초록 ▼

A multiple bypass turbofan engine includes axially spaced-apart first and second stage fans of the engine fan connected in driving engagement to a low pressure shaft. A fan bypass duct circumscribes the second stage fan. A first bypass inlet to the fan bypass duct is disposed axially between the fir

A multiple bypass turbofan engine includes axially spaced-apart first and second stage fans of the engine fan connected in driving engagement to a low pressure shaft. A fan bypass duct circumscribes the second stage fan. A first bypass inlet to the fan bypass duct is disposed axially between the first and second stage fans and a second bypass inlet is axially disposed between the second stage fan and an annular core engine inlet. A fan shroud divides the second stage fan blades into radially inner and outer fan hub and tip sections, respectively. The tip sections are radially disposed in a fan tip duct. An axially translatable deflector is positioned to close the fan tip duct when it opens the first bypass inlet and open the fan tip duct when it closes the first bypass inlet.

대표청구항 ▼

1. A multiple bypass turbofan gas turbine engine comprising:axially spaced-apart first and second stage fans of the engine fan connected in driving engagement to a low pressure shaft;a fan bypass duct circumscribing the second stage fan;a first bypass inlet to the fan bypass duct disposed axially be

1. A multiple bypass turbofan gas turbine engine comprising:axially spaced-apart first and second stage fans of the engine fan connected in driving engagement to a low pressure shaft;a fan bypass duct circumscribing the second stage fan;a first bypass inlet to the fan bypass duct disposed axially between the first and second stage fans;a second bypass inlet to the fan bypass duct axially disposed between the second stage fan and an annular core engine inlet;first stage fan blades of the first stage fan disposed axially across a first fan duct and second stage fan blades radially disposed axially across a second fan duct;the second fan duct located axially aft of the first bypass inlet and disposed radially inwardly of the fan bypass duct;a fan shroud dividing the second stage fan blades into radially inner and outer fan hub and tip sections, respectively;the tip sections radially disposed in a fan tip duct including an annular duct wall having a non-rotatable forward duct wall portion adjacently forward of the rotatable fan shroud; andan axially translatable deflector positioned to close the fan tip duct when it opens the first bypass inlet and open the fan tip duct when it closes the first bypass inlet.2. An engine as claimed in claim 1 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.3. An engine as claimed in claim 2 further comprising the forward conical section having a first flow splitter.4. An engine as claimed in claim 3 further comprising the non-rotatable forward duct wall portion having a second flow splitter.5. An engine as claimed in claim 1 further comprising the annular duct wall having non-rotatable aft duct wall portion of the annular duct wall located adjacently aft of the rotatable fan shroud and axially extending to the second bypass inlet.6. An engine as claimed in claim 5 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.7. An engine as claimed in claim 6 further comprising the forward conical section having a first flow splitter and the non-rotatable forward duct wall portion having a second flow splitter.8. An engine as claimed in claim 1 further comprising an annular open space axially extending between the second stage fan and the core engine inlet and a non-rotatable retractable aft duct wall portion of the annular duct wall aft of the rotatable fan shroud.9. An engine as claimed in claim 8 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.10. An engine as claimed in claim 9 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.11. An engine as claimed in claim 10 further comprising the forward conical section having a first flow splitter.12. An engine as claimed in claim 11 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.13. An engine as claimed in claim 8 further comprising the aft duct wall portion being controllably linked to the deflector.14. An engine as claimed in claim 13 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.15. An engine as claimed in claim 14 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.16. An engine as claimed in claim 15 further comprising the forward conical section having a first flow splitter.17. An engine as claimed in claim 16 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.18. A multiple bypass turbofan gas turbine engine comprising:a fan section, a core engine, and a low pressure turbine in downstream serial flow relationship;the core engine including in downstream serial flow relationship a high pressure compressor, a combustor, and a high pressure turbine;the high pressure compressor connected in driving engagement to the high pressure turbine blades by a core engine shaft;axially spaced-apart first and second stage fans of the engine fan connected in driving engagement to the low pressure turbine by a low pressure shaft;a fan bypass duct circumscribing the second stage fan and the core engine;a first bypass inlet to the fan bypass duct disposed axially between the first and second stage fans;a second bypass inlet to the fan bypass duct axially disposed between the second stage fan and an annular core engine inlet to the core engine;first stage fan blades of the first stage fan disposed axially across a first fan duct and second stage fan blades radially disposed axially across a second fan duct;the second fan duct located axially aft of the first bypass inlet and disposed radially inwardly of the fan bypass duct;a fan shroud dividing the second stage fan blades into radially inner and outer fan hub and tip sections, respectively;the tip sections radially disposed in a fan tip duct including an annular duct wall having a non-rotatable forward duct wall portion adjacently forward of the rotatable fan shroud; andan axially translatable deflector positioned to close the fan tip duct when it opens the first bypass inlet and open the fan tip duct when it closes the first bypass inlet.19. An engine as claimed in claim 18 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.20. An engine as claimed in claim 19 further comprising the forward conical section having a first flow splitter.21. An engine as claimed in claim 20 further comprising the non-rotatable forward duct wall portion having a second flow splitter.22. An engine as claimed in claim 18 further comprising the annular duct wall having non-rotatable aft duct wall portion of the annular duct wall located adjacently aft of the rotatable fan shroud and axially extending to the second bypass inlet.23. An engine as claimed in claim 22 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.24. An engine as claimed in claim 23 further comprising the forward conical section having a first flow splitter and the non-rotatable forward duct wall portion having a second flow splitter.25. An engine as claimed in claim 18 further comprising an annular open space axially extending between the second stage fan and the core engine inlet and a non-rotatable retractable aft duct wall portion of the annular duct wall aft of the rotatable fan shroud.26. An engine as claimed in claim 25 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.27. An engine as claimed in claim 26 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.28. An engine as claimed in claim 27 further comprising the forward conical section having a first flow splitter.29. An engine as claimed in claim 28 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.30. An engine as claimed in claim 18 further comprising:a tail pipe extending aftwardly between the low pressure turbine and a variable area exhaust nozzle, anda rear variable area bypass injector open to the tail pipe and located at a rear end of the fan bypass duct.31. An engine as claimed in claim 30 further comprising an afterburner in the tail pipe axially disposed between the variable area exhaust nozzle and the rear variable area bypass injector.32. An engine as claimed in claim 31 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.33. An engine as claimed in claim 32 further comprising the forward conical section having a first flow splitter.34. An engine as claimed in claim 33 further comprising the non-rotatable forward duct wall portion having a second flow splitter.35. An engine as claimed in claim 30 further comprising the non-rotatable aft duct wall portion of the annular duct wall located adjacently aft of the rotatable fan shroud and axially extending to the second bypass inlet.36. An engine as claimed in claim 35 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.37. An engine as claimed in claim 36 further comprising the forward conical section having a first flow splitter and the non-rotatable forward duct wall portion having a second flow splitter.38. An engine as claimed in claim 30 further comprising an annular open space axially extending between the second stage fan and the core engine inlet.39. An engine as claimed in claim 38 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet.40. An engine as claimed in claim 39 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.41. An engine as claimed in claim 40 further comprising the forward conical section having a first flow splitter.42. An engine as claimed in claim 41 further comprising an annular third splitter radially disposed between the second bypass inlet and the core engine inlet.43. An engine as claimed in claim 30 further comprising an annular open space axially extending between the second stage fan and the core engine inlet and a non-rotatable retractable aft duct wall portion of the annular duct wall aft of the rotatable fan shroud.44. An engine as claimed in claim 43 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.45. An engine as claimed in claim 44 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.46. An engine as claimed in claim 45 further comprising the forward conical section having a first flow splitter.47. An engine as claimed in claim 46 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.48. An engine as claimed in claim 26 further comprising the deflector is linked to the retractable aft duct wall portion such that when the deflector extends forwardly the aft duct wall portion extends forwardly and when the deflector retracts aftwardly the aft duct wall portion retracts aftwardly.49. An engine as claimed in claim 48 further comprising the deflector having a forward conical section including followed by an aft cylindrical section.50. An engine as claimed in claim 49 further comprising the forward conical section having a first flow splitter.51. An engine as claimed in claim 48 wherein the second bypass inlet to the fan bypass duct is disposed axially between the open space and the core engine inlet and the retractable aft duct wall portion is radially disposed between the second bypass inlet and the core engine inlet.52. An engine as claimed in claim 48 further comprising a mechanical linkage linking the deflector to the retractable aft duct wall portion.53. An engine as claimed in claim 52 further comprising the mechanical linkage proportionally linking the deflector to the retractable aft duct wall portion.54. An engine as claimed in claim 48 further comprising the deflector linked to the retractable aft duct wall portion such that the retractable aft duct wall portion extends and retracts in non-linear relationship with respect to the deflector.55. An engine as claimed in claim 48 further comprising:first and second actuators translatably operably connected to the deflector and the aft duct wall portion respectively,the first and second actuators controllably linked by an actuating system, andthe actuating system is controlled by a controller to directly or proportionally translate the deflector and the aft duct wall portion.