To investigate the forcing function effects on the fundamental 2 E gust unsteady aerodynamic response of a multistage turbomachine blade row

a series of fundamental experiments are performed in an axial flow research compressor.The 2 E unsteady aerodynamic forcing function excitations are generated by both a circumferential inlet flow distortion and the wakes from airfoil type obstructions which are representative of an airfoil

strut

or probe excitation.