초록

A regulator system includes a slidable ramp intermediate a secondary flow path and a primary flow path of a gas turbine engine nozzle section.

대표청구항 ▼

1. A jet area regulator system for a gas turbine engine comprising: a ramp adjacent a secondary flow path for a secondary flow and a primary flow path for a primary flow, said ramp axially slidable to regulate said secondary flow, said ramp adjacent to a plenum to facilitate a pressure balance of sa

1. A jet area regulator system for a gas turbine engine comprising: a ramp adjacent a secondary flow path for a secondary flow and a primary flow path for a primary flow, said ramp axially slidable to regulate said secondary flow, said ramp adjacent to a plenum to facilitate a pressure balance of said ramp, said plenum downstream of said ramp, and wherein said ramp is downstream of a planar primary nozzle of said primary flow path. 2. The system as recited in claim 1, further comprising an actuator system which axially slides said ramp parallel to a longitudinal axis of the gas turbine engine with respect to a passage in communication with said secondary flow path. 3. The system as recited in claim 1, wherein said ramp is pressure balanced to a reference pressure. 4. The system as recited in claim 1, wherein a passage in communication with said secondary flow path is transverse to a longitudinal axis of said engine, said ramp axially slidable with respect to said passage to regulate said secondary flow therethrough. 5. The system as recited in claim 1, wherein said secondary flow is selectively sourced from a fan section of the gas turbine engine. 6. The system as recited in claim 1, wherein said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine. 7. The system as recited in claim 6 wherein said secondary flow includes a variable cycle third stream fan flow selectively sourced from a fan section of the gas turbine engine. 8. The system as recited in claim 6 wherein said secondary flow is selectively sourced from a fan section of the gas turbine engine. 9. The system 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. 10. The system as recited in claim 1, wherein said plenum is downstream, relative to said secondary flow, of said ramp. 11. The system as recited in claim 1, wherein said plenum urges said ramp upstream, relative to said secondary flow. 12. A nozzle section for a gas turbine engine comprising: a secondary flow duct with a generally planar secondary nozzle to communicate a secondary flow therethrough;a primary flow duct with a generally planar primary nozzle to communicate primary flow therethrough, said generally planar primary nozzle adjacent to said generally planar secondary nozzle;a ramp axially slidable relative to a passage in communication with said secondary flow path to regulate said secondary flow though said passage, said ramp adjacent to a plenum to facilitate a pressure balance of said ramp, said plenum downstream of said ramp; andwherein said primary duct is generally circular in cross-section at an upstream segment and transitions into said planar primary nozzle at a downstream segment. 13. The nozzle section as recited in claim 12, wherein said ramp is pressure balanced to a reference pressure. 14. The nozzle section as recited in claim 12, wherein said secondary duct is bifurcated. 15. The nozzle section as recited in claim 14, wherein said bifurcated secondary duct joins at said secondary nozzle. 16. The nozzle section as recited in claim 12, wherein said passage is downstream of said planar primary nozzle. 17. The nozzle section as recited in claim 12, wherein said ramp is transverse to a longitudinal axis of the gas turbine engine. 18. The nozzle section as recited in claim 12, wherein said generally planar secondary nozzle is downstream of said generally planar primary nozzle. 19. The nozzle section as recited in claim 12, 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. 20. The nozzle section as recited in claim 12, 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. 21. A gas turbine engine comprising: an engine duct structure and an inner structure which at least partially define a secondary flow path for a secondary flow and a primary flow path for a primary flow, said secondary flow path defined at least partially around a perimeter of said primary flow path;a secondary flow duct with a generally planar secondary nozzle to communicate said secondary flow therethrough;a primary flow duct with a generally planar primary nozzle to communicate said primary flow therethrough, said generally planar primary nozzle adjacent said generally planar secondary nozzle;a ramp axially slidable relative to a passage in communication with said secondary flow path to regulate said secondary flow though said passage, said ramp adjacent to a plenum to facilitate a pressure balance of said ramp, said plenum downstream of said ramp; andwherein said primary duct is generally circular in cross-section at an upstream segment and transitions into said planar primary nozzle at a downstream segment. 22. The engine as recited in claim 21, wherein said secondary duct is bifurcated. 23. A jet area regulator system for a gas turbine engine comprising: a ramp adjacent a secondary flow path for a secondary flow and a primary flow path for a primary flow, said ramp axially slidable to regulate said secondary flow, said ramp adjacent to a plenum to facilitate a pressure balance of said ramp, said plenum downstream of said ramp; andwherein 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.