Patent ID: 8668431
Filing Date: 2014-03-11
Classification: F01D,F02C,F05D,Y02T

Abstract:
1. 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 cool, low pressure air in contact with and substantially parallel to an exterior surface of the engine core casing circumscribing the turbine; and directing a flow of relatively hot, pressurized air in contact with and orthogonal to the exterior surface of the engine core casing circumscribing the turbine to displace the flow of relatively cool, low pressure air away from contact with the exterior of the engine core casing.