United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Anthony Van

John S Tu

San Quach

Robert M Sonntag

John J Rup, Jr

Robert Selinsky, Jr

Timothy S Snyder

James B Hoke

Monica Pacheco-Tougas

Lawrence A Binek

Dennis M Moura

Jose R Paulino

Sean R Jackson

Jeffrey Leon

Frank J Trzcinski

Joseph James Sedor

David Kwoka

Scott A Elliott

Neil B Ridgeway

Timothy J Gaudet

Andrew Cervoni

Thomas A Bush

Gerard V Cadieux

Victor M Pinedo

Lisa A Jenkins

Lisa Tse

Jr Robert Selinsky

Scott A Elliot

Robert Selinsky Jr

John J Rup Jr

Matthew G Van Eck

Joseph J Sedor

Robert Selinsky

John J Rup

Jr John J Rup

An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector aperture and a fuel supply passage. The injector aperture extends longitudinally through the engine structure along a centerline. The fuel supply passage extends laterally within the engine structure to the injector aperture. The fuel injector is mated with the injector aperture. The fuel injector includes a nozzle passage and a nozzle orifice. The nozzle passage extends longitudinally along the centerline within the fuel injector to the nozzle orifice. The nozzle passage is fluidly coupled with the fuel supply passage.

Modular injector bolt for an engine

A combustor panel of a combustor may include a combustion facing surface, a cooling surface opposite the combustion facing surface, and heat transfer pins extending from the cooling surface. A grouping of the heat transfer pins may include a metallic coating.

Systems and methods for combustor panel

A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

Wall panel assembly for a gas turbine engine

Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.

Hybrid through holes and angled holes for combustor grommet cooling

Aspects of the disclosure are directed to controlling a distribution of fuel to a plurality of nozzles associated with at least one aircraft engine by: determining a state of operation associated with the at least one aircraft engine, causing a valve coupled to a fuel supply and each of the nozzles to open when it is determined that the state of operation indicates a high power state relative to at least one threshold, and causing the valve to close when it is determined that the state of operation indicates a low power state relative to the at least one threshold.

Fuel system for tone control and operability

Growing community of inventors

Palm City, FL, United States of America

Anthony Van