General Electric Company

Michael J Epstein

Narendra Digamber Joshi

Robert Proctor

Mehdi Milani Baladi

Kevin Richard Leamy

Robert Harold Weisgerber

Zhifeng Dong

Benjamin Paul Breig

Javier Armando Parrilla

Thomas Edward Brinson

Andrew James Fleming

Matthew John Hurt

Christopher Charles Glynn

Steven Douglas Johnson

Thomas Kupiszewski

Julius John Montgomery

William Carl Anderson

Jesse Senyo

John Andrew Kemme

Michael E Ewbank

William Dwight Gerstler

George A Coffinberry

Robert Joseph Albers

Chiranjeev Kalra

Edward E Ekstedt

Adon Delgado, Jr

Paul H Kutschenreuter, Jr

George Eugene Wilmot, Jr

Deepak Manohar Kamath

Vaibhav Bahadur

Roger Owen Barbe

Andrew David Kemp

Laura Michele Hudy

Glen William Royal

John William Hanify

Bryan Keith Doloresco

Todd James Buchholz

Hai Buu Sam

George Eugene Wilmot

Paul Bernard Stumbo

Scott Edward Farley

James Bernar Ogzewalla

Gordon G Fraser

Richard F Koch

Robert W Siebert

Debra Lynn Prikkel

A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flowto a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.

Monolithic tube-in matrix heat exchanger

Methods and devices for cooling systems () are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler () receiving bleed air from the jet engine compressor; a heat exchanger () downstream from the first precooler (); a cooling system compressor () downstream from the first precooler (), wherein the heat exchanger () and the cooling system compressor () are in separate flow paths from the first precooler (); a cooling system precooler () downstream from the cooling system compressor (); a VGT cooling system turbine () downstream from the cooling system precooler (); and a discharge conduit () downstream from the cooling system turbine () and the heat exchanger (). A bypass line () for bypassing the turbine can also be included.

Jet engine cold air cooling system

Methods and devices for cooling systems () are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler () receiving bleed air from the jet engine compressor; a heat exchanger () downstream from the first precooler (); a cooling system compressor () downstream from the first precooler (), wherein the heat exchanger () and the cooling system compressor () are in separate flow paths from the first precooler (); a cooling system precooler () downstream from the cooling system compressor (); a cooling system turbine () with variable guide vanes&#x2014;VGT&#x2014;and downstream from the cooling system precooler (); and a discharge conduit () downstream from the cooling system turbine () and the heat exchanger (). A bypass line () can also be included that bypasses the cooling system turbine ().

A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.

Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.

A method for managing boil-off from an LNG tank located on board of an aircraft. The method, including removing the boil-off from the aircraft and disposing of the removed boil-off from the aircraft and an equipment assembly for use with an aircraft having an on-board LNG tank with a vent system having an outlet coupling, including a removal system configured to remove boil-off from the aircraft and a disposal system configured to dispose of the boil-off.

Method for managing LNG boil-off and LNG boil-off management assembly

A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine.

Cryogenic fuel system and method for delivering fuel in an aircraft

An aircraft having a turbine engine having a bleed air output line, a cryogenic fuel system having a cryogenic fuel tank for storing cryogenic fuel and a supply line operably coupling the tank to the turbine engine, and an on board inert gas generating system (OBIGGS) fluidly coupled to the bleed air output and having a nitrogen rich stream output line and an oxygen rich stream output line.

Aircraft and a retrofit cryogenic fuel system

A method of managing evaporated cryogenic fuel in a storage tank of a cryogenic fuel system of an aircraft and an aircraft having at least one turbine engine providing propulsive force for the aircraft and a cryogenic fuel system including a passively cooled cryogenic fuel storage tank located within the aircraft, a pressure vent fluidly coupled to the cryogenic fuel storage tank and exhausting evaporated gas from the cryogenic fuel to define a natural gas vent stream, and a catalytic converter fluidly coupled to the pressure vent.

Aircraft and method of managing evaporated cryogenic fuel

A system in one embodiment includes a mixing module, an oxidation module, and a heat exchanger. The mixing module is configured to receive and mix a boil-off gas stream from a cryotank. The oxidation module is configured to receive the mixed stream, and to oxidize the boil-off gas in the mixed stream to produce an exhaust stream. The heat exchanger is configured to exchange heat between streams passing through a first passage configured to receive at least a portion of the exhaust stream, and a second passage configured to receive a fluid including the boil-off gas. The heat exchanger is configured to heat the fluid including the boil-off gas and cool the at least a portion of the exhaust stream. The fluid including the boil-off gas is heated by the heat exchanger upstream of the oxidation module.

Systems and methods for oxidation of boil-off gas

A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced fasteners. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts.

Aerodynamic fastener shield for turbomachine

A method enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferentially around the rotor assembly such that a clearance is defined between an inner shroud surface of the casing assembly and the rotor blade tips, and coupling a clearance control system to the casing assembly to facilitate maintaining the clearance between the casing assembly and the rotor blade tips, wherein at least a portion of an external surface of the clearance control system is formed with a textured pattern that facilitates increasing the clearance control closure capability during engine operation.

Methods and apparatus for maintaining rotor assembly tip clearances

A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced bolts. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts. A plurality of closely spaced-apart, spirally-oriented channels are formed in the fastener shield cover for deflecting the fluid flow impinging on the fastener shield cover, thereby increasing the tangential velocity and lowering the relative temperature of the fluid flow.

Swirl-enhanced aerodynamic fastener shield for turbomachine

A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.

Methods and apparatus for regulating turbine clearance control system airflow

A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

Growing community of inventors

West Chester, OH, United States of America

Michael J Epstein