Rtx Corporation

Rohr, Inc.

Murat Yazici

Marc J Muldoon

Jeffrey T Morton

Thomas E Clark

Andrew E Breault

Brian A Sherman

An assembly is provided for an aircraft propulsion system. This assembly includes an open propulsor rotor and an open guide vane structure. The open propulsor rotor is configured to rotate about a rotational axis. The open guide vane structure is axially next to the open propulsor rotor. The open guide vane structure includes a plurality of open guide vanes arranged circumferentially about the rotational axis. The open guide vanes include a first open guide vane. The first open guide vane includes a first vane leading edge, a first vane trailing edge and a fixed first vane chord length measured from the first vane leading edge to the first vane trailing edge. The first open guide vane is configured to translate axially along the rotational axis.

Translatable guide vanes for aircraft propulsion system

A swirl recovery vane (SRV) includes a trunnion configured to pivotally connect to an exterior surface of an inner platform of an SRV structure system. The SRV includes a body extending radially from the trunnion to an unshrouded distal vane tip of the vane. The SRV includes a heat exchanger that includes a gas inlet configured to couple a bleed air valve of a compressor section of a gas generator to a gas channel. The heat exchanger includes the gas channel adapted to: enable gas to flow into the gas inlet as cool gas and out through a gas outlet as warm gas; and extend into the body of the vane to enable heat transfer from a heat source within the vane to the cool gas. The heat exchanger includes the gas outlet configured to output the warm gas from the channel to an ambient environment outside of the vane.

Thermal management system for gas turbine engine with open propulsor

An aircraft powerplant assembly includes a gearbox and a power coupler. The gearbox includes a first power transfer apparatus and a second power transfer apparatus independent of the first power transfer apparatus. The power coupler includes a clutch. The first power transfer apparatus is configured to operatively couple and transfer mechanical power through the gearbox between a first engine apparatus and an engine accessory. The power coupler is configured to operatively couple a power coupled accessory to the second power transfer apparatus when the clutch is engaged. The second power transfer apparatus and the power coupler are collectively configured to operatively couple and transfer mechanical power through the gearbox between a second engine apparatus and the power coupled accessory when the clutch is engaged. The power coupler is configured to operatively decouple the second power transfer apparatus from the power coupled accessory when the clutch is disengaged.

Aircraft powerplant gearbox with selectable power coupler

A propulsion system of an aircraft includes a hybrid electric gas turbine engine, and a nacelle at least partially enclosing the hybrid electric gas turbine engine. The nacelle includes a first nacelle half and a second nacelle half. Each of the first nacelle half and the second nacelle half include an outer nacelle sleeve, an inner nacelle sleeve radially offset from the outer nacelle sleeve such that a flowpath is defined between the outer nacelle sleeve and the inner nacelle sleeve, and an upper bifurcation connecting the outer nacelle sleeve to the inner nacelle sleeve at an upper end of the nacelle. The flowpath is circumferentially continuous between the upper bifurcation of the first nacelle half and the upper bifurcation of the second nacelle half.

Hybrid electric engine and nacelle system

A gas turbine engine is provided that includes fan, compressor, combustor, and turbine sections, an outer casing, an outside core annular region, and a fan air circulation system. The outer casing is disposed radially outside of the compressor, combustor, and turbine sections. The engine has a core gas path and a fan bypass air duct. The core gas path extends through the compressor, combustor, and turbine sections, and is disposed radially inside of the outer casing. The fan bypass air duct is defined by inner and outer radial flow path boundaries. The outside core annular region is disposed radially between the outer casing and the inner radial boundary flow path boundary. The fan air circulation system is configured to receive fan bypass air from the fan bypass air duct and selectively pass the received fan bypass air into the outside core annular region.

Ducted firewall with upper bifi bleed for modulated core ventilation

A gas turbine engine includes a propulsor delivering air into a core engine inward of an outer core panel. The core engine has a compressor section, a combustor and a turbine section. A compressor bleed system includes a bleed valve on a conduit communicating with compressed air from the compressor section. The bleed valve is configured to deliver air into a chamber where it can flow outwardly of the core engine at an exit location radially inward of the outer core panel.

Growing community of inventors

Glastonbury, CT, United States of America

Murat Yazici