| dc.description.abstract | Power enhancement technologies for gas turbines such as inlet fogging, interstage water injection, saturation cooling, inlet chillers, and combustor injection are being used by end users without evaluating the potentially negative effects these devices may have on the operational integrity of the gas turbine. Specifically, the effect of these add-on devices, off-design operating conditions, nonstandard fuel, and compressor degradation/fouling on the gas turbine’s axial compressor surge margin and aerodynamic stability is often overlooked. However, aerodynamic axial compressor instabilities caused by these factors can be directly linked to blade high-cycle fatigue and subsequent catastrophic gas turbine failure. A careful analysis should always proceed the application of power enhancement devices, especially if the gas turbine is operated at extreme conditions, uses older internal parts that are degraded and weakened, or uses nonstandard fuels. This paper discusses a simple method to assess the major factors that affect the aerodynamic stability of a single shaft guas turbine’s axial compressor. As an example, the method is applied to a frame type gas turbine, and the results are presented. These results show that inlet cooling alone will not cause gas turbine aerodynamic instabilities, but it can be a contributing factor if, for other reasons, the machine’s surge margin is already slim. The approach described herein can be employed to identify high-risk applications and bound the gas turbine operating regions to limit the risk of blade life reducing aerodynamic instability and potential catastrophic failure. | en |
