Pratt-whitney Canada Corp

Raytheon Technologies Corporation

Assaf Farah

Daniel Summers-Lepine

Eric Durocher

Daniel Coutu

Marc Tardif

Gary J Dillard

Karl D Blume

Bruce Fielding

Theodore W Kapustka

Lam Nguyen

Philippe Boyer

Terrence Lucas

Mateusz Ozog

A hydrogen supply assembly for an aircraft propulsion system includes a storage housing, a hydrogen supply component, and a leak detection system. The storage housing surrounds and forms a storage plenum. The hydrogen supply component is disposed within the storage housing coincident with the storage plenum. The leak detection system includes an interior pressure sensor, an exterior pressure sensor, and a controller. The interior pressure sensor is connected in fluid communication with the storage plenum. The exterior pressure sensor is connected in fluid communication with an ambient atmosphere outside the storage housing. The controller is configured to determine a differential pressure between the storage plenum and the ambient atmosphere with the interior pressure sensor and the exterior pressure sensor and identify a presence or an absence of hydrogen leakage from the hydrogen supply component to the storage plenum by comparing the determined differential pressure to a first differential pressure threshold.

Hydrogen leak detection system for an aircraft propulsion system

An engine system is provided that includes an engine core, a fuel containment structure, a fuel containment plenum, a fuel delivery system and a plenum purge circuit. The engine core includes an engine housing structure which houses a compressor section, a combustor section and a turbine section. The fuel containment structure is outboard of and connected to the engine housing structure. The fuel containment plenum is formed by and located between the fuel containment structure and the engine housing structure. The fuel delivery system includes a plurality of fuel injectors, a fuel supply line and a fuel manifold fluidly coupling the fuel supply line to the plurality of fuel injectors. The fuel manifold is arranged within the fuel containment plenum. The plenum purge circuit is configured to purge fuel, when leaked into the fuel containment plenum from the fuel delivery system, out of the fuel containment plenum.

Fuel containment structure for engine fuel delivery system

An exhaust casing for a gas turbine engine comprises a shroud configured to surround an exhaust cone, and a heat shield attached to the shroud. The heat shield has a first end and a second end axially spaced apart from each other. A gap is defined radially between the shroud and the heat shield. The gap is configured to enclose at least a portion of an interface defined between at least one strut and the shroud. The exhaust casing is configured to surround the exhaust cone and configured to be connected to the exhaust cone via the at least one strut.

Exhaust casing for a gas turbine engine

A combustor for use in a gas turbine engine comprising: an outward shell; an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining a combustion chamber therebetween; an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint; an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising: an outward wall located proximate the outward shell; an inward wall located proximate the inward shell; and a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall.

Slot cooled combustor

A gas turbine engine comprises a main gas path having an inner flow boundary wall and an outer flow boundary wall. A turbine exhaust case inner body defines a portion of the inner flow boundary wall of the main gas path. A lobed exhaust mixer defines a portion of the outer flow boundary wall of the main gas path. A stiffener ring is interconnected to at least a number lobes of the lobed exhaust mixer by a plurality of circumferentially spaced-apart struts extending through the main gas path. The stiffener ring is attached to the turbine exhaust case inner body by flexible features, such as circumferentially spaced-apart spring blades.

Flow mixer stiffener ring segmented springs

A case assembly for a gas turbine engine comprising annular case components each having a central axis. Radial struts each have a radial axis and intersect the annular case components. A stress dissipation mass projecting from a continuous surface of at least one of the struts at the intersection with a corresponding annular case component, the stress dissipation mass being on either side of a plane passing through the radial axis of the strut and the central axis of the corresponding annular case component. A method for dissipating thermal and mechanical stresses on a strut in a case assembly for a gas turbine engine is also provided.

Gas turbine case and reinforcement strut for same

A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.

Gas turbine rotor containment

A method of cooling a shroud ring in a turbine section of gas turbine engine includes identifying a series of alternating high temperature regions and lower temperature regions of a circumferential temperature distribution about the inner surface of the shroud ring, and impinging cooling air on to an outer surface of the shroud ring. More cooling air is impinged onto regions which correspond to the high temperature regions on the shroud ring than to regions corresponding to the lower temperature regions of the shroud ring.

Turbine shroud cooling system

A shroud segment of a turbine shroud of a gas turbine engine comprises a platform with front and rear legs. The platform defines a plurality of axially extending holes with individual inlets on an outer surface of the platform for transpiration cooling of the platform of the turbine shroud segment.

Growing community of inventors

Brossard, Canada

Assaf Farah