An Approximate Solution of the Sudden Area Expansion Flow Process for Flows in a Rotating Coordinate System
Final rept. Dec 1968-Dec 1969
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pagination or Media Count:
An approximate quasi-three-dimensional method of solution is described for the sudden area expansion flow process in the relative coordinate system under the assumptions of frictionless, adiabatic flow of a perfect gas. The objective was to determine the radial variation of the flow properties at the trailing edge of a rotor given the measured flow properties downstream of the rotor through use of the stream-tube approximation. Results are derived from one configuration of the blunt trailing-edge supersonic compressor rotors tested at AEDC. The results are shown of neglecting the free turbulent shear flows occurring in the blade wakes in conjunction with neglecting large radial secondary flows.
- Fluid Mechanics
- Jet and Gas Turbine Engines