Abstract
During the rocket propulsion process, the jet vane which is installed in the rear side of rocket nozzle part is ablated chemically or mechanically due to the interaction of vane with a combusted gas. In this study, the simulation for the chemical ablation phenomenon of jet vane is tried out as a basic research on the jet vane performance test. Also, distributions of thermal boundary conditions such as heat transfer coefficient and recovery temperature are calculated and used as the input values for the acquisition of surface ablation rate. The thermal boundary layer integral method is applied to the calculation of these boundary conditions. User defined functions are inserted into a numerical code (FLUENT) for calculation of thermal boundary conditions and surface ablation rate. Leading edge on a jet vane is heated heavily compared with the side surfaces and therefore the ablation occurs primarily on that part. When the jet vane is rotated, the windward surface is heated and ablated more than the leeward surface. However, the ablation rate on a side surface is much lower than that on a leading edge of vane, so ablation of jet vane side surface can be ignored during the jet vane ablation simulation. In about 10 seconds of vane operation time, total ablation area is calculated not to be over 4% of the vane side surface area.
| Original language | English |
|---|---|
| Title of host publication | 37th AIAA Thermophysics Conference |
| Publication status | Published - 2004 Dec 1 |
| Event | 37th AIAA Thermophysics Conference 2004 - Portland, OR, United States Duration: 2004 Jun 28 → 2004 Jul 1 |
Other
| Other | 37th AIAA Thermophysics Conference 2004 |
|---|---|
| Country | United States |
| City | Portland, OR |
| Period | 04/6/28 → 04/7/1 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Mechanical Engineering
- Condensed Matter Physics
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A study on a surface ablation of the jet vane system in a rocket nozzle. / Yu, M. S.; Cho, H. H.; Hwang, K. Y.; Bae, J. C.
37th AIAA Thermophysics Conference. 2004.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
TY - GEN
T1 - A study on a surface ablation of the jet vane system in a rocket nozzle
AU - Yu, M. S.
AU - Cho, H. H.
AU - Hwang, K. Y.
AU - Bae, J. C.
PY - 2004/12/1
Y1 - 2004/12/1
N2 - During the rocket propulsion process, the jet vane which is installed in the rear side of rocket nozzle part is ablated chemically or mechanically due to the interaction of vane with a combusted gas. In this study, the simulation for the chemical ablation phenomenon of jet vane is tried out as a basic research on the jet vane performance test. Also, distributions of thermal boundary conditions such as heat transfer coefficient and recovery temperature are calculated and used as the input values for the acquisition of surface ablation rate. The thermal boundary layer integral method is applied to the calculation of these boundary conditions. User defined functions are inserted into a numerical code (FLUENT) for calculation of thermal boundary conditions and surface ablation rate. Leading edge on a jet vane is heated heavily compared with the side surfaces and therefore the ablation occurs primarily on that part. When the jet vane is rotated, the windward surface is heated and ablated more than the leeward surface. However, the ablation rate on a side surface is much lower than that on a leading edge of vane, so ablation of jet vane side surface can be ignored during the jet vane ablation simulation. In about 10 seconds of vane operation time, total ablation area is calculated not to be over 4% of the vane side surface area.
AB - During the rocket propulsion process, the jet vane which is installed in the rear side of rocket nozzle part is ablated chemically or mechanically due to the interaction of vane with a combusted gas. In this study, the simulation for the chemical ablation phenomenon of jet vane is tried out as a basic research on the jet vane performance test. Also, distributions of thermal boundary conditions such as heat transfer coefficient and recovery temperature are calculated and used as the input values for the acquisition of surface ablation rate. The thermal boundary layer integral method is applied to the calculation of these boundary conditions. User defined functions are inserted into a numerical code (FLUENT) for calculation of thermal boundary conditions and surface ablation rate. Leading edge on a jet vane is heated heavily compared with the side surfaces and therefore the ablation occurs primarily on that part. When the jet vane is rotated, the windward surface is heated and ablated more than the leeward surface. However, the ablation rate on a side surface is much lower than that on a leading edge of vane, so ablation of jet vane side surface can be ignored during the jet vane ablation simulation. In about 10 seconds of vane operation time, total ablation area is calculated not to be over 4% of the vane side surface area.
UR - http://www.scopus.com/inward/record.url?scp=84897585448&partnerID=8YFLogxK
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M3 - Conference contribution
AN - SCOPUS:84897585448
SN - 9781624100352
BT - 37th AIAA Thermophysics Conference
ER -