In this paper, a diffuser is used to integrate a transonic high-pressure turbine with a rotating detonation combustor (RDC). The paper focuses on the required design modifications to the turbine endwalls (EW) to enable high efficiency, while preserving the airfoil blade-to-blade geometry. The main challenge is the stator passage unstarting, due to the high inlet Mach number. First of all, steady Reynolds Averaged Navier Stokes simulations were performed to compare the efficiency of turbines with constant-radius EWs to turbines with axisymmetric EWs. A modified EW design prevented the unstarting of the stator passage, enabling a significant gain in performance. Afterward, the influence on the turbine efficiency and damping due to the unsteadiness from the diffuser-like fluctuations of the RDC was evaluated with unsteady Reynolds Averaged Navier Stokes simulations with a mixing plane approach (MPA). Full unsteady simulations were carried out on selected inlet conditions and compared to the mixing plane results. This parametric study provides turbine designers with recommended diffusion rates along the vane EWs. Additionally, we provide guidance on the upstream diffuser design, specifically the required damping and outlet Mach number.

中文翻译：

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跨音速高压涡轮与旋转爆震燃烧器和扩散器的集成

在本文中，使用扩散器将跨音速高压涡轮与旋转爆震燃烧器（RDC）集成在一起。本文着重于对涡轮机端壁（EW）进行必要的设计修改，以实现高效率，同时保留翼型叶片到叶片的几何形状。主要挑战是由于高进气马赫数，定子通道无法启动。首先，进行了稳定的雷诺平均Navier Stokes模拟，以比较具有恒定半径EW的涡轮机和具有轴对称EW的涡轮机的效率。改进的电子战设计防止了定子通道的启动，从而显着提高了性能。之后，通过使用混合平面方法（MPA）进行的非稳态雷诺平均Navier Stokes模拟，评估了RDC的类似扩散器的波动对涡轮效率和阻尼造成的影响。在选定的入口条件下进行了完全非稳态模拟，并将其与混合平面结果进行了比较。该参数研究为涡轮设计人员提供了沿叶片EW的推荐扩散率。此外，我们提供有关上游扩散器设计的指南，特别是所需的阻尼和出口马赫数。