Abstract
Transpiration cooling is one of the serviceable technologies for thermal protection systems of hypersonic vehicles. This paper presents an experimental investigation on transpiration cooling of a new porous cylindrical structure made of sintered metal particles, the behaviors of aviation kerosene as the coolant in supersonic flow are investigated. Both the single and triple cylinders are used in the installation. Infrared thermography is used to observe the temperature of the porous cylinder in the experiment. When the total mass flow of aviation kerosene is 26 g/s, the porous cylinders are well cooled in the airflow of Mach 2.1 and total temperature 1165 K, and the maximum wall temperature of the porous cylinder does not exceed 600 K.
| Original language | English |
|---|---|
| Pages (from-to) | 3053-3060 |
| Number of pages | 8 |
| Journal | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics |
| Volume | 41 |
| Issue number | 12 |
| State | Published - Dec 2020 |
| Externally published | Yes |
Keywords
- Cylinder
- Porous media
- Supersonic flow
- Transpiration cooling
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