TY - GEN
T1 - Visualization of flames in combustion chamber of hybrid rocket engine with multi-section swirl injection method
AU - Tada, Hiroshi
AU - Aso, Shigeru
AU - Tani, Yasuhiro
AU - Ohyama, Sho
AU - Araki, Kentaro
AU - Ohe, Kengo
AU - Mizuchi, Masato
AU - Shimada, Toru
N1 - Funding Information:
This research is supported by the Hybrid Rocket Research Working Group (HRrWG) of Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency. The authors thank members of HRrWG for their helpful discussion.
Publisher Copyright:
© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2014
Y1 - 2014
N2 - In order to clarify combustion phenomena of hybrid rocket engines with multi-section swirl injection method, visualization tests of combustion flames has been conducted. In the present paper, paraffin fuel whose regression rate is high was used, and several types of placement of ports which inject oxygen into combustion chamber were compared. The number of the ports in each section had marginal effect on a combustion phenomenon. On the other hand the distance between each cross-section affected performance and combustion phenomena. In multi-section opposite injection method, the flow toward downstream of combustion chamber was observed. In both methods, enlarging the surface area that high temperature gas flows along was very important to increase regression rate.
AB - In order to clarify combustion phenomena of hybrid rocket engines with multi-section swirl injection method, visualization tests of combustion flames has been conducted. In the present paper, paraffin fuel whose regression rate is high was used, and several types of placement of ports which inject oxygen into combustion chamber were compared. The number of the ports in each section had marginal effect on a combustion phenomenon. On the other hand the distance between each cross-section affected performance and combustion phenomena. In multi-section opposite injection method, the flow toward downstream of combustion chamber was observed. In both methods, enlarging the surface area that high temperature gas flows along was very important to increase regression rate.
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U2 - 10.2514/6.2014-3850
DO - 10.2514/6.2014-3850
M3 - Conference contribution
AN - SCOPUS:84913570266
T3 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
BT - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
Y2 - 28 July 2014 through 30 July 2014
ER -