Abstract
A system-level modularization numerical model which can deal with the coupling effect of combustion and flow was established for combustion device, with air and kerosene as reactants, of a turbine test rig and its outlet section, and a thermodynamic calculation scheme based on mixture fraction and a mixture fraction equation were put forward. Comparison with simulation results of the model based on mass-flow-rate mixture ratio and experimental results indicates that the mixture fraction-based model can solve the problem of transient simulation stability in the previous research, and reach the accuracy of simulation consistent with experimental results.
| Original language | English |
|---|---|
| Pages (from-to) | 981-986 |
| Number of pages | 6 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 33 |
| Issue number | 6 |
| State | Published - Dec 2012 |
Keywords
- Combustion device
- Liquid propellant rocket engine
- Mixture fraction
- Numerical simulation
- Turbine test rig
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