Compressor surge is a form of aerodynamic instability in axial compressors or centrifugal compressors. The term describes violent air flow oscillating in the axial direction of a compressor, which indicates the axial component of fluid velocity varies periodically and may even become negative. In early literature, the phenomenon of compressor surge was identified by audible thumping and honking at frequencies as low as 1 Hertz, pressure pulsations throughout the machine, and severe mechanical vibration.
Description
Compressor surge can be classified into deep surge and mild surge. Compressor surge with negative mass flow rates is considered as deep surge while the one without reverse flows is generally termed mild surge. On a performance map, the stable operating range of a compressor is limited by the surge line. Although the line is named after a surge, technically, it is an instability boundary which denotes onsets of discernible flow instabilities, such as compressor surge or rotating stall. When the mass flow rate drops to a critical value at which discernible flow instabilities take place, nominally, the critical value should be determined as a surge mass flow rate on a constant speed line; however, in practice, the surge line on a performance map is affected by specific criteria adopted for determining discernible flow instabilities.
Effects
Compressor surge is a disaster to the compressor and the whole machine. When compressor surge happens, the operating point of a compressor, which is usually denoted by the pair of the mass flow rate and pressure ratio, orbits along a surge cycle on the compressor performance map. The unstable performance caused by compressor surge is not acceptable to machines on which a compressor is mounted to ventilate or dense air. Except for affecting performance, compressor surge is also accompanied with loud noises. Frequencies of compressor surge can range from a few to dozens Hertz depending on the configuration of a compression system. Although Helmholtz resonance frequency is often employed to characterize the unsteadiness of mild surge; it was found that Helmholtz oscillation did not trigger compressor surge in some cases. Another effect of compressor surge is on solid structure. Violent flows of compressor surge repeatedly hit blades in the compressor, resulting in blade fatigue or even mechanical failure. While fully developed compressor surge is axisymmetric, its initial phase is not necessarily axisymmetric. Actually, severe damage of compressor surge is often related to very large transverse loads on blades and casing in its initial transient. A chain reaction of compressor surge is the flameout of a jet engine. Due to a lack of air intake in the case of compressor surge, there will be unburnt fuel in the combustion chamber, and that unburnt fuel will burn and cause flameout near the exit of the engine where oxygen is sufficient.
Causes
In most low-speed and low-pressure cases, rotating stall comes prior to compressor surge; however, a general cause-effect relation between rotating stall and compressor surge has not been determined yet. On a constant speed line of a compressor, the mass flow rate decreases as the pressure delivered by the compressor gets higher. Internal flows of the compressor are in a very large adverse pressure gradient which tends to destabilize the flow and cause flow separation. A fully developed compressor surge can be modeled as a one-dimensional global instability of a compression system which typically consists of inlet ducts, compressors, exit ducts, gas reservoir, and throttle valve. A cycle of compressor surge can be divided into several phases. If the throttle valve is turned to be a very small opening, the gas reservoir would have a positive net flux. The pressure in the reservoir keeps increasing and then exceeds the pressure at compressor exit, thus resulting in an adverse pressure gradient in exit ducts. This adverse pressure gradient naturally decelerates flows in the whole system and reduces the mass flow rate. The slope of a constant speed line near surge line is usually zero or even positive, which implies that the compressor cannot provide a much higher pressure as lowering the mass flow rate. Thus, the adverse pressure gradient could not be suppressed by the compressor and the system would rapidly involves an overshoot of adverse pressure gradient which would dramatically reduce the mass flow rate or even cause flows to reverse. On the other hand, the pressure in the reservoir would gradually drops due to less flux delivered by the compressor, thus rebuilding a favorable pressure gradient in exit ducts. And then the mass flow rate would be recovered, and the compressor is back to work on a constant speed line again, which would eventually trigger the next surge cycle. Therefore, compressor surge is a process which keeps breaking the flow path of a compression system down and rebuilding it. Several rules of thumb can be inferred from the interpretation above. Compressor surge in a system with a small gas reservoir is high-frequency and low-amplitude whereas a large gas reservoir leads to low-frequency and high-amplitude compressor surge; another rule of thumb is that compressor surge happens in a compressor with a large external volume and compressor stall tends to show up in a system with a short exit duct. It is also worth noting that the surge line of a compressor can have small variations in different systems, such as a test bench or an engine.
