Numerical and Experimental Study on Transient Flows in Axial Compressor Rotor/Stator Cascades

轴流式压缩机转子/定子叶栅瞬态流动的数值与实验研究

• 批准号: 05452157
• 负责人: YOSHIOKA Eisuke
• 金额: $ 4.35万
• 依托单位: Waseda University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for General Scientific Research (B)
• 财政年份: 1993
• 资助国家: 日本
• 起止时间: 1993 至 1995
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-05452157/
• 关键词: Axial Compressor; Numerical Analysis; Unsteady Compressible Flows; Cascade Flows; Rotating Stall; Vortical Flows; Hot-Film Anemometer Probe; Rotating Stall Control; 航空エンジン圧縮機; 非定常圧縮性流れ解析; 失速セル構造; 3次元乱れ計測; 翼列; 数値流体力学; 非定常流; 渦; 非定常流速計測; 圧縮機

Development of technologies for extending the stable range of axial compressor operation by suppressing onset of rotating stall, or by recovering swiftly from stall, is one of the main subjects in improving the jet engine performance. This research aims at understanding mechanisms of rotating stall and of related unsteady flow phenomena through experiments and a numerical study of 2-D compressible Navier-Stokes equations.In the numerical analysis, various aspects of unsteady flows generated by the relative motion of a rotor and a stator are presented with a special emphasis on features of vortical flow patterns in the cascades. With a rotor-stator cascades of a sufficiently large number of blades, it simulates a whole compressor characteristic from normal to deep-stall flow range, in the speed range up to transonic regime. For the subsonic case of rotor Mach number 0.3, comparisons are made on various flow data with measured data, whereas for the transonic case, total-pressure rise cha … More racteristics are compared to rig test data from an engine company.On rotating stall structure, a twin-vortex cell structure is presented, which is formed by the collision of an incoming flow to the cascades with a high pressure stagnant zone produced in some portion of the cascade. The cell propagation speed as well as the induced reverse-flow velocity agree well with the data measured by hot-film probes. In the transonic regime, cell exhibits a structure slightly different from subsonic cases due to the presence of shock waves. Although the analysis is two-dimensional, it can be expected that, by focusing on this vortex system, dynamic model of the cell be established, and that, by introducing the model into a simplified three-dimensional analysis, some three-dimensional features of the stall cell be evaluated.On the flow structure leading to stall inception, it can be prospected that, in such a highly loaded condition where the flow passing over the pressure surface of a blade rolls up to the suction surface, a blade-tip vortex stimulates this flow configuration, synchronized with the inlet distortion.Various findings regarding stall behavior and cell structure, as well as some specific subjects for future study are obtained. These were applied to develop a stall control technique, and an improvement of 15% in stable flow range was attained up to this moment. It is noted that one of the papers on this project has received a 1995 Gas Turbine Society of Japan award. Less

通过抑制旋转失速的发生或从失速中快速恢复来扩展轴流压气机稳定运行范围的技术的发展是提高喷气发动机性能的主要课题之一。本文通过实验和二维可压缩N-S方程的数值研究，对旋转失速及其相关非定常流动现象的机理进行了研究，在数值分析中，对动、静叶相对运动产生的非定常流动的各个方面进行了分析，特别强调了叶栅中旋涡流态的特征。通过大量叶片组成的转子-定子叶栅，模拟了从正常到深度失速流动范围、从速度范围到跨音速状态的整个压气机特性。对于亚音速旋翼马赫数为0.3的情况，对各种流动数据和测量数据进行了比较，而对于跨音速旋翼，则对总压上升特性进行了比较。 ...更多信息 在旋转失速结构方面，提出了一种双涡胞结构，它是由进入叶栅的气流与叶栅某些部位产生的高压滞止区碰撞而形成的。细胞增殖速度以及诱导的逆流速度与热膜探针测量的数据吻合良好。在跨音速区域，由于激波的存在，单元的结构与亚音速情况略有不同。虽然分析是二维的，但可以期望，通过关注该涡系，建立该单元的动力学模型，并将该模型引入到简化的三维分析中，评估失速单元的某些三维特征。在这种高负荷条件下，流过叶片压力面的气流卷起至吸力面，叶尖涡流刺激了这种气流结构，与进口畸变同步。关于失速特性和单元结构的各种研究结果，以及今后研究的一些具体课题。这些都被应用于发展失速控制技术，并在稳定的流量范围内获得了15%的改善，到目前为止。值得注意的是，关于该项目的一篇论文获得了1995年日本燃气涡轮机协会奖。少

项目成果

Eisuke OUTA (YOSHIOKA), Dai KATO,Kaoru CHIBA: ""A Two-Dimensional Compressible Navier-Stokes Simulation of Transient Flows in Compressor Rotor/Stator Cascades (1st.Report, Starting Flow Process in Cascades of an Equal Blade-Pitch)", in Japanese." Transact

Eisuke OUTA (YOSHIOKA)、Dai KATO、Kaoru CHIBA：“压缩机转子/定子叶栅中瞬态流动的二维可压缩纳维-斯托克斯模拟（第 1 份报告，等叶片节距叶栅中的启动流动过程）”

Dai KATO,Eisuke OUTA,Kaoru CHIBA: ""A Two-Dimensional Compressible Navier-Stokes Simulation of Transient Flows in Compressor Rotor/Stator Cascades (2nd Report, Unsteady Flow and Stall Process in Multi-Bladed Rotor and Stator)", in Japanese." Transaction o

Dai KATO、Eisuke OUTA、Kaoru CHIBA：“压缩机转子/定子叶栅中瞬态流动的二维可压缩纳维-斯托克斯模拟（第二份报告，多叶片转子和定子中的不稳定流动和失速过程）”，日语

Eisuke OUTA (YOSHIOKA): "A 2-D Compressible N-S Simulation of Starting- and Stalling-Flows in a Compressor Cascades System" Proceedings of the 11th International Symposium on Air Breathing Engines,Tokyo,AIAA (Paper no.ISABE 93-7006).53-62 (1993)

Eisuke OUTA (YOSHIOKA)：“压缩机级联系统中启动和失速流的二维可压缩 N-S 模拟”第 11 届空气呼吸发动机国际研讨会论文集，东京，AIAA（论文编号：ISABE 93-7006）

大田 英輔(吉岡 英輔): "圧縮機動・静翼列系における旋回失速の二次元NS数値解析(深い失速セルの構造および非定常計測との比較)" 日本機械学会第72期通常総会講演会(1995年3月)にて発表予定.(1995)

Eisuke Ota（吉冈荣介）：“压缩机驱动和固定叶片叶栅系统中旋转失速的二维 NS 数值分析（与深失速单元结构和非定常测量的比较）”在日本学会第 72 届常务大会上的演讲机械工程师（预定于1995年3月公布。（1995）

加藤 大: "圧縮機動翼列・静翼列システムの過渡流れに関する二次元圧縮性NS方程式の数値解析(第3報,深い旋回失速セルの渦構造および圧縮機実験との比較)" 日本機械学会論文集B編. (発表予定).

加藤大：《压缩机转子和定子叶片系统中瞬态流动的二维可压缩NS方程的数值分析（第3部分，深旋转失速单元的涡结构以及与压缩机实验的比较）》日本机械工程师学会论文集， B 卷（已安排演示）。