Turbine blade tip clearance control

Patent metadata

Field	Value
Publication number	US-9644490-B2
Application number	US-201615019189-A
Country	US
Kind code	B2
Filing date	Feb 9, 2016
Priority date	Mar 31, 2010
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

An aircraft engine according to an example of the present disclosure includes, among other things, a high pressure turbine having a blade, an engine casing disposed about the blade, a shield disposed around the casing adjacent to the blade and creating an area between the shield and the casing, and a gate disposed along the shield. The gate is rotatable about the engine casing between an opened position and a closed position for selectively controlling entry of cooling air into the area. A method of cooling an engine is also disclosed.

First claim

What is claimed is:

1. An aircraft engine for use in a fighter jet, said aircraft engine comprising:
a high pressure turbine having a blade;
an engine casing disposed about said blade;
a shield disposed around said casing adjacent to said blade and creating an area between said shield and said casing;
a gate disposed along said shield, said gate rotatable about said engine casing between an opened position and a closed position for selectively controlling entry of cooling air into said area.

2. The aircraft engine of claim 1 , wherein said gate is configured to be partially open between the opened and closed positions when said engine is being operated in a steady state.

3. The aircraft engine of claim 1 , wherein said gate is built into a front of said shield.

4. The aircraft engine of claim 1 , wherein said shield defines an opening, said gate comprises a strap having a slot, said strap being movable relative to said opening such that said slot and said opening may be in register with each other.

5. The aircraft engine of claim 4 , wherein said opening is disposed in a face of said shield, said face extending in a radial direction relative to an axis of said high pressure turbine.

6. The aircraft engine of claim 5 , wherein said face has a race therein for holding said strap.

7. The aircraft engine of claim 6 , wherein said strap is moveable within said race for moving said slot of said strap into and out of register with said opening.

8. The aircraft engine of claim 5 , wherein an outer wall of said shield slopes radially inward from said face relative to said axis.

9. The aircraft engine of claim 5 , wherein said strap is moveable about said axis.

10. The aircraft engine of claim 5 , wherein said opening is one of a plurality of openings circumferentially distributed about said face, and said slot is one of a plurality of slots circumferentially distributed about said strap, each of said plurality of slots corresponding to one of said plurality of openings.

11. The aircraft engine of claim 4 , wherein said shield and said strap form an annulus.

12. The aircraft engine of claim 4 , wherein said shield defines a duct opening configured to receive a boss, said boss defining a passage configured to communicate cooling airflow to said high pressure turbine, said boss fluidly separating said passage and said area.

13. The aircraft engine of claim 1 , comprising a controller coupled to an actuator, said controller operable to cause said actuator to selectively move said gate relative to said shield.

14. The aircraft engine of claim 1 , wherein said gate is configured to be located in said closed position when said engine is maneuvering, and said gate is configured to be located in said opened position when said engine is cruising.

15. A cooling system for an aircraft engine for use in a fighter jet, the aircraft engine having a high pressure turbine having a blade and an engine casing disposed about said blade, said cooling system comprising:
a shield disposed around said casing adjacent to said blade and for creating an area between said shield and said casing; and
a gate disposed along said shield, said gate rotatable about said engine casing between an opened position and a closed position for selectively controlling entry of cooling air into said area, said gate disposed about said casing.

16. The cooling system of claim 15 , wherein said gate is adapted to be partially open between the opened and closed positions when said engine is being operated in a steady state.

17. The cooling system of claim 15 , wherein said gate is built into a front of said shield.

18. The cooling system of claim 15 , wherein said shield defines an opening, said gate comprises a strap having a slot, said strap being movable relative to said opening such that said slot and said opening are in register with each other.

19. The cooling system of claim 18 , wherein said opening is disposed in a front of said shield.

20. The cooling system of claim 19 , wherein said front has a race therein for holding said strap, and said strap is moveable within said race for moving said slot of said strap into and out of register with said opening.

21. The cooling system of claim 15 , wherein said gate is configured to be located in said closed position when said engine is in a maneuvering mode, said gate is configured to be located in said opened position when said engine is in a cruising mode.

22. A method of cooling an engine used in a fighter jet comprising:
providing a shield around a casing adjacent to a high pressure turbine blade in said engine, said shield including a radially extending face;
providing a gate adjacent to said face, the gate moveable between an opened position and a closed position; and
moving said gate about said engine casing toward the opened position such that cooling air is delivered to an area between said shield and said casing to shrink said casing around said blade.

23. The method of claim 22 , further comprising:
moving said gate from the opened position toward the closed position to partially block cooling air from entering said area when operation of said engine changes between a cruise mode and a steady state mode.

24. The method of claim 22 , further comprising:
moving said gate to the closed position to fully block cooling air from entering said area when said engine is in a maneuvering mode.

Assignees

• United Technologies Corp

Inventors

• Joe Christopher R
• Ward Daniel A

Classifications

• F05D2260/234

  of the generator by compressor inlet air · CPC title

• F01D25/14

  Casings modified therefor (double casings F01D25/26) · CPC title

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title