Experimental Investigation Characteristics of the Related Wake of Linear Compressor by Hot-Wire Anemometer

In this paper, due to the importance of incoming flow turbulence intensity into combustion chamber, tripping wire effect on the flow wake has been experimentally investigated within a linear compressor cascade. Besides, effects of changes in the attack angle of compressor blades on the characteristics of wake are investigated. Investigation on the velocity, turbulence intensity and vortex frequency in the wake of blade in the attack angles of -10, 0 and 10 is done. In previous work the effects of a smaller angle of attack has been examined [1]. Therefore, to better understand the flow in the wake, more essential investigations appeared to be necessary for more angles of attack. Thus, two wires were implemented along each blade and their effects on average velocity, turbulence intensity and vortices frequencies were accurately considered. Increasing the angle of attack, leads to increase in the domain of wake and frequency at maximum amplitude, and the maximum Strouhal number. To do this, single channel hot wire anemometer was used to measure the wake parameters.