General Electric Company

William Thomas Bennett

Craig Alan Gonyou

Gregory Allen Boardman

John Howard Starkweather

Jared Peter Buhler

Kevin Samuel Klasing

Valeria Proano Cadena

Douglas Downey Turner

Anthony S Urbanski

Marco Venturato

John Gibbons

A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.

Gas turbine engine with igniter stack or borescope mount having noncollinear cooling passages

A gas turbine engine includes a combustion section space between a compressor section in a turbine section. The combustion section defines a combustion chamber and includes a combustor member defining an opening to the combustion chamber. A mounting assembly extends around or is positioned adjacent to the opening defined by the combustor member. In igniter extends through a ferrule of the mounting assembly and includes a distal end positioned proximate the opening in the combustor member. The igniter defines a plurality of channels each channel extending between a first end and a second end. The first end is positioned away from the distal end of the igniter relative to the second end, and the second end is a terminal end spaced from the distal end of the igniter.

Igniter for a gas turbine engine

The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.

Fuel nozzle assembly with impingement purge

The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. The forward wall defines at least one channel inlet orifice. At least one sidewall defines at least one channel outlet orifice. At least one micro channel cooling circuit is defined between the one or more channel inlet orifices and the one or more channel outlet orifices.

Fuel nozzle assembly with micro channel cooling

A method for making shaped cooling holes in a substrate by pulsing and stopping a laser while moving the laser or substrate. The method produces shaped cooling holes with a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension.

Growing community of inventors

Cincinnati, OH, United States of America

William Thomas Bennett