LIFT FAN SYSTEM

• US 20100193643A1
• Filed: 12/21/2009
• Published: 08/05/2010
• Est. Priority Date: 12/31/2008
• Status: Abandoned Application

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Inventors: Sidelkovskiy, Dmitriy B., Barlow, Andrew
• Application Number:
  US12/643,745
• Publication Number:
  US 20100193643A1
• Time in Patent Office: Days
• US Class Current: 244/23.00B
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage

Abstract

Embodiments of the present invention include a system, e.g., for a short takeoff and vertical landing (STOVL) aircraft. The system includes a power generator, such as a gas turbine engine; a lift fan powered by the power generator; and includes two or more nozzles in fluid communication with the lift fan.

Claims

1. A system, comprising:

a power generator; and

a lift fan system, wherein said lift fan system includes;

a lift fan coupled to and driven by said power generator, wherein said lift fan is adapted for mounting to an aircraft and is structured to pressurize air;

a main nozzle in fluid communication with said lift fan and adapted to discharge a first portion of pressurized air from said lift fan to provide direct lift to said aircraft; and

an auxiliary nozzle in fluid communication with said lift fan and adapted to discharge a second portion of pressurized air from said lift fan to provide auxiliary thrust.

2. The system of claim 1, wherein said lift fan system further includes a valve structured to regulate said second portion of pressurized air discharged from said auxiliary nozzle.

3. The system of claim 1, wherein said lift fan system further includes a main duct and an auxiliary duct, and wherein:

said main duct is fluidly disposed between said lift fan and said main nozzle, said main duct being structured to direct said first portion of pressurized air to said main nozzle; and

said auxiliary duct is fluidly disposed between said lift fan and said second nozzle, said auxiliary duct being structured to direct said second portion of pressurized air to said auxiliary nozzle.

4. The system of claim 3, wherein said auxiliary duct is in fluid communication with said lift fan via said main duct.

5. The system of claim 1, wherein said lift fan system further includes an other auxiliary nozzle in fluid communication with said lift fan, and wherein said other auxiliary nozzle is adapted to discharge a third portion of pressurized air from said lift fan to provide additional auxiliary thrust.

6. The system of claim 5, wherein said lift fan system further includes a main duct and an auxiliary duct, and wherein:

said main duct is fluidly disposed between said lift fan and said main nozzle, and wherein said main duct is structured to direct said first portion of pressurized air to said main nozzle; and

said auxiliary duct is fluidly disposed between said lift fan, said auxiliary nozzle and said other auxiliary nozzle;

wherein said auxiliary duct is structured to channel said second portion of pressurized air to said auxiliary nozzle; and

wherein said auxiliary duct is structured to channel said third portion of pressurized air to said other auxiliary nozzle.

7. The system of claim 6, wherein said auxiliary duct is fluidly disposed between said main duct, said auxiliary nozzle and said other auxiliary nozzle.

8. The system of claim 1, wherein said power generator is a gas turbine engine.

9. A lift fan system, comprising:

a lift fan adapted for installation onboard an aircraft and structured to pressurize air;

a first nozzle in fluid communication with said lift fan, wherein said first nozzle is a variable geometry nozzle structured to controllably discharge a first portion of pressurized air from said lift fan; and

a second nozzle in fluid communication with said lift fan, wherein said second nozzle is independent of said first nozzle and structured to controllably discharge a second portion of pressurized air.

10. The lift fan system of claim 9, further comprising a valve structured to regulate said second portion of said pressurized air discharged from said second nozzle.

11. The lift fan system of claim, 9, further comprising a first duct fluidly coupling said lift fan with said first nozzle and said second nozzle.

12. The lift fan system of claim 11, further comprising a second duct fluidly coupling said first duct with said second nozzle.

13. The lift fan system of claim 12, wherein said second duct includes a first end and a second end;

wherein said first end is adjacent to said first duct and said second end is opposite said first end and adjacent to said second nozzle, further comprising a valve structured to regulate said second portion of pressurized air discharged from said second nozzle, wherein said valve is positioned adjacent to said first end.

14. The lift fan system of claim 12, wherein said second duct includes a first end and a second end, said first end being adjacent to said first duct and said second end being opposite said first end and adjacent to said second nozzle, further comprising a valve structured to regulate said second portion of said pressurized air discharged from said second nozzle, said valve being positioned adjacent said second end.

15. The lift fan system of claim 9, wherein said second nozzle is perimetrically disposed around said first nozzle.

16. The lift fan system of claim 9, wherein said lift fan has a substantially vertical axis of rotation.

17. A lift fan system, comprising:

a lift fan adapted for installation onboard an aircraft and structured to pressurize air;

means for providing direct lift thrust using a first portion of pressurized air received from said lift fan; and

means for providing auxiliary thrust using a second portion of pressurized air.

18. The lift fan system of claim 17, wherein said means for providing direct lift thrust includes means for discharging said first portion of pressurized air.

19. The lift fan system of claim 17, wherein said means for providing auxiliary thrust includes means for discharging said second portion of pressurized air.

20. The lift fan system of claim 19, wherein said means for providing auxiliary thrust includes means for ducting said second portion of pressurized air from said lift fan to said means for discharging.

21. The lift fan system of claim 19, wherein said means for providing auxiliary thrust includes means for regulating said second portion of pressurized air.