高负荷跨声速轴流风扇/压气机内流结构的复杂性，特别是转子叶尖区流动状况通常影响决定着整个压气机的流动稳定性。全面弄清转子通道内复杂二次流结构的形成、类型、空间分布、相互作用机制及其对总体气动性能的影响规律等，有利于为前期的气动设计优化和后期的流动分析与控制提供详实的机理性研究基础。CFD数值模拟技术通常比实验测量能够更有效地获得全时空的流场数据信息，能够更加清晰地观察到全通道流场结构的全景物理图像，可以任意提取和处理任何空间位置处的流场信息，它对于机理性研究具有天然的独特优势。本文基于本课题组自主研制的叶轮机高精度数值模拟并行计算程序—NUAA Turbo 2.0，对跨声速轴流孤立转子和单级压气机详细开展了相关定常和非定常数值模拟研究。

本文首先采用定常数值模拟方法，详细研究了不同间隙尺寸和间隙模化方式在两种不同负荷水平压气机转子Rotor 67和Rotor 37中对总体气动性能、流场结构以及叶尖间隙处流动特性等的影响规律。研究结果表明：与“周期性”间隙相比，“网格化”间隙对流量、效率、出口绝对气流角的预测更佳，并且对间隙尺寸和间隙模化效应表现出更强的敏感性；同时，“网格化”间隙更加不易于形成明显的泄漏涡诱导涡结构，它所预测的泄漏涡轨迹更加靠近相邻叶片压力面侧上游位置；与Rotor 67相比，Rotor 37的间隙模化效应和工况变化对叶尖泄漏涡轨迹的影响表现出低敏感性。

通过对跨声速轴流压气机转子的定常数值模拟研究，本文提出了一个典型的跨声速轴流压气机转子通道涡系结构模型、叶尖涡系结构模型以及激波/泄漏涡相互作用模型。同时，将一种旋涡稳定性理论分析方法应用于真实跨声速压气机转子中的激波诱导泄漏涡流动稳定性分析，它的分析结果与传统分析方法取得了很好的一致性，但它在揭示叶尖泄漏涡流动稳定性的影响因素方面具有明显独特优势。关于转子轮盘与静止轮毂之间轮毂泄漏流的影响效应研究，本文详细探讨了轮毂泄漏流流量和周向速度效应对压气机总体气动性能和流动结构的影响规律，深刻地揭示出上述两种轮毂泄漏流效应通过影响轮毂壁面流动结构空间分布来对气动性能产生重大负面影响的内在作用机制。

从非定常数值模拟研究出发，作者在NUAA Turbo 2.0核心求解器中开发了DES97、DDES和IDDES三种DES类RANS/LES组合模拟方法，本文利用它们对Rotor 67和Rotor 37转子叶尖区叶尖泄漏涡脉动特征频率开展了详细的对比研究。研究结果显示：相同网格分辨率条件下，DDES和IDDES两种模式比其它模式能更快进入非定常周期性数值收敛状态，两种模式预测效果具有很强相似性，但从Rotor 37在NS工况下的预测效果来看IDDES模式要优于DDES模式。然而，针对单级压气机定常和非定常数值模拟研究，一方面定常数值模拟结果再次检验了转子叶尖涡模型和旋涡稳定性理论分析方法的可靠性，另一方面通过转/静非定常计算详细分析了转子叶尖区和静子通道内三个特征展向高度位置处静压脉动特征频率的空间分布特征，并且总结了转/静非定常效应在压气机三个特征展向高度位置处所表现出的不同非定常现象特征类型。

The complexity of the internal flow structure in a highly-loaded transonic axial fan/compressor, especially the flow status in the rotor tip region, usually affects and determines the flow stability of the whole compressor. Comprehensive understandings of the formation, type, spatial distribution, interaction mechanism and its influence on the overall aerodynamic performance of the complex secondary flow structure in the rotor passage, which are helpful to provide a detailed mechanical research basis for aerodynamic design optimization in the early stage and flow analysis and control in the later stage. CFD numerical simulation technology is usually more effective than experimental measurement to obtain the whole space-time flow field data information, and it can more clearly observe the panoramic physical image of flow field structure in the whole passage, the flow field information at any spatial position can be extracted and processed arbitrarily, it has natural and unique advantages for the study of mechanism. Based on the high-precision core solver with parallel computation version—NUAA Turbo 2.0, which is developed by our research group and specially designed for turbomachinery, the steady and unsteady numerical simulations of transonic axial flow isolated rotor and single-stage compressor are carried out in detail.

Firstly, the effects of different tip cleaance sizes and modeling methods on the overall aerodynamic performance, flow field structure and the tip leakage flow characteristic, which are studied in detail by using the steady-state numerical simulation method, mainly for two compressor rotors Rotor 67 and Rotor 37 with different load levels. The results show that : compared with the "periodic" gap, the "gridded" gap has better prediction of mass flow rate, efficiency and exit absolute flow angle, and is more sensitive to the gap size and gap modeling effects. Meanwhile, the "gridded" gap is is more difficult to form an obvious TLV-IV structure, and the predicted leakage vortex trajectory is closer to the upstream position of the pressure surface side of adjacent blade; compared with Rotor 67, the change of tip leakage vortex trajectory for Rotor 37 has low sensitivities to the gap modeling effect and operating condition variation. 

Through the steady-state numerical simulation of transonic axial compressor rotor, a relatively typical rotor passage vortex model, blade tip vortex model and shock / leakage vortex interaction model in a typical transonic axial flow compressor are constructed and proposed in this paper. Meanwhile, a theoretical analysis method of vortex stability is introduced and successfully applied to the analysis of shock-induced leakage flow stability in a real transonic compressor rotor. Its analysis results are in good agreement with those of traditional analysis methods, but it has obvious unique advantages in revealing the influencing factors of tip leakage vortex stability. In this paper, the effects of mass flow rate and circumferential velocity of hub leakage flow on the overall aerodynamic performance and flow structure for the compressor are discussed in detail. It deeply reveals the internal mechanism that the above two hub leakage flow effects have a significant negative impact on aerodynamic performance by affecting the spatial distribution of hub wall flow structure.

With regard to unsteady numerical simulation research, the author developed three different hybrid RANS/LES simulation methods (DES97、DDES、IDDES) and embedded them into the NUAA Turbo 2.0 core solver. Then, this paper uses them to detailedly compare and study the characteristic frequency of tip leakage vortex pulsation in the tip region of Rotor 67 and Rotor 37. The results show that : under the same grid resolution, DDES and IDDES modes can enter the unsteady periodic numerical convergence state faster than other modes. The prediction effects of the two modes are very similar, IDDES mode is better than DDES mode from the prediction effect of Rotor 37 under NS condition. However, for the steady and unsteady numerical simulation of single-stage compressor, on the one hand, the steady numerical simulation results verify the reliability of the rotor tip vortex model and the theoretical analysis method of vortex stability; On the other hand, through the rotor/stator unsteady simulation, the spatial distribution characteristics of the characteristic frequency of static pressure pulsation both in the rotor tip region and at three characteristic spanwise positions of stator passage are analyzed in detail, and the different unsteady phenomenon types at three characteristic spanwise positions of the compressor are summarized.

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