Pratt-whitney Canada Corp

Guorong Yan

Mark Cunningham

Franco Di Paola

Philippe Beauchesne-Martel

Richard Ivakitch

Oleg Iskra

Damien Le Pape

An aircraft engine comprises an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine, to an outlet within the aircraft engine. At least one strut has a leading edge and a trailing edge and extends across at least part of the air inlet duct. The at least one strut has a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage.

Air inlet strut for aircraft engine

An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

Turbo-shaft ejector with flow guide ring

An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.

Inertial particle separator for aircraft engine

Gas turbine engine ejector

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Montreal, Canada

Guorong Yan