A finite difference method of blade-to-blade calculation for incompressible turbulent, viscous flow through radial turbomachines having log-spiral blades lying entirely in the r-θ plane is presented. A Newtonian stress system is incorporated into the calculation which employs a slip model for flow close to the blade surfaces. The effects of turbulence are simulated by use of an enhanced molecular viscosity. This problem is of a higher mathematical order than the usual free slip, inviscid calculation commonly applied in the design and analysis of these machines and raises interesting considerations of understanding with respect to mathematical closure and boundary conditions. Experimental results for flow through an actual machine of similar geometry to that analyzed are available and comparison of streamlines and velocity profiles are made.
Skip Nav Destination
Article navigation
July 1979
This article was originally published in
Journal of Engineering for Power
Research Papers
A Calculation Method for Incompressible Viscous, Blade-to-Blade Flow through Radial Turbomachines with Log-Spiral Blade Surfaces
C. Bosman,
C. Bosman
Department of Mechanical Engineering, The University of Manchester Institute of Science and Technology, Manchester, England
Search for other works by this author on:
K. C. Chan,
K. C. Chan
Department of Mechanical Engineering, The University of Manchester Institute of Science and Technology, Manchester, England
Search for other works by this author on:
A. P. Hatton
A. P. Hatton
Department of Mechanical Engineering, The University of Manchester Institute of Science and Technology, Manchester, England
Search for other works by this author on:
C. Bosman
Department of Mechanical Engineering, The University of Manchester Institute of Science and Technology, Manchester, England
K. C. Chan
Department of Mechanical Engineering, The University of Manchester Institute of Science and Technology, Manchester, England
A. P. Hatton
Department of Mechanical Engineering, The University of Manchester Institute of Science and Technology, Manchester, England
J. Eng. Power. Jul 1979, 101(3): 450-458 (9 pages)
Published Online: July 1, 1979
Article history
Received:
December 28, 1977
Online:
July 14, 2010
Citation
Bosman, C., Chan, K. C., and Hatton, A. P. (July 1, 1979). "A Calculation Method for Incompressible Viscous, Blade-to-Blade Flow through Radial Turbomachines with Log-Spiral Blade Surfaces." ASME. J. Eng. Power. July 1979; 101(3): 450–458. https://doi.org/10.1115/1.3446600
Download citation file:
Get Email Alerts
Cited By
A Multi-Stage Nonlinear Method for Aeroengine Health Parameter Estimation Based on Adjacent Operating Points
J. Eng. Gas Turbines Power
A Combined Experimental and Turbulence-Resolved Modeling Approach for Aeroengine Turbine Rim Seals
J. Eng. Gas Turbines Power (August 2024)
Related Articles
The Calculation of Three-Dimensional Viscous Flow Through Multistage Turbomachines
J. Turbomach (January,1992)
Adjoint Aerodynamic Design Optimization for Blades in Multistage Turbomachines—Part I: Methodology and Verification
J. Turbomach (April,2010)
A Practical Combined Computation Method of Mean Through-Flow for 3D Inverse Design of Hydraulic Turbomachinery Blades
J. Fluids Eng (November,2005)
Related Chapters
Approximate Analysis of Plates
Design of Plate and Shell Structures
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis
Fluid Mechanics
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis