초록 ▼

An ultra-efficient “green” aircraft propulsor utilizing an augmentor fan is disclosed. A balanced design is provided combining a fuel efficient and low-noise high bypass ratio augmentor fan and a low-noise shrouded high bypass ratio turbofan. Three mass flow streams are utilized to reduce propulsor

An ultra-efficient “green” aircraft propulsor utilizing an augmentor fan is disclosed. A balanced design is provided combining a fuel efficient and low-noise high bypass ratio augmentor fan and a low-noise shrouded high bypass ratio turbofan. Three mass flow streams are utilized to reduce propulsor specific fuel consumption and increase performance relative to conventional turbofans. Methods are provided for optimization of fuel efficiency, power, and noise by varying mass flow ratios of the three mass flow streams. Methods are also provided for integration of external propellers into turbofan machinery.

대표청구항 ▼

1. An ultra-efficient aircraft propulsor comprising: a turbofan propulsor comprising a core engine and a ducted fan driven by the core engine, the ducted fan comprising a plurality of ducted fan blades circumferentially contained by a fan cowl, and the core engine comprising a combustion engine; an

1. An ultra-efficient aircraft propulsor comprising: a turbofan propulsor comprising a core engine and a ducted fan driven by the core engine, the ducted fan comprising a plurality of ducted fan blades circumferentially contained by a fan cowl, and the core engine comprising a combustion engine; an augmentor hub ring substantially surrounding an inner perimeter of the fan cowl, and configured to rotate separately from the ducted fan; andan augmentor fan mechanically coupled to and driven by the core engine, and comprising a plurality of augmentor fan blades arranged circumferentially around the augmentor hub ring. 2. The ultra-efficient aircraft propulsor according to claim 1, further comprising a drive operable to rotationally drive the augmentor fan by using power from the core engine. 3. The ultra-efficient aircraft propulsor according to claim 1, wherein the combustion engine has a thermodynamic cycle comprising Brayton, Otto, Diesel, Rankine, Stirling, Humphrey, Fickett-Jacobs, Wave, Carnot, or Hybrid. 4. The ultra-efficient aircraft propulsor according to claim 1, further comprising a thrust reverser operable to produce reverse thrust. 5. The ultra-efficient aircraft propulsor according to claim 4, wherein the thrust reverser is operable to change at least one of: a pitch orientation of the augmentor fan blades, fan flow, core flow, or a combination thereof. 6. The ultra-efficient aircraft propulsor according to claim 4, wherein the thrust reverser comprises reverser elements comprising cascade reverser elements, flow deflecting vane reverser elements, blocker door reverser elements, clamshell reverser elements, target, or petal reverser elements. 7. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan blades comprise airfoil sections, and wherein a number of the augmentor fan blades ranges from three to sixty inclusive. 8. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan blades comprise a blade pitch control operable to variably control pitch angles of the augmentor fan blades to provide desirable augmentor fan blades angles of attack along their span to enable optimization of an optimization parameter. 9. The ultra-efficient aircraft propulsor according to claim 8, wherein the optimization parameter is a function of a measure of at least one of: aerodynamic efficiency, fuel efficiency, community noise, cabin noise, emissions, takeoff performance, climb performance, cruise performance, performance in descending flight, reverse thrust performance, and power division between the augmentor fan, the ducted fan and the core engine, or a combination thereof. 10. The ultra-efficient aircraft propulsor according to claim 1, wherein a ratio of a span of each of the augmentor fan blades to a span of each of the ducted fan blades ranges from about 0.05 to about 5. 11. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan blades each have an average chord to span ratio ranging from about 0.02 to about 2. 12. The ultra-efficient aircraft propulsor according to claim 1, wherein a number of augmentor fan blades and a number of the ducted fan blades are chosen to avoid sum and difference tones for reducing noise. 13. The ultra-efficient aircraft propulsor according to claim 12, further comprising: a second augmentor hub ring substantially surrounding an inner perimeter of the fan cowl and longitudinally spaced from the augmentor hub ring, and operable to contra-rotate relative to the augmentor hub ring; anda second augmentor fan driven by the core engine comprising a plurality of second augmentor fan blades arranged circumferentially around the second augmentor hub ring, wherein a number of the second augmentor fan blades is chosen to avoid sum and difference tones for reducing noise. 14. The ultra-efficient aircraft propulsor according to claim 1, wherein an aerodynamic tip-sweep of a mid chord line of each of the augmentor fan blades relative to a plane perpendicular to local inflow streamlines is greater than about 10 degrees and less than or equal to about 60 degrees. 15. The ultra-efficient aircraft propulsor according to claim 1, further comprising at least a dual load path attachment operable to couple the augmentor fan blades to the augmentor hub ring. 16. The ultra-efficient aircraft propulsor according to claim 1, wherein a property of tips of the augmentor fan blades comprises nonzero taper, nonzero sweep, morphably controllable surfaces, or aerodynamic blowing. 17. The ultra-efficient aircraft propulsor according to claim 1, wherein a tip of each of the augmentor fan blades is coupled to an augmentor fan tip ring encircling all of the augmentor fan blades, and wherein the augmentor fan tip ring is operable to rotate with the augmentor fan. 18. The ultra-efficient aircraft propulsor according to claim 17, further comprising blade pitch variability operable to allow coupling of the augmentor fan blades to the augmentor fan tip ring. 19. The ultra-efficient aircraft propulsor according to claim 17, wherein the augmentor fan tip ring comprises a ring airfoil configuration. 20. The ultra-efficient aircraft propulsor according to claim 19, wherein an average chord of a ring airfoil of the ring airfoil configuration ranges from 1 to 5 times an average chord of each of the augmentor fan blades. 21. The ultra-efficient aircraft propulsor according to claim 19, wherein an average chord of the augmentor fan tip ring ranges from about 0.025 to about 0.5 of an average chord of the fan cowl. 22. The ultra-efficient aircraft propulsor according to claim 19, wherein an average thickness to chord ratio of a ring airfoil of the ring airfoil configuration ranges from about 0.03 to about 0.30. 23. The ultra-efficient aircraft propulsor according to claim 17, wherein: the augmentor fan tip ring has a slightly noncircular shape when the augmentor fan is not rotating; androtational loads cause the augmentor fan tip ring to take a substantially circular shape when the augmentor fan is rotating at operational rotation speeds. 24. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan blades comprise airfoil acoustic shaping features. 25. The ultra-efficient aircraft propulsor according to claim 24, wherein an aerodynamic tip-sweep of a mid chord line of each of the augmentor fan blades in degrees relative to streamlines is less than or equal to about 60. 26. The ultra-efficient aircraft propulsor according to claim 2, wherein the drive comprises a gear operable to transmit power concurrent with changing revolutions per minute. 27. The ultra-efficient aircraft propulsor according to claim 26, wherein the gear comprises: at least one driving gear ring;at least one driven gear ring provided around a periphery of the augmentor hub ring; anda plurality of connecting gear elements provided between the at least one driving gear ring and the at least one driven gear ring. 28. The ultra-efficient aircraft propulsor according to claim 27, wherein: the at least one driving gear ring is provided around the inner perimeter of the fan cowl; andthe connecting gear elements comprise: a first gear sprocket engaged by the at least one driving gear ring;a second gear sprocket engaging the at least one driven gear ring; anda shaft operable to connect the first gear sprocket and the second gear sprocket. 29. The ultra-efficient aircraft propulsor according to claim 28, wherein a circumference of the second gear sprocket is less than a circumference of the first gear sprocket, to cause an effective gearing wherein rotational revolutions per minute (RPM) of the driven gear ring is reduced relative to rotational RPM of the driving gear ring. 30. The ultra-efficient aircraft propulsor according to claim 1, further comprising propulsor control operable to control at least two of: core engine power, core engine thrust, core engine revolutions per minute (RPM), core engine fuel flow, a core engine critical temperature parameter, ducted fan thrust, ducted fan RPM, augmentor fan blade pitch, augmentor fan thrust, augmentor fan RPM, or a combination thereof. 31. The ultra-efficient aircraft propulsor according to claim 30, wherein the propulsor control further comprises mass flow control operable to control at least a fraction of propulsor total mass flow which is run through the augmentor fan. 32. The ultra-efficient aircraft propulsor according to claim 30, wherein the propulsor control further comprises power sharing control operable to control at least a fraction of propulsor total power which is run through the augmentor fan. 33. The ultra-efficient aircraft propulsor according to claim 1, further comprising flow vectoring means operable to vector a flow downstream of at least one of the group consisting of: the core engine, the ducted fan, and the augmentor fan. 34. The ultra-efficient aircraft propulsor according to claim 1, wherein a diameter of the augmentor hub ring is within about ±25% of a diameter of the ducted fan. 35. The ultra-efficient aircraft propulsor according to claim 1, wherein the core engine comprises a spool core. 36. The ultra-efficient aircraft propulsor according to claim 35, wherein the spool core-comprises at least one of the group consisting of: a 1-spool core, a 2-spool core, a 3-spool core, and a 4-spool core. 37. The ultra-efficient aircraft propulsor according to claim 1, wherein tips of the augmentor fan blades are substantially located on a circle surrounding an outer perimeter of all of the ducted fan blades of the ducted fan and an outer perimeter of the fan cowl. 38. The ultra-efficient aircraft propulsor according to claim 37, further comprising a bearing operable to enable a rotating structural connection, wherein the augmentor hub ring is structurally coupled by the bearing to the fan cowl. 39. The ultra-efficient aircraft propulsor according to claim 37, wherein a diameter of the augmentor hub ring ranges from about 15% to about 90% of a diameter of the circle. 40. The ultra-efficient aircraft propulsor according to claim 37, further comprising a drive comprising a gear operable to rotationally drive the augmentor fan at lower revolutions per minute than the ducted fan, using power from the core engine. 41. The ultra-efficient aircraft propulsor according to claim 40, wherein the gear is further operable to drive the ducted fan at lower revolutions per minute than turbine elements of the core engine. 42. The ultra-efficient aircraft propulsor according to claim 1, further comprising a rotating gear ring operable to provide torque from blade pitch control unit drives to the augmentor fan blades. 43. The ultra-efficient aircraft propulsor according to claim 1, further comprising a lobed mixer operable to cool gasses that drive a power turbine which directly drives the augmentor fan. 44. The ultra-efficient aircraft propulsor according to claim 43, wherein cooled gasses from the lobed mixer reduces temperature related wear on the at least one of the augmentor fan blades and at least one blade pitch control drive. 45. The ultra-efficient aircraft propulsor according to claim 1, wherein the core engine comprises at least one compressor comprising at least one of: an axial compressor, a centrifugal compressor, or a combination thereof. 46. The ultra-efficient aircraft propulsor according to claim 1, wherein the core engine comprises an electric motor. 47. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan blades are twisted from their root ends to their tip ends. 48. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan is added to the ducted fan and the core engine to provide three separate and individually controllable mass flow streams. 49. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan, the ducted fan and the core engine provide three separate and individually controllable mass flow streams. 50. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan circumscribes the turbofan. 51. The ultra-efficient aircraft propulsor according to claim 1, wherein the augmentor fan is mechanically coupled to the core engine via gearing.