Pratt-whitney Canada Corp

Ian Alexander MacFarlane

Keith Morgan

Lazar Mitrovic

Guy Lefebvre

Eric Durocher

Peter Townsend

Ghislain Plante

Hong Yu

Roger Gates

Thomas Francis Haslam-Jones

Zenon Szlanta

Nigel Walters

Jean Gagnon

An apparatus is provided for a gas turbine engine. This gas turbine engine apparatus includes a hot section structure of the gas turbine engine. The hot section structure is configured with a plurality of surfaces respectively forming boundaries of a gas path through the hot section structure. The surfaces include a first surface and a second surface. The hot section structure includes metal and thermal barrier material. The first surface is formed by the metal. The second surface is formed by the thermal barrier material.

Selectively coated gas path surfaces within a hot section of a gas turbine engine

A low pressure compressor section of a gas turbine engine includes low pressure compressor stages spaced apart along an axis of rotation of the low pressure compressor section. The low pressure compressor section includes at least one of a fluid conduit extending between an air inlet of the gas turbine engine and the low pressure compression stages. The fluid conduit having at least one flow diverter displaceable between a first position and a second position to modulate air through the low pressure compressor stages. And/or a compressor stage disabler is engageable with at least one of the low pressure compressor stages and configured to reduce a rotation thereof.

Gas turbine engine with low pressure compressor stages

A labyrinth seal assembly comprising: an outer seal having a radially inner cavity surface, and an axial cavity surface inward of the radially inner cavity surface; a floating seal received by the outer seal so as to be movable in a radial direction relative to the outer seal, the floating seal having a radially outer seal surface spaced inwardly from the radially inner cavity surface, a radially inner surface inward of the radially outer seal surface, and an axial seal surface bearing against the axial cavity surface; and an inner seal received by the floating seal, the inner seal having a radially outer surface spaced inwardly from the radially inner surface, a first one of the radially outer surface and the radially inner surface defining one tooth projecting toward a second one of the radially outer surface and the radially inner surface to inward of the axial seal surface.

Labyrinth seal

A method of manufacturing a compressor stator having: a first stator blade with a first leading edge and a first trailing edge; a second stator blade disposed a circumferential distance from the first stator blade, the second stator blade having a second leading edge disposed an axial distance from the first leading edge and a second trailing edge disposed an axial distance from the first trailing edge; the method comprising: using additive manufacturing to deposit and fuse together progressive layers of metal material commencing at a substrate to form the first stator blade, the second stator blade, at least one intermediate support structure disposed between the first stator blade and the second stator blade, and at least one primary support structure disposed between the substrate and at least one of: the first stator blade; and the second stator blade; and removing the primary support structure and the intermediate support structure.

Double row compressor stators

A radial air inlet for a gas turbine engine. The air inlet has an inlet duct defined between two axially-spaced radially-extending annular walls and has a plurality of circumferentially-spaced axially-extending struts extending between the annular walls adjacent a radially-outer portion of the air inlet. At least one of the struts has an internal passage extending between a first opening in a forward end of the strut and a second opening in an aft end of the strut, the first and second openings being axially spaced apart. A transmission shaft extends through the internal passage of said strut.

Air inlet for a gas turbine engine

A method of isolating a turbine shroud from propeller loads in an engine having an outer case with a mount defining a mount plane and an attachment location within the mount plane, the mount configured for attachment of the engine to an aircraft at the attachment location to transfer the propeller loads. The shaft of the engine is supported with a portion of the outer case extending from the mount and defining a load path for the propeller loads. The turbine support case is attached to extend free of the load path, by attaching the turbine support case to the outer case only through a connection along the plane, the connection defining a pivot point allowing a limited relative pivoting motion around the pivot point between the turbine support case and the mount. The turbine shroud is located by directly connecting it to the turbine support case.

Turboprop engine with compressor turbine shroud

Systems and methods for driving an oil cooling fan () of a gas turbine engine () during different modes of operation of the gas turbine engine () are described. A system may include a coupling device () configured to: transmit motive power from a power turbine shaft () of the gas turbine engine () to the oil cooling fan () during a first mode of operation where the power turbine shaft () is turning, and to decouple the oil cooling fan () from the power turbine shaft () during a second mode of operation where the power turbine shaft () is prevented from turning. An alternate source () of motive power may be configured to drive the oil cooling fan () during the second mode of operation.

Systems and methods for driving an oil cooling fan of a gas turbine engine

A method and apparatus for heating fuel in an aircraft gas turbine engine, for example to provide fuel anti-icing to the fuel, comprises directing a fuel flow through a heat exchanger associated with a generator power conditioning unit as a sole means for providing anti-icing heating to fuel supplied for engine combustion. The method and apparatus permits the heat exchanger to heat the fuel sufficiently so that other dedicated heating means may be unnecessary.

Fuel system for gas turbine engine

A cap for sealing an outer end of an oil filler tube of an engine where the oil filler tube has an inner end with ball valve having a float ball and mating valve seat for impeding any reverse flow of oil during engine operation. The cap includes a sealable plug mating the tube outer end; a rod extending from the plug toward the inner end of the tube; and a valve opening device mounted to the rod for dislodging the float ball from the valve seat.

Oil filter cap with ball valve anti-sticking device

A gas turbine engine including a gas generator module and a reduction gearbox module. The gas generator module has an axis which extends longitudinally along a centreline of the gas generator module, and the reduction gearbox module has an axis which extending longitudinally along the centreline of the reduction gearbox and is offset from said generator axis. The reduction gearbox is driven by an intermediate shaft angled relative to the turbine output shaft.

Offset drive for gas turbine engine

A convectively-cooled hydraulic fluid tank system comprises a hydraulic fluid tank and a fluid cooler incorporated into the hydraulic fluid tank. The fluid cooler includes a vortex chamber having a wall made of a heat conductive material. An inlet is provided to direct incoming pressurized hydraulic fluid tangentially onto the inner surface of the vortex chamber wall to create a swirled flow of hydraulic fluid against the inner surface of the wall. A cooling structure extends from an exterior surface of the vortex chamber wall to promote heat dissipation.

Combined hydraulic fluid cooler/tank

A power plant and transmission arrangement for a helicopter wherein the helicopter engine is integrated to the helicopter transmission to form therewith a single unit rigidly mounted to the helicopter frame. By so integrating the engine to the helicopter transmission the center of gravity of the engine can be placed closer to the rotor mast of the helicopter, thereby enhancing the stability and the handling characteristics of the helicopter.

Growing community of inventors

St-Bruno, Canada

Ian Alexander MacFarlane