초록

A flexible panel assembly for a gas turbine engine selectively exhibits a range of positions to regulate exhaust of the engine.

대표청구항 ▼

1. A nozzle assembly for a gas turbine engine comprising: a flexible panel adjacent a two dimensional secondary nozzle in communication with a secondary flow path for a secondary flow, said second flow path adjacent to a primary flow path for a primary flow, said flexible panel operable to selective

1. A nozzle assembly for a gas turbine engine comprising: a flexible panel adjacent a two dimensional secondary nozzle in communication with a secondary flow path for a secondary flow, said second flow path adjacent to a primary flow path for a primary flow, said flexible panel operable to selectively define a range of positions to regulate said two dimensional secondary nozzle;a cavity on a non-gas side of said flexible panel; andan actuator located in said cavity, said actuator configured to deflect said flexible panel, said actuator oriented in a direction that is non-parallel to an axis of rotation of the gas turbine engine. 2. The nozzle assembly of claim 1, further comprising: a stiffening rib configured to provide a desired aerodynamic shape to the flexible panel. 3. The nozzle assembly of claim 2, wherein said actuator is connected to the stiffening rib and is operative to position the stiffening rib such that the flexible panel is deflected. 4. The nozzle assembly of claim 1, wherein the flexible panel is configured to be placed in at least one of a throat area and an exit area of a third stream exhaust nozzle to variably open and close the exit area of the third stream exhaust nozzle and operatively regulate a third stream exhaust. 5. The nozzle assembly of claim 1, wherein the flexible panel is formed at least partially of an elastomeric material. 6. The nozzle assembly as recited in claim 5, wherein said secondary flow is selectively sourced only from a fan section of the gas turbine engine and said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine and a flow from said fan section. 7. The nozzle assembly as recited in claim 5, wherein said secondary flow is selectively sourced only from a fan section of the gas turbine engine and said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine and a flow from a compressor section. 8. The nozzle assembly of claim 1, wherein the flexible panel is formed at least partially of an organic matrix composite. 9. The nozzle assembly of claim 1, wherein the flexible panel further comprises a stiffening stay operative to maintain a profile of a throat area. 10. The nozzle assembly of claim 1, wherein the flexible panel further comprises a support structure operative to support the flexible panel. 11. The nozzle assembly as recited in claim 1, wherein said secondary flow is selectively sourced only from a fan section of the gas turbine engine and said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine and a flow from said fan section. 12. The nozzle assembly as recited in claim 1, wherein said secondary flow is selectively sourced only from a fan section of the gas turbine engine and said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine and a flow from a compressor section. 13. A nozzle assembly for a gas turbine engine, the nozzle assembly comprising: a two-dimensional secondary nozzle having a throat area and an exit area;a flexible panel operative to variably alter at least one of the throat area and the exit area to regulate a secondary flow from the two-dimensional secondary nozzle, said secondary flow different than a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine;a cavity on a non-gas side of said flexible panel; andan actuator located in said cavity, said actuator configured to deflect said flexible panel, said actuator oriented in a direction that is non-parallel to an axis of rotation of the gas turbine engine. 14. The nozzle assembly of claim 13, further comprising: a stiffening rib operative to deflect the flexible panel such that at least one of the throat area and the exit area is altered. 15. The nozzle assembly of claim 14, wherein said actuator is connected to the stiffening rib and is operative to deflect the flexible panel by positioning the stiffening rib. 16. The nozzle assembly of claim 13, wherein the panel is operative to symmetrically affect the secondary flow with respect to yaw. 17. The nozzle assembly of claim 13, wherein the nozzle assembly further comprises a support structure operative to support the flexible panel. 18. The nozzle assembly of claim 13, wherein said cavity is operative to reduce an actuation load associated with positioning of the panel by reducing pressure imbalances on the non-gas side and a gas path side of the flexible panel. 19. A gas turbine engine comprising: a secondary flow duct with a two-dimensional secondary nozzle to communicate a secondary flow therethrough;a primary flow duct with a two-dimensional primary nozzle to communicate primary flow therethrough, said two-dimensional primary nozzle adjacent to said two-dimensional secondary nozzle, wherein said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine, and wherein said secondary flow is different than said combustion core gas exhaust flow;a flexible panel adjacent said two-dimensional secondary nozzle, said flexible panel operable to selectively define a range of positions to regulate said two-dimensional secondary nozzle;a cavity on a non-gas side of said flexible panel; andan actuator located in said cavity, said actuator configured to deflect said flexible panel, said actuator oriented in a direction that is non-parallel to an axis of rotation of the gas turbine engine. 20. The gas turbine engine of claim 19, further comprising a stiffening rib configured to deflect the flexible panel. 21. The gas turbine engine of claim 20, wherein said actuator is connected to the rib and is configured to operatively rotate the stiffening rib and deflect the flexible panel in a throat area and an exit area of the two-dimensional secondary nozzle. 22. The gas turbine engine of claim 20, wherein the two-dimensional secondary nozzle is a third stream exhaust nozzle assembly. 23. The gas turbine engine of claim 20, wherein further comprising a stiffening stay configured to maintain a profile of a throat area of said two-dimensional secondary nozzle. 24. The gas turbine engine of claim 19, wherein said flexible panel is located on one side of said two-dimensional secondary nozzle opposite said two-dimensional primary nozzle. 25. The gas turbine engine of claim 19, wherein said two-dimensional secondary nozzle is downstream of said two dimensional primary nozzle. 26. The gas turbine engine of claim 19, wherein said two-dimensional secondary nozzle is adjacent to said two-dimensional primary nozzle.