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首页> 外文期刊>International journal of numerical methods for heat & fluid flow >Aero-design of transonic LH2 and LOX contra rotating turbopumps in an expander rocket engine
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Aero-design of transonic LH2 and LOX contra rotating turbopumps in an expander rocket engine

机译：跨音速LH2和LOX的航空设计与膨胀火箭发动机中的旋转涡轮泵相对

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Purpose - Contra-rotating turbines offer reduced size, weight, and cooling requirements, compared to conventional co-rotating machinery. In spite of the associated mechanical complexity, their aero-thermal performance is superior to conventional turbines, not only due to the elimination of stator blade rows, but also because lower turning airfoils can be implemented as a result. The purpose of this paper is to present a methodology to determine the optimum velocity triangles of the turbine, together with a two-dimensional design and optimization tool to minimize the blade unsteady force using radial basis function network, coupled to a genetic algorithm. The proposed design methodology is illustrated with the aerodynamic design of a contra-rotating two-axis turbine, which is able to deliver the power necessary to drive the LOX and LH2 pumps of an improved expander rocket engine. Design/methodology/approach - This paper presents a methodology to determine the optimum velocity triangles of the turbine, together with a two dimensional design and optimization tool to minimize the blade unsteady force using radial basis function network, coupled to a genetic algorithm. The proposed design methodology is illustrated with the aerodynamic design of a contra-rotating two-axis turbine, which is able to deliver the power necessary to drive the LOX and LH2 pumps of an expander rocket engine, namely the Japanese LE-5B. Findings - The airfoil optimizer allows reductions in the downstream pressure distortion of 40 per cent. Consequently, the unsteady forces in the downstream blade row are minimized. Originality/value - This paper presents to turbomachinery designers in liquid propulsion a novel tool to enhance the aerodynamic performance while reducing the unsteady forces on the blades.
机译：目的-与传统的同向旋转机械相比，对向旋转涡轮提供了更小的尺寸，重量和冷却要求。尽管存在相关的机械复杂性，但其气热性能优于常规涡轮机，这不仅是因为消除了定子叶片排，而且还因为其结果是可以实现较低的旋转翼型。本文的目的是提出一种确定涡轮机最佳速度三角形的方法，以及一个二维设计和优化工具，以使用遗传算法将径向基函数网络最小化叶片的非定常力。反向旋转的两轴涡轮机的空气动力学设计说明了拟议的设计方法，该设计能够提供驱动改进的膨胀火箭发动机的LOX和LH2泵所需的动力。设计/方法/方法-本文介绍了一种确定涡轮机最佳速度三角形的方法，并结合了二维设计和优化工具，以使用径向基函数网络和遗传算法将叶片非定常力降至最低。反向旋转的两轴涡轮的空气动力学设计说明了所提出的设计方法，该涡轮能够提供驱动膨胀火箭发动机（即日本LE-5B）的LOX和LH2泵所需的功率。研究结果-翼型优化器可将下游压力畸变降低40％。因此，下游叶片排中的不稳定力被最小化。独创性/价值-本文向涡轮机械设计人员提供了一种在液体推进方面新颖的工具，可以提高空气动力学性能，同时减少叶片上的不稳定力。

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