Turbine blade tip clearance control
AssigneeUnited Technologies Corporation
InventorsChristopher R. Joe, Daniel A. Ward
Life of this patent
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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.
Claims24
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.
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.
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.
Dependencies are inferred from the claim text.