Pratt-Whitney Canada Corp

Scott Walker Smith

Eric Durocher

Joseph John Swiderski

Lawrence Marshall

Mark Cunningham

Guy Bouchard

Paul Weaver

Steven John Fett

Bich Nhu Le

In accordance with at least one aspect of this disclosure, there is provided a heat exchange system. The heat exchange system includes a first heat exchanger and a second heat exchanger. The first heat exchanger includes an engine fluid conduit fluidly connecting an engine fluid inlet to an engine fluid outlet. A first internal buffer fluid conduit fluidly connects a first buffer fluid inlet to a first buffer fluid outlet where the engine fluid conduit is in fluid isolation from the first internal buffer fluid conduit but is in thermal communication with the first internal buffer fluid conduit for heat exchange between the engine fluid and the buffer fluid.

Buffer heat exchangers for hydrogen engines

In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

Means for handling gaseous fuel

In accordance with at least on aspect of this disclosure, there is provided a hydrogen fuel system for aircraft. The hydrogen fuel system includes a gas turbine engine and a fuel feed conduit. The fuel feed conduit is defined at least in part by, in fluid series, a liquid hydrogen tank fluidly connected to a combustor of the gas turbine engine, a liquid hydrogen pump to drive fuel to the combustor of the gas turbine engine, an evaporator, and an electric heat source in thermal communication with the evaporator to add heat into a flow of hydrogen passing through the evaporator. In embodiments, the electric energy source associated with the electric heat source to power the electric heat source.

Gas turbine engine comprising liquid hydrogen evaporators and heaters

In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.

Dual cycle intercooled hydrogen engine architecture

A system and method for measuring average temperature of gas in an axial cross-section of a gas turbine engine gas path, involving diverting gas samples from different positions in the axial cross-section to a gas mixing chamber and measuring a temperature of the resulting mixed gas.

Method and system for measuring temperature in a gas turbine engine

The aircraft can have an aircraft engine and a cowl, the engine having an engine part disposed within the cowl, the cowl having a cowl section movable relative to a remainder of the cowl, the engine further having a gas path duct internal to the cowl with a first portion and a cooperating second portion, the second portion mounted to the cowl section, the cowl section moveable between a first position in which the first portion and the second portion are in fluid flow communication with one another and a second position in which the cowl section and the second portion are moved away from the first portion, wherein in the first position at least the second portion obstructs external access to the engine part and in the second position at least the second portion is displaced to permit external access to the engine part.

Moveable aircraft cowl and bypass section

A gas turbine engine comprises a turbine within a turbine case defining a hot combustion gas path. The turbine case has an inner port. An outer case is disposed radially outward from the turbine case. The outer case has an outer port. A sleeve releasably engages the outer port and the inner port. A sensor is mounted to a distal end of the sleeve. The sensor has a probe extending through the inner port into the hot combustion gas path.

Removable turbine gaspath sensor

One or more support elements radially extend through one or more openings defined in a turbine engine casing and are configured to centralize and at least partially support a rotor assembly of the engine during an engine disassembly or assembly procedure. The support elements are configured to transfer any rotor assembly weight loads to an engine casing while a bearing support of the rotor assembly is absent or removed.

Rotor centralization for turbine engine assembly

An apparatus and method for at least one of stiffening a rotor blade of a gas turbine engine and raising a natural vibration frequency of the blade. The blade has a recess extending radially and inwardly into the blade. A reinforcing element is provided in the recess at a selected position to thereby allow a large blade chord at the tip end of the blade.

Growing community of inventors

St. Lambert, Canada

Scott Walker Smith