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stream sheet
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     The effects of the variation in stream surface radius and stream sheet thickness on the flow property was investigated by numerical method.
     用数值方法研究了流面半径和流片厚度随轴向变化对于流动的影响。
短句来源
  “stream sheet”译为未确定词的双语例句
     Aerodynamical Calculation and Analysis of the Blade-to-Blade Flow on S_1 Stream Sheet of Centrifugal Compressor
     涡轮增压器压气机叶栅S_1流面的气动计算及结果分析
短句来源
     Variational Principles for Rotational Flow on S_2 Stream Sheet Using Pseudo-Potential Function
     S_2流面有旋流动的赝势函数变分原理族
短句来源
     Based on the variational principles and the work, aerodynamical calculation was presented for the blade-to-blade flow on S_1 stream sheet of centrifugal compressor (Type: 11GJ and 110J).
     本文在文献[1]和文献[3]的基础上对无锡动力机厂提供的11GJ及110J型涡轮增压器离心式压气机叶栅S_1流面的气动特性进行计算。
短句来源
     A New Finite Element Solution for the Aerodynamic Direct Problem on S_1 Stream Sheet of Revolution in Cascade with Multi-splitter Vanes and Experimental Research
     多分流叶栅S_1旋成流面上的气动正命题有限元新解法及试验研究
短句来源
     In this report,principle is based on Wu's theory of flow on blade-to -blade( S 1) and hub-to-shroud( S 2)surfaces Stream sheet thickness and boundary conditions are introduced The equations of motion of fluid on S 1and S 2surfaces are reasoned from the basic equations of motion of fluid After calculating three-dimensional inviscid field through a Francis Runner with iteration,Quasi-three-dimensional solutions are obtained
     根据两类相对流面的理论,引入边界条件及流面厚度,建立了S1流面和S2流面的运动微分方程,用有限元法离散处理,编制了网格自动生成程序,通过数值计算方法对一混流式水轮机转轮的流场进行了迭代计算,得出了流场的准三元解
短句来源
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  相似匹配句对
     Reason and Prevention of Cracking on Tube Sheet of Oil Slurry Stream Generator
     重催油浆蒸气发生器管板开裂原因及防治
短句来源
     Calculation of the Boundary-layers and Aerodynamic Coefficients on Arbitrary Stream-sheet of Revolution in Cascades
     任意旋成面叶栅边界层和损失计算
短句来源
     THE USES OF CORRUGATED SHEET
     波纹板的用途
短句来源
     Evenness of paper sheet
     纸的匀度
短句来源
     The Innovation of Stream of Consciousness
     意识流小说艺术创新论
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  stream sheet
The stream-sheet thickness variation obtained from a meridional-plane solu tion is required as input for a blade-to-blade solution.
      


The present paper is devoted to the search for variational principles for the direct aerodynamic problem of channels and aerofoil cascades (with prescribed distributed mass injection or/and suction along the profile contours for blade cooling or boundary layer control) on an arbitrary stream sheet of revolution and aimed mainly at providing a rigkms and sound theoretical basis for introducing and widely applying the finite element method to computational aerodynamics of turbomachines. Three generalized...

The present paper is devoted to the search for variational principles for the direct aerodynamic problem of channels and aerofoil cascades (with prescribed distributed mass injection or/and suction along the profile contours for blade cooling or boundary layer control) on an arbitrary stream sheet of revolution and aimed mainly at providing a rigkms and sound theoretical basis for introducing and widely applying the finite element method to computational aerodynamics of turbomachines. Three generalized variational principles (among which two are for homoentropic flow, and the other for nonhomoentropic flow) are developed first, and then from them three families of variational principles are derived respectively by means of successive transformations. Furthermore, for homoentropic subsonic flows a pair of dual extremum principles are also shown to exist.Special attention is payed to taking full advantage of 2 effective means: "natural boundary conditions" and "artificial boundaries", in order to greatly simplify the numerical treatment of various boundary conditions characterizing the complexitg of the cascade problem. So in all variational principles all boundary conditions have been converted to natural ones.The variational principles presented here can be used to advantage as basis also for variational-finite difference method and for various direct variational methods (e.g. Ritz's method, Kantorovich's method etc.).

本文致力于任意旋成面叶栅和流道气动正命题(沿叶面可有气体喷人或吸出,例如边界层控制、气膜式或发汗式冷却等)的变分原理的探索研究,为在叶轮机气动计算领域中引进和推广有限元法提供一个较严密的理论基础.结果有:1.对均熵流动,建立了两条广义变分原理,并从它们派生出两族亚广义变分原理,包括亚声速下的一对互偶极值原理;2.对非均熵流动,建立了一条广义变分原理,并由此派生出一族亚广义变分原理.文中着重充分发挥自然边界条件和人工界面的有力作用,以简化叶栅复杂多样的边界条件的处理.除用于有限元法外,它们也为变分一差分法和各种变分直接解法创造了有利条件.

The paper shows that the stream-surface theory does not take account of the actions of secondary flow induced by the disturbance blade force. Based on the stream-surface, the generalised equation of such a secondary flow in an axial-turbomachine is deduced. Compressibility of flow is corrected with the local Much number of the primary flow to avoid the errors which are brought out by using only Much number upstream or a given average Much number in the traditional linearlized theory. The existance...

The paper shows that the stream-surface theory does not take account of the actions of secondary flow induced by the disturbance blade force. Based on the stream-surface, the generalised equation of such a secondary flow in an axial-turbomachine is deduced. Compressibility of flow is corrected with the local Much number of the primary flow to avoid the errors which are brought out by using only Much number upstream or a given average Much number in the traditional linearlized theory. The existance of the primary flow vorticity reflects in a so-called stream-sheet thickness 6 of the S2 stream surface of the primary flow. The b=1 represents an irrotational primary flow or the case in which the primary flow vortex is negligible small. The b=0 is a limiting case which represents that the vorticity of the primary flow becomes infinite. Then an attempt to approach the secondary flow problem of large shear and large disturbance flow is tested.The paper also shows the equations deduced from generalised equation under the conditions of the compressible axi-symmetric axial-inlet flow and the incompressible 2-D plane cascade flow. Then it shows that the generalised equation is appropriate for correcting the effects of the secondary flow on the stream surface flow after comparing with the equations in the reference [10], [11] and [12] when the assumptions of lifting line theory are adopted.

本文论证了流面理论未能计及由举力场的扰动所诱导的二次流的影响,并以流面为基础,推导了轴流式涡轮机械中此类二次流场所遵循的一般方程式。流场的可压缩性用当地的基本流场M数来校正,避开了通常的线性化理论中用叶排上游M数或某个平均M数所带来的误差。基本流场的旋度影响用基本流场5_2中心流面的流片厚度b来代表。b=1代表了基本流场无旋或旋度影响可忽略的情形,b=0的极限情况代表了基本流场的旋度为无穷大的情况。从而为探索解决大剪切大扰动流场中的二次流问题提供了一种可能的途径。文中分析了一般方程在不可压平面叶栅流动和可压缩轴对称轴向进气流动中所具有的形式,并指出,在举力线理论的假设前提下,它们和文献[10—12]中的基本方程的形式相同,从而证明了本方程的适用性。

In this part Ⅱ, another type "B" of the hybrid problem of airfoil cascades on a general stream sheet of revolution, in which the profile thickness distribution and the aerodynamic loading distribution [i. e. the pressure diffcrence distribution on the suctionand pressure sides (Pp-Ps)] along the profile chord are prescribed, is formulated and studied, in order to meet various practical requirements of turbomachinery blade design more closely and flexibly. Two families of variational principles and generalized...

In this part Ⅱ, another type "B" of the hybrid problem of airfoil cascades on a general stream sheet of revolution, in which the profile thickness distribution and the aerodynamic loading distribution [i. e. the pressure diffcrence distribution on the suctionand pressure sides (Pp-Ps)] along the profile chord are prescribed, is formulated and studied, in order to meet various practical requirements of turbomachinery blade design more closely and flexibly. Two families of variational principles and generalized variational principles are developed for this hybrid problem B in terms of the moment function Ω and arzimuthal angular function introduced in part I formerly. Full advantage has been taken of two powerful means——natural boundary conditions and artificial interfaces——in order to facilitate the handling of various boundary conditions of complex character. As a result, in every variational principle all boundary conditions appear as natural ones.This part Ⅱ is also aimed at providing a broader and sound theoretical foundation for introducing the finite element method, variational-difference method or direct variational methods into computational aerodynamics of turbomachinery as well as providing some new rational ways for cascade design.

在这第Ⅱ部分里,我们将专门研究下列一种杂交型命题:给定叶型厚度分布和叶型的气动负荷(即叶型凹、凸面上的压差)分布。我们为这种杂交型命题建立了相应的两族变分原理与广义变分原理,旨在为将有限元法、变分一差分法以及变分直接解法引进和推广到叶轮机叶栅气动问题中去提供一个更广泛、完密的理论基础,同时也为叶栅气动设计提供一些新的合理途径。在诸变分原理中充分发挥了自然边界条件和人工分界面的有力作用,已将全部边界条件都化成自然边界条件,以简化边界条件的处理。

 
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