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

・开发了基于旋转环形级联的线性三维稳定提升表面理论的计算程序，以预测超音速横流风扇的稳定性能。与轴向马赫数相关，旋转速度，boss比，叶片数量和刀片轮廓的稳定性能的参数研究。・开发了根据旋转环形级联反射的三维三维不稳定的提升表面理论，以预测超音速通行风扇的不稳定空气动力学特性的计算程序。进行了与设计参数相关的叶片振动空气动力不稳定的参数研究。在零平均负载下的纯弯曲运动总是在空气动力学上受阻。纯扭转运动的空气动力学不稳定在很大程度上取决于扭转轴的位置和相互的相位角度。・ bas上的计算程序……更多的是三维双线性的双线性线性和旋转环形级联反应与轴向速度的旋转旋转级数，以预测无稳定的vibration veibration nonemanty forefer vibrand for cascacding cascacding cascacading cascacading aDe cascacading cascacading bl cascacading cascacading cascacading a cascacading a cascacading a cascacading aDade vel n s cascacading aDade vele seragisy a cascacading aDade。发现由于非零的平均载荷，可能会发生单度纯曲线弹跳。空气动力的刺激力对稳定载荷在很大程度上受到依赖的刀片倾斜度非常敏感。・基于非线性Euler方程的计算程序，可以开发出具有超音速前端端口的二维级联反向的非线性稳定流。进行了数值结果与线性化理论的比较。线性化理论可以预测在小入射角10％精度内的稳定升力力，但是随着入射的增加，偏离变得显着。差异的主要原因是对冲击波反射的位置的预测不准确。・测量系统（包括Mach-Zehnder干涉仪和图像处理系统）已建立。正在开发处理干涉图的技术。较少的