IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0070881
(2013-11-04)
|
등록번호 |
US-9458796
(2016-10-04)
|
우선권정보 |
TW-102119323 A (2013-05-31) |
발명자
/ 주소 |
- Chen, Yen-Sen
- Wu, Men-Zen
- Wu, Jong-Shinn
- Lai, Alfred
- Lin, Jhe-Wei
- Chou, Tzu-Hao
|
출원인 / 주소 |
- National Applied Research Laboratories
|
대리인 / 주소 |
Birch, Stewart, Kolasch & Birch, LLP
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
8 |
초록
▼
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 axi
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.
대표청구항
▼
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 a
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; anda nozzle connected at an end of the main body. 2. The dual-vortical-flow rocket engine as claim 1, wherein, each oxidizer injection nozzle and a corresponding tangent line of the circumference surface of each disk-like combustion chamber form a 10˜20 degree angle such that an oxidizer injects into each disk-like combustion chamber with the 10˜20 degree angles measured from the corresponding tangent line of the circumference surface of each disk-like combustion chamber. 3. The dual-vortical-flow rocket engine as claim 2, wherein, the number of the disk-like combustion chambers is even. 4. The dual-vortical-flow rocket engine as claim 3, wherein, the number of the disk-like combustion chambers is two. 5. The dual-vortical-flow rocket engine as claim 1, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is even and the oxidizer injection nozzles disposes symmetrically. 6. The dual-vortical-flow rocket engine as claim 2, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is even and the oxidizer injection nozzles disposes symmetrically. 7. The dual-vortical-flow rocket engine as claim 3, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is even and the oxidizer injection nozzles disposes symmetrically. 8. The dual-vortical-flow rocket engine as claim 4, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is even and the oxidizer injection nozzles disposes symmetrically. 9. The dual-vortical-flow rocket engine as claim 5, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is at least four. 10. The dual-vortical-flow rocket engine as claim 6, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is at least four. 11. The dual-vortical-flow rocket engine as claim 7, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is at least four. 12. The dual-vortical-flow rocket engine as claim 8, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is at least four. 13. The dual-vortical-flow rocket engine as claim 9, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is four, six, or eight. 14. The dual-vortical-flow rocket engine as claim 10, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is four, six, or eight. 15. The dual-vortical-flow rocket engine as claim 11, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is four, six, or eight. 16. The dual-vortical-flow rocket engine as claim 12, wherein, the number of the oxidizer injection nozzles disposed at the inner circumference surface of each disk-like combustion chamber is four, six, or eight.
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