This study's motivation is to investigate the effects of shock wave instability in transonic compressor cascades, a potentially groundbreaking area of research that is essential for understanding the physics of this phenomenon and generating an experimental database for further understanding the origins of flutter and non-synchronous blade vibrations in these machines. Investigation of shock wave instability and intermittency on real machines is technologically complicated and economically prohibitively expensive. The adopted approach relies on experimental data acquired in linear transonic cascades. Data acquired in two different dedicated test facilities confirmed that the nature of the shock wave intermittency was nearly identical, displaying similarly transitional random behavior. However, the test arrangements, the tested compressor cascades, and the airfoils differed. A preliminary analysis of the obtained data implies that two mechanisms generate intensive pressure fluctuations in a cascade with oscillating blades. First, periodic blade oscillatory motion induces periodic low amplitude pressure fluctuations. Second, the passage shock wave intermittency and instability excite the large amplitude pressure fluctuations. It appears that the contribution of the blade oscillatory motion to the magnitude of pressure fluctuation is relatively weak, at least for the current exploratory test range. The level of the pressure fluctuations generated by the shock wave intermittency completely overpowers the level of pressure fluctuations induced by the blade motion alone. The amplitude of pressure fluctuations is independent of the blade oscillation frequency and is entirely determined by the intensity of the passage shock wave intermittency.