System for modulating turbine blade tip clearance

Patent metadata

Field	Value
Publication number	US-10415419-B2
Application number	US-201715406324-A
Country	US
Kind code	B2
Filing date	Jan 13, 2017
Priority date	Jan 13, 2017
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance between a turbine blade tip and a blade outer air seal (BOAS). Each actuator may be coupled to the BOAS. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. The actuators may be configured to move the BOAS in a radial direction from a first position to a second position to control tip clearance.

First claim

What is claimed is:

1. An actuation control system, comprising:
an actuator comprising an inner shell, an outer shell and a control wire, the outer shell being radially opposite the inner shell, and the control wire being configured to control an actuation of the actuator;
a bias spring coupled to the outer shell of the actuator; and
a blade outer air seal (BOAS) segment coupled to the inner shell of the actuator, wherein the BOAS segment is configured to move from a first position to a second position in response to the actuation from the actuator.

2. The actuation control system of claim 1 , wherein the control wire comprises a shape memory alloy (SMA) wire configured to contract in response to receiving an electrical current, and wherein a contraction of the SMA wire controls the actuation of the actuator.

3. The actuation control system of claim 2 , further comprising a power supply having a controller, wherein the power supply is configured to transmit the electrical current to the control wire in response to the controller determining a tip clearance actuation event.

4. The actuation control system of claim 1 , wherein the actuator is configured to move the BOAS segment a distance of about 0.02 inches (0.508 mm) to about 0.05 inches (1.27 mm).

5. A turbine section of a gas turbine engine, comprising:
a turbine blade having a blade tip;
a blade outer air seal (BOAS);
an actuation control system comprising an actuator having an inner shell, wherein the inner shell is coupled to the BOAS, and wherein the actuator is configured to modulate a tip clearance between the blade tip and the BOAS; and
a bias spring coupled to the inner shell of the actuator between the coupling of the inner shell of the actuator and the BOAS.

6. The turbine section of claim 5 , wherein the actuator is configured to move the BOAS a distance of about 0.02 inches (0.508 mm) to about 0.05 inches (1.27 mm) to control the tip clearance.

7. The turbine section of claim 5 , wherein the actuator comprises an outer shell radially opposite the inner shell, wherein the outer shell is coupled to a radially inner surface of a turbine case.

8. The turbine section of claim 5 , wherein the actuator comprises a control wire configured to control an actuation of the actuator, wherein the control wire comprises a shape memory alloy (SMA) wire configured to contract in response to receiving an electrical current, and wherein a contraction of the SMA wire controls the actuation of the actuator.

9. The turbine section of claim 8 , further comprising a power supply having a controller, wherein the power supply is configured to transmit the electrical current to the control wire in response to the controller determining a tip clearance actuation event.

10. An actuation control system, comprising:
a blade outer air seal (BOAS) segment having a first end opposite a second end;
a first actuator coupled proximate the first end of the BOAS segment;
a second actuator coupled proximate the second end of the BOAS segment, wherein the first actuator is in electrical communication with the second actuator, and wherein the first actuator and the second actuator are configured to move the BOAS segment from a first position to a second position in response to an actuation from the first actuator and the second actuator; and
a bias spring coupled to at least one of a first outer shell of the first actuator, a second outer shell of the second actuator, a first inner shell of the first actuator between the coupling of the first actuator and the BOAS segment, or a second inner shell of the second actuator between the coupling of the second actuator and the BOAS segment.

11. The actuation control system of claim 10 , wherein the first actuator and the second actuator comprise a control wire having a shape memory alloy (SMA) wire configured to contract in response to receiving an electrical current, wherein a contraction of the SMA wire controls the actuation of each actuator.

12. The actuation control system of claim 11 , further comprising a power supply having a controller, wherein the power supply is configured to transmit the electrical current to the control wire in response to the controller determining a tip clearance actuation event.

13. The actuation control system of claim 10 , wherein the first actuator and the second actuator are configured to move the BOAS segment a radial distance of about 0.02 inches (0.508 mm) to about 0.05 inches (1.27 mm).

Assignees

• United Technologies Corp

Inventors

• Sun Fanping
• Chaudhry Zaffir A
• Hoffman Lee A
• Wu Hailing
• Kim Seung Bum
• Mccaffrey Michael G
• Wagner Joel H

Classifications

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/18

  using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title

• F01D11/22 Primary

  by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor · CPC title

• F05D2300/505

  Shape memory behaviour · CPC title

• F05D2250/131

  polygonal · CPC title