Abstract
One of the most important technical problem is the moniroting of the combustion flow, concerning the aircraft turbo-engine during its continuous operation.
Considering the combustion process as a dynamic excitation, we measure the noise and the vibration on chosen points on the engine. By doing that we come to conclusions concerning the combustion flow. In this experimental work appear the spectra of the noise and vibration measurements as a parameters of engine revolutions (R.P.M.).
The spectra of random combustion forces and spectra of noise and vibration borne noise structure are investigates using transient analysis.
Their analysis by P.C. and the construction 3-D diagrams which combine the noise level, the vibration level and the R.P.M., give us important information about the interdependance of the above sizes and the combustion flow. The measurements take place on the F-104 G Starfighter aircraft with the General Electric-J79 turboengine, which is the oldest military aircraft in today use.
