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	APPLICATION OF RADIAL-EQUILIBRIUM CONDITION TO AXIAL-FLOW COMPRESSOR AND TURBINE DESIGN*
	Wu Zhonghua
	2002
卷号	1期号:1页码:1，51
英文摘要	" Basic general equations governing the three-dimensional compressible flow of gas through a compressor or turbine are given in terms of total enthalpy , entropy , and velocity components of the gas .Two methods of solution are obtained for the simplified , steady axially symmetric flow ; one involves the use of a number of successive planes normal to the axis of the machine and short distances apart , and the other involves only three stations for a stage in which an appropriate radial-flow path is used . Methods of calculation for the limiting cases of zero and infinite blade aspect ratios and approximate method of calculation for finite blade aspect ratio are also given. In these methods , the blade loading and the shape of the annular passage wall may be arbitrarily specified. The analysis shows that, radial motion of gas consists of a gradual, generally monotone component due to the taper in the passage wall , and an oscillatory component due to the radial variation of the specifically mass flow at different stations along the axis of the machine specified in the design . The streamline is curved by this radial flow and a corresponding radial pressure gradient is required to maintain this curvature .The magnitude of this gradient is increased with high Mach number of gas flow and high aspect ratio of blade row . The conventional method of calculation , in which the effect of radial motion on the radial distribution gas state is neglected , is found to be applicable only for the limiting case of zero aspect ratio . An analysis of the equations governing the flow shows that a designer is free to prescribe a reasonable, radial variation of one of the velocity components or other thermodynamic properties of the gas at any station within the blade region . The various ways of using this degree of freedom and the different types of design obtained are discussed . Numerical computations are then made for two types of compressor and one type of turbine . The results indicate that , even in the case of nontapered passage walls , appreciable radial motion occurs and the corresponding effects are of significant magnitude and should be considered in design"
公开日期	2013-04-11
内容类型	期刊论文
源URL	[http://ir.etp.ac.cn/handle/311046/59685]
专题	工程热物理研究所_图书馆_所院士论文选集_吴仲华_期刊论文
推荐引用方式 GB/T 7714	Wu Zhonghua. APPLICATION OF RADIAL-EQUILIBRIUM CONDITION TO AXIAL-FLOW COMPRESSOR AND TURBINE DESIGN*[J],2002,1(1):1，51.
APA	Wu Zhonghua.(2002).APPLICATION OF RADIAL-EQUILIBRIUM CONDITION TO AXIAL-FLOW COMPRESSOR AND TURBINE DESIGN*.,1(1),1，51.
MLA	Wu Zhonghua."APPLICATION OF RADIAL-EQUILIBRIUM CONDITION TO AXIAL-FLOW COMPRESSOR AND TURBINE DESIGN*".1.1(2002):1，51.

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