GAS TURBINE INLET PARTICLE SEPARATOR.

摘要

A gas turbine engine (1) in a helicopter has an air intake separator (4) from which separated particles are removed by an ejector (5), driven by high pressure gas supplied by an auxiliary power unit (6). The invention provides a reduction in fuel and main engine power consumption compared with known systems which drive the ejector (5) with gas bled from the main engine (1). Valve (9) enables ejector (5) to be switched off during high flying, when the separator is not needed.