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针对目前在涡轮内燃烧技术的研究中,等温燃烧数学模型较为复杂以及这些模型中利用了较为复杂的熵进行计算等工程技术问题,从等温过程的基本热力过程原理出发,推导出新的涡轮内等温燃烧数学模型。通过数学模型之间的比较与分析以及计算结果与文献之间的比较与分析之后,得出结论:①在采用涡轮内燃烧技术的航空发动机总体热力性能计算中,推导出的涡轮内等温燃烧数学模型的应用具有可行性;②新建立的涡轮内等温燃烧数学模型更为简便,可以大幅度地提高编程效率和计算效率,在工程实际中具有较好的应用性。
In the current research of turbine internal combustion technology, mathematical models of isothermal combustion are complex and engineering problems such as complex entropy calculation are used in these models. Based on the basic thermodynamic process principle of isothermal process, Isothermal combustion mathematical model. After comparing and analyzing the mathematical models and comparing the results with the literature, the conclusions are drawn as follows: (1) In the calculation of the overall thermal performance of the aeroengine with the turbine internal combustion technology, the in-turbine isothermal combustion mathematical The application of the model is feasible; ② The newly established mathematical model of isothermal combustion in the turbine is more simple, can greatly improve the programming efficiency and computational efficiency, and has good applicability in engineering practice.