Pratt-whitney Canada Corp

Pratt & Whitney Canada Cororation

Oleg Morenko

Bhawan Bhai Patel

Nagaraja Rudrapatna

Ryan Miskie

Aleksandar Kojovic

Lev Alexander Prociw

Eric Durocher

Bryan William Olver

Kian McCaldon

Kenneth D Parkman

Nicolas Grivas

Bryan Micheal Bond

Sandeep Singh Dhalla

Sandeep Vishal Dhalla

Harris Shafique

Honza Stastny

Enzo Macchia

Parthasarathy Sampath

Nagaraja S Rudrapatna

Lorin Markarian

Tin-Cheung John Hu

Hervé Turcotte

Ioan Sasu

Tin Cheung John Hu

Si-Man Amy Lao

Hisham Alkabie

Jeffrey Richard Verhiel

Saeid Oskooei

Stephen Phillips

Gavin Rohiteshwar Kisun

Parham Zabeti

George Guglielmin

Jian-Ming Zhou

Owen Ho-Yin Wong

Hayley Ozem

Nicholas Guglielmin

Sylvain Jette

Jean-Francois Grenier

Maximilian Baranowicz

Robert Richard Davis

Doug Roberts

Kian Mccaldon

Tin Cheung Hu

Bhawan B Patel

Bryan Olver

Bryan Michael Bond

Jiam-Ming Zhou

In one aspect of the present disclosure, there is provided a nozzle assembly comprises a first fuel conduit defined between a nozzle body and a fuel swirler and extending along a longitudinal axis from an inlet of the first fuel conduit to an outlet of the fuel nozzle assembly. A second fuel conduit is defined between the fuel swirler and a heat shield and extending along the fuel swirler along the longitudinal axis from an inlet of the second fuel conduit to the outlet of the fuel nozzle assembly. An air conduit extends through the heat shield along the longitudinal axis from an inlet of the air conduit to the outlet of the fuel nozzle assembly.

Nozzle tip with shielded core for a dual combustion systems

A fuel supply system for a gas turbine engine comprises a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler has an upstream end and downstream end relative to a fuel flow direction along a fuel nozzle longitudinal axis. The fuel swirler has a first axial fuel passage along the longitudinal axis in fluid communication with a first fuel supply and terminating at a first fuel outlet at the downstream end, a second axial fuel passage along the longitudinal axis in fluid communication with a second fuel supply and terminating at a second fuel outlet at the downstream end, and a plurality of compressed air outlets at the downstream end. The first fuel outlet is positioned on an outermost surface of the fuel swirler and leads directly to a mixing site downstream of the fuel swirler.

Dual pressure fuel nozzles

A bearing housing cover for a gas turbine engine having an impeller. The bearing housing comprises an annular collar having a flange mountable to an exterior surface of a bearing housing. The bearing housing further comprises an impeller baffle integrated with the annular collar, the impeller baffle having an annular body with a front baffle face positionable adjacent a rear face of the impeller, a rear baffle face having a plurality of stiffening elements extending between the rear baffle face and the annular collar, and a central baffle opening.

Bearing housing assembly

An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.

Diffuser ring with air manifold

A multi-seal coupling for fluidly interconnecting a first component and a second component within a hydrogen fuel supply system of a gas turbine engine includes a female joint portion and a male joint portion. A first seal, a second seal and a third seal, all of which are hydrogen fuel seals, are formed between the male joint portion and the female joint portion. The first seal is formed by face-to-face abutting contact between a first axially-facing surface of the male joint portion and an axially-facing surface of the female joint portion. The second seal is formed by a gasket axially compressed between the first axially-facing surface of the male joint portion and the female joint portion. The third seal is formed by a sealant ring disposed between a second axially-facing surface of the male joint portion and an adjacent surface of the female joint portion.

Multi-seal coupling for a hydrogen fuel system of a gas turbine engine

A bearing housing for supporting a bearing of a gas turbine engine. The bearing housing comprises an annular body extending around an axis and having an oil inlet and an oil outlet. The bearing housing further comprises an oil manifold integrated into the annular body, the oil manifold having an inner oil channel defined in the annular body and extending circumferentially around the axis, the inner oil channel in fluid communication with the oil inlet and at least one oil jet directed towards the bearing.

Bearing housing and method of making

A method of operating a fuel delivery system of an aircraft engine of an aircraft includes operating the aircraft engine in a standby mode by maintaining combustion in a combustor of the aircraft engine by supplying fuel to the combustor via a first set of fuel nozzles of a first fuel manifold while providing a trickle flow of fuel via a second set of fuel nozzles of a second fuel manifold into the combustor during engine operation, the trickle flow being defined as a fuel flow rate selected to prevent flame-out of the combustion while providing one of: substantially no motive power to the aircraft, and no motive power to the aircraft, via the combustion of the trickle flow of fuel. An aircraft gas turbine engine is also described.

Fuel delivery system and method

A fuel supply system for an aircraft engine, comprises a gaseous fuel source and a fuel nozzle. The fuel nozzle includes a housing having a housing interior chamber and a fuel swirler disposed inside the housing interior chamber. The fuel swirler is fluidly connected to the gaseous fuel source for directing gaseous fuel to a combustor of the aircraft engine. The fuel swirler defines a gaseous fuel path extending from a fuel inlet to a fuel outlet. The gaseous fuel path includes a plurality of discrete apertures distributed around a circumference of the fuel swirler, each of the plurality of discrete apertures having a cross-sectional area selected to prevent a flame from propagating in an upstream direction through the gaseous fuel path towards the gaseous fuel source.

Fuel nozzle with integrated metering and flashback system

A fuel supply assembly for a gas turbine engine comprises a plurality of fuel injectors configured for mounting circumferentially to an engine casing of the gas turbine engine and to be serially interconnected. At least one pair of the plurality of the fuel injectors has a first fuel injector including a first manifold adapter having a first outlet defined around a first outlet axis, and a first stem connected to the first manifold adapter at the first outlet and extending longitudinally along a first stem axis; and a second fuel injector including a second manifold adapter having a second outlet defined around a second outlet axis, and a second stem connected to the second manifold adapter at the second outlet, the first and second outlet axes being disposed circumferentially between the first and second stem axes.

Fuel manifold assembly

A combustor for a gas turbine engine comprises a combustor chamber defined at least partially by an outer combustor skin and an inner combustor skin. A plurality of stand-off devices have a body including a first end and a second end, the second end of the body retained in an opening in the outer combustor skin, the first end spaced apart from the second end and abutting the inner combustor skin to space the inner combustor skin apart from the outer combustor skin.

Stand-off device for double-skin combustor liner

A gas turbine engine, has: a case extending circumferentially around a central axis of the gas turbine engine; a boss protruding from the case away from the central axis, the boss defining an internal passage; a tubular member received within the internal passage of the boss and secured to the boss; an annular gap extending all around the tubular member and located between the tubular member and the boss; and a fitting hydraulically connecting a fluid source to the tubular member, the fitting having a portion received within the tubular member and encircled by both of the annular gap and the tubular member, the fitting sealingly engaged to the tubular member.

Boss for gas turbine engine

A tube assembly for a gas turbine engine includes a rigid tube having first and second ends for connection to first port and second ports on the gas turbine engine. The first and second ports have different orientations providing for different installation vectors. The tube assembly further includes a tube adapter adjustably connected to the second port and a coupling, which, is, in turn, adjustably mounted to a distal end of the tube adapter for connection with the second end of the tube.

Tube assembly for a gas turbine engine

A gas turbine engine fuel supply system has a plurality of fuel nozzles fluidly connected to a source of fuel by transfer tubes extending between the fuel nozzles. At least one plug extends between first and second adjacent nozzles of the set of fuel nozzles. The plug has a first end plugging a port on the first adjacent nozzle and a second end plugging another port on the second adjacent nozzle.

Transfer tube manifold with integrated plugs

A fuel swirler, for a gas turbine engine, has a primary cone housing defining an interior chamber. The interior chamber has an inlet in communication with a source of pressurized fuel. The interior chamber has a transition portion and a socket portion with an axisymmetric interior surface. A swirler core is disposed within the interior chamber. The swirler core has a downstream end and an upstream shank portion having an exterior surface mating the axisymmetric interior surface of the socket portion. The shank portion has a plurality of axially extending grooves. The grooves are disposed axisymmetrically about the exterior surface of the shank portion.

Fuel swirler for pressure fuel nozzles

An annular heat shield arrangement for a combustor liner comprises annular heat shield assemblies. The annular heat shield assemblies include heat shield segments circumferentially distributed around an axis of the annular heat shield assembly. The heat shield segments extend from a first lateral edge face to a second lateral edge face, a first overlap joint portion being defined at the first lateral edge face, a second overlap joint portion being defined at the second lateral edge face. The first overlap joint portion and the second overlap joint portion are complementary to form an overlap joint when pairs of the heat shield segments are side by side in any one of the heat shield assemblies. An adjacent pair of the annular heat shield assemblies are connected to one another at an overlap between the pair, and wherein the overlap joints from a first of the annular heat shield assemblies of the pair are circumferentially offset from a second of the annular heat shield assemblies of the pair.

Annular heat shield assembly for combustor

Growing community of inventors

Oakville, Canada

Oleg Morenko