Analysis of an axial compressor stage with infinitesimal and finite blade spacing /
H. J. Reissner and L. Meyerhoff.

Description

Main Author

Reissner, H. J.

Related Names

Meyerhoff, L.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1951.

Subjects

Equations.
Axial flow compressors > Axial flow compressors / Design and construction.
Axial flow compressors > Axial flow compressors / Blades.

Summary

A method of designing circular blade systems of finite spacing is developed. First, the theory of flow and through a system of infinitesimally spaced surfaces is formulated by means of a continuous axially symmetric force field which is uniform in the cricumferential direction. This force field replaces the effect of the blade system, with its hub and shroud boundary surfaces. Second, the force field is the space between the blades, hub, and shroud is replaced in the equations of finite spacing by inertia and pressure terms, which were omitted in equations of infinitesimal spacing. These terms will change values of flow variables of infinitesimal spacing.

Note

NACA TN No. 2493.
"October 1951."

Physical Description

32 p. : ill. ; 28 cm.

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