Numerical simulation of micro gas turbine engine based on time-marching one-dimensional method
•A time-marching one-dimensional model is developed for gas turbine engine simulation.•The characteristic interface method is developed to facilitate multi-zone time-marching computations.•Time-marching one-dimensional model eliminates the dependence on generic map of components.•Time-marching one-d...
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Veröffentlicht in: | Applied thermal engineering 2025-01, Vol.259, p.124786, Article 124786 |
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Format: | Artikel |
Sprache: | eng |
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Zusammenfassung: | •A time-marching one-dimensional model is developed for gas turbine engine simulation.•The characteristic interface method is developed to facilitate multi-zone time-marching computations.•Time-marching one-dimensional model eliminates the dependence on generic map of components.•Time-marching one-dimensional model obtains meridional distributions of flow parameters.
The advancement of gas turbine technology serves as a crucial indicator of high-tech and technological prowess, with widespread applications in aviation, marine vessels, power generation, and clean energy. The precision of the performance simulation model stands as a pivotal component in the development of gas turbines. The present study deals with the one-dimensional modeling and validation of gas turbines by utilizing a time-marching scheme, in order to establish the correlation between the engine components and full-engine performance. The flow through the turbomachinery was solved by the one-dimensional model. The combustor was modelled as a compressible actuator disk. The accuracy of the turbomachinery solver was validated using the KJ66 compressor and turbine, and the predicted results demonstrated consistency with the experimental data or the three-dimensional simulations. The characteristic interface method was developed based on Riemann invariants, in order to provide the flow properties on both sides of the combustor. The results indicated that compared to the component-by-component approach, the developed characteristic interface method significantly reduced the computational time. Finally, the developed one-dimensional method was employed to simulate the performance of the KJ66 micro gas turbine engine. The predicted performance for the KJ66 gas turbine engine was consistent with the trend in the experiment results. The novelty of the present study was its modeling approach, and its ability to eliminate the dependence on the general component map, and obtain meridional distributions of flow parameters, which cannot be achieved in traditional zero-dimensional thermal cycle calculations. These results can provide an accurate and powerful tool for the analysis and optimization of component and full-engine performance in the preliminary design stage. |
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ISSN: | 1359-4311 |
DOI: | 10.1016/j.applthermaleng.2024.124786 |