Aerojet Rocketdyne, Inc.

Aerojet Rocketdyne of De, Inc.

Frederick E Dodd

Douglas S Parker

William S Brown

Rodney Noble

Thomas M Walczuk

Daniel P Cap

An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with an ignition fluid supply downstream of the ignition fluid supply, and a second annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with a fuel supply downstream of the fuel supply. The second annulus is fluidly coupled between the first annulus and the central cavity.

Injector element for rocket engine

An engine start system includes a facility that has a ground based hydraulic pressurization system and a combustor of a liquid propellant rocket engine. The engine is fluidly coupled to the ground based hydraulic pressurization system. The liquid propellant rocket engine is operably detachable from the ground based hydraulic pressurization system.

Ground hydraulic system hypergolic slug injection

A fuel manifold for a thrust chamber assembly includes a main fuel chamber which is generally frustro-conical in shape. The main fuel chamber provides a resonance frequency that is different than an acoustic resonance frequency of a combustion chamber.

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Sacramento, CA, United States of America

Frederick E Dodd