THREE-DIMENSIONAL TURBOMACHINE FLOW EQUATIONS EXPRESSED WITH RESPECT TO NON-ORTHOGONAL CURVILINEAR COORDINATES AND METHODS OF SOLUTION
THREE-DIMENSIONAL TURBOMACHINE FLOW EQUATIONS EXPRESSED WITH RESPECT TO NON-ORTHOGONAL CURVILINEAR COORDINATES AND METHODS OF SOLUTION
复制标题
非正交曲线坐标表示的三维涡轮机流动方程及其求解方法
DOI：
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发表时间：
2002
期刊：
影响因子：
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通讯作者：
Wu Zhonghua
中科院分区：
文献类型：
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作者：
Wu Zhonghua
In the first part of the paper, basie aerothermodynamic equations governing the flow of a viscous fluid in a turbomachine is presented . A unified approach is taken in analysing the relative three-dimensional flow and its one-dimensional approximation. ernphasis is placed on the different forms of the work done by the fluid and the increase of its internal energy from the stand point of a stationary observer and an observer moving with the fluid. The true physical meaning of the corrsponding viscous terms appcaring in the two forms of energy equation expressing the first law of thermodynamics and in the entropy equation exprcssing the second law of thermodynamic becomes apparent.
In the second part of the paper, general non-orthogonal curvilinear coordinates are suggested for use in the three-dimensional turbomachine flow calculations. After a brief discussion of some basie relations in non-orthogonal curvilinear coordinate system, equations governing fluid flow on S1 and S2 relative surfaces are expressed in terms of non-orthogonal curvilinear coordinates . A number of special forms of these equations are obtained corresponding to a number of special choice of the coordinates. In general, two groups of methods of solution are applieable to both surfaces. The first is based on the "mean-streamline circumferential (or radial) extension" technique, and the second is essentially the matrix and iterative methods previously used for solving the飞矿 equations which were expressed in terms of orthogonal cylindrical coordinates. This new set of equations ernploying non-orthogonal curvilinear coordinates enables one to calculate accurately and conveniently the inverse and direct turbomachine problerns for any arbitrary geometry,such as compressor blades having curved leading and trailing edge contours situated in a curved passage.