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首页> 外文期刊>Aerospace science and technology >Viscous flow and performance issues in a 6:1 supersonic mixed-flow compressor with a tandem diffuser
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Viscous flow and performance issues in a 6:1 supersonic mixed-flow compressor with a tandem diffuser

机译：带串联扩压器的6：1超音速混合流压缩机的粘性流和性能问题

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The advancement of multi-dimensional and viscous computational tools has eased the accessibility and overall effort for thorough analysis of complex turbomachinery designs. In this paper, we computationally evaluate a high-pressure ratio supersonic mixed-flow compressor stage designed using an in-house mean line code. Objective is to include three dimensionalities, viscous flow and compressibility effects including the shock wave systems into account. As mixed-flow compressors are advantageous especially for small jet engine applications we choose mass flow rate, stage total pressure ratio and maximum diameter as the main design constraints. This computational analysis is the second paper of a two-part series explaining strategy for designing a high-pressure ratio mixed-flow compressor stage. The high-pressure ratio and small diameter requirements push this compressor for a highly-loaded supersonic 'shock-in rotor' design with supersonic stator/diffuser.The used RANS based computational fluid dynamics model is thoroughly assessed for its ability to predict compressor performance using existing well-established experimental data. NASA Rotor 37 and RWTH Aachen supersonic tandem stator are chosen as the test cases for exhibiting similar flow characteristics to present design. The computational approach helps to shed light upon the mixed-rotor and supersonic stator 3D shock structures and viscous/secondary flow. Stage performance map, pressure and velocity distribution of this high-pressure ratio mixed-flow compressor is obtained. Areas of design optimization are highlighted to further improve performance and efficiency. The in-house mean-line design code predicted a pressure ratio of 6.0 with 75.5% efficiency for a mass flow rate of 3.5 kg/s. The mean-line code obviously lacked to fully represent three-dimensionality effects due to its inherent over-simplifying assumptions thus, inclusion of RANS based computations improves the fidelity of mixed-flow compressor design performance calculations at a great rate. Comprehensive computational analysis of the stage shows that our design goal is met with a stage total pressure ratio of Pi(TT) = 5.83 with an efficiency of eta(IS) = 77% for a mass flow rate of (m)over dot = 3.03 kg/s. A total pressure ratio of 6.12 at 75.5% efficiency is reached with a 33% increase in design rotational speed. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：多维和粘性计算工具的进步简化了对复杂涡轮机械设计进行全面分析的可访问性和整体工作量。在本文中，我们通过内部平均线代码设计评估了高压比超音速混合流压缩机级。目标是包括三个维度，粘性流动和可压缩性效应，其中包括冲击波系统。由于混流式压缩机特别适合小型喷气发动机应用，因此我们选择质量流量，级总压比和最大直径作为主要设计约束。该计算分析是由两部分组成的系列文章的第二篇文章，该系列文章解释了设计高压比混合流压缩机级的策略。高压比和小直径的要求促使该压缩机成为具有超音速定子/扩散器的高负荷超音速“冲击转子”设计。基于RANS的计算流体动力学模型充分评估了其使用压缩机预测压缩机性能的能力。现有完善的实验数据。选择NASA转子37和RWTH亚琛超音速串联定子作为测试案例，以展现与当前设计相似的流动特性。该计算方法有助于阐明混合转子和超音速定子3D冲击结构以及粘性/二次流。获得该高压比混流压缩机的级性能图，压力和速度分布。重点介绍了设计优化领域，以进一步提高性能和效率。内部平均线设计规范预测质量比为3.5 kg / s时的压力比为6.0，效率为75.5％。平均线代码由于其固有的过分简化的假设而明显地不能完全表示三维效果，因此，基于RANS的计算可以大大提高混合流压缩机设计性能计算的保真度。该阶段的综合计算分析表明，对于阶段（m）的质量流量= 3.03，该阶段的总压力比Pi（TT）= 5.83，效率eta（IS）= 77％，达到了我们的设计目标。千克/秒在设计转速提高33％的情况下，以75.5％的效率实现了6.12的总压力比。 （C）2019 Elsevier Masson SAS。版权所有。

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