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THE METHOD OF COMPLEX CHARACTERISTICS FOR DESIGN OF TRANSONIC COMPRESSORS.

机译:超音速压缩机设计的复杂特性方法。

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摘要

We calculate shockless transonic flows past two-dimensional cascades of airfoils characterized by a prescribed speed distribution. The approach is to find solutions of the partial differential equation (c('2)-u('2)) (PHI)(,xx) - 2uv (PHI)(,xy) + (c('2)-v('2)) (PHI)(,yy) = 0 by the method of complex characteristics. Here (PHI) is the velocity potential, so (DEL)(PHI) = (u,v), and c is the local speed of sound. Our method consists in noting that the coefficients of the equation are analytic, so that we can use analytic continuation, conformal mapping, and a spectral method in the hodograph plane to determine the flow.; After complex extension we obtain canonical equations for (PHI) and for the stream function (psi) as well as an explicit map from the hodograph plane to complex characteristic coordinates. In the subsonic case, a new coordinate system is defined in which the flow region corresponds to the interior of an ellipse. We construct special solutions of the flow equations in these coordinates by solving characteristic initial value problems in the ellipse with initial data defined by the complete system of Chebyshev polynomials. The condition (psi) = 0 on the boundary of the ellipse is used to determine the series representation of (PHI) and (psi). The map from the ellipse to the complex flow coordinates is found from data specifying the speed q as a function of the arc length s. The transonic problem for shockless flow becomes well posed after appropriate modifications of this procedure. The nonlinearity of the problem is handled by an iterative method that determines the boundary value problem in the ellipse and the map function in sequence.; We have implemented this method as a computer code to design two-dimensional cascades of shockless compressor airfoils with gap-to-chord ratios as low as .5 and supersonic zones on both the upper and lower surfaces. The method may be extended to solve more general boundary value problems for second order partial differential equations in two independent variables.
机译:我们计算经过以预定速度分布为特征的二维翼型的无冲击跨音速流。该方法是找到偏微分方程(c('2)-u('2))(PHI)(,xx)-2uv(PHI)(,xy)+(c('2)-v( '2))(PHI)(,yy)= 0通过复数特征方法。这里(PHI)是速度势,所以(DEL)(PHI)=(u,v),而c是声音的局部速度。我们的方法在于注意到方程的系数是解析的,因此我们可以在全息图平面中使用解析延续,共形映射和频谱方法来确定流量。复数扩展后,我们获得(PHI)和流函数(psi)的规范方程,以及从全息图平面到复数特征坐标的显式映射。在亚音速情况下,定义了一个新的坐标系,其中流动区域对应于椭圆的内部。我们通过用完整的切比雪夫多项式系统定义的初始数据来解决椭圆中的特征初始值问题,从而构造这些坐标系中流动方程的特殊解。椭圆边界上​​的条件(psi)= 0用于确定(PHI)和(psi)的级数表示。从将速度q定义为弧长s的函数的数据中可以找到从椭圆到复杂流坐标的映射。在对该程序进行适当的修改后,无冲击流的跨音速问题变得很容易解决。问题的非线性是通过一种迭代方法来处理的,该迭代方法依次确定椭圆和映射函数中的边值问题。我们已将此方法作为计算机代码实施,以设计间隙对弦比低至.5且上下表面均具有超音速区域的无冲击压缩机翼型的二维级联。该方法可以扩展为解决两个独立变量中二阶偏微分方程的更一般的边值问题。

著录项

  • 作者

    BLEDSOE, MARGARET RANDOLPH.;

  • 作者单位

    New York University.;

  • 授予单位 New York University.;
  • 学科 Physics Fluid and Plasma.
  • 学位 Ph.D.
  • 年度 1983
  • 页码 190 p.
  • 总页数 190
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 等离子体物理学;
  • 关键词

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