Optimization of downstream open fan propeller position and placement of acoustic sensors

Patent metadata

Field	Value
Publication number	US-9637221-B2
Application number	US-201314079550-A
Country	US
Kind code	B2
Filing date	Nov 13, 2013
Priority date	Dec 21, 2009
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

A method and apparatus for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft is provided. A diameter of the propeller is set to be at a first diameter during at least a portion of a first flight condition of the aircraft. The diameter of the propeller is set to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft.

First claim

What is claimed is:

1. A method for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft, comprising:
setting a diameter of the propeller to be at a first diameter during at least a portion of a first flight condition of the aircraft; and
setting the diameter of the propeller to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft, wherein setting is performed using at least one electric motor.

2. The method of claim 1 , wherein the propeller comprises a downstream propeller of the contra-rotation open fan (CROF) engine.

3. The method of claim 2 , wherein the first flight condition comprises a take-off and climb flight condition, and wherein setting the diameter of the downstream propeller to be at the first diameter during the at least a portion of the first flight condition of the aircraft comprises:
setting the diameter of the downstream propeller to be at a first retracted diameter that is less than a diameter of an upstream propeller of the contra-rotation open fan CROF engine during at least a portion of the take-off and climb flight condition.

4. The method of claim 3 , wherein the second flight condition comprises a cruising flight condition, and wherein setting the diameter of the downstream propeller to be at the second diameter, different from the first diameter, during the at least a portion of the second flight condition of the aircraft, comprises:
setting the diameter of the downstream propeller to be at a second extended diameter that is substantially equal to the diameter of the upstream propeller of the contra-rotation open fan CROF engine during at least a portion of the cruising flight condition.

5. The method of claim 3 , wherein setting the diameter of the downstream propeller to be at the first retracted diameter comprises:
setting the diameter of the downstream propeller at the first retracted diameter prior to a takeoff and climb flight condition.

6. The method of claim 4 , wherein setting the diameter of the downstream propeller to be at the second extended diameter that is substantially equal to the diameter of the upstream propeller of the contra-rotation open fan CROF engine during the at least a portion of the cruising flight condition, comprises:
increasing the diameter of the downstream propeller during the at least a portion of the takeoff and climb flight condition.

7. The method of claim 6 , wherein increasing the diameter of the downstream propeller during the at least a portion of the takeoff and climb flight condition comprises:
increasing the diameter of the downstream propeller as a function of a speed of the aircraft during the at least a portion of the takeoff and climb flight condition.

8. The method of claim 6 , wherein the downstream propeller comprises a plurality of propeller blades, and wherein:
setting a diameter of the downstream propeller to be at the first retracted diameter comprises setting a length of each propeller blade of the plurality of propeller blades to be at a first retracted length; and
increasing the diameter of the downstream propeller during the at least a portion of the takeoff and climb flight condition comprises increasing the length of each propeller blade of the plurality of propeller blades during the at least a portion of the takeoff and climb flight condition.

9. The method according to claim 8 further comprising:
equalizing the increasing of the length of each propeller blade of the plurality of propeller blades such that the length of each propeller blade of the plurality of propeller blades increases in length in unison and each propeller blade of the plurality of propeller blades are always at substantially a same length.

10. The method according to claim 1 , further comprising:
adjusting a pitch of a propeller blade that is a component of a variable diameter system.

11. An apparatus, comprising:
a contra-rotation open fan (CROF) engine having a plurality of propellers; and
an electrically powered actuator for setting a diameter of a propeller of the plurality of propellers at a first diameter during at least a portion of a first flight condition of an aircraft, and for setting the diameter of the propeller to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft.

12. The apparatus of claim 11 , wherein the propeller comprises a downstream propeller of the plurality of propellers.

13. The apparatus of claim 12 , wherein the first flight condition comprises a take off and climb flight condition, and wherein the first diameter comprises a first retracted diameter that is less than a diameter of an upstream propeller of the contra-rotation open fan (CROF) engine.

14. The apparatus of claim 13 , wherein the second flight condition comprises a cruising flight condition, and wherein the second diameter comprises a second extended diameter that is substantially equal to the diameter of the upstream propeller of the contra-rotation open fan (CROF) engine.

15. The apparatus of claim 13 , wherein the actuator setting the diameter of the downstream propeller to be at the second diameter, different from the first diameter, during the at least a portion of the second flight condition of the aircraft, comprises:
the actuator increasing the diameter of the downstream propeller during at least a portion of the takeoff and climb flight condition.

16. The apparatus of claim 15 , wherein the actuator increasing the diameter of the downstream propeller during the at least a portion of the takeoff and climb flight condition, comprises:
the actuator increasing the diameter of the downstream propeller as a function of a speed of the aircraft during the at least a portion of the takeoff and climb flight condition.

17. The apparatus of claim 12 , wherein the downstream propeller comprises a plurality of propeller blades, and wherein the actuator comprises a plurality of blade root housings, each blade actuator of the plurality of blade root housings controlling a length of a propeller blade of the plurality of propeller blades from a first retracted length to a second extended length.

18. The apparatus of claim 17 further comprising:
a blade equalizer system for ensuring that the length of each propeller blade of the plurality of propeller blades increases in length in unison and that each propeller blade of the plurality of propeller blades are always at substantially a same length.

19. The apparatus of claim 18 , wherein the blade equalizer comprises:
a first plate having a plurality of lateral slots;
a second plate having a plurality of spiral curved slots aligned with the plurality of lateral slots to form a plurality of aligned slots;
a pin connected to each blade actuator and extending through a respective one of the plurality of aligned slots; and
a pitch control system for controlling a pitch of each propeller blade of the plurality of propeller blades, wherein the pitch control system comprises a rotatable plate connected to each blade actuator of the plurality of blade actuators.

20. An apparatus, comprising:
a contra-rotation open fan (CROF) engine having a plurality of propellers;
an electric-powered actuator configured to set a diameter of propellers at a first diameter during at least a portion of a first flight condition on an aircraft, and for setting the diameter of the propeller to be at a second diameter, different from the first diam

Assignees

• Boeing Co

Inventors

• Moore Matthew David
• Boren Kelly L
• Langtry Robin Blair

Classifications

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64C11/003 Primary

  Variable-diameter propellers; Mechanisms therefor · CPC title

• B64C11/48

  Units of two or more coaxial propellers · CPC title

• B64D2027/026

  Operations & Transport · mapped topic

• B64D27/026

  comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33) · CPC title