Aerothermodynamics of Turbomachinery: Analysis and Design by Naixing Chen

By Naixing Chen

Computational Fluid Dynamics (CFD) is now a vital and potent device utilized in the layout of all kinds of turbomachine, and this subject constitutes the most topic of this ebook. With over 50 years of expertise within the box of aerodynamics, Professor Naixing Chen has built quite a lot of numerical tools masking virtually the whole spectrum of turbomachinery purposes. additionally, he has additionally made major contributions to useful experiments and real-life designs.

The e-book makes a speciality of rigorous mathematical derivation of the equations governing movement and particular descriptions of the numerical equipment used to resolve the equations. quite a few functions of the easy methods to varieties of turbomachine are given and, in lots of instances, the numerical effects are in comparison to experimental measurements. those comparisons illustrate the strengths and weaknesses of the equipment – an invaluable consultant for readers. classes for the layout of greater blading also are indicated after many purposes.

  • Presents real-world viewpoint to the previous, current and destiny difficulty in turbomachinery
  • Covers direct and inverse options with theoretical and useful elements
  • Demonstrates large software historical past in China
  • Supplementary directions can be found at the significant other web site

Aerothermodynamics of Turbomachinery: research and Design is perfect for senior undergraduates and graduates learning within the fields of mechanics, strength and tool, and aerospace engineering; layout engineers within the company of producing compressors, steam and gasoline generators; and learn engineers and scientists operating within the components of fluid mechanics, aerodynamics, and warmth move.

Supplementary lecture fabrics for teachers can be found at www.wiley.com/go/chenturboContent:
Chapter 1 creation (pages 1–8):
Chapter 2 Governing Equations Expressed in Non?Orthogonal Curvilinear Coordinates to Calculate 3D Viscous Fluid move in Turbomachinery (pages 9–24):
Chapter three creation to Boundary Layer concept (pages 25–35):
Chapter four Numerical strategies of Boundary Layer Differential Equations (pages 37–57):
Chapter five Approximate Calculations utilizing essential Boundary Layer Equations (pages 59–85):
Chapter 6 program of Boundary Layer strategies to Turbomachinery (pages 87–101):
Chapter 7 flow functionality tools for 2? and Three?Dimensional circulation Computations in Turbomachinery (pages 103–143):
Chapter eight strain Correction approach for Two?Dimensional and Three?Dimensional movement Computations in Turbomachinery (pages 145–198):
Chapter nine Time?Marching technique for Two?Dimensional and Three?Dimensional stream Computations in Turbomachinery (pages 199–250):
Chapter 10 Numerical research at the Aerodynamic layout of Circumferential? and Axial?Leaned and Bowed Turbine Blades (pages 251–286):
Chapter eleven Numerical learn on Three?Dimensional move Aerodynamics and Secondary Vortex Motions in Turbomachinery (pages 287–328):
Chapter 12 Two?Dimensional Aerodynamic Inverse challenge resolution examine in Turbomachinery (pages 329–359):
Chapter thirteen Three?Dimensional Aerodynamic Inverse challenge answer learn in Turbomachinery (pages 361–373):
Chapter 14 Aerodynamic layout Optimization of Compressor and Turbine Blades (pages 375–427):

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Extra info for Aerothermodynamics of Turbomachinery: Analysis and Design

Example text

2c. 2 Nature of the two-dimensional boundary layer and velocity distributions of laminar, transitional and turbulent boundary layer flow regimes In the case of low turbulence intensity and low incidence the laminar boundary layer is formed near the leading edge. At point 2 the boundary layer begins transit from the laminar to the turbulent regime. At point 3 the boundary layer becomes fully turbulent. In the turbulent region there is a very thin laminar sublayer. 2 Boundary Layer Thicknesses For approximate calculation of the boundary layer the definitions of different boundary layer thickness properties are frequently used and are given below.

Yu. (1962) Hydrodynamics of Turbomachine Cascades, State Physics and Mathematics Press, Moscow, (in Russian). Traupel, W. (1977 and 1982) Thermische Turbomachinen, vols. 1 (1977) and 2 (1982), Springer, New York. V. (1950) Long Blade Profile Building of Steam and Gas Turbines, Defense Press, Moscow, (in Russian). H. (1960) Aerothermodynamics and Flow in Turbomachinery, John Wiley & Sons, New York. Wang, Baoguo (1998) Computational Methods of Subsonic and Transonic Flow Fields in Turbomachinery, Defense Industry Press, Beijing, (in Chinese).

Using Prandtl’s concept of boundary layer on an aerodynamic body wall, the Navier–Stokes equations can be reduced to a more treatable form called boundary layer equations, and then some of the viscous flow problems can be solved. In this chapter first the boundary layer equations expressed in differential equation form for two-dimensional flows and the flow past blade cascades on the stream surface of revolution are given and solved, and then a set of examples are calculated and compared with experiment.

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