United Technologies Corporation

Aerojet Rocketdyne of De, Inc.

Mark J Ricciardo

Russell B Hanson

Joey Wong

Jose E Ruberte Sanchez

Jim A Clark

Bradley C Johnson

Randolph T Lyda

Ryan W Brandt

A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.

Alignment system and methodology to account for variation in a gas turbine engine

A cap for a liquid propellant injection assembly of a rocket engine includes a cap body and a valve assembly. The cap body extends between first and second ends. The cap body has a bore that fluidly connects one or more inlets to an outlet. The inlets are disposed in a tubular sidewall of the cap body. The outlet is disposed in the second end of the cap body. The valve assembly includes a valve cap disposed around the first end of the cap body. The valve assembly is adapted to selectively regulate flow of a propellant through the inlets in the cap body as a function of pressure exerted by the propellant against the valve assembly.

Injector assembly for a rocket engine

A system for cooling a combustion chamber of an engine, such as a rocket engine, is provided. The system has a plurality of coolant tubes or passages surrounding the combustion chamber, a torroidal coolant-collection manifold for receiving coolant from the coolant tubes or passages and for discharging the coolant through a discharge port, and a plurality of turning vanes within the torroidal manifold for reducing pressure loss and improving pressure uniformity associated with the torroidal coolant-collection manifold.

Enhanced performance torroidal coolant-collection manifold

Growing community of inventors

Royal Palm Beach, FL, United States of America

Mark J Ricciardo