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1D gas dynamic code for performance prediction of one turbocharger radial turbine with different finite difference schemes

机译：具有不同有限差分方案的一个涡轮增压器径向涡轮机性能预测的1D气体动态码

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摘要

The turbine, a key component of a turbocharger, is usually characterized by steady flow solutions. This method seems to be physically unrealistic as the fluid flow within a turbine is strongly unsteady due to the pulsating nature of the flow in the exhaust manifold of a reciprocating engine. This paper presents a new 1D gas dynamic code, written in the FORTRAN language, to characterize a radial turbine of one turbocharger embedded to a small gasoline engine. This code presents the novelty of meanline-1D coupling and the feature of numerical schemes choice. In this study, the turbocharger turbine is simulated with six different finite difference schemes. The computed distribution of the downstream mass flow rate, from the different cases, is compared to test data in order to choose the most suitable scheme. Test data are gathered from a developed test facility. Based on the computed results, unsteady performance of the turbine has been computed and discussed for the different schemes at two engine frequencies of 50 and 83.33?Hz. The results showed a significant impact of the numerical scheme on the 1D prediction of the turbine performance. Results indicated that the MR2LW finite-difference scheme has led to the minimum deviation of the numerical results to test data compared to the other considered schemes.
机译：涡轮机是涡轮增压器的关键部件，通常是通过稳定的流量解决方案的特征。由于往复式发动机的排气歧管中的流动的脉动性质，这种方法似乎是物理上不现实的，因为涡轮机内的流体强烈不稳定。本文介绍了一种新的1D气体动态代码，写入Fortran语言，以嵌入到小型汽油发动机的一个涡轮增压器的径向涡轮机。此代码介绍了意义-1d耦合的新颖性和数字方案选择的特征。在本研究中，涡轮增压器涡轮机用六种不同的有限差分方案进行模拟。将下游质量流量的计算分布与不同情况不同，与测试数据进行比较，以便选择最合适的方案。测试数据从开发的测试设施收集。基于计算结果，已经计算了涡轮机的不稳定性能，并在两个发动机频率为50和83.33Ω·赫兹的不同方案中讨论。结果表明数值方案对涡轮机性能的1D预测的显着影响。结果表明，与其他考虑的方案相比，MR2LW有限差分方案导致数值结果对测试数据的最小偏差。

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