Dual-vortical-flow hybrid rocket engine

摘要

The present invention discloses a dual-vortical-flow hybrid rocket engine, including a main body and a nozzle communicating with an end of the main body. The main body includes a plurality of disk-like combustion chambers arranged longitudinally, and a central combustion chamber formed along the axial portion and communicating the disk-like combustion chambers. Each of the disk-like combustion chambers is provided with a plurality of oxidizer injection nozzles at its inner circumference surface. Inside the disk-like combustion chambers, the oxidizer is injected in nearly the tangent directions of the circumference, and the injection directions are opposite for the neighboring disk-like combustion chambers, which creates vortical flows with opposite rotating directions so as to increase the total residence time of the combustion reactions of the oxidizer and the solid-state fuel in the disk-like combustion chambers of the present invention.

主权项

1. A dual-vortical-flow rocket engine comprising:
a main body having:
a plurality of disk-like combustion chambers arranged longitudinally;a central combustion chamber communicating with an axial portion of each disk-like combustion chamber; anda plurality of oxidizer injection nozzles disposed at an inner circumference surface of each disk-like combustion chamber, wherein the plurality of oxidizer injection nozzles of one of the plurality of disk-like combustion chambers face toward a clockwise direction of the inner circumference surface of the one the plurality of disk-like combustion chambers, and the plurality of oxidizer injection nozzles of another one of the plurality of disk-like combustion chambers face toward a counterclockwise direction of the inner circumference surface of the another one the plurality of disk-like combustion chambers, such that a rotating direction of the oxidizer injected into the one of the plurality of disk-like combustion chambers is clockwise, and a rotating direction of the oxidizer injected into the another one of the plurality of disk-like combustion chambers is counterclockwise, wherein the one the plurality of disk-like combustion chambers and the another one of the plurality of disk-like combustion chambers are two immediately adjacent disk-like combustion chambers; and a nozzle connected at an end of the main body.