Some Effects of Compressibility on the Flow Through Fans and Turbines
Abstract
The laws of conservation of mass, momentum, and energy are applied to the compressible flow through a two-dimensional cascade of airfoils. A fundamental relation between the ultimate upstream and downstream flow angles, the inlet Mach number, and the pressure ratio across the cascade is derived. Comparison with the corresponding relation for incompressible flow shows large differences. The fundamental relation reveals two ranges of flow angles and inlet Mach numbers, for which no ideal pressure ratio exists. One of these nonideal operating ranges is analogous to a similar type in incompressible flow. The other is characteristic only of compressible flow. The effect of variable axial-flow area is treated. Some implications of the basic conservation laws in the case of nonideal flow through cascades are discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1945
- Accession Number
- ADB196845
Entities
People
- H. T. Epstein
- W. Perl
Organizations
- Glenn Research Center