Pratt-whitney Canada Corp

Ronald Trumper

Kevin Allan Dooley

Joseph Horace Brand

Stephen Arthur Anderson

Richard Ullyott

Guy Bouchard

Michel Bellerose

Bruce Fielding

Gary Weir

Isabelle Bacon

Stephan Arthur Anderson

A hybrid gas compressor has at least one rotor and shroud which define a compressor gas path extending from an inlet to an outlet. The compressor includes at least two compression stages and one diffusion stage between the inlet and outlet, the compression stages including respective circumferential arrays of blades extending from the rotor and the diffusion stage including a circumferential array of vanes between the compression stages. Blade aerodynamic loadings may be controlled, particularly in the last stage, to provide desired compression characteristics across the compressor. A bleed outlet is optionally located between the inlet and outlet for bleeding from the gas path.

Hybrid compressor

A method of operating a gas turbine engine having a rotatable turbine shaft with an electric machine mounted to the shaft. The method includes providing supplemental acceleration and/or deceleration of the turbine shaft of the gas turbine engine through the use of the electric machine operated as an electric motor and/or an electric generator, in order to avoid an undesirable engine speed range during engine operation.

Method of operating a gas turbine engine

A blade for a rotor assembly including a root portion, a platform with an overhang, an airfoil portion and a sealing plate. The sealing plate protrudes from the blade along a circumferential direction.

Blades for a gas turbine engine with integrated sealing plate and method

A device is provided which can serve one or more of the multiple functions of impeding rotation of a shaft de-coupled turbine rotor, selectively impeding rotation of a first spool of the engine, for example to permit a second spool to generate power for use in ground operation, and facilitating reduced aircraft ground speed.

Gas turbine braking apparatus and method

A fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oil cooler in the event of a fire in the compartment. An associated means and method are also disclosed.

Apparatus and method for providing fireproofing to an aircraft auxiliary power unit

A multi-stage compressor rotor for a gas turbine engine comprises an axial-flow rotor followed by a centrifugal rotor. The axial-flow rotor and the centrifugal rotor are diffusion bonded together to form a unitary dual flow impeller having blades with continues axial-flow and centrifugal stage sections. By eliminating the gap between the axial flow and centrifugal stages, unsynchronized air deflection between the successive arrays of blades is prevented, thereby improving the aerodynamic performance of the compressor rotor.

Growing community of inventors

St. Bruno, Canada

Ronald Trumper