Pratt-Whitney Canada Corp

Pratt & Whitney Canada Corp.

Sri Sreekanth

Michael Papple

Si-Man Amy Lao

Michael Leslie Clyde Papple

Robert Sze

Toufik Djeridane

Dominique Nadeau

Honza Stastny

Marc Tardif

Jeffrey Richard Verhiel

Alan Juneau

Nadia Cheri Swaby

Dominique Michel Nadeau

Michael Leslie Papple

Eric Durocher

William Abdel-Messeh

Kian McCaldon

Sami Girgis

Eduardo David Hawie

Ricardo Trindade

Remo Marini

Tin-Cheung John Hu

Edward Vlasic

Jakub Strzepek

Ion Dinu

Douglas Maccaul

Hayley Ozem

Jayaprakash Kannan

Dan Titirica

Stephen Conway

Jeffrey William Quick

Roger N A Francis

Jeffrey W Quick

Eduardo Hawie

John Tin Cheung Hu

Jeffrey Verhiel

Nadia Swaby

Roger Na Francis

An injector includes a mount, a stem, a nozzle, and a heat shield. The heat shield extends from the mount to surround the stem and at least a portion of the nozzle. The nozzle includes an exterior annular body. The distal end of the heat shield is spaced from a lip extending from the exterior annular body or a cap surrounding the nozzle to form an axial gap.

Controlled gap fuel nozzle heat shield

A fuel injector is provided for a turbine engine. This fuel injector includes a fuel nozzle, and the fuel nozzle includes a gallery, one or more feed passages and a plurality of exit passages. The gallery extends within the fuel nozzle circumferentially around an axis between a first end of the gallery and a second end of the gallery. A size of the gallery changes as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. The one or more feed passages extend within the fuel nozzle to the gallery. The one or more feed passages are configured to supply fuel to the gallery. The exit passages extend within the fuel nozzle from the gallery. The exit passages are configured to receive the fuel from the gallery.

Tapered fuel gallery for a fuel nozzle

A nozzle assembly for a gas turbine engine, comprising: a nozzle at a downstream end of the assembly relative to fuel flow; a first and a second body upstream of the nozzle, the first body defining a first passage between a first inlet connectable to a source and a first outlet, and the second body defining a second passage between a second inlet and a second outlet in fluid communication with the nozzle, the inlets in fluid communication with each other; the bodies matingly engaged together along an axis, the inlets spaced apart relative to the axis to define a gallery having a depth in an axial direction and a width in a transverse direction; and a gap filler within the gallery, compressible in at least one of the directions, having an uncompressed dimension greater than a corresponding dimension of the gallery in the at least one of the directions.

Gap filler for a fuel system gallery

A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.

Internally cooled dilution hole bosses for gas turbine engine combustors

There is disclosed a double skin combustor for a gas turbine engine. The combustor has a radially inner liner and a radially outer liner defining therebetween an annular combustion chamber. The radially inner liner and the radially outer liners both have a hot skin and a cold skin defining a cooling cavity therebetween. The cold skin has a plurality of segments joined to one another by sliding joints. The cooling cavity between the hot skin and the cold skin may be compartmentalized into individual cavities between the sliding joints.

Double skin combustor

A gas turbine engine combustor has a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone. The shell has an outer skin and an inner skin defining an air gap therebetween. The inner skin in the upstream portion of the primary zone is free from effusion holes and has heat transfer augmenters projecting from a back side thereof into the air gap. Effusion holes in the inner skin are only disposed downstream towards the tail end of the primary zone in order to delay the injection of any disruptive cooling air that could potentially interfere with the combustion process.

Combustor primary zone cooling flow scheme

A turbine component has a plurality of cooling passages each extending through a body of a structure between opposite hot and cold surfaces of the structure. According to one embodiment, at least one of the cooling passages includes a plurality of upstream paths defining respective inlet openings on the cold surface and merging into a number of downstream paths defining respective outlet openings on the hot surface.

Cooling passages in a turbine component

A turbine component includes a structure having hot and cold surfaces opposite each other; and a plurality of cooling holes extending between the cold and hot surfaces, each of the cooling holes including at least one projection or recess element to form part of a fluid path surface with enhanced in-hole heat convection.

Effusion cooling holes

A gas turbine engine combustor is described which includes outer and inner annular combustor liners formed of sheet metal. The exit duct circumscribes an annular combustor exit and defines a combustion gas path. The exit duct includes a large exit duct having an annular forged metal section which is butt welded at an upstream end to the outer combustor liner to form a first annular joint. The annular forged metal section is fixed at a downstream end to an annular sheet metal wall to form a second annular joint. Methods of forming and of repairing a gas turbine engine combustor are also disclosed.

Gas turbine engine combustor and method of forming same

A combustor for a gas turbine engine comprises a single skin liner defining a combustion chamber. The single skin liner has an inner surface facing the combustion chamber and an outer surface exposed to a coolant flow discharged in a plenum extending from the outer surface of the single skin liner to the engine casing. Cooling holes extend through the single skin liner. Cooling protuberances, such as fins or pin fins, project integrally from the outer surface of the single skin liner into the plenum, the cooling fins being interspersed between the cooling holes.

Single skin combustor with heat transfer enhancement

A floating collar assembly for a gas turbine engine combustor includes a ferrule having a peripheral wall and a recessed surface bounded by the peripheral wall, the recessed surface of the ferrule including a particulate collecting groove adjacent the peripheral wall, and a cap secured to the peripheral wall of the ferrule. The recessed surface of the ferrule, an interior surface of the cap and the peripheral wall of the ferrule define a cavity. A floating collar is disposed within the cavity and includes a peripheral flange inwardly spaced a distance from the peripheral wall of the ferrule.

Particulate buildup prevention in ignitor and fuel nozzle bosses

A combustor heat shield has lips with fins distributed on the lips. The lip-fins have an extended end portion projecting rearwardly from the back face of the heat shield. Impingement jets may be directed against the rearwardly extended end portions of the lip-fins to enhance cooling. The heat shield may define a fuel nozzle opening surrounded by a rail on the back side of the heat shield. Impingement holes or slots may be defined in the rail for allowing cooling air passing therethrough to impinge upon the lip-fins.

Combustor dome heat shield

There is provided a combustor comprising a dome and a shell extending from the dome defining a combustion chamber. A dome heat shield is mounted to the dome inside the combustion chamber. A front heat shield is mounted to the shell and spaced therefrom. The dome heat shield has a lip extending generally away from the dome heat shield and generally parallel to the shell and spaced inwardly of the front heat shield to define a gap between the lip and the front heat shield. The front heat shield has a leading edge opposite the lip. The combustor has impingement holes extending through the shell and disposed to direct impingement cooling jets to the upstream portion of the front heat shield. The leading edge, of the front heat shield has at least one scallop defining an opening and disposed to allow the impingement cooling jets to impinge directly on a portion of the peripheral lip adjacent the scallop.

Combustor heat shield

A turbine vane of a gas turbine engine is provided with a hollow core in the leading edge of the outer platform thereof. The core is interconnected with the leading edge core of the airfoil whereby to create a cooling air stream having a dual purpose and cooling both the leading edge of the outer platform and of the airfoil and thereby reducing cooling air consumption. The cooling air enters the core of the outer platform through an inlet port and exits through cooling holes provided in the leading edge of the airfoil.

Growing community of inventors

Mississauga, Canada

Sri Sreekanth