Dual-Vortical-Flow Hybrid Rocket Engine
| dc.citation.patentcountry | USA | zh_TW |
| dc.citation.patentnumber | 20140352276 | zh_TW |
| dc.contributor.author | Chen Yen-Sen | en_US |
| dc.contributor.author | Wu Men-Zen | en_US |
| dc.contributor.author | Wu Jong-Shinn | en_US |
| dc.contributor.author | Lai Alfred | en_US |
| dc.contributor.author | Lin Jhe-Wei | en_US |
| dc.contributor.author | Chou Tzu-Hao | en_US |
| dc.date.accessioned | 2014-12-16T06:14:41Z | |
| dc.date.available | 2014-12-16T06:14:41Z | |
| dc.date.issued | 2014-12-04 | en_US |
| dc.description.abstract | 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. | zh_TW |
| dc.identifier.govdoc | F02K009/00 | zh_TW |
| dc.identifier.uri | https://ir.lib.nycu.edu.tw/handle/11536/104854 | |
| dc.language.iso | zh_TW | en_US |
| dc.title | Dual-Vortical-Flow Hybrid Rocket Engine | zh_TW |
| dc.type | Patents | en_US |