Method for calculating threedimensional flow in bladed turbomachine by using arbitary quasi perpendicular intersecting planes
Abstract
The mutual influence between two groups of flow surfaces is simultaneously considered, so that no correction need to be made from each other by successive substitution between these two groups of flow surfaces. The theory of a variable curve sample is applied. After appropriate successive substitutions of spatial streamlines, the three dimensional solution of the entire blade channel can be directly calculated, including shapes of arbitrary S sub 1 and S sub 2 flow surfaces, shapes of spatial streamlines, and the distribution of flow parameters, such as velocity and pressure. As the first step in solving the real three dimensional flow field, the approximate hypothesis that the S sub 1 flow surface is a surface of revolution is applied. The solution obtained is basically still the quasi three dimensional solution. The next step is to eliminate the hypothesis that the S sub 1 surface is a surface of revolution in order to obtain the solution of a real three dimensional flow field. Then the curvature of S sub 1 flow surface can be calculated.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 October 1981
 Bibcode:
 1981STIN...8217467X
 Keywords:

 Computational Fluid Dynamics;
 Flow Geometry;
 Gas Turbines;
 Three Dimensional Flow;
 Turbine Blades;
 Flow Velocity;
 Laminar Flow;
 Pressure Distribution;
 Two Dimensional Flow;
 Fluid Mechanics and Heat Transfer