Abstract
A micro annular combustor was designed based on research both inland and oversea, and simulated the combustion in the annual combustor. And then, according to the simulation result, the design of combustor was optimized and re-computed. All case including chemical reaction, heat radiation, evaporating of fuel and secondary breakup of spray was comprised in numerical simulation, the boundary condition of inlet was gained through computing and the parameter of spray was gained through experiment. The result of computation can reflect the reality case exactly. At last, the numerical simulation result of two combustor was compared, the result indicate the optimized design is reasonable, fuel can combusted sufficiently in chamber and the performance parameter is satisfied the design requirement. All data can provide numerical foundation for better performance in combustion chamber.
| Original language | English |
|---|---|
| Pages (from-to) | 1783-1787 |
| Number of pages | 5 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 23 |
| Issue number | 10 |
| Publication status | Published - Oct 2008 |
Keywords
- Combustor design
- Micro-turbine engine
- Numerical simulation