Abstract
To solve the housing damage problem of a fractured compressor blade (CB) caused by an impact on the inner casing of a gas turbine in the seventh stage (from 15 stages), modifications of the trailing edge (TE) of the CB have been proposed, namely 6.5 mm curved cutting and a combination of 4 mm straight cutting with 6.5 mm curved cutting. The simulation results of the modifications in both aerodynamics variables Cl and Cd and the pressure ratio, including structural dynamics such as a normalized power spectrum, frequency, total deformation, equivalent stress, and the safety factor, found that 6.5 mm curved cutting could deliver the aerodynamics and structural dynamics similar to the original CB. This result also overcomes the previous work that proposed 5.0 mm straight cutting. This work also indicates that the operation of a CB gives uneven pressure and temperature, which get higher in the TE area. The slightly modified CB can present the difference in the properties of both the aerodynamics and the structural dynamics. Therefore, any modifications of the TE should be investigated for both properties simultaneously. Finally, the results from this work can be very useful information for the modification of the CB in the housing damage problem of the other rotating types of machinery in a gas turbine power plant.
Highlights
In 2019, Thailand’s electricity production relied on natural gas turbine power plants for up to 64% of total production
To solve the housing damage problem that happened in stage seven of the compressor stage in the gas turbine, this research proposed decent modifications of a compressor blade (CB) composed of 6.5 mm curve cutting and the combination of 4 mm straight cutting with 6.5 mm curve cutting
Using ANSYS CFX R19.2 with the stress transport (SST) k-ω turbulence model in the transient state, the AD results showed that the 6.5 mm curve cutting CB delivered results for the pressure ratio, Cl, Cd, and normalized power spectrum similar to the original CB
Summary
In 2019, Thailand’s electricity production relied on natural gas turbine power plants for up to 64% of total production. The results led to the conclusion that the most suitable modification was the straight cutting at 5 mm at the specific stage which caused pressure ratio alterations less than 0.2%, and the Cl and Cd changed less than 3.7% and 8.7%, respectively. This modification maintained the aerodynamics at the same level as the original CB. This method has been applied to gas turbine power plants for actual usage and showed steady efficiency of the power generator, as usual. It is unlikely that the previous work proposed the appropriate simulation of the CB’s modification, which applied these two calculations in their work
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