Gas turbine rapid response clearance control system with annular piston

Patent metadata

Field	Value
Publication number	US-10815813-B2
Application number	US-201414903836-A
Country	US
Kind code	B2
Filing date	May 9, 2014
Priority date	Jul 11, 2013
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

An active clearance control system for a gas turbine engine includes an annular piston with a multiple of piston lift lugs. A method of active blade tip clearance control for a gas turbine engine includes translating axial movement of an annular piston to radial movement of a multiple of blade outer air seal segments.

First claim

What is claimed is:

1. An active clearance control system for a gas turbine engine having a central longitudinal engine axis, the system comprising:
a single annular piston configured to move axially and that radially surrounds the central longitudinal engine axis and that includes an annular piston face that radially surrounds the central longitudinal engine axis and includes a multiple of piston lift lugs, wherein said multiple of piston lift lugs extend from said annular piston toward the central longitudinal engine axis
a full-hoop mount ring that contains said single annular piston; and
a pneumatic subsystem in communication with said full-hoop mount ring thru a valve to operate said single annular piston in response to a control subsystem.

2. The system as recited in claim 1 , further comprising a multiple of blade outer air seal segments, each of said multiple of piston lift lugs engaged with one of said multiple of blade outer air seal segments.

3. The system as recited in claim 2 , wherein said multiple of piston lift lugs translate axial movement of said single annular piston to radial movement of said multiple of blade outer air seal segments.

4. The system as recited in claim 3 , wherein each of said multiple of blade outer air seal segments include a blade outer air seal lift lug engaged with one of said multiple of piston lift lugs at a ramped interface.

5. The system as recited in claim 3 , wherein each of said multiple of blade outer air seal segments include a blade outer air seal lift lug engaged with one of said multiple of piston lift lugs through a link.

6. The system as recited in claim 1 , further comprising a multiple of annular piston ring seals mounted to said single annular piston to seal said single annular piston within said full-hoop mount ring.

7. The system as recited in claim 6 , wherein said single annular piston includes a multiple of piston faces.

8. The system as recited in claim 7 , wherein said multiple of piston faces includes a first piston face, a second piston face and a third piston face, at least one piston face pass thru in said first piston face and said second piston face.

9. The system as recited in claim 8 , wherein said first piston face, said second piston face and said third piston face are sealed by said multiple of annular piston ring seals.

10. The system as recited in claim 1 , wherein said full-hoop mount ring supports a multiple of blade outer air seal segments.

11. The system as recited in claim 10 , wherein each of said multiple of blade outer air seal segments include a lift lug engaged with one of said multiple of piston lift lugs.

12. The system as recited in claim 11 , wherein each of said multiple of blade outer air seal segments includes a forward hook and an aft hook which respectively cooperate with a forward hook and an aft hook of said full-hoop mount ring.

13. The system as recited in claim 12 , wherein said lift lug is located axially between said forward hook and said aft hook of each of said multiple of blade outer air seal segments.

14. The system of claim 1 , where the valve comprises a three-way valve.

15. A method of active blade tip clearance control for a gas turbine engine having a central longitudinal engine axis, the method comprising:
translating axial movement of a single annular piston that radially surrounds the central longitudinal engine axis to radial movement of a multiple of blade outer air seal segments;
supporting each of the multiple of blade outer air seal segments with a full-hoop mount ring that contains the single annular piston; and
pneumatically pressurizing the full-hoop mount ring to drive the single annular piston and lift the multiple of blade outer air seal segments.

16. The method as recited in claim 15 , further comprising lifting the multiple of blade outer air seal segments with a ramp interface between a multiple of piston lift lugs that radially extend from the single annular piston and a lift lug on each of the multiple of blade outer air seal segments.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Blaney Ken F
• Jarochym Christopher M

Classifications

• F01D11/22 Primary

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

• F05D2260/56

  using cams or eccentrics · CPC title

• F05D2270/65

  Pneumatic actuators · CPC title

• F05D2250/232

  conical · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title