Apparatus for operating gas turbine engines
A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine, coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, such that at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas and channeled to the auxiliary engine for generating power, and coupling a modulating valve in flow communication to the propelling gas turbine engine to control the flow of airflow from the propelling gas turbine engine to the auxiliary engine, wherein the modulating valve is selectively operable to control an extraction point of airflow from the propelling gas turbine engine.
1. A gas turbine engine assembly comprising:
at least one propelling gas turbine engine comprising a fan, a core engine downstream from the fan, and a plurality of extraction points;
a modulating valve coupled in flow communication to said at least one propelling gas turbine engine; and
an auxiliary engine used for generating electrical power, said auxiliary engine comprising at least one turbine and an inlet, said inlet coupled in flow communication with said modulating valve, such that a portion of airflow entering said at least one propelling engine is extracted for use by said auxiliary engine and such that said modulating valve controls the flow of airflow from said at least one propelling engine to said auxiliary engine, said modulating valve is selectively operable to extract and mix airflow from at least two of said plurality of extraction points.
2. A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is coupled to a first of said plurality of extraction points for selectively controlling a flow of high-pressure airflow to said auxiliary engine and to a second of said plurality of extraction points for selectively controlling a flow of low-pressure airflow to said auxiliary engine.
3. A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is selectively operable to facilitate controlling at least one of a pressure, a temperature, and a density of airflow channeled to said auxiliary engine.
4. A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is selectively operable to facilitate increasing at least one of a stall margin and an operability of said propelling gas turbine engine.
5. A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is selectively operable to facilitate increasing an operating efficiency of said propelling gas turbine engine.
6. A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is coupled to at least two of said extraction points such that during at least some engine operations, said auxiliary engine receives airflow from at least one extrication point coupled in flow communication with a high-pressure source of air and from an extrication point coupled in flow communication with a low-pressure source of air.
7. A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve facilitates said auxiliary engine generating increased shaft horsepower during operation of said gas turbine engine assembly.
8. An aircraft gas turbine engine assembly, said assembly comprising;
at least one propelling gas turbine engine comprising a core engine and an exhaust, said core engine comprising at least one turbine, said at least one propelling gas turbine engine for generating thrust for the aircraft;
a modulating valve coupled in flow communication with at least one of a plurality of airflow extraction points defined within said at least one propelling gas turbine engine, said modulating valve is selectively operable to extract and mix airflow from at least two of said plurality of airflow extraction points; and
at least one auxiliary engine comprising an inlet, at least one turbine, and an exhaust, said inlet coupled in flow communication with said modulating valve such that a portion of airflow flowing through said propelling engine is selectively extractable from said at least one propelling engine and is channeled to said auxiliary engine for generating electrical power.
9. An aircraft gas turbine engine assembly in accordance with claim 8 wherein said modulating valve is selectively operable to facilitate controlling at least one of a pressure, a temperature, and a density of airflow extracted from said at least one propelling engine and channeled to said at least one auxiliary engine.
10. An aircraft gas turbine engine assembly in accordance with claim 8 wherein said at least one auxiliary engine is operable independently of said at least one propelling gas turbine engine.
11. An aircraft gas turbine engine assembly in accordance with claim 8 wherein said modulating valve facilitates said auxiliary engine generating increased shaft horsepower during operation of said gas turbine engine assembly.
12. An aircraft gas turbine engine assembly in accordance with claim 8 wherein operation of said modulating valve facilitates enhancing at least one of a stall margin and the operability of said at least one propelling engine.
13. An aircraft gas turbine engine assembly in accordance with claim 8 wherein operation of said modulating valve facilitates improving operating performance of said at least one propelling engine, said modulating valve is coupled to at least two of said airflow extraction points such that during at least some engine operations, said auxiliary engine receives airflow from at least one extrication point coupled in flow communication with a high-pressure source of air and from at least one extrication point coupled in flow communication with a low-pressure source of air.