Investigation of the unsteady pressure distribution on the blade of an axial flow fan
Abstract
A major source of the noise generated by high bypass ratio aircraft fan engines is the unsteady pressures (forces and moments) acting on the fan blades. These unsteady pressures are the result of the interaction of the blades with the wakes of upstream blade rows, inlet flow distortions, and inlet turbulence. An experimental system was developed which will permit the measurement of the unsteady pressure distributions; a series of experiments were conducted to investigate these effects, and the results are compared with predictions from existing theoretical analyses.
- Publication:
-
Semiannual Progress Report
- Pub Date:
- October 1975
- Bibcode:
- 1975penn.reptR....H
- Keywords:
-
- Axial Flow Turbines;
- Pressure Distribution;
- Turbine Blades;
- Data Reduction;
- Flow Distribution;
- Inlet Flow;
- Prediction Analysis Techniques;
- Fluid Mechanics and Heat Transfer