Seal clearance control on non-cowled gas turbine engines
AssigneeUnited Technologies Corporation
InventorsDaniel T. Rog, Ronald T. Clawson
Life of this patent
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Abstract
A method for controlling turbine blade tip seal clearance on a non-cowled gas turbine engine includes the step of directing a flow of relatively hot, pressurized air in contact with an exterior surface of the engine core casing circumscribing the turbine. The flow of relatively hot, pressurized air may be selectively directed in contact with the exterior surface of the engine core casing circumscribing the turbine when it is desired to expand the turbine shroud radially outward, such as during transient operation of the gas turbine engine.
Claims11
A method for controlling turbine blade tip seal clearance on a non-cowled gas turbine engine having a compressor, a turbine and an engine core casing, the turbine having a plurality of turbine blades circumscribed by a turbine shroud supporting a plurality of seals in juxtaposition with the tips of the plurality of turbine blades, the method of controlling turbine blade tip seal clearance comprising the step of:
- directing a flow of relatively hot, pressurized air in contact with an exterior surface of the engine core casing circumscribing the turbine.
A method for controlling turbine blade tip seal clearance on a non-cowled gas turbine engine having an engine core casing, an outer casing circumscribing in radially spaced relationship the engine core casing, a fan air duct defined between the engine core casing and the outer casing, a compressor and a turbine, the turbine having a plurality of turbine blades circumscribed by a turbine shroud supporting a plurality of seals in juxtaposition with the tips of the plurality of turbine blades, the method of controlling turbine blade tip seal clearance comprising the steps of:
- during operation of the gas turbine engine in a steady state mode, passing a relatively cool, low pressure air flow through the fan air duct in contact with an exterior surface of the engine core casing circumscribing the turbine;
- and
- during operation of the gas turbine engine in a transient mode, selectively passing a relatively hot, high pressure air flow in contact with the exterior surface of the engine core casing circumscribing the turbine.
Dependencies are inferred from the claim text.