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A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of variable fan guide vanes which are var

A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of variable fan guide vanes which are variable fan outlet guide vanes downstream of the forward fan rotor blades. An exemplary embodiment of the engine includes an afterburner downstream of the fan bypass duct between the core engine and an exhaust nozzle. The variable fan outlet guide vanes are operable to pivot from a nominal OGV position at take-off to an open OGV position at a high flight Mach Number which may be in a range of between about 2.5-4+. Struts extend radially across a radially inwardly curved portion of a flowpath of the engine between the forward fan section and the core engine.

대표청구항 ▼

What is claimed is: 1. A turbofan gas turbine engine comprising: a forward fan section including at least one row of circumferentially spaced apart longitudinally forward fan rotor blades; a core engine located aft and downstream of the forward fan section and including in downstream serial flow re

What is claimed is: 1. A turbofan gas turbine engine comprising: a forward fan section including at least one row of circumferentially spaced apart longitudinally forward fan rotor blades; a core engine located aft and downstream of the forward fan section and including in downstream serial flow relationship a core compressor, a core combustor, and a high pressure turbine drivingly connected to the core compressor by a core engine shaft; a fan bypass duct located downstream of the forward fan section and disposed radially outwardly of the core engine; the forward fan section located axially forward and upstream of a radially outer inlet of the fan bypass duct; an exhaust duct downstream of and in fluid communication with the core engine; a fan bypass duct outlet from the fan bypass duct to the exhaust duct downstream of the core engine; and the forward fan section having only a single stage of fan guide vanes and the fan guide vanes being variable fan outlet guide vanes located downstream of and adjacent to the forward fan rotor blades, for adjusting the flow into the fan duct. 2. A turbofan gas turbine engine as claimed in claim 1 further comprising: a low pressure turbine located aft and downstream of the core engine and drivingly connected to the forward fan rotor blades by a low pressure shaft, an exhaust nozzle disposed at a downstream end of the exhaust duct, and an afterburner disposed in the exhaust duct between the low pressure turbine and the exhaust nozzle. 3. A turbofan gas turbine engine as claimed in claim 2 further comprising: a flowpath of the engine, a transition section of the flowpath extending axially between the forward fan section and the core engine, and struts extending radially across a radially inwardly curved portion of the transition section. 4. A turbofan gas turbine engine as claimed in claim 3 further comprising a forward variable area bypass injector at an inlet to the fan bypass duct and a rear variable area bypass injector at the fan bypass duct outlet from the fan bypass duct. 5. A turbofan gas turbine engine as claimed in claim 4 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 6. A turbofan gas turbine engine as claimed in claim 5 wherein the high flight Mach Number is in a range of between about 2.5-4.9. 7. A turbofan gas turbine engine as claimed in claim 2 further comprising a forward variable area bypass injector at an inlet to the fan bypass duct and a rear variable area bypass injector at a fan bypass duct outlet from the fan bypass duct. 8. A turbofan gas turbine engine as claimed in claim 7 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 9. A turbofan gas turbine engine as claimed in claim 8 wherein the high flight Mach Number is in a range of between about 2.5-4.9. 10. A turbofan gas turbine engine as claimed in claim 2 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 11. A turbofan gas turbine engine as claimed in claim 1 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 12. A turbofan gas turbine engine as claimed in claim 11 wherein the high flight Mach Number is in a range of between about 2.5-4.9. 13. A turbofan gas turbine engine as claimed in claim 1 further comprising each of the variable fan outlet guide vanes having a pivotal forward section and a fixed aft section. 14. A turbofan gas turbine engine as claimed in claim 13 further comprising: an exhaust duct downstream of and in fluid communication with the fan bypass duct and a low pressure turbine located aft and downstream of the core engine and drivingly connected to the forward fan rotor blades by a low pressure shaft, an exhaust nozzle disposed at a downstream end of the exhaust duct, and an afterburner disposed in the exhaust duct between the low pressure turbine and the exhaust nozzle. 15. A turbofan gas turbine engine as claimed in claim 14 further comprising: a flowpath of the engine, a transition section of the flowpath extending axially between the forward fan section and the core engine, and struts extending radially across a radially inwardly curved portion of the transition section. 16. A turbofan gas turbine engine as claimed in claim 15 further comprising a forward variable area bypass injector at an inlet to the fan bypass duct and a rear variable area bypass injector at a fan bypass duct outlet from the fan bypass duct. 17. A turbofan gas turbine engine as claimed in claim 16 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 18. A turbofan gas turbine engine as claimed in claim 17 wherein the high flight Mach Number is in a range of between about 2.5-4.9. 19. A turbofan gas turbine engine comprising: a forward fan section including at least one row of circumferentially spaced apart longitudinally forward fan rotor blades; a core engine located aft and downstream of the forward fan section and comprising in downstream serial flow relationship an aft core driven fan, a compressor, a core combustor, and a high pressure turbine drivingly connected to the core driven fan and the core compressor by a core engine shaft; a low pressure turbine located aft and downstream of the core engine and drivingly connected to the forward fan rotor blades by a low pressure shaft; a fan bypass duct downstream of the forward fan section and disposed radially outwardly of the core engine; the forward fan section located axially forward and upstream of a radially outer inlet of the fan bypass duct; an exhaust duct downstream of and in fluid communication with the fan bypass duct and the low pressure turbine; the fan bypass duct including radially outer and inner inlets from the forward fan section to the fan bypass duct; an inner inlet duct extending from the inner inlet to the fan bypass duct and having a supercharger disposed in the inlet duct; and the forward fan section having only a single stage of fan guide vanes and the fan guide vanes being variable fan outlet guide vanes located downstream of and adjacent to the forward fan rotor blades and axially between the forward fan rotor blades and the fan bypass duct for adjusting the flow into the fan duct. 20. A turbofan gas turbine engine as claimed in claim 19 further comprising an exhaust nozzle disposed at a downstream end of the exhaust duct and an afterburner disposed in the exhaust duct between the low pressure turbine and the exhaust nozzle. 21. A turbofan gas turbine engine as claimed in claim 20 further comprising: a flowpath of the engine, a transition section of the flowpath extending axially between the forward fan section and the core engine, and struts extending radially across a radially inwardly curved portion of the transition section. 22. A turbofan gas turbine engine as claimed in claim 21 further comprising a forward variable area bypass injector at an inlet to the fan bypass duct and a rear variable area bypass injector at a fan bypass duct outlet from the fan bypass duct. 23. A turbofan gas turbine engine as claimed in claim 22 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 24. A turbofan gas turbine engine as claimed in claim 23 wherein the high flight Mach Number is in a range of between about 2.5-4.9. 25. A turbofan gas turbine engine as claimed in claim 20 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 26. A turbofan gas turbine engine as claimed in claim 19 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 27. A turbofan gas turbine engine as claimed in claim 26 wherein the high flight Mach Number is in a range of between about 2.5-4.9. 28. A turbofan gas turbine engine as claimed in claim 20 wherein the supercharger includes radially outwardly extending blade tips of rotor blades of the core driven fan. 29. A turbofan gas turbine engine as claimed in claim 28 further comprising: a flowpath of the engine, a transition section of the flowpath extending axially between the forward fan section and the core engine, and struts extending radially across a radially inwardly curved portion of the transition section. 30. A turbofan gas turbine engine as claimed in claim 29 further comprising a forward variable area bypass injector at an inlet to the fan bypass duct and a rear variable area bypass injector at a fan bypass duct outlet from the fan bypass duct. 31. A turbofan gas turbine engine as claimed in claim 30 further comprising the variable fan outlet guide vanes being operable to pivot from a nominal outlet guide vane position at take-off to an open outlet guide vane position at a high flight Mach Number. 32. A turbofan gas turbine engine as claimed in claim 31 wherein the high flight Mach Number is in a range of between about 2.5-4.9. 33. A turbofan gas turbine engine as claimed in claim 32 further comprising each of the variable fan outlet guide vanes having a pivotal forward section and a fixed aft section.