Rocket engine combustion chamber liner
AssigneeShapefidelity, Inc.
InventorRobert Black
Life of this patent
Estimating the term…
Abstract
A rocket engine combustion chamber liner of the present disclosure has a combustion chamber in which fuel and oxygen are ignited thereby generating low-velocity gases. The rocket engine combustion chamber liner further has a throat integral with and in fluid communication with the combustion chamber that generates high-velocity gases from the low-velocity gases received from the combustion chamber. Additionally, the rocket engine combustion chamber has a nozzle integral with and in fluid communication with the throat through which the high-velocity gases are emitted causing thrust for a rocket. The combustion chamber, the throat, and the nozzle have a common outer surface and etched into the outer surface are a plurality of channels wherein the channels have the same width and depth.
Claims8
A rocket engine combustion chamber liner, comprising:
- a combustion chamber configured for ignition therein of fuel and oxygen generating low-velocity gases;
- a throat integral with and in fluid communication with the combustion chamber configured for generating high-velocity gases from the low-velocity gases received from the combustion chamber;
- and
- a nozzle integral with and in fluid communication with the throat through which the high-velocity gases are emitted causing thrust for a rocket,
- wherein the combustion chamber, the throat, and the nozzle share a common outer surface comprising a plurality of channels and wherein the channels have the same width and depth.
A rocket, comprising:
- a thrust chamber assembly comprising a combustion chamber, a throat, and a nozzle, the combustion chamber configured for receiving oxygen and fuel;
- a rocket engine, in fluid communication with the thrust chamber assembly for delivering the oxygen to the combustion chamber, the rocket engine further configured for delivering fuel to a manifold positioned around an exit opening of the nozzle;
- a combustion chamber liner that is positioned within the thrust chamber assembly, the combustion chamber liner having a plurality of channels in fluid communication with the manifold and configured for receiving the fuel, the channels configured for delivering the fuel to the combustion chamber,
- wherein the plurality of channels each have the same width and depth.
Dependencies are inferred from the claim text.