Impact of Dust Particle Flow on the Geometrical Integrity of Gas Turbine Compressor Blades

Abstract

The compressor in a gas turbine is a central component, directly influencing its geometry, aerodynamics, weight, efficiency, and operational reliability. Technological properties in compressor blades play a determining role in terms of determining engine aerodynamics as well as its behavior mechanically. The blade's strength and rotor integrity directly imply their reliability, where failure in blades may result in localized damage in engines and harsh consequences. Operational conditions of compressor blades subject them to varied forms of degradation in terms of geometry, mass, material properties, and surface conditions. The leading edge is exposed to erosion, blade tips may experience deformation, and roughness of surfaces may increase dramatically through contact by external particles such as dust. The work examines motion and behavior of particles of dust in flow's path in an axial compressor as well as their consequences in terms of erosion in blades, geometric variations, as well as engine's general performance. A computational simulation is developed to mimic airflow as well as behavior of particles in the compressor, and ANSYS Fluent simulation is used. Comparative analysis from simulation results to experimental values provide insight into dust-driven influences in terms of degradation. The results provide a basis point in terms of assessing operational risk, developing protection against blade erosion, as well as superior diagnostic methods in terms of gas turbine engines.