction as, the direction of rotation to create a swirl in the inlet air flow to the compressor inducer. The apparatus also includes conduits in flow communication between the compressor diffuser and the nozzles, one or more valves operatively connected to control the flow of compressed air from the diffuser to the nozzles, and a controller operatively connected to the valves to cause compressed air flow to the nozzles during operation at part load conditions.

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1. Method for reducing air mass flow in a single shaft gas turbine engine, over an extended operating range including part load conditions, the gas turbine engine having a rotating air compressor with an axis of rotation, an inlet region and an outlet region, the method comprising: creating swirl in

1. Method for reducing air mass flow in a single shaft gas turbine engine, over an extended operating range including part load conditions, the gas turbine engine having a rotating air compressor with an axis of rotation, an inlet region and an outlet region, the method comprising: creating swirl in inlet air mass flow by controllably injecting compressed air into the compressor inlet region generally tangential to said axis of rotation, and in the same angular direction as, the direction of rotation of the compressor during operation at part load conditions. 2. The method as in claim 1 further including extracting the compressed air to be injected from the compressor outlet region. 3. The method as in claim 1 wherein the compressed air is injected during engine operation between about 90% and about 70% of full load. 4. The method as in claim 1 wherein the flow rate of the injected compressed air is controlled by at least one valve acting in response to a turbine engine gas controller. 5. The method as in claim 4 wherein the valve is an on-off valve or a proportional valve. 6. The method as in claim 1, where in the compressor is a centrifugal compressor, the method further including extracting the compressed air from a diffuser in the compressor outlet region. 7. The method as in claim 1 wherein the flow rate of the injected compressed air is between greater than 0% and less than or equal to about 15% of the air mass flow through the compressor at full load condition. 8. The method as in claim 1, wherein the compressor includes an inlet shroud, and wherein the controllably injecting includes flowing the compressed air through one or more nozzles positioned in the inlet shroud. 9. The method as in claim 1 wherein the compressor includes an inlet stator hub, and wherein controllably injecting compressed air includes flowing the compressed air through at least one nozzle positioned in the inlet stator hub. 10. The method as in claim 8, wherein 2-8 angularly spaced-apart nozzles are used to inject the compressed air. 11. The method as in claim 9, wherein 2-8 angularly spaced-apart nozzles are used to inject the compressed air. 12. The method as in claim 8, wherein the compressor further includes an inlet stator hub, and wherein the controllably injecting compressed air also includes flowing the compressed air through at least one nozzle positioned in the inlet stator hub. 13. Apparatus for reducing air mass flow in a single shaft gas turbine engine having an extended operating range including part load conditions, the gas turbine engine having a compressor with an axis of rotation, an inlet region, and an outlet region, the apparatus comprising: at least one nozzle positioned for injecting compressed air into the inlet region, the nozzle being oriented to direct the compressed air tangentially to said axis of rotation, and in the same angular direction as, the direction of rotation of the compressor to create a swirl in the inlet air flow to the compressor;a source of compressed air in communication with the one or more nozzles; one or more valves operatively connected to control the flow of compressed air to the one or more nozzles; anda controller operatively connected to the one or more valves to cause compressed air flow to the one or more nozzles during engine operation at part load conditions. 14. The apparatus as in claim 13 wherein the gas turbine engine includes an engine controller, and wherein the engine controller also controls the compressed air flow. 15. The apparatus as in claim 13, where in the compressor is a centrifugal compressor, and wherein the source of compressed air is a diffuser in the outlet region of the compressor. 16. The apparatus as in claim 13 wherein the one or more valves is an on-off valve or a proportional valve. 17. The apparatus as in claim 13 wherein the controller is configured to provide compressed air injection between about 90% and about 70% part load conditions. 18. The apparatus as in claim 13 wherein the compressed air mass flow rate through the one or more nozzles is between about 10% and about 15% of a full load gas turbine engine air mass flow rate. 19. The apparatus as in claim 13 wherein the compressor includes an inlet shroud, and wherein the one or more nozzles includes 2-8 nozzles mounted in the inlet shroud. 20. The apparatus as in claim 13 wherein the compressor includes an inlet stator having a hub and wherein the one or more nozzles includes 2-8 nozzles mounted in the stator hub.