초록

A method for controlling radial clearance in a gas turbine engine (10) uses a mathematical algorithm to synthesize the current clearance d202) to a schedule of desired clearance (206) for closing d44) as required to avoid rubbing between the rotating blade tips and surrounding shroud.

대표청구항 ▼

A method for modulating the flow of cooling air for reducing the radial clearance between a plurality of rotating blade tips and a surrounding shroud in a gas turbine engine, comprising the steps of: measuring engine operating parameters, including high rotor speed, low rotor speed, low compressor i

A method for modulating the flow of cooling air for reducing the radial clearance between a plurality of rotating blade tips and a surrounding shroud in a gas turbine engine, comprising the steps of: measuring engine operating parameters, including high rotor speed, low rotor speed, low compressor inlet temperature, low compressor outlet temperature and low compressor inlet pressure, determining, responsive to the measured engine operating parameters, a flow parameter m such that [Figure] determining, responsive to the measured engine parameters, a current estimated clearance dddG′case-G′rotor-Gw(N2) wherein the rate of change of G′case and G′rotor per unit time are determined by the equations: [Figure] [Figure] wherein h(ff