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STEADY AND UNSTEADY AERODYNAMIC CHARACTERISTICS OF SUPERSONIC THROUGH-FLOW FAN CASCADE

超声速贯流式风扇叶栅稳态与非稳态气动特性

基本信息

批准号：
03452099
负责人：
NAMBA Masanobu
金额：
$ 4.54万
依托单位：
KYUSHU 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：
1991
资助国家：
日本
起止时间：
1991 至 1992
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-03452099/
关键词：
Supersonic Through-Flow Fan Cascade Performance Unsteady Aerodynamics Cascade Flutter Rotating Cascade Compressible Flow Three-Dimensional Flow Lifting Surface Theory

项目摘要

・The computation program to predict the steady performance of a supersonic through-flow fan on the basis of the linearized three-dimensional steady lifting surface theory for a rotating annular cascade was developed. A parametric study of the steady performance in correlation with the axial Mach number, rotating speed, boss ratio, number of blades and blade profile was conducted.・The computation program to predict the unsteady aerodynamic characteristics of a supersonic through-flow fan on the basis of the Iinearized three-dimensional unsteady lifting surface theory for a rotating annular cascade was developed. A parametric study of the aerodynamic instability of blade vibration in correlation with design parameters was conducted. The pure bending motion under zero mean loading is always aerodynamically damped. The aerodynamic instability of pure torsional motion is heavily dependent on the location of the torsion axis and the interblade phase angle.・The computation programs on the bas … More is of the three-dimensional double linearization theory for linear and rotating annular cascades with supersonic axial velocity were developed to predict the unsteady aerodynamic characteristics of cascading blades vibrating under nonzero mean loading. It is found that the single-degree-of-freedom pure bending flutter can occur due to nonzero mean loading. The aerodynamic exciting force is very sensitive to the blade camber on which the steady loading is heavily dependent.・The computation program on the basis of the nonlinear Euler equation to predict the nonlinear steady flow through a two-dimensional cascade with a supersonic leading edge locus was developed. Comparison of the numerical results with those by the linearized theory was conducted. The linearized theory can predict the steady lift force within 10% accuracy at small incidence angles, but the deviation becomes significant as the incidence increases. The main reason of the difference is inaccurate prediction of location of shock wave reflections.・The measurement system including the Mach-Zehnder interferometer and the image processing system have been constructed. The technology of processing interferograms is being developed. Less

·编制了基于旋转环形叶栅线性化三维定常升力面理论的超音速贯流风扇定常性能计算程序。对轴向马赫数、转速、凸台比、叶片数和叶片型线与定常性能的关系进行了参数研究。·基于旋转环形叶栅的线性化三维非定常升力面理论，编制了超音速贯流风扇非定常气动特性计算程序。对叶片振动的气动不稳定性与设计参数的关系进行了参数研究。在零平均载荷作用下的纯弯曲运动往往具有气动阻尼性。纯扭转运动的气动不稳定性很大程度上依赖于扭转轴的位置和叶片间的相位角。·BAS…上的计算程序进一步发展了具有超音速轴向速度的环状叶栅和旋转环状叶栅的三维双线性化理论，以预测在非零平均载荷作用下叶栅振动的非定常气动特性。结果表明，在非零平均载荷作用下，可能会发生单自由度纯弯曲颤振。气动激振力对叶片外倾角非常敏感，而叶片的稳态载荷对叶片外倾角的依赖程度很大。·编制了基于非线性欧拉方程的二维超音速叶栅前缘轨迹非线性定常流动计算程序。将数值计算结果与线性化理论计算结果进行了比较。线性化理论在小角度入射时，对定常升力的预测精度在10%以内，但随着入射角度的增大，误差变大。造成这种差异的主要原因是对冲击波反射位置的预测不准确。·搭建了包括马赫-曾德尔干涉仪在内的测量系统和图像处理系统。干涉图的处理技术正在发展中。较少