Pratt-whitney Canada Corp

Hytham Mokhtar

James Robert Jarvo

Cédric Saintignan

Patrick Manoukian

Michael Paul Smith

Daniel Arnone

Fuel systems of gas turbine engines of aircraft, and associated methods are provided. The fuel systems and methods can permit reverse purging of one or more fuel manifolds of a gas turbine engine to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds fluidly connectable to a combustor of the gas turbine engine. A valve is operatively disposed between the second fuel manifold and a fuel supply line for controlling fuel supply to the second fuel manifold. A reservoir includes a movable piston disposed therein and dividing the reservoir into a first chamber and a second chamber. The first chamber is fluidly connectable to the fuel supply line or to a fuel purge line via the valve. The second chamber is in fluid communication with the second fuel manifold to receive residual fuel from the second fuel manifold.

Systems and methods for purging a fuel manifold of a gas turbine engine

A method of operating a gas turbine engine having a bleed air system with a switching valve, operable to switch between multiple air sources depending on an operating mode of the gas turbine engine (e.g. a motive powered mode or a standby mode), is described. The method includes operating the switching valve to provide pressurized air from a selected one or more of the multiple air sources to a cavity of the gas turbine engine having seals, and testing the switching valve to determine if the switching valve is functioning normally or abnormally. The switching valve is functioning normally when operable to switch between the multiple air sources and is functioning abnormally when switching between the multiple air sources is not possible. If the switching valve is determined to be functioning abnormally, the gas turbine engine is controlled to prevent a change of the operating mode.

Growing community of inventors

Pointe-Claire, Canada

Hytham Mokhtar