General Electric Company

Hyliion Holdings Corp.

Alex William Ariapad

Jeffrey Douglas Rambo

Joshua Tyler Mook

Michael Robert Notarnicola

Stefaan Guido Van Nieuwenhove

Mark Samuel Bailey

Ramon Martinez

Sultan Shair

Jared Matthew Wolfe

Nicolas Kristopher Sabo

Hojjat Nasr

Thomas Kluge

David Scott Simmermon

Matthew Ryan Johns

Johannes Hornof

Nikolaus Mroncz

Alexander Hofmann

Rene Hertha

A thermal control apparatus including a body defining a centerline axis extended along a height and a circumferential direction extended relative to the centerline axis. The body forms a flow circuit therethrough, an inlet opening, and an outlet opening each in fluid communication with the flow circuit. The flow circuit is extended in parallel flow arrangement along the circumferential direction from the inlet opening to the outlet opening. A cavity is extended at least partially through the body along the centerline axis. A thermal control system includes the thermal control apparatus, a fluid flow device configured to provide a flow of heat transfer fluid to the apparatus through the inlet opening and to receive the flow of heat transfer fluid from the outlet opening of the apparatus, and a flow conduit providing fluid communication of the flow of heat transfer fluid between the fluid flow device and the apparatus.

Thermal control apparatus for laser system

A method of pressurizing a closed-cycle engine includes performing a non-steady state operation in which a working fluid flows to or from a pressurized tank: i) to or from a plurality of sumps defined by respective ones of a plurality of cylinder-piston assemblies of the closed-cycle engine; or ii) to or from one or more air bearings associated with each one of the plurality of the cylinder-piston assemblies; or iii) both and performing, before and/or after performing the non-steady state operation, a steady-state operation in which the working fluid flows through the plurality of sumps and the one or more air bearings along a steady-state loop that is fluidly decoupled from the pressurized tank.

Pressure control system for a closed-cycle engine

A heat exchanger for an aircraft includes an inlet plenum housing defining an inlet plenum configured to receive a fluid and an outlet plenum housing defining an outlet plenum configured to discharge the fluid. Furthermore, the heat exchanger includes a core configured to heat or cool a first portion of the fluid, with the core defining a plurality of fluid passages extending from the inlet plenum to the outlet plenum. Moreover, the heat exchanger includes a passive bypass defining a passive bypass flow path fluidly coupled to and extending between the inlet plenum and the outlet plenum. As such, the passive bypass flow path is in parallel with at least a portion of the core such that a second portion of the fluid bypasses at least a portion of the core and flows continuously and unobstructed through the passive bypass flow path to the outlet plenum.

Heat exchanger for an aircraft

A powder removal assembly includes a build module comprising module sidewalls and a moveable build plate slidably coupled to the module sidewalls, and an extraction housing removably engaged with the module sidewalls of the build module and defining a turbulence chamber between the build module and the extraction housing. The extraction housing includes one or more sidewalls comprising one or more sidewall fluid flow channels extending through the one or more sidewalls and a top wall coupled to the one or more sidewalls, wherein the one or more sidewall fluid flow channels extend from a position proximate a base of the one or more sidewalls to the top wall.

Powder removal systems and assemblies for additive manufacturing

Growing community of inventors

Cincinnati, OH, United States of America

Alex William Ariapad