Pratt-whitney Canada Corp

Ian A Macfarlane

Keith M Morgan

Keith Morgan

Peter Townsend

Lazar Mitrovic

Ghislain Plante

Zenon Szlanta

Hong Yu

Martin Poulin

Sean Powers

Jean-Jacques Forest

Nigel Walters

Jean O Gagnon

Thomas R Haslam-Jones

A gas turbine engine includes a casing including a plurality of interconnected casing segments defining an outer surface of the casing. One of the casing segments is a gearbox segment enclosing a gearbox and having a gearbox flange extending radially outwardly from the outer surface of the casing. The engine includes a bearing housing enclosing at least one bearing and having an annular body with an inner segment disposed within the casing. The annular body having an extension segment extending radially outwardly from the inner segment to a bearing housing flange disposed radially-outwardly of the outer surface of the casing. The bearing housing flange is engageable with the gearbox flange to removably mount the gearbox segment to the bearing housing.

Gas turbine engine casing arrangement

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 sleeve is provided for supplying lubricant to an inter-shaft bearing mounted between co-axially mounted inner and outer shafts of a gas turbine engine. The sleeve has a sleeve annular outer surface and a sleeve annular inner surface. At least one lubricant supply connecting member extends from the sleeve outer surface for connection to a lubricant supply. At least one sleeve channel fluidly links the sleeve annular inner surface to the lubricant supply connecting member.

Inter-shaft bearing arrangement

A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool. The LP spool has an LP shaft for transferring a torque from an LP turbine to an LP compressor. The HP spool has an HP shaft for transferring a torque from an HP turbine to an HP compressor. The LP shaft is coaxially mounted inside the HP shaft. An inter-shaft bearing is mounted radially between the LP shaft and the HP shaft. The inter-shaft bearing is disposed axially between the HP compressor and the LP compressor.

Inter-shaft bearing connected to a compressor boost system

A turboprop engine including an annular outer case including a mount ring for attachment to an aircraft along a plane to transfer loads from a propeller and having an annular flange extending radially inwardly therefrom within the plane, an annular turbine support case received within the outer case and connected to the outer case only through a direct connection with the annular flange allowing a limited relative pivoting motion between the turbine support case and the mount ring, and a turbine section including a rotor closely surrounded by a shroud with an annular tip clearance being defined therebetween, the shroud being directly connected to and located by the turbine support case. A method of isolating a turbine shroud from propeller loads in a propeller engine is also disclosed.

Turboprop engine with compressor turbine shroud

Systems and methods for changing a speed ratio between a compressor boost stage () and at least one power turbine () of a gas turbine engine () are described. Such a system may comprise a coupling device () configured to selectively transmit energy from the at least one power turbine () to the boost stage () according to at least a first speed ratio and a second speed ratio. The system may also comprise an auxiliary power device () configured to cause a rotational speed of the boost stage () to change from a first speed corresponding substantially to the first speed ratio to a second speed corresponding substantially to the second speed ratio when the boost stage () is decoupled from the at least one power turbine ().

Systems and methods for changing a speed of a compressor boost stage in a gas turbine

An apparatus for extending the effective exhaust gas path in order to allow gradual diffusion of the exhaust gases in a turboshaft engine wherein the engine includes an annular engine case with at least an exhaust gas duct having an axial component communicating with an annular duct with a substantially radial component and traversing the engine case, the apparatus comprising a collector plenum having a convex annular shape and a diameter larger than that of the engine case with at least one exhaust outlet defined in the plenum and wherein the annular duct extends into the plenum beyond the diameter of the engine case to extend the exhaust gas path.

Exhaust gas discharge system and plenum

A gas turbine engine having an oil cavity architecture and bearing placement which reduce heat rejection and oil system complexity by enclosing the reduction gearbox bearings and at least the shaft bearings supporting the high pressure shaft in the same oil cavity.

Growing community of inventors

St. Bruno, Canada

Ian A Macfarlane