Actuator control

Patent metadata

Field	Value
Publication number	US-10662801-B2
Application number	US-201615218511-A
Country	US
Kind code	B2
Filing date	Jul 25, 2016
Priority date	Aug 21, 2015
Publication date	May 26, 2020
Grant date	May 26, 2020

Abstract

An actuation system 100 comprises a fluid supply 130 that is fluidly connected to a position control actuator 110. The output of the position control actuator is determined by the fluid supply. The fluid supply is controlled by a piezoelectric actuator 150.

First claim

I claim:

1. A gas turbine engine comprising an actuation system, the actuation system comprising:
a fluid supply conduit;
a piezoelectric actuator; and
a position control actuator, wherein:
the fluid supply conduit is in fluid communication with the position control actuator, such that the position control actuator can be controlled by the supply of fluid thereto,
the piezoelectric actuator includes piezoelectric material positioned in the fluid supply conduit, such that the flow in the fluid supply conduit can be regulated by the piezoelectric actuator,
the piezoelectric material is transformable between a first configuration and second configuration, and
when the piezoelectric material is in the first configuration, fluid in the fluid supply conduit can pass from an upstream side of the piezoelectric actuator to a downstream side of the piezoelectric actuator, whereas in the second configuration of the piezoelectric material, fluid is blocked by the piezoelectric material from passing from the upstream side to the downstream side of the piezoelectric actuator.

2. The gas turbine engine according to claim 1 , further comprising an actuator position control system arranged to control the excitation of the piezoelectric actuator based on the position of the position control actuator.

3. The gas turbine engine according to claim 2 , wherein the actuator position control system comprises:
a position sensor arranged to sense the position of the position control actuator; and
a control unit arranged to receive a signal representative of the sensed position from the position sensor, and to send an excitation signal to the piezoelectric actuator based at least in part on the sensed position of the position control actuator.

4. The gas turbine engine according to claim 1 , wherein in the second configuration the fluid conduit is open at the piezoelectric actuator so as to allow fluid that is in communication with the position control actuator to pass out of the fluid supply conduit.

5. The gas turbine engine according to claim 1 , wherein:
the position control actuator comprises a piston that is contained and moveable within a chamber; and
the fluid supply conduit is fluidly connected to the chamber.

6. The gas turbine engine according to claim 5 , wherein:
the chamber is separated by the piston into an actuator retract chamber and an actuator extend chamber;
the fluid supply conduit is fluidly connected to one of the actuator retract chamber and the actuator extend chamber; and
a resilient member is provided in the other of the actuator retract chamber and the actuator extend chamber and arranged to act on the piston against the fluid pressure of the fluid supplied by the fluid supply conduit.

7. The gas turbine engine according to claim 5 , wherein:
the chamber is separated by the piston into an actuator retract chamber and an actuator extend chamber;
the fluid supply conduit is fluidly connected to one of the actuator retract chamber and the actuator extend chamber; and
a further fluid supply conduit is fluidly connected to the other of the actuator retract chamber and the actuator extend chamber, the further fluid supply conduit being provided with a further piezoelectric actuator, such that the flow in the further fluid supply conduit can be regulated by the further piezoelectric actuator.

8. The gas turbine engine according to claim 1 , further comprising a high pressure gas supply, wherein:
the fluid supply conduit is connected to the high pressure gas supply; and
the piezoelectric actuator is positioned between the high pressure gas supply and the position control actuator.

9. The gas turbine engine according to claim 8 , wherein the high pressure gas supply is a compressor of a gas turbine engine.

10. The gas turbine engine according to claim 1 , wherein the position control actuator is connected to a valve for controlling a separate fluid supply to that of fluid supply conduit.

11. The gas turbine engine according to claim 1 , further comprising a turbine case cooling system, wherein the position control actuator is connected to a valve for regulating the flow of cooling fluid to a turbine case.

12. The gas turbine engine according to claim 1 , further comprising a variable vane control system, wherein the position control actuator is used to control the position of the variable vanes.

Assignees

• Rolls Royce Plc

Inventors

• Sutherland Roger A

Classifications

• F01D17/16

  by means of nozzle vanes · CPC title

• F15B2211/7052

  Single-acting output members · CPC title

• F15B2211/3057

  having two valves, one for each port of a double-acting output member · CPC title

• F15B2211/7053

  Double-acting output members · CPC title

• F01D11/24

  by selectively cooling-heating stator or rotor components · CPC title