Among the solutions to reduce emissions from stationary gas turbines, replacing conventional combustion through pressure gain combustion is one of the most promising options. Nevertheless, coupling pressure gain combustion with a turbine can result in increased losses within the cycle, mainly because of the resulting very unsteady turbine inflow conditions. A reliable simulation tool can help to overcome this challenge and optimize turbine geometries and designs for the specific application. The harsh unsteady flow downstream of pressure gain combustors makes three-dimensional CFD computationally expensive. Thus, the development of a fast computational method is crucial. This paper introduces and explores such an alternative methodology. A one-dimensional Euler gas dynamic approach is combined with blade source terms, computed out of a steady-state turbine meanline analysis. To evaluate the methodology, three-dimensional CFD simulations are performed in parallel and the results are compared with those of the 1D method. The energy extraction of a turbine expander is computed with both methods for three different configurations of pulsed detonation combustor arrays connected at the turbine inlet. The results show that the proposed approach is capable of simulating the turbine in such an unsteady environment accurately. Additionally, it is indicated that around 45% of the total unsteadiness is damped throughout the first blade row, which is almost irrespective of the inlet fluctuation amplitude. Due to its accuracy and very low computational cost, the developed methodology can be integrated into optimization loops in the early design and development stages of turbomachinery for pressure gain combustion applications.

在减少固定式燃气轮机排放的解决方案中，通过增压燃烧代替传统燃烧是最有前途的选择之一。然而，将压力增益燃烧与涡轮机耦合会导致循环内的损失增加，这主要是因为涡轮机流入条件非常不稳定。可靠的仿真工具可以帮助克服这一挑战并针对特定应用优化涡轮机几何形状和设计。压力增益燃烧器下游的剧烈不稳定流动使得三维 CFD 的计算成本很高。因此，开发快速计算方法至关重要。本文介绍并探索了这种替代方法。一维欧拉气体动力学方法与叶片源项相结合，计算出稳态涡轮机平均线分析。为了评估该方法，并行执行三维 CFD 模拟，并将结果与​​一维方法的结果进行比较。涡轮膨胀机的能量提取使用两种方法计算，用于连接在涡轮入口处的三种不同配置的脉冲爆震燃烧器阵列。结果表明，所提出的方法能够准确地模拟这种不稳定环境中的涡轮机。此外，还表明在整个第一叶片排中，大约 45% 的总不稳定性受到阻尼，这几乎与入口波动幅度无关。由于其准确性和非常低的计算成本，