Patent ID: 7909566
Filing Date: 2011-03-22
Classification: F01D,F04D,F05D,Y02T

Abstract:
1. A gas turbine engine with a blade tip clearance control, the engine comprising: a rotor shaft extending along an axis of the engine; a turbine rotor disc having a plurality of turbine rotor blades extending therefrom; a turbine blade tip shroud forming a blade tip gap with the plurality of turbine rotor blades; a compressor rotor disc having a plurality of compressor blades extending therefrom; a rotor shaft bias means to bias the rotor shaft in a direction such that the turbine rotor blade tip clearance increases; a pressure force developed from the engine operation and acting on the compressor and turbine rotor discs to bias the rotor shaft in a direction such that the turbine rotor blade tip clearance decreases; the rotor shaft is a horizontal aligned rotor shaft; and, the rotor shaft bias means is a compression spring.