Abstract
We have previously proposed a new type of rocket engine that uses the new compressive combustion principle based on supermulti-jets colliding with pulse, which may further improve the thermal efficiency of present rocket engines. In this research, we calculate the flow inside the combustion chamber of our new rocket engine by computation in two cases of injection nozzle distributions, half-sphere and sphere-like. We used the unsteady three-dimensional compressible Navier-Stokes equation, by using a method alike the C-CUP method. Computational results showed that in the sphere-like injection nozzle distribution, combustion efficiency and the pressure of combustion chamber are higher than those in the half-sphere injection nozzle distribution.
| Original language | English |
|---|---|
| Title of host publication | AIAA Aerospace Sciences Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Edition | 210059 |
| ISBN (Print) | 9781624105241 |
| DOIs | |
| Publication status | Published - 2018 Jan 1 |
| Event | AIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States Duration: 2018 Jan 8 → 2018 Jan 12 |
Other
| Other | AIAA Aerospace Sciences Meeting, 2018 |
|---|---|
| Country | United States |
| City | Kissimmee |
| Period | 18/1/8 → 18/1/12 |
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ASJC Scopus subject areas
- Aerospace Engineering
Cite this
Computations for improving the performance of a new hydrogen-oxygen rocket engine based on supermulti-jets colliding with pulse. / Kawaguchi, Sota; Konagaya, Remi; Tsuru, Kohta; Naitoh, Ken.
AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Computations for improving the performance of a new hydrogen-oxygen rocket engine based on supermulti-jets colliding with pulse
AU - Kawaguchi, Sota
AU - Konagaya, Remi
AU - Tsuru, Kohta
AU - Naitoh, Ken
PY - 2018/1/1
Y1 - 2018/1/1
N2 - We have previously proposed a new type of rocket engine that uses the new compressive combustion principle based on supermulti-jets colliding with pulse, which may further improve the thermal efficiency of present rocket engines. In this research, we calculate the flow inside the combustion chamber of our new rocket engine by computation in two cases of injection nozzle distributions, half-sphere and sphere-like. We used the unsteady three-dimensional compressible Navier-Stokes equation, by using a method alike the C-CUP method. Computational results showed that in the sphere-like injection nozzle distribution, combustion efficiency and the pressure of combustion chamber are higher than those in the half-sphere injection nozzle distribution.
AB - We have previously proposed a new type of rocket engine that uses the new compressive combustion principle based on supermulti-jets colliding with pulse, which may further improve the thermal efficiency of present rocket engines. In this research, we calculate the flow inside the combustion chamber of our new rocket engine by computation in two cases of injection nozzle distributions, half-sphere and sphere-like. We used the unsteady three-dimensional compressible Navier-Stokes equation, by using a method alike the C-CUP method. Computational results showed that in the sphere-like injection nozzle distribution, combustion efficiency and the pressure of combustion chamber are higher than those in the half-sphere injection nozzle distribution.
UR - http://www.scopus.com/inward/record.url?scp=85044375539&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85044375539&partnerID=8YFLogxK
U2 - 10.2514/6.2018-0668
DO - 10.2514/6.2018-0668
M3 - Conference contribution
AN - SCOPUS:85044375539
SN - 9781624105241
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
ER -