Abstract
The convection heating method of high temperature combustion-gas generated by the gas-heating wind tunnel is used as a popular test method for performance assessment of thermal protection systems (TPS) of hypersonic vehicles. In this paper, a combustion-gas wind tunnel device based on two-stage atomization, two-stage combustion/mixing mode of high-temperature rise combustor (ACWT-TATCM) is designed. In the performance test under normal atmospheric temperature and atmospheric pressure, the continuous, accurate, rapid, and ultra-wide linear adjustment of the combustion-gas temperature can be achieved by adjusting the mass flow of aviation kerosene while keeping the total air supply unchanged. The results show that the combustion-gas temperature can rise from 300 K to 2100 K within 3 s. In addition, when the air mass flow is 100 g/s, the ACWT-TATCM can reach the optimal operation state. The combustion efficiency can be up to 97.55%, while the optimal values of outlet temperature distribution coefficient and total pressure recovery coefficient are 0.209 and 97.3%, respectively.
| Original language | English |
|---|---|
| Pages (from-to) | 21-36 |
| Number of pages | 16 |
| Journal | Heat Transfer Research |
| Volume | 53 |
| Issue number | 13 |
| DOIs | |
| State | Published - 2022 |
Keywords
- aviation kerosene
- combustion-gas
- combustor
- high temperature rise
- wind tunnel
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