United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Gary D Roberge

William J Brindley

Gabriel L Suciu

William G Sheridan

Brian D Merry

Michael E McCune

Daniel Bernard Kupratis

Grant O Cook, Iii

James W Norris

Jorn Axel Glahn

Craig A Nordeen

Andrew P Berryann

Neil J Terwilliger

Wendell V Twelves

Evan J Butcher

Joe Ott

Mark W Costa

Michael Joseph Murphy

Alan H Epstein

Lexia Kironn

Edward B Thayer

Jayant Sabnis

Robert J Morris

George J Kramer

Curtis C Cowan

Gary M Perkins

Rebecca R Dunnigan

James E Jones

Douglas A Thonebe

Brandon T Slaney

Marsha E Perkins, Legal Representative

Jams W Norris

Scott A Carr

Charles R Lejambre

A fuel power transfer system for an engine may include a cryogenic fuel supply, a fuel pump in fluid communication with the cryogenic fuel supply, a multi-position valve in fluid communication with the fuel pump and a combustion chamber of the engine, a fuel turbine operatively coupled to the fuel pump and having a primary discharge port in fluid communication with the combustion chamber, a primary heat exchanger in fluid communication between the multi-position valve and the fuel turbine, and a gearbox operatively coupled to the fuel turbine and the fuel pump and configured to transfer power from the fuel turbine to the engine.

Methods for power transfer in cryogenic fuel applications

A gas turbine engine includes an engine case along an engine axis, a conformal accessory drive gearbox housing mounted to the engine case, and at least one accessory mounted to the conformal housing.

Conformal accessory gearbox for low bypass gas turbine engine

A gas turbine engine includes a propulsor section and a speed change mechanism for driving the propulsor section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers extending from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first propulsor section support bearing is mounted on a first axial side of the speed change mechanism and a second propulsor section support bearing is mounted on the bearing support on a second axial side of the speed change mechanism. The second propulsor section support bearing is a propulsor thrust bearing. Each of the plurality of fingers include a pin opening with a pin extending through the pin opening and into the epicyclic gear train.

Fan drive gear system

A gas turbine engine includes a fan rotor, a compressor section, a combustor section, and a turbine section. The turbine section is positioned downstream of the combustor section. A fan drive turbine in the turbine section, and a shaft connects the fan drive turbine to the fan rotor. An inlet duct is connected to a cooling air source and connected to a cooling compressor downstream of the fan drive turbine. The cooling compressor is connected to an air source, and connected to a turning duct for passing compressed air in an upstream direction through the shaft. A method is also disclosed.

Thermal management of a gas turbine engine shaft

A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

Thermal management system for gas turbine engine

A method for forming a reinforced metallic structure includes providing a tool having a formation surface corresponding to a desired structure shape of the reinforced metallic structure. The method also includes positioning a plurality of fibers on the formation surface of the tool. The method also includes depositing a layer of material on the plurality of fibers using a cold-spray technique. The method also includes removing the layer of material with the plurality of fibers from the tool to create the reinforced metallic structure.

Reinforcement of a deposited structure forming a metal matrix composite

A gas turbine engine includes a turbine rotor connected to a main compressor rotor. A tail cone is mounted inward of an exhaust core flow. A generator rotor is adjacent a generator stator. The generator rotor and stator are mounted within the tail cone. A passage connects a bypass flow path to the tail cone. A cooling air compressor is operable within the passage. The turbine rotor drives a shaft to drive the generator rotor and the cooling compressor. A method is also disclosed.

Thermal management of tail cone mounted generator

A heat exchanger duct includes a wall having ends spaced along a central axis. An inlet manifold is positioned within a downstream portion of the duct at a radially outward location. An outlet manifold is positioned within an upstream portion of the duct at a radially outward location. At least one of the inlet and outlet manifolds extend at least 10 degrees around the circumference of the duct. A central manifold is disposed between the inlet and outlet manifolds, and radially inwardly of the inlet and outlet manifolds. Heat exchanger entrance elements extend radially inward from the inlet manifold to the central manifold, and heat exchanger exit elements extend radially outward from the central manifold to the outlet manifold. A gas turbine engine is also disclosed.

Duct mounted heat exchanger

A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

A seal assembly for a gas turbine engine, including: a first finger seal assembly, the first finger seal assembly including two layers each being secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the first finger seal assembly are secured to each other; a second finger seal assembly, the second finger seal assembly including two layers each secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the second finger seal assembly are secured to each other; and an arc-shaped segment finger seal assembly located between the first finger seal assembly and the second finger seal assembly, the arc-shaped finger seal assembly including two layers each secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the arc-shaped finger seal assembly are secured to each other.

Finger seal assembly for gas turbine engine and method of making

A fluid injection system for a gas turbine engine may comprise a fluid injector configured to inject a fluid into an exhaust flow exiting a turbine section of the gas turbine engine. The fluid injector may be coupled to a turbine exit guide vane located at a forward end of an exhaust system of the gas turbine engine. The fluid may decrease a temperature of the exhaust flow exiting the turbine section and/or increase a thrust of the gas turbine engine.

Fluid injection systems for gas turbine engines

A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.

Heat exchanger supply plenum

Growing community of inventors

Tolland, CT, United States of America

Gary D Roberge