Research on Aeroelastic Phenomena in Thin Airfoil Cascades.
Final summary rept.,
GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
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The advent of high tip, high work, blading in the fan stages of advanced gas turbine engines has led to the recognition of a new type of blading instability - unstalled supersonic flutter. As a result, a concerted effort to develop an appropriate predictive mathematical model has taken place. To determine the range of validity and to direct refinements to the basic flow model, fundamental supersonic oscillating cascade data are required. This is the report for an experimental research program directed at obtaining these unique time-variant aerodynamic data. The approach involved harmonically oscillating dynamically instrumented 2-D rectilinear cascades of airfoils in a supersonic inlet flow field, with the unsteady operation of the cascade computer controlled. Data were obtained in both torsion and translation over a range of steady and time-variant aerodynamic conditions. All of these data were then correlated with predictions obtained from a current state-of-the-art model.
- Fluid Mechanics
- Jet and Gas Turbine Engines