Gas turbine engine

Claim 1

A turbopropeller gas turbine engine comprising at least one propeller, a gas generator, and intake means, the at least one propeller being positioned upstream of the gas generator, the gas generator comprising a compressor and a gas generator casing, the intake means supplying air to the gas generator being positioned downstream of the at least one propeller, the intake means comprising at least one intake opening formed in the gas generator casing and an associated inlet duct extending from the intake opening to the gas generator, the intake duct including: separating means for removing foreign bodies from the air supplied to the gas generator, the separating means including a separating duct comprising: a mixing duct, connected to said intake duct for receiving foreign bodies, the mixing duct having a tubular wall and having a length to diameter ratio of between two and five; a transition duct connected to said mixing duct, downstream of said mixing duct; an outlet duct connected to said transition duct, downstream of said transition duct, the outlet duct having an outlet opening and being of rectangular cross-section; ejector means to produce a fluid flow through the separating duct for drawing foreign bodies through the separating duct, the ejector means comprising a plurality of equi-spaced ejector nozzles arranged circumferentially in the mixing duct wall, the compressor supplying air to the ejector nozzles to produce a fluid flow through the separating duct, conduit means fluidly interconnecting the compressor and the ejector nozzles for supplying air from the compressor to the ejector nozzles, and a control valve controlling the flow of air from the compressor to the ejector nozzles through the conduit means.