Pratt-whitney Canada Corp

Raytheon Technologies Corporation

Ghislain Plante

Keith Morgan

Patrick Valois

Jean Dubreuil

Eric Durocher

Eugene Gekht

Philippe Beauchesne-Martel

Remy Synnott

Michael Papple

Panagiota Tsifourdaris

Timothy J Jennings

Johnny Vinski

Daniel Lecuyer

Hervé Turcotte

Robert Peluso

Stephen Mah

Jaideep Gahlawat

Poi Loon Tang

Rene Paquet

Michael Leslie Clyde Papple

Domenico Di Florio

David A Niezelski

Othmane Leghzaouni

Ian Alexander MacFarlane

Ian A Macfarlane

Daniel Blais

John R Battye

Kevin Ng

Vincent Couture-Gagnon

Andrew Hayes Thompson

Patrick Peloquin

Joël Larose

Anthony Pham

Francois Caron

Andrew Thompson

XingYun Haggard

Tania Fauchon

Phillippe Beauchesne-Martel

A gas turbine engine having: an engine core having, in serial flow communication, a low-pressure compressor, a high-pressure compressor, a high-pressure turbine drivingly connected to the high-pressure compressor, and a low-pressure turbine drivingly connected to an output shaft; and a clutch having a disengaged configuration in which the low-pressure turbine is drivingly disconnected from the low-pressure compressor such that, in the disengaged configuration, the clutch disengages the low-pressure turbine from the low-pressure compressor, and an engaged configuration in which the low-pressure turbine is drivingly connected to the low-pressure compressor, the low-pressure turbine drivingly connected to the output shaft in both of the engaged and disengaged configurations of the clutch.

Gas turbine engine with clutch system between low-pressure compressor and low-pressure turbine

Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.

Corrected parameters control logic for variable geometry mechanisms

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 gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

Reverse-flow gas turbine engine

A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.

Reverse flow engine architecture

An aircraft engine has a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor. A low pressure spool including a low pressure compressor is fluidly connected to the high pressure compressor. A low pressure turbine is drivingly connected to the low pressure compressor to drive the low pressure compressor. A load is drivingly connected to the low pressure turbine, the load consisting of one of a propeller and a helicopter rotor. A method of creating classes of an aircraft engine from an engine platform is disclosed.

Gas turbine engine and method of creating classes of same

A method of providing an engine family includes providing a first engine having a low pressure turbine driving a low pressure compressor at a first speed ratio, and a high pressure turbine driving a high pressure compressor. The method includes providing a second engine by changing the first speed ratio of the first engine to a second speed ratio.

Engine family platform design

A gas turbine engine has a first spool having a low pressure compressor section in fluid communication with an air inlet, the low pressure compressor section including a first plurality of variable guide vanes therein, and a low pressure turbine section drivingly engaged to the low pressure compressor section. A second spool has a high pressure compressor section in fluid communication with the low pressure compressor section to receive pressurized air therefrom, the high pressure compressor section including a second plurality of variable guide vanes at an entry thereof, and a high pressure turbine section drivingly engaged to the high pressure compressor section, the high pressure turbine section disposed upstream of the low pressure turbine section and in fluid communication therewith. An output drive shaft drivingly engages the low pressure turbine section and is adapted to drivingly engage a rotatable load of the gas turbine engine.

A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.75-2.20 inches. A chord length at 50% span is 1.05-1.35 inches. At least two of: a first mode resonance frequency is 2400&#xb1;10% Hz; a second mode resonance frequency is 4950&#xb1;10% Hz; a third mode resonance frequency is 7800&#xb1;10% Hz; a fourth mode resonance frequency is 8700&#xb1;10% Hz; and a fifth mode resonance frequency is 12500&#xb1;10% Hz.

Turbomachine blade

A method and a turbine rotor system for reducing over-speed potential of a turbine of a gas turbine engine involve mechanically connecting the turbine to at least two mechanical loads via first and second mechanical drives extending in opposite directions from the turbine.

Turbine rotor with low over-speed requirements

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Verdun, Canada

Ghislain Plante