Pratt-Whitney Canada Corp

Rtx Corporation

Pratt & Whitney Canada Cororation

Kian McCaldon

Richard Freer

Michel Bousquet

Tin-Cheung John Hu

André Fortin

David Waddleton

Cédric Saintignan

Joseph Daniel Maxim Cirtwill

James Robert Jarvo

Jakub Strzepek

Ignazio Broccolini

Marc-Andre Tremblay

Marc-André Tremblay

Stephen Tarling

Oleg Morenko

Honza Stastny

Hisham Alkabie

Owen Wong

Maxime La Fleche

Anna Mamrol

Jason Fish

Jason Araan Fish

Robert Sze

Sri Sreekanth

Parthasarathy Sampath

Saeid Oskooei

Jian-Ming Zhou

Dan Titirica

Joseph Cirtwill

Robert Ming Aze

A fuel mixture distributor for a turbine engine assembly includes a mixing chamber that is disposed about a central axis from a back wall to an outlet of a combustion chamber, and a fuel inlet that extends into the mixing chamber along the central axis. The fuel inlet includes a plurality of fuel openings that are angled relative to the central axis and a first air inlet that encircles the mixing chamber and is spaced apart from the fuel inlet. The first air inlet includes a plurality of first air openings that introduce a first air flow into the mixing chamber. A second air inlet introduces a secondary air flow that is axially forward of the fuel inlet and the first air inlet and proximate to the outlet of the mixing chamber.

High shear fuel distributor

A fuel mixture distribution system for a turbine engine assembly includes a combustor that includes a wall that defines a combustion chamber, a fuel mixture distributor that includes an air conduit that defines a mixing chamber that extends through the wall along between an inlet to an exit opening to the combustion chamber, the air conduit shape is defined to achieve the desired mixing and prevent flashback at all operating conditions, and a fuel distributor extends into the mixing chamber at a location upstream of the exit opening. The fuel distributor includes a plurality of fuel openings where a fuel flow is communicated and mixed with an airflow passing through the mixing chamber.

Hydrogen fuel distributor

A fuel injector for a gas turbine engine combustor is provided that includes a swirler, a mounting stage, and a distributor. The swirler has a shaft, a collar, a throat section, and first and second axial ends. The throat section includes an inner radial surface that defines a central passage that extends between the swirler inner bore and the collar. The collar includes a plurality of apertures extending therethrough disposed radially outside of the central passage. The mounting stage is disposed in the inner bore, and has an annular flange, a central hub, and at least one strut. The distributor has a stem attached to a head. The stem has a distal end opposite the head portion engaged with the central hub. The head portion has an end surface and a side surface. The distributor is selectively positionable relative to the throat section.

Adjustable gaseous fuel injector

Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.

System and method for purging a fuel manifold of a gas turbine engine through a flow divider valve

Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.

System and method for purging a fuel manifold of a gas turbine engine using a flow divider assembly

A method of servicing a gas turbine engine having an igniter socket, the method comprising: inserting a glow plug into the igniter socket of the gas turbine engine until a rod end of a glow plug heater rod of the glow plug is exposed to a combustion chamber of the gas turbine engine; and blocking a gap between the glow plug heater rod and an aperture defined in a combustor liner of the gas turbine engine to block fluid communication between the combustion chamber and an environment outside the combustion chamber via the aperture.

Igniter for gas turbine engine

A method of purging fuel injectors of a gas turbine engine, the fuel injectors fluidly connected to a fuel manifold and having primary and secondary fuel passages fluidly connectable to the fuel manifold, the method includes: selectively fluidly disconnecting one or more of the primary and secondary fuel passages from the fuel manifold; and purging the one or more of the primary and secondary fuel passages by injecting a purging fluid into the one or more of the primary and secondary fuel passages while bypassing the fuel manifold. A fuel injector having two fuel passages, a flow divider valve, and a purging valve is disclosed.

Fuel injectors and method of purging fuel injectors

A gas turbine engine has: a casing; a combustor liner delimiting a combustion chamber; a fuel nozzle in fluid communication with the combustion chamber; and an igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a sleeve extending around the glow plug heater rod, the sleeve radially spaced apart from the glow plug heater rod by an annular gap, the sleeve defines fins circumferentially distributed around the axis, each two circumferentially adjacent fins of the fins spaced apart from one another by a spacing communicating with the annular gap, the fins extending in a direction having an axial component from roots to tips, the roots axially closer to the base than the tips, the rod end extending axially beyond the tips of the fins such that the rod end is located outside the annular gap.

There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a plurality of fins disposed circumferentially around the glow plug heater rod, the fins extending axially along at least a portion of the glow plug heater rod. A gas turbine engine including such an igniter is further disclosed.

There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a flow impeding member extending along the axis and having a distal end spaced from the base and extending axially relative to the axis beyond the rod end, the flow impeding member sized and configured such that the distal end extends into a combustion chamber of the gas turbine engine upon the base connected to the casing.

There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the heater rod extending from the base along an axis and terminating in a rod end, a peripheral wall extending circumferentially around the rod end and having a distal end directed away from the base, a gap between the peripheral wall and the heater rod, the rod end being axially retracted relative the distal end of the peripheral wall.

Growing community of inventors

Orangeville, Canada

Kian McCaldon