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 for use in a low-bypass turbofan application has a high pressure turbine having a blade and an engine casing disposed about the blade. A shield is disposed around the casing adjacent to the blade to create an area between the shield and the casing. A gate selectively controls entry of cooling air into the area and may be closed if the engine is maneuvering and may be open if cruising.
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 for selectively controlling entry of cooling air into said area, wherein said gate is closed when said engine is maneuvering, and wherein said gate is open when said engine is cruising.
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 for selectively controlling entry of cooling air into said area, said gate disposed about said casing, wherein said gate is adapted to be closed if said engine is maneuvering, and wherein said gate is open when said engine is cruising.
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;
- and
- moving said gate about said engine casing such that cooling air is delivered to an area between said shield and said casing to shrink said casing around said blade when said engine is in a cruise mode.
Dependencies are inferred from the claim text.