The Impact of Blade and Material Damping in Turbine Blades
Year: 2015
Type: article
Abstract: : A method of determining equivalent viscous damping ratio for different rotational speeds and modes as a function of displacement or strain at a reference point in a blade is presented. This method can be adopted using a suitable finite element code, e.g., ANSYS or ABAQUS. The friction damping concept is widely used to reduce resonance stresses in turbomachines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. The capability to assess damping in the blade from finite element codes avoids costly tests at the initial stages of design.
Authors: I. Hamidipoor, N. Golsanamlou, Iman Zare, P. Moradi
Institution: Miami University
Language: English
Subfield: Mechanical Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: diamond
OpenAlex ID: W2153582955