Static Structural Analysis of Gas Turbine Compressor Stator Blades Made of Different Alloys

Gas turbines are among the most versatile pieces of turbomachinery today, utilized in various applications including power generating, home settings, aviation, oil and gas, process plants, associated minor industries, and related small industries. This paper addresses issues related to blade profile selection, material selection, and structural analysis on the gas turbine compressor stator blades which significantly impacts the induced stress-deformation and structural performance of developmental gas turbine engines. However, maintaining extremely high pressure, centrifugal force, and temperatures within a gas turbine is challenging due to various metallurgical issues that develop on the compressor blade surface. These problems could cause the gas turbine compressor to fail structurally. Many researchers focus on the rotor blades of the turbine compressor, but stator blades are essential to recognize which are integral components of the turbine compressor and play a crucial role in converting high velocity into high pressure. The performance analysis is carried out on four different alloys that are previously recognized as rotor blade materials, namely GTD 450, Ti-6Al-4V, Nimonic-80A, and AISI-403 as the potential stator blade materials in terms of strain, von Mises stress, and displacement. According to the study’s findings, Ti-6Al-4V performs the best among the four materials examined GTD 450, Nimonic-80A, Ti-6Al-4V, and AISI-403—in terms of von Mises stress and least displacement under the specified boundary conditions. Because of its exceptional mechanical qualities and capacity to tolerate high stresses with minimal deformation, Ti-6Al-4V is the best material to use in the production of gas turbine compressor stator blades. AISI-403, on the other hand, performed the worst, not meeting the necessary structural integrity under the specified circumstances. Because of its robustness and longevity in harsh operating conditions, Ti-6Al-4V is thus suggested as a dependable material for crucial applications in gas turbine compressor blades.