Reduced noise gas turbine engine system and supersonic exhaust nozzle system using elector to entrain ambient air
View Patent ↗One embodiment of the present invention is a unique gas turbine engine system. Another embodiment is a unique exhaust nozzle system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine systems and exhaust nozzle systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
1. A gas turbine engine system, comprising:
a fan system;
a compressor system in fluid communication with the fan system;
a combustion system in fluid communication with the compressor system;
a turbine system in fluid communication with the combustion system, wherein the turbine system is configured to discharge a first stream flow in the form of an engine core flow;
and wherein the fan system is configured to discharge a second stream flow in the form of a bypass flow and to discharge a third stream flow in the form of another bypass flow; and
an exhaust nozzle system in fluid communication with the fan system and the turbine system, including:
a first nozzle configured to discharge the first stream flow and the second stream flow;
an ejector configured to entrain ambient free stream air into the third stream flow, the ejector including a plurality of ejector doors extending from forward ends to aft ends located aft of the forward ends, the ejector doors pivotably mounted for rotation about points closer to the aft ends of the ejector doors than the forward ends of the ejector doors; and
a lobed mixer configured to mix the first stream flow and the second stream flow.
2. The gas turbine engine system of claim 1 , wherein the ejector doors are configured to vary an amount of the ambient free stream air entrained into the third stream flow.
3. The gas turbine engine system of claim 2 , wherein the ejector doors are configured to selectively close and prevent entrainment of the ambient free stream air.
4. The gas turbine engine system of claim 1 , wherein the ejector doors are configured to form a second nozzle that provides a converging nozzle or a diverging nozzle.
5. The gas turbine engine system of claim 1 , wherein the exhaust nozzle system includes a second nozzle configured to discharge the first stream flow and the second stream flow.
6. The gas turbine engine system of claim 5 , wherein the second nozzle is configured as a variable nozzle.
7. The gas turbine engine system of claim 6 , wherein the variable nozzle is configured as a variable diverging nozzle having a variable divergence angle.
8. The gas turbine engine system of claim 1 , wherein the first nozzle is a converging nozzle.
9. The gas turbine engine system of claim 1 , further comprising a second ejector configured to entrain air into the flow stream discharged by the first nozzle, the second ejector including a plurality of ejector doors extending from forward ends to aft ends located aft of the forward ends, the ejector doors of the second ejector pivotably mounted for rotation about points closer to the aft ends of the ejector doors included in the second ejector than the forward ends of the ejector doors included in the second ejector.
10. An exhaust nozzle system for a gas turbine engine, comprising:
a first nozzle configured to discharge a flow stream of the gas turbine engine, wherein the first nozzle is a converging nozzle;
a first ejector in fluid communication with another flow stream discharged by the gas turbine engine and configured to entrain ambient free stream air into the another flow stream to form a mixed flow; and
a second ejector disposed inward of the first ejector, wherein the second ejector is configured to entrain air from the mixed flow or the another flow stream into the flow stream discharged by the first nozzle, wherein the second ejector is formed by a plurality of variable-position flaps extending from forward ends to aft ends located aft of the forward ends, and wherein each of the plurality of variable-position flaps is pivotably mounted for rotation about points located closer to the aft end of the variable-position flap than the forward end of the variable position flap.
11. The exhaust nozzle system of claim 10 , wherein the first ejector includes a plurality of variable-position ejector doors.
12. The exhaust nozzle system of claim 11 , wherein the ejector doors are configured to vary an amount of the ambient free stream air entrained into the another flow stream.
13. The exhaust nozzle system of claim 12 , wherein the ejector doors are configured to selectively close and prevent entrainment of the ambient free stream air.
14. The exhaust nozzle system of claim 11 , wherein the ejector doors are configured to form a second nozzle that provides a converging nozzle or a diverging nozzle.
15. The exhaust nozzle system of claim 10 , wherein the second ejector is formed by a second nozzle, wherein the second nozzle is disposed downstream of the first nozzle.
16. The exhaust nozzle system of claim 10 , wherein the first ejector is configured to entrain ambient free stream air into the third stream flow, the first ejector including a plurality of ejector doors extending from forward ends to aft ends located aft of the forward ends, the ejector doors of the first ejector pivotably mounted for rotation about points closer to the aft ends of the ejector doors included in the first ejector than the forward ends of the ejector doors included in the first ejector.
17. An exhaust nozzle system for a gas turbine engine, comprising:
a first nozzle configured to discharge a flow stream of the gas turbine engine, wherein the first nozzle is a fixed-position nozzle that converges toward a central axis at an aft end of the first nozzle and the flow stream is a combination of an engine core flow and a first bypass flow stream;
a first ejector in fluid communication with another flow stream discharged by the gas turbine engine and configured to entrain ambient free stream air into the another flow stream to form a mixed flow; and
a mixer disposed upstream of the first nozzle and configured to mix the engine core flow and the first bypass flow stream.