General Electric Company

Concept Laser Gmbh

Ge Additive Germany Gmbh

Changjin Yoon

Narendra Digamber Joshi

Kishore Ramakrishnan

Kwanwoo Kim

Nikolai N Pastouchenko

Joseph Douglas Monty

Peter Pontiller-Schymura

Andrey Meshkov

David Perveiler

John Thomas Herbon

Shawn David Wehe

Owen James Sullivan Rickey

Umesh Paliath

Benedikt Roidl

ShihYang Hsieh

Jason A Lee

A propulsion system is provided, wherein the propulsion system includes an afterburner assembly. The afterburner assembly including: an exhaust section and a fuel injector assembly that is operable to inject fuel in the exhaust section. The fuel injector assembly includes a plurality of fuel injection members. The plurality of fuel injection members defines a hot zone and a cold zone. The cold zone is positioned to provide a noise insulation barrier for the hot zone.

Propulsion system for jet noise reduction

A method of additively manufacturing a three-dimensional object may be performed using an irradiation sequence that is based at least in part on a predicted location of one or more fume plumes emitted from the powder material when irradiated by a plurality of energy beams. An exemplary method may include determining, with a computing device, an irradiation sequence for selectively consolidating powder material using an energy beam system of an additive manufacturing machine, and providing control commands, from the computing device to the energy beam system, configured to cause the energy beam system to emit a plurality of energy beams to selectively consolidate the powder material.

Irradiation sequences for consolidating powder material in an additive manufacturing machine

A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.

Gas turbine engine and combustor having air inlets and pilot burner

An acoustic damping device is provided that includes a resonating tube defining a resonating cavity with a predetermined characteristic length and a tube end defining a cavity opening, as well as a case configured to reversibly secure the tube end in fluidic communication with a fluid volume enclosed by a liner. The cavity opening is connected with the resonating cavity. The case includes a vented ferrule adpressed over a perforated region of the liner. The vented ferrule defines a ferrule opening that is aligned with the perforated region of the liner and the cavity opening to form the fluidic communication between the fluid volume and the resonating cavity.

High frequency acoustic damper for combustor liners

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Schenectady, NY, United States of America

Changjin Yoon