Accession Number : ADA118135

Title :   Viscoelastic Damping of Turbine and Compressor Blade Vibrations.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s) : Vest,Stephen Lee

PDF Url : ADA118135

Report Date : Mar 1982

Pagination or Media Count : 81

Abstract : An experimental and an analytical model of a turbine/compressor blade is developed in order to investigate the feasibility of using a viscoelastic material to damper the vibrations of the blade. The experimentally determined response of the blade at various frequencies is studied. In order to make a qualitative comparison of damping effectiveness, the response of a similar model using friction damping is also experimentally studied. A model of a modified cantilever beam is used to develop the equation of motion of the blade and the resulting eigenvalve problem is solved using an iterative technique. An analysis of the rigid body mode is performed. A comparison and an analysis of the results of the experimental and analytical models are delineated. (Author)

Descriptors :   *Gas turbine blades, *Compressor blades, *Vibration, *Oscillation, *Damping, Mathematical models, Viscoelasticity, Cantilever beams, Equations of motion, Eigenvalues, Rigidity, Experimental data, Friction, Theses

Subject Categories : Numerical Mathematics
      Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE