Active control of compressor instability and surge by stator blades adjustment

A method of active aerodynamic control and prevention of axial compressor instability and surge was applied to a single-spool, two-shaft power-generation gas turbine engine with a multistage compressor. Two complete dynamic engine simulations were performed. In the course of the first simulation, the stator-row stagger groups revealed high-frequency, short-duration mass flow fluctuations with large amplitudes and alternatively positive and negative values. The HP-compressor stage group exhibited only positive mass flow fluctuations that were apparently propagated downstream and did not originate from the HP part. Introducing the stator blade stagger angle adjustment brought substantial change in operational behavior. Adjusting the LP and IP-compressor stagger angle caused a significant shift in surge limit and established a fully stable operation regime for all three compressor parts.

Active control of compressor instability and surge by stator blades adjustment Academic Article