A Proper Shape of the Trailing Edge Modification to Solve a Housing Damage Problem in a Gas Turbine Power Plant

To solve the housing damage problem of a fractured compressor blade (CB) caused by an impact on inner casing gas turbine in seventh stage (from 15 stages), modifications trailing edge (TE) CB have been proposed, namely 6.5 mm curved cutting and combination 4 straight with cutting. The simulation results both aerodynamics variables Cl Cd pressure ratio, including structural dynamics such as normalized power spectrum, frequency, total deformation, equivalent stress, safety factor, found that could deliver similar to original CB. This result also overcomes previous work proposed 5.0 indicates operation gives uneven temperature, which get higher TE area. slightly modified can present difference properties dynamics. Therefore, any should be investigated for simultaneously. Finally, from this very useful information modification other rotating types machinery plant.