EXPERIMENTAL-AND-COMPUTATIONAL PREDICTION OF AEROELASTIC STABILITY IN BLADE ASSEMBLIES AGAINST SUBSONIC FLUTTER
Abstract eng: The basic principles of the experimental-and-computational complex for predicting the subsonic flutter stability of aircraft gas turbine compressor blading are stated. The methodology is described for the experimental determination of non-stationary aerodynamic forces and moments acting on blades during their in-flow vibrations; the calculation of the dynamic stability of a blade assembly against flutter; the aerodynamic rig design and peculiar features of its components to perform testing of airfoil cascades. The results of testing of the developed experimental-and-computational complex are presented.
Contributors:
Publisher:
Institute of Thermomechanics AS CR, v.v.i., Praha
Conference Title:
Conference Title:
Engineering Mechanics 2013
Conference Venue:
Svratka (CZ)
Conference Dates:
2013-05-13 / 2013-05-16
Rights:
Text je chráněný podle autorského zákona č. 121/2000 Sb.
Record appears in:
Record created 2014-11-12, last modified 2014-11-18
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