Abstract
The rotordynamic coefficients of squeeze film dampers of an aircraft gas turbine engine were investigated experimentally. Rotordynamic model(XLROTOR) for Gas Generator and Power Turbine were constructed. The XLROTOR response plots with changing bearing damping and stiffness coefficients were well matched with the coastdown plots of the test runs. The squeeze film dampers reduced effective support stiffness with respect to the rotational speed. Damping coefficients of squeeze film dampers were mainly determined by the XLROTOR model simulations. The damping coefficients changed with respect to the rotational speed. High oil supply pressure helped to suppress vibrationamplitudes at critical speeds. Great amount of air bubbles were observed at the oil return lines.
Na, Uhn Joo (1996). Experimental study of rotordynamic coefficients of squeeze film dampers of an aircraft gas turbine engine. Master's thesis, Texas A&M University. Available electronically from
https : / /hdl .handle .net /1969 .1 /ETD -TAMU -1996 -THESIS -N33.