Abstract
In order to learn more gas-dynamic resonance heating rules and to provide experimental foundation for investigating gas-dynamic resonance igniter, gas-dynamic resonance heating experiments based upon initial tests were carried out. Factors investigated, which affect resonance heating characteristics, include variation of flow rate, different structures of exhaust hole and different diameters of connect cavity. Through lots of experiments with different design parameters, some gas-dynamic resonance heating rules were found, and optimum structure design parameters were obtained for gas-dynamic resonance igniter design.
| Original language | English |
|---|---|
| Pages (from-to) | 323-327 |
| Number of pages | 5 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 20 |
| Issue number | 2 |
| State | Published - Apr 2005 |
Keywords
- Aerodynamic heating
- Aerospace propulsion system
- Ignition
- Liquid rocket engines
- Resonance tube
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