Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan

Patent metadata

Field	Value
Publication number	US-9759160-B2
Application number	US-201414181684-A
Country	US
Kind code	B2
Filing date	Feb 16, 2014
Priority date	Sep 9, 2009
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

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.

First claim

The invention claimed is:

1. A method of generating thrust with an aircraft propulsor having an augmentor fan, a core engine, and a ducted fan, the method comprising
providing thrust from the core engine at a first thrust to total power ratio;
providing thrust from the ducted fan at a second thrust to total power ratio; and
providing thrust from the augmentor fan at a third thrust to total power ratio,
wherein the third thrust to total power ratio is greater than the second thrust to total power ratio for a first set of flight conditions,
wherein the first set of flight conditions comprises takeoff,
wherein the second thrust to total power ratio is greater than the third thrust to total power ratio for a second set of flight conditions, and
wherein the second set of flight conditions comprises climb out at a speed of about Mach 0.35.

2. The method of claim 1 , further comprising powering the ducted fan and the augmentor fan by the core engine.

3. The method of claim 1 , further comprising varying the first thrust to total power ratio, the second thrust to total power ratio, and the third thrust to total power.

4. The method of claim 1 , further comprising flow vectoring a flow downstream of the core engine, the ducted fan, or the augmentor fan.

5. A method of generating thrust with an aircraft propulsor having an unducted augmentor fan, a core engine, and a ducted fan, the method comprising
providing thrust from the core engine at a first thrust to total power ratio;
providing thrust from the ducted fan at a second thrust to total power ratio; and
providing thrust from the unducted augmentor fan, which circumscribes the ducted fan, at a third thrust to total power ratio.

6. The method of claim 5 , wherein the ducted fan comprises a plurality of ducted fan blades circumferentially contained by a fan cowl,
wherein the augmentor fan comprises a plurality of augmentor fan blades arranged circumferentially around an augmentor hub,
wherein the augmentor hub substantially surrounds an inner perimeter of the fan cowl and is configured to rotate separately from the ducted fan.

7. The method of claim 6 , further comprising driving the ducted fan and the augmentor fan using power from the core engine,
wherein the core engine and the ducted fan comprise a turbofan propulsor,
wherein the core engine comprises a combustion engine, and
wherein the augmentor fan is mechanically coupled to and driven by the core engine.

8. The method of claim 5 , wherein:
the third thrust to total power ratio is greater than the second thrust to total power ratio for a first set of flight conditions; and
the second thrust to total power ratio is greater than the third thrust to total power ratio for a second set of flight conditions.

9. The method of claim 8 , wherein:
the first set of flight conditions comprises takeoff; and
the second set of flight conditions comprises climb out.

10. The method of claim 5 , further comprising varying the first thrust to total power ratio, the second thrust to total power ratio, and the third thrust to total power.

11. The method of claim 5 , further comprising flow vectoring a flow downstream of the core engine, the ducted fan, or the augmentor fan.

12. The method of claim 5 , further comprising:
providing a first mass flow stream from the augmentor fan;
providing a second mass flow stream from the ducted fan; and
providing a third mass flow stream from the core engine,
wherein the first mass flow stream circumscribes the second mass flow stream and the second mass flow stream circumscribes the third mass flow stream.

13. The method of claim 6 , further comprising varying, based on an optimization parameter, a pitch angle of the plurality of augmentor fan blades to provide angles of attack along a span of the plurality of augmentor fan blades.

14. The method of claim 13 , further comprising determining the optimization parameter by measuring at least one parameter selected from a group consisting of: an aerodynamic efficiency, a fuel efficiency, a takeoff performance, a climb performance, a cruise performance, a performance in descending flight, and a reverse thrust performance.

15. The method of claim 13 , further comprising determining the optimization parameter by measuring at least one parameter selected from a group consisting of: a community noise and a cabin noise.

16. The method of claim 13 , further comprising determining the optimization parameter by measuring a power division between the augmentor fan, the ducted fan, and the core engine.

17. The method of claim 5 , wherein a tip of each of the plurality of augmentor fan blades is coupled to an augmentor fan tip ring encircling all of the plurality of augmentor fan blades, and wherein the method further comprises rotating the augmentor fan tip ring with the augmentor fan.

18. A method of generating thrust with an aircraft propulsor having an augmentor fan, a core engine, and a ducted fan, the method comprising
providing thrust from the core engine at a first thrust to total power ratio;
providing thrust from the ducted fan at a second thrust to total power ratio;
providing thrust from the augmentor fan at a third thrust to total power ratio, wherein the augmentor fan comprises a plurality of unducted propeller blades aft of the ducted fan;
providing a first mass flow stream from the augmentor fan;
providing a second mass flow stream from the ducted fan; and
providing a third mass flow stream from the core engine,
wherein the second mass flow stream is circumscribed by the first mass flow stream and the third mass flow stream is circumscribed by the second mass flow stream.

19. The method of claim 18 , wherein the ducted fan comprises a plurality of ducted fan blades circumferentially contained by a fan cowl,
wherein the augmentor fan comprises a plurality of augmentor fan blades arranged circumferentially around an augmentor hub, and
wherein the augmentor hub substantially surrounds an inner perimeter of the fan cowl and is configured to rotate separately from the ducted fan.

Assignees

• Boeing Co

Inventors

• Sankrithi Mithra M K V
• Seidel Gerhard E
• Prichard Alan K
• Moore Matthew

Classifications

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2220/325

  to drive unshrouded, high solidity propeller · CPC title

• B64D2027/026

  Operations & Transport · mapped topic

• F02K3/077 Primary

  the plant being of the multiple flow type, i.e. having three or more flows · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title