Design Support Numerical Code for Stall Flutter Analysis.

设计支持失速颤振分析的数字代码。

• 批准号: 05555061
• 负责人: TAKATA Hiroyuki
• 金额: $ 2.11万
• 依托单位: Tokai University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Developmental Scientific Research (B)
• 财政年份: 1993
• 资助国家: 日本
• 起止时间: 1993 至 1994
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-05555061/
• 关键词: Stall Flutter; Unsteady Aerodynamic Characteristics; Cascade of Blades; Turbomachinery

This study aims to develop a numerical calculation code which enables us to predict the unsteady aerodynamic characteristics of the stalled compressor and turbine cascades as well as their stall flutter limits.For this end, the numerical code which authors have used so far to analyze the unsteady flow of rotating stall was extended so that it can deal with the flow through the cascades, of which the blades oscillate rotationally or translationally.With use of this code, a series of numerical analyzes of the stalled flow through a typical compressor cascade with each blade oscillating rotaionally around the mid-point of the mean camber line was carried out. The reduced frequency and the inter-blade phase angle were changed in wide varieties and it was found that the unsteady exciting moment of the stall flutter was closely connected with the propagation of rotating stall along the cascade. The numerical code was also applied to the analysis of oscillating turbine cascades. Rotational oscillation of a nozzle cascade with large deflection angle, and translational oscillation of a rotor cascade with high stagger and low turning angles were selected as examples for the analysis. A series of unsteady aerodynamic characteristics were obtained for wide range of unsteady oscillation parameters.Further, a cascade wind-tunnel test of the same rotationally oscillating cascade as used in the numerical analysis of the compressor cascade was performed. Unsteady pressure distributions on the oscillating blade surface were measured, and the unsteady aerodynamic works given to the blades were calculated. The experimental results agreed well with those predicted by the numerical calculation.

本研究旨在开发一种数值计算代码，使我们能够预测失速压气机和涡轮叶栅的非定常空气动力特性及其失速颤振极限。为此，作者对迄今为止用于分析旋转失速非定常流动的数值代码进行了扩展，使其能够处理通过叶栅的流动，其中叶片旋转或振荡 通过使用该代码，对通过典型压气机叶栅的失速流进行了一系列数值分析，其中每个叶片围绕平均弧线的中点旋转振荡。通过对降低频率和叶片间相位角进行大范围的改变，发现失速颤振的非定常激振力矩与旋转失速沿叶栅的传播密切相关。数值代码还应用于振动涡轮叶栅的分析。选择大偏转角喷管叶栅的旋转振动和高错开、小转角的转子叶栅的平动振动作为分析实例。对于大范围的非定常振荡参数，获得了一系列非定常空气动力特性。此外，对用于压气机叶栅数值分析的同一旋转振荡叶栅进行了叶栅风洞试验。测量了摆动叶片表面的非定常压力分布，并计算了给予叶片的非定常气动功。实验结果与数值计算的预测结果吻合良好。