Hydraulic system for an aircraft

Patent metadata

Field	Value
Publication number	US-11072418-B2
Application number	US-201815952767-A
Country	US
Kind code	B2
Filing date	Apr 13, 2018
Priority date	Apr 13, 2018
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

A hydraulic system for an aircraft. The hydraulic system can include a hydraulic actuator that is operatively coupled to a flight control member. Hydraulic fluid is moved through the hydraulic system by an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure, and a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure. The hydraulic system is configured such that the hydraulic fluid returning from the actuator to the engine driven pump can be delivered to the boost pump prior to reaching the engine driven pump.

First claim

What is claimed is:

1. A hydraulic system for an aircraft, the hydraulic system comprising:
a hydraulic actuator that is operatively coupled to a flight control member;
an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure; and
a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure;
a valve positioned upstream from the boost pump and movable between a first valve position in which hydraulic fluid is delivered to the boost pump from the engine driven pump and a second valve position in which hydraulic fluid is delivered to the boost pump from a return line that leads away from the hydraulic actuator; and
wherein hydraulic fluid returning from the actuator to the engine driven pump is delivered to the boost pump prior to reaching the engine driven pump.

2. The hydraulic system of claim 1 , wherein in the first valve position the hydraulic fluid is delivered to the boost pump from just the engine driven pump.

3. The hydraulic system of claim 1 , further comprising an accumulator positioned upstream from the valve to supply hydraulic fluid to the boost pump when the valve is in the second valve position.

4. The hydraulic system of claim 1 , wherein the valve is at the first valve position when a load demand at the actuator is below the first pressure and at the second valve position when the load demand is above the first pressure.

5. The hydraulic system of claim 3 , further comprising a first pressure sensor that detects pressure of the hydraulic fluid at an outlet of the boost pump and one or more second pressure sensors that detects pressure of the hydraulic fluid in the actuator.

6. The hydraulic system of claim 1 , further comprising a return line that extends between the actuator and the engine driven pump to deliver the hydraulic fluid from the actuator to the engine driven pump, and a spare line that extends between the return line and the boost pump to deliver the hydraulic fluid that is returning towards the engine driven pump to the boost pump.

7. The hydraulic system of claim 6 , further comprising a reservoir positioned along the return line between the engine driven pump and the spare line, the reservoir holds hydraulic fluid that has moved along the return line prior to being moved to the engine driven pump.

8. The hydraulic system of claim 1 , wherein the boost pump is an axial piston pump that includes an adjustable swashplate to control a pressure of the hydraulic fluid that is supplied by the boost pump.

9. A hydraulic system for an aircraft, the hydraulic system comprising:
an engine driven pump that delivers hydraulic fluid at a first pressure;
a hydraulic actuator;
a supply line through which the hydraulic fluid is delivered from the engine driven pump to the hydraulic actuator;
a boost pump that delivers the hydraulic fluid to the actuator at a second pressure that is higher than the first pressure;
a return line that returns the hydraulic fluid from the actuator to the engine driven pump; and
a spare line that extends between the return line and the boost pump, the spare line positioned along the return line upstream from the engine driven pump;
wherein at least a portion of the time the hydraulic fluid that is supplied to the boost pump comprises the hydraulic fluid that is returning along the return line from the actuator towards the engine driven pump.

10. The hydraulic system of claim 9 , further comprising a boost line that extends between the boost pump and the actuator to deliver the hydraulic fluid from the boost pump to the actuator, the boost line being different than the supply line.

11. The hydraulic system of claim 9 , further comprising an accumulator positioned upstream from the boost pump to supply hydraulic fluid to the boost pump.

12. The hydraulic system of claim 9 , further comprising a valve positioned upstream of the boost pump and configured between a first valve position in which hydraulic fluid is delivered to the boost pump from just the engine driven pump and a second valve position in which the hydraulic fluid is delivered to the boost pump from the spare line.

13. The hydraulic system of claim 9 , wherein the boost pump is an axial piston pump that includes an adjustable swashplate to control a pressure of the hydraulic fluid is supplied by the boost pump.

14. A method of operating a hydraulic system of an aircraft, the method comprising:
supplying hydraulic fluid at a first pressure from an engine driven pump to an actuator without the hydraulic fluid being supplied with a boost pump with the actuator being operatively connected to a flight control member;
returning the hydraulic fluid from the actuator to the engine driven pump along a return line;
in response to a load pressure demand, supplying hydraulic fluid to the actuator from a boost pump at an elevated pressure that is above the first pressure; and
in response to the load pressure demand, supplying at least a portion of the hydraulic fluid to the boost pump from the return line prior to the hydraulic fluid being returned to the engine driven pump.

15. The method of claim 14 , further comprising in response to the load pressure demand, supplying hydraulic fluid to the boost pump from an accumulator positioned upstream from the boost pump.

16. The method of claim 15 , further comprising in response to the load pressure demand, continuing to supply hydraulic fluid to the boost pump from the engine driven pump.

17. The method of claim 14 , further comprising supplying the boost pump with hydraulic fluid that is supplied from just the engine driven pump when the load pressure demand is below a predetermined amount and supplying the boost pump with hydraulic fluid from just each of an accumulator and the return line in response to determining the load pressure demand is above the predetermined amount.

18. The method of claim 14 , further comprising adjusting an angular position of a swashplate in the boost pump and adjusting a pressure of the hydraulic fluid supplied to the actuator from the boost pump.

19. The method of claim 14 , further comprising changing a shuttle valve from a first valve position, based on the pressure of the hydraulic fluid at the shuttle valve, to a second valve position when the hydraulic system pressure is below a predetermined pressure at the actuator.

20. The method of claim 14 , further comprising delivering hydraulic fluid to the actuator through a single input line that is supplied with hydraulic fluid from both the engine driven pump and the boost pump.

Assignees

• Boeing Co

Inventors

• Fox Michael Thomas
• Howell Eric Anton
• Roach Jeffrey M

Classifications

• F15B1/04 Primary

  Accumulators · CPC title

• Y02T50/40

  Weight reduction · CPC title

• F15B13/06

  for use with two or more servomotors · CPC title

• F15B15/063

  Actuator having both linear and rotary output, i.e. dual action actuator · CPC title

• F15B11/17

  using two or more pumps · CPC title