Pratt-whitney Canada Corp

Jason Araan Fish

Bhawan Bhai Patel

Bryan William Olver

Vittorio Bruno

Lev Alexander Prociw

Daniel Alecu

Eduardo David Hawie

Harris Shafique

Parthasarathy Sampath

Pierre-Yves Legare

Andreas Eleftheriou

Tibor Urac

Kian McCaldon

Kenneth D Parkman

Gabriel Naccache

Saeid Oskooei

Lafleche Gagnon

Ljubisa Vrljes

Jian-Ming Zhou

Pierre-Yves Légaré

Dany Clarence Gaudet

Bhawan Bhal Patel

Zoran Markovic

Steven Hunt

Charlie Molina

Dany Gaudet

Steven Bokan

Lafléche Gagnon

An aircraft engine has a flammable fluid containment assembly including a component containing a flammable fluid. A transfer tube is fluidly connected to the component. A sealing ring is provided at an interface between the aircraft engine component and the transfer tube. A first thermal barrier is provided between the sealing ring and a first one of the aircraft engine component and the flammable fluid inside the transfer tube. The first thermal barrier includes a first annular cavity filled with a first thermal insulation medium and axially spanning the sealing ring.

Thermal protection for seals

A system for an aircraft engine, has: an aircraft component; and a heat exchanger having: a housing defining a first inlet, a first outlet, a second inlet, and a second outlet; first conduits within the housing, the first conduits fluidly connecting the first inlet to the first outlet; one or more second conduit within the housing, the one or more second conduits fluidly connecting the second inlet to the second outlet, the one or more second conduit in heat exchange relationship with the first conduits; a mixing chamber intersecting two or more of the first conduits, the mixing chamber having a peripheral wall extending around a mixing volume and a central axis; and protrusions extending from the peripheral wall into the mixing volume, the protrusions extending around the central axis and across a direction of the flow through the mixing chamber.

Heat exchanger having a mixing chamber and protrusions

The heat exchanger can have a first fluid circuit extending from a first inlet to a first outlet, one or both having a first mouth dividing internally into a number of passages within a periphery, a second fluid circuit fluidly distinct from the first fluid circuit, extending from a second inlet to a second outlet, the second fluid circuit in thermal exchange contact with the number of passages in a heat transfer region of the heat exchanger, and an adapter having a second mouth secured to the first mouth in a manner to establish internal fluid flow communication therewith.

Heat exchanger and associated method of assembly

A gas turbine engine includes a fan assembly, a compressor assembly, a combustion chamber, a turbine assembly, a bypass duct conveying rearward a bypass airstream driven by the fan assembly when the gas turbine engine is in use, a fairing extending across at least a portion of the bypass duct downstream of the fan assembly, and a heat exchanger having an inlet fluidly connected to the compressor assembly and an outlet fluidly connected to a pneumatic actuator of the gas turbine engine. The fairing has a leading edge and a trailing edge. The heat exchanger is disposed adjacent the trailing edge of the fairing.

Gas turbine engine with trailing edge heat exchanger

A turbofan engine comprising an outer bypass duct, an annular bypass flow path between the outer bypass duct and a core engine, an engine component forming an airflow obstruction adjacent the outer bypass duct, an air cooler having a tube, the tube having at least a sinuous portion extending in the annular bypass flow path, the sinuous portion extending along the outer bypass duct, downstream of the airflow obstruction, the sinuous portion configured for exchanging heat between a fluid circulating in the tube and air circulating in the bypass flow path during operation of the turbofan engine.

Air cooler for gas turbine engine

A mounting method and system for supporting and positioning an internal fuel manifold relative to a combustor in a fuel injection system for a gas turbine engine. The method includes positioning the fuel manifold within a gas generator casing, applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, and using the heat shield to at least partially support the fuel manifold within the gas generator casing.

Gas turbine internal manifold mounting arrangement

A fuel manifold assembly for a gas turbine engine fuel system comprises a fuel manifold at least partly enclosed by a heat shield, the internal manifold being made of a first material having a first coefficient of thermal expansion, and the heat shield being made of a second material having a second coefficient of thermal expansion that is lower than the first coefficient of thermal expansion.

Reduced stress internal manifold heat shield attachment

An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.

Turbine wash port for a gas turbine engine

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

A mounting system supporting and positioning an internal fuel manifold of a gas turbine engine includes at least a heat shield surrounding a fuel inlet of the fuel manifold, the heat shield bearing at least a portion of a load to support the fuel manifold.

An apparatus for internally mounting a fuel manifold within a surrounding casing in a gas turbine engine which includes a fuel manifold and support pins which are displaceable relative to mounting portions on the fuel manifold between a retracted position, wherein the fuel manifold is able to be inserted within a casing of the engine, and an extended position, wherein the support pins project outwardly from the fuel manifold for engagement with the casing.

Internally mounted fuel manifold with support pins

A system for mounting an internal fuel manifold within a gas generator case of a gas turbine engine includes at least one fastener support assembly having a fastener pin and at least one receiving element, respectively engaged to either the internal fuel manifold or the gas generator case. A biasing member is located between the fastener pin and the receiving element to axially preload the joint between the fastener pin and the receiving element, such as to constrain relative movement between the two parts in an axial direction while allowing relative movement in a radial direction.

Pre-loaded internal fuel manifold support

A gas turbine engine fuel nozzle system having a fuel conveying member with a channel formed in a surface thereof defined between a pair of facing spaced apart walls, and at least one sealing member disposed within the channel and sealingly fastened to the spaced apart walls.

Fuel conveying member with side-brazed sealing members

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

A mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener engaging the receiving element to constrain a relative movement between the fuel manifold and the gas generator case in an axial direction while allowing the relative movement in a radial direction and a secondary fastener in position to passively and automatically engage the receiving element upon failure of the primary fastener.

Growing community of inventors

Brompton, Canada

Jason Araan Fish