Abstract
The flowfield in liquid fuel purge method and the effect of parameters on purging process are analyzed using one-dimensional numerical simulation. The combustor length, total pressure of oxidizer, the width of propellant region from the ignition point to the upstream side and back pressure are taken as the parameters. The purge process occupies a large part of the entire cycle and the back flow of burned gas which has linear relationship with the time required for the burned gas needs to be suppressed. The maximum back flow distance of burned gas depends on the pressure ratio of burned gas to oxidizer flow and is minimized when the oxidizer flow is choked and the propellant does not exist upstream from the ignition point at the ignition time. For realizing the high frequency operation, it is desired to make the flow choked by increasing total pressure of oxidizer and decreasing back pressure and to shorten the width of propellant region upstream from the ignition point at the ignition time.
| Original language | English |
|---|---|
| Title of host publication | AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc. |
| ISBN (Electronic) | 9781624104473 |
| DOIs | |
| Publication status | Published - 2017 |
| Event | 55th AIAA Aerospace Sciences Meeting - Grapevine, United States Duration: 2017 Jan 9 → 2017 Jan 13 |
Other
| Other | 55th AIAA Aerospace Sciences Meeting |
|---|---|
| Country | United States |
| City | Grapevine |
| Period | 17/1/9 → 17/1/13 |
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ASJC Scopus subject areas
- Aerospace Engineering
Cite this
Numerical investigation on burned gas backflow in liquid fuel purge method. / Watanabe, Hiroaki; Matsuo, Akiko; Matsuoka, Ken; Kasahara, Jiro.
AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2017. AIAA 2017-1284.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
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TY - GEN
T1 - Numerical investigation on burned gas backflow in liquid fuel purge method
AU - Watanabe, Hiroaki
AU - Matsuo, Akiko
AU - Matsuoka, Ken
AU - Kasahara, Jiro
PY - 2017
Y1 - 2017
N2 - The flowfield in liquid fuel purge method and the effect of parameters on purging process are analyzed using one-dimensional numerical simulation. The combustor length, total pressure of oxidizer, the width of propellant region from the ignition point to the upstream side and back pressure are taken as the parameters. The purge process occupies a large part of the entire cycle and the back flow of burned gas which has linear relationship with the time required for the burned gas needs to be suppressed. The maximum back flow distance of burned gas depends on the pressure ratio of burned gas to oxidizer flow and is minimized when the oxidizer flow is choked and the propellant does not exist upstream from the ignition point at the ignition time. For realizing the high frequency operation, it is desired to make the flow choked by increasing total pressure of oxidizer and decreasing back pressure and to shorten the width of propellant region upstream from the ignition point at the ignition time.
AB - The flowfield in liquid fuel purge method and the effect of parameters on purging process are analyzed using one-dimensional numerical simulation. The combustor length, total pressure of oxidizer, the width of propellant region from the ignition point to the upstream side and back pressure are taken as the parameters. The purge process occupies a large part of the entire cycle and the back flow of burned gas which has linear relationship with the time required for the burned gas needs to be suppressed. The maximum back flow distance of burned gas depends on the pressure ratio of burned gas to oxidizer flow and is minimized when the oxidizer flow is choked and the propellant does not exist upstream from the ignition point at the ignition time. For realizing the high frequency operation, it is desired to make the flow choked by increasing total pressure of oxidizer and decreasing back pressure and to shorten the width of propellant region upstream from the ignition point at the ignition time.
UR - http://www.scopus.com/inward/record.url?scp=85017236392&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85017236392&partnerID=8YFLogxK
U2 - 10.2514/6.2017-1284
DO - 10.2514/6.2017-1284
M3 - Conference contribution
AN - SCOPUS:85017236392
BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
ER -