System and method for actuating gas turbine engine components using integrated jamming devices

Patent metadata

Field	Value
Publication number	US-10502086-B2
Application number	US-201615071264-A
Country	US
Kind code	B2
Filing date	Mar 16, 2016
Priority date	Mar 16, 2016
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.

First claim

What is claimed is:

1. A system for actuating components of a gas turbine engine, the system comprising:
a turbine component incorporating a jamming device, the jamming device including a bladder and a jammable media contained within the bladder, the jammable media being jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder, the jamming device forms a portion of a side of the turbine component; and
a fluid coupling in fluid communication with the bladder,
wherein at least a portion of the turbine component is located at a first position when the jammable media is in the unjammed state, and wherein the at least a portion of the turbine component is located at a second position when the jammable media is in the jammed state.

2. The system of claim 1 , wherein the at least a portion of the turbine component is actuated from the first position to the second position as the fluid is at least partially evacuated from the bladder to transition the jammable media from the unjammed state to the jammed state.

3. The system of claim 1 , wherein the bladder is formed from a fiber-reinforced composite, the fiber-reinforced composite including an elastic matrix material.

4. The system of claim 1 , further comprising a negative pressure source in fluid communication with the fluid coupling, the negative pressure source being configured to apply a vacuum to the fluid coupling such that the fluid contained within the bladder is at least partially evacuated to transition the jammable media to the jammed state.

5. The system of claim 1 , wherein the jammable media is transitioned from the unjammed state to the jammed state to maintain the at least a portion of the turbine component at the second position.

6. The system of claim 1 , wherein the turbine component corresponds to an airfoil of the gas turbine engine, the airfoil including a first side and a second side extending between a leading edge and a trailing edge, the jamming device being positioned on one of the first side or the second side of the airfoil.

7. The system of claim 6 , wherein, when the at least a portion of the airfoil is actuated from the first position to the second position, one of the trailing edge or the leading edge is moved relative to the other of the trailing edge or the leading edge.

8. The system of claim 6 , wherein the jamming device is positioned on the first side of the airfoil, the airfoil further comprising a flexible joint extending from the jamming device to the second side of the airfoil.

9. The system of claim 1 , wherein the turbine component corresponds to a flow splitter positioned adjacent to a compressor inlet of the gas turbine engine.

10. The system of claim 9 , wherein the at least a portion of the flow splitter is actuated from the first position to the second position to vary an airflow through the compressor inlet.

11. The system of claim 1 , wherein the turbine component corresponds to a valve actuator coupled to a valve of the gas turbine engine, the valve actuator including an actuator arm, the actuator arm being moved to the first position to actuate the valve to one of an opened position or a closed position, the actuator arm being moved to the second position to actuate valve to the other of the opened position or the closed position.

12. The system of claim 11 , wherein the valve actuator further includes a fixed jamming surface, the actuator arm being configured to be jammed against the fixed jamming surface when the jammable media is transitioned to the jammed state.

13. The system of claim 11 , wherein the valve corresponds to a variable bleed valve of the gas turbine engine.

14. A turbine component for a gas turbine engine, the turbine component comprising:
a body;
a jamming device provided in operative association with the body, the jamming device including a bladder and a jammable media contained within the bladder, the jammable media being jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder, the jamming device forms a portion of a side of the body; and
wherein at least a portion of the body is located at a first position when the jammable media is in the unjammed state, and wherein the at least a portion of the body is located at a second position when the jammable media is in the jammed state.

15. The turbine component of claim 14 , wherein the at least a portion of the body is actuated from the first position to the second position as the fluid is at least partially evacuated from the bladder to transition the jammable media from the unjammed state to the jammed state.

16. The turbine component of claim 14 , wherein the body forms all or part of one of an airfoil, a flow splitter or a valve actuator of the gas turbine engine.

17. The turbine component of claim 14 , wherein the jammable media is transitioned from the unjammed state to the jammed state to maintain the at least a portion of the turbine component at the second position.

18. A method for actuating a turbine component of a gas turbine engine, the turbine component incorporating a jamming device including a bladder and a jammable media contained within the bladder, the method comprising:
directing fluid into the bladder such that the jammable media is placed in an unjammed state, at least a portion of the turbine component being located at a first position when the jammable media is in the unjammed state, the jamming device forms a portion of a side of the turbine component; and
adjusting a pressure being applied to the jamming device such that the fluid is at least partially evacuated from the bladder to actuate the at least a portion of the turbine component from the first position to a second position as the jammable media transitions from the unjammed state to a jammed state.

19. The method of claim 18 , wherein adjusting the pressure being applied to the jamming device comprises applying a negative pressure to the jamming device via a fluid coupling provided in fluid communication with the bladder.

20. The method of claim 18 , further comprising increasing the pressure being applied to the jamming device such that the evacuated fluid is redirected back into the bladder to actuate the at least a portion of the turbine component from the second position back to the first position as the jammable media transitions from the jammed state to the unjammed state.

Assignees

• Gen Electric

Inventors

• Sellinger Aaron Todd
• Kray Nicholas Joseph
• Lin Wendy Wenling

Classifications

• F05D2300/501

  Elasticity · CPC title

• F05D2250/90

  Variable geometry · CPC title

• F01D5/148

  Blades with variable camber, e.g. by ejection of fluid · CPC title

• F05D2270/64

  Hydraulic actuators · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title