Turbopump, thrust chamber, and injector with distribution system and a circular array of support columns to flow liquid from the distribution system into a combustion chamber
Disclosed herein are various technologies pertinent to rocket engines, including injector, thrust chamber, and electrical turbopump devices that may be combined to provide a more efficient rocket engine. The thrust chamber may be coupled with an injector having a circular array of support columns supporting a distribution system. Liquid may be flowed from the distribution system, through the support columns, and into a combustion chamber of the thrust chamber.
B33Y 80/00 - Produits obtenus par fabrication additive
F28F 13/18 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution par application de revêtements, p. ex. absorbant les radiations ou les réfléchissantDispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution par application d'un traitement de surface, p. ex. un polissage
F02K 9/64 - Chambres de combustion ou de poussée comportant des aménagements pour le refroidissement
F28F 13/14 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution en créant sur les parois des canalisations des zones ayant des degrés différents de conduction de la chaleur
2.
Jettisonable battery systems for powering electrical turbopumps for launch vehicle rocket engine systems
Disclosed herein are various technologies pertinent to jettisonable battery systems for use in rocket engine-based launch vehicles. Such systems may feature batteries that are configured to be used to power one or more electric turbopumps that may be used to supply fuel to a rocket engine or engines. One or more of the batteries may be jettisoned during flight in order to reduce weight and as they are depleted. In some implementations, a depleted battery may remain electrically connected with the turbopump(s) while a new battery is electrically connected with the turbopump(s). The depleted battery may then be electrically disconnected from the turbopump and jettisoned.
Disclosed herein are various technologies pertinent to jettisonable battery systems for use in rocket engine-based launch vehicles. Such systems may feature battery units that are configured to be used to power one or more electric turbopumps that may be used to supply fuel to a rocket engine or engines. One or more of the battery units may be jettisoned during flight in order to reduce weight and as they are depleted. In some implementations, the battery units may be connected in parallel with the turbopump(s), with a depleted battery unit being electrically disconnected from the parallel circuit and jettisoned.
Disclosed herein are various technologies pertinent to rocket engines, including injector, thrust chamber, and electrical turbopump devices that may be combined to provide a more efficient rocket engine. The electrical turbopump impeller includes a coolant bypass port fluidically connected with a coolant passage that passes through the impeller central hub and allows some of the propellant that is acted on by the impeller to bypass the impeller outlet and instead be flowed into the electrical turbopump housing so that the diverted propellant may be used to cool the various components housed within the housing such as the electric motor bearings, stator, rotor, and electronics.
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