General Electric Company

Christopher Dale Mathias

Adon Delgado, Jr

Todd James Buchholz

Apostolos Pavlos Karafillis

Guanghua Wang

Nirm Velumylum Nirmalan

Jeremy Clyde Bailey

Dylan James Fitzpatrick

Mohamed Sakami

Dennis Robert Jonassen

Kyle Earl Roland Henry

Paul W Donahue

Ronald W Ferree, Jr

A gas turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a hollow probe extending from the housing and having a longitudinal axis, and an image receiving device at an end of the hollow probe configured to receive at least one of a perspective or image.

Optical imaging system for a gas turbine engine

An attachment assembly for attaching a center structure to an outer structure at least partially circumscribing the center structure, the attachment assembly having a bushing provided within the center structure or the outer structure, the bushing defining a first through passage, a bushing adapter slidably mounted within the first through passage and defining a second through passage, a threaded passage provided on the other of the center structure or the outer structure and a bolt passing through the first through passage and the second through passage and threaded into the threaded passage.

Attachment assembly and gas turbine engine with attachment assembly

An electrical power system for an aircraft including a turbine engine coupled to the aircraft and providing propulsive thrust and emitting heat during operation to define a high temperature source, a cryogenic fuel system located within the aircraft and providing fuel for the turbine and emitting heat at a lower temperature than the heat from the turbine engine to define a low temperature source and an electrical power generator located on the aircraft and having a thermodynamic generator using the temperature difference to generate electrical power and a method for producing electric power.

System and method for aviation electric power production

A turbine engine assembly including a turbine core and a cryogenic fuel system. The turbine core includes: a compressor section; a combustion section; and a turbine section, which are axially aligned. The a cryogenic fuel system includes: a cryogenic fuel reservoir; a vaporizer heat exchanger; a liquid supply line operably coupling the fuel reservoir to an input of the vaporizer heat exchanger; a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section; and a second heat exchanger thermally connecting the liquid supply line and the gas supply line to transfer heat from the gas supply line to the liquid supply line.

Turbine engine assembly and dual fuel aircraft system

Growing community of inventors

Cincinnati, OH, United States of America

Christopher Dale Mathias