초록 ▼

An aft FLADE gas turbine engine including a fan section drivenly connected to a low pressure turbine section followed by an aft FLADE turbine having at least one row of aft FLADE fan blades radially extending across a FLADE duct circumscribing the aft FLADE turbine, and at least one thrust vectoring

An aft FLADE gas turbine engine including a fan section drivenly connected to a low pressure turbine section followed by an aft FLADE turbine having at least one row of aft FLADE fan blades radially extending across a FLADE duct circumscribing the aft FLADE turbine, and at least one thrust vectoring nozzle in pressurized fluid flow receiving communication with the FLADE duct. One embodiment of the engine includes spaced apart right and left hand FLADE exhaust nozzles in pressurized fluid flow receiving communication with the FLADE duct and offset from a main engine exhaust nozzle located downstream of the aft FLADE turbine. Right and left hand valves disposed in right and left hand ducts extending between a FLADE airflow manifold in pressurized fluid flow receiving communication with the FLADE duct may be used to vector thrust. The right and left hand FLADE exhaust nozzle may be fixed or thrust vectoring nozzles.

대표청구항 ▼

What is claimed is: 1. An aft FLADE gas turbine engine comprising: a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, an aft FLADE turbine downstream of the low pressure turbine section, at least on

What is claimed is: 1. An aft FLADE gas turbine engine comprising: a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, an aft FLADE turbine downstream of the low pressure turbine section, at least one row of aft FLADE fan blades disposed radially outwardly of and connected to the aft FLADE turbine, the row of aft FLADE fan blades radially extending across a FLADE duct circumscribing the aft FLADE turbine, and at least one thrust vectoring nozzle in pressurized fluid flow receiving communication with the FLADE duct. 2. An aft FLADE gas turbine engine as claimed in claim 1 further comprising: the one thrust vectoring nozzle being a right hand FLADE exhaust nozzle, a left hand FLADE exhaust nozzle in pressurized fluid flow receiving communication with the FLADE duct, and the right and left hand FLADE exhaust nozzle are offset from a main engine exhaust nozzle located downstream of the aft FLADE turbine. 3. An aft FLADE gas turbine engine as claimed in claim 2 wherein the right and left hand FLADE exhaust nozzle are fixed nozzles. 4. An aft FLADE gas turbine engine as claimed in claim 2 wherein the right and left hand FLADE exhaust nozzle are thrust vectoring nozzles. 5. An aft FLADE gas turbine engine as claimed in claim 2 further comprising: a FLADE airflow manifold in pressurized fluid flow receiving communication with the FLADE duct, the right and left hand FLADE exhaust nozzles connected in pressurized fluid flow receiving communication with the FLADE airflow manifold by FLADE air exhaust right and left hand ducts respectively, right and left hand valves respectively disposed in the right and left hand ducts, and the right and left hand valves being operable to control amounts of FLADE exhaust airflow flowed from the FLADE duct to each of the right and left hand FLADE exhaust nozzles respectively. 6. An aft FLADE gas turbine engine as claimed in claim 5 wherein the right and left hand FLADE exhaust nozzle are fixed nozzles. 7. An aft FLADE gas turbine engine as claimed in claim 5 wherein the right and left hand FLADE exhaust nozzle are thrust vectoring nozzles. 8. An aft FLADE gas turbine engine as claimed in claim 5 further comprising: a fan bypass duct circumscribing the core engine and in fluid communication with the fan section, a mixer in fluid communication with the fan bypass duct and being operably disposed to mix bypass air from the fan bypass duct with core discharge air exiting the low pressure turbine section, and the aft FLADE turbine being downstream of the mixer. 9. An engine as claimed in claim 8 further comprising: a fan inlet to the fan section, an annular FLADE inlet to the FLADE duct, and the FLADE inlet is axially located substantially aftwardly of the fan section. 10. An engine as claimed in claim 9 wherein the FLADE inlet is axially located aftwardly of the core engine. 11. An engine as claimed in claim 8 further comprising the aft FLADE turbine connected to and rotatable with a low pressure turbine of the low pressure turbine section. 12. An engine as claimed in claim 11 further comprising: a fan inlet to the fan section, an annular FLADE inlet to the FLADE duct, and the FLADE inlet is axially located substantially aftwardly of the fan section. 13. An engine as claimed in claim 12 wherein the FLADE inlet is axially located aftwardly of the core engine. 14. An engine as claimed in claim 8 wherein the aft FLADE turbine is a free turbine. 15. An engine as claimed in claim 14 further comprising: a fan inlet to the fan section, an annular FLADE inlet to the FLADE duct, and the FLADE inlet is axially located substantially axially aftwardly of the fan section. 16. An engine as claimed in claim 15 wherein the FLADE inlet is located axially aftwardly of the core engine. 17. An engine as claimed in claim 14 further comprising a variable area turbine nozzle with variable turbine nozzle vanes located between the mixer and the aft FLADE turbine. 18. An engine as claimed in claim 17 further comprising: a fan inlet to the fan section, an annular FLADE inlet to the FLADE duct, and the FLADE inlet is axially located substantially axially aftwardly of the fan section. 19. An engine as claimed in claim 18 wherein the FLADE inlet is located axially aftwardly of the core engine. 20. An engine as claimed in claim 14 further comprising a row of variable first FLADE vanes radially extending across the FLADE duct axially forwardly of the row of aft FLADE fan blades. 21. An engine as claimed in claim 20 further comprising: a fan inlet to the fan section, an annular FLADE inlet to the FLADE duct, and the FLADE inlet is axially located substantially axially aftwardly of the fan section. 22. An engine as claimed in claim 21 wherein the FLADE inlet is located axially aftwardly of the core engine. 23. An engine as claimed in claim 20 further comprising a variable area turbine nozzle with variable turbine nozzle vanes located between the mixer and the aft FLADE turbine. 24. An engine as claimed in claim 23 further comprising: a fan inlet to the fan section, an annular FLADE inlet to the FLADE duct, and the FLADE inlet is axially located substantially axially aftwardly of the fan section. 25. An engine as claimed in claim 24 wherein the FLADE inlet is located axially aftwardly of the core engine. 26. An aircraft comprising: an aft FLADE gas turbine engine within a fuselage of the aircraft, the gas turbine engine comprising; a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, an aft FLADE turbine downstream of the low pressure turbine section, at least one row of aft FLADE fan blades disposed radially outwardly of and connected to the aft FLADE turbine, the row of aft FLADE fan blades radially extending across a FLADE duct circumscribing the aft FLADE turbine, and at least one thrust vectoring nozzle in pressurized fluid flow receiving communication with the FLADE duct. 27. An aircraft as claimed in claim 26 further comprising: the one thrust vectoring nozzle being a right hand FLADE exhaust nozzle, a left hand FLADE exhaust nozzle in pressurized fluid flow receiving communication with the FLADE duct, and the right and left hand FLADE exhaust nozzle are offset from a main engine exhaust nozzle located downstream of the aft FLADE turbine. 28. An aircraft as claimed in claim 27 wherein the right and left hand FLADE exhaust nozzle are fixed nozzles. 29. An aircraft as claimed in claim 27 further comprising: FLADE air intakes and an engine air intake mounted flush with respect to the fuselage, the FLADE air intakes axially offset from the engine air intake, the engine air intake connected to and in fluid communication with the fan inlet by an engine fixed inlet duct, and the FLADE air intakes connected to and in fluid communication with the FLADE inlets by FLADE fixed inlet ducts. 30. An aircraft as claimed in claim 29 further comprising: inlet duct passages of the engine and FLADE fixed inlet ducts respectively being two-dimensional and terminating in transition sections between the inlet duct passages and the fan and FLADE inlets respectively. 31. An aircraft as claimed in claim 27 further comprising: a FLADE airflow manifold in pressurized fluid flow receiving communication with the FLADE duct, the right and left hand FLADE exhaust nozzles connected in pressurized fluid flow receiving communication with the FLADE airflow manifold by FLADE air exhaust right and left hand ducts respectively, right and left hand valves respectively disposed in the right and left hand ducts, and the right and left hand valves being operable to control amounts of FLADE exhaust airflow flowed from the FLADE duct to each of the right and left hand FLADE exhaust nozzles respectively. 32. An aircraft as claimed in claim 31 wherein the right and left hand FLADE exhaust nozzle are fixed nozzles. 33. An aircraft as claimed in claim 31 wherein the right and left hand FLADE exhaust nozzle are thrust vectoring nozzles. 34. An aircraft as claimed in claim 31 further comprising: a fan bypass duct circumscribing the core engine and in fluid communication with the fan section, a mixer in fluid communication with the fan bypass duct and being operably disposed to mix bypass air from the fan bypass duct with core discharge air exiting the low pressure turbine section, and the aft FLADE turbine being downstream of the mixer. 35. An aircraft as claimed in claim 31 further comprising: a fan inlet to the fan section, an annular FLADE inlet to the FLADE duct, and the FLADE inlet is axially located substantially aftwardly of the fan section. 36. An aircraft as claimed in claim 35 wherein the FLADE inlet is axially located aftwardly of the core engine. 37. An aircraft as claimed in claim 35 wherein the aft FLADE turbine is a free turbine. 38. An aircraft as claimed in claim 37 wherein the FLADE inlet is axially located aftwardly of the core engine. 39. An aircraft as claimed in claim 31 further comprising: FLADE air intakes and an engine air intake mounted flush with respect to the fuselage, the FLADE air intakes axially offset from the engine air intake, the engine air intake connected to and in fluid communication with the fan inlet by an engine fixed inlet duct, and the FLADE air intakes connected to and in fluid communication with the FLADE inlets by FLADE fixed inlet ducts. 40. An aircraft as claimed in claim 39 wherein the right and left hand FLADE exhaust nozzle are fixed nozzles. 41. An aircraft as claimed in claim 39 wherein the right and left hand FLADE exhaust nozzle are thrust vectoring nozzles. 42. An aircraft as claimed in claim 39 further comprising: a fan bypass duct circumscribing the core engine and in fluid communication with the fan section, a mixer in fluid communication with the fan bypass duct and being operably disposed to mix bypass air from the fan bypass duct with core discharge air exiting the low pressure turbine section, and the aft FLADE turbine being downstream of the mixer. 43. An aircraft as claimed in claim 39 further comprising: a fan inlet to the fan section, an annular FLADE inlet to the FLADE duct, and the FLADE inlet is axially located substantially aftwardly of the fan section. 44. An aircraft as claimed in claim 43 wherein the FLADE inlet is axially located aftwardly of the core engine. 45. An aircraft as claimed in claim 43 wherein the aft FLADE turbine is a free turbine.