Pratt-whitney Canada Corp

Harris Shafique

Lev Alexander Prociw

Brant Duke

Jim R Jarvo

Benoit Lachance

Marc Tardif

Bhawan Bhai Patel

Jason Araan Fish

David Waddleton

Mario Guerra

Aleksander Kojovic

Claude Raymond Pelletier

John Sokalski

Oleg Morenko

Parthasarathy Sampath

Richard Alan Kostka

Aleksandar Kojovic

Lafleche Gagnon

Victor Gandza

Dany Clarence Gaudet

Roger Jonathan Gates

Alexsandar Kojovic

Dimitrios Garinis

Patrice Fiset

Bastien Ste Marie

Giovanni Mario Mulas

Pierre Juteau

Lew Alexander Prociw

A method of pumping fuel in a fuel system of a composite aircraft having a gas turbine engine includes feeding un-heated fuel from a fuel tank to the gas turbine engine, by using an ejector pump to draw the fuel from the fuel tank and feeding the fuel through an engine fuel pump within a main fuel line upstream of the gas turbine engine. Fuel from the main fuel line is bled and directed to the ejector pump via a motive flow pump assembly, the motive flow pump assembly including a motive flow pump generating a motive flow for the ejector pump. The bleed fuel flow is then passed through a hydrophobic fuel screen located upstream of the motive flow pump.

Engine fuel system for use with composite aircraft

A fuel system for a composite aircraft is described which includes an ejector pump having a vacuum inlet in communication with a fuel storage tank, an engine feed pump having an inlet in fluid communication with an outlet of the ejector pump, a primary outlet in communication with an engine, and a motive flow outlet, upstream of an oil-fuel heat exchanger, that is in fluid communication with an inlet of the ejector pump. A motive flow pump assembly is disposed between the motive flow outlet of the engine feed pump and the inlet of the ejector pump. The motive flow pump assembly includes an inlet screen and a motive flow pump, the inlet screen having a plurality of openings therein and a hydrophobic upstream surface. The openings are dimensioned to prevent passage of particles greater than a selected threshold size while allowing liquids to flow therethrough.

Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters.

Control of gas turbine engine

A turbine blade growth pocket provides a feature to measure blade growth due to engine operation while maintaining dynamic characteristics of the turbine blade within acceptable limits by providing a variable radius fillet between the pocket and a side rail of the pocket.

Method for manufacturing a turbine blade

A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.

Gas turbine engine fuel conveying member

Dynamically tuned turbine blade growth pocket

A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at least a first discrete conduit and a second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets.

Nested channel ducts for nozzle construction and the like

A turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 1. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z arc joined smoothly to one another to form a complete airfoil shape.

Compressor turbine blade airfoil profile

A fuel conveying member for an engine, the fuel conveying member having heating means integrated therein to permit pyrolysis of carbonaceous deposits.

Integral heater for fuel conveying member

The present invention provides a method of calibrating a fuel nozzle patternation system. The method includes testing a master nozzle having desired spray characteristics in the system to determine a virtual origin of the system and then using the virtual origin to replace a fixed spatial origin of the system for testing other nozzles of the same nozzle family.

Calibration of optical patternator spray parameter measurements

A combustor swirler for a gas turbine engine and method of manufacturing by metal injection molding an inner component and an outer cylindrical component. Indentations are molded in one of the inner and outer components and sealed by the engagement of the components together to form a series of fluid flow passages. The inner and outer components are molded with interlocking features for ensuring proper alignment of the components during assembly.

Method of manufacturing a metal injection moulded combustor swirler

A fuel manifold for a gas turbine engine having a first peripheral surface having a first channel defined therein and a second peripheral surface having a second channel defined therein, each of the first and second channels being sealingly enclosed to define a corresponding conduit.

Growing community of inventors

Longueuil, Canada

Harris Shafique