Stress Analysis of High Pressure Compressor Rotor Blade of Gas Turbine Engine

The compressor is a device that pressurizes a working fluid/gas/steam, which flow from the inlet and leaves the gas with higher temperature and pressure to the outlet. Load imposed upon the components of compressors results in compressor blade stresses, which vary considerably over the operational envelope of the compressor edge of the blade stresses, which is important in evaluating the operational limits of the compressor speed and total pressure combination. Stress analysis of high pressure compressor rotor blade of an experimental gas turbine engine will be carried out. The analyses will be performed for different combinations of speed, mass flow rate and pressure gradient across the stage. Reduced order stress model will be developed and verify for an arbitrary loading condition. The above activities include 3D solid model generation (UG), Finite element meshing (HYPERMESH) of rotor blade and static stress simulations using ANSYS software. Using the simulation results a mathematical model (Reduced Order Stress Function) will be developed.