Gas turbine for aircraft propulsion - has axial alignment of high pressure shaft maintained by electrical servo system

摘要

The aircraft gas turbine has a high pressure turbine driving a high pressure compressor and a low pressure turbine driving a low pressure fan. Part of the fan discharge enters the high pressure compressor and part forms the propulsive thrust. The combustion chambers have outlet nozzle directing gas into the high pressure turbine. The nozzles are held on a support ring which carries an annular electrode. The turbine disc carries a similar electrode. The capacitance between the electrodes is measured and controls a servomotor. This drives a hydraulic valve which regulates the admission of oil to a piston which displaces the high pressure shaft axially.