Patent ID: 9476690
Filing Date: 2016-10-25
CPC Classification: F01D,F05D,G01B

Claim Text:
1. A method for controlling clearance between tips of blades of a turbine rotor of a gas turbine aircraft engine and a ring-shaped turbine shroud of a housing surrounding the blades, the method comprising: measuring a temperature using a temperature sensor including a sensitive element laid out in a free space of the aircraft engine during standstill of the aircraft engine on the ground; estimating the clearance based on the measured temperature during the standstill of the aircraft engine on the ground; and controlling at least one of a flow rate and a temperature of air directed towards the housing according to the estimated clearance based on the measured temperature, wherein the standstill is a state of the aircraft engine on the ground in which the aircraft engine is started following a stoppage period of the aircraft engine.