| To control deviations in turbine throat area from manufacturing tolerances and mitigate adverse effects on turbine
performance and reliability, a turbine throat area tolerance design method based on numerical simulation and a genetic algorithm was
proposed. For a two-stage high-pressure turbine, sensitivity relationships between mass flow rate, inter-stage static pressure, rotor axial
force, efficiency, and deviations in the four-row blade throat areas were analyzed using commercial software, establishing a turbine
performance evaluation model based on throat area deviations. Based on this model, a tolerance evaluation function for turbine throat area
tolerance was constructed, and the genetic algorithm was employed to optimize the tolerance ranges for the four-row blade throat areas
within specified ranges. Results show that for key turbine performance parameters, the deviations between the performance evaluation
model's predictions and CFD results are less than 0.1%. For population sizes of 50, 100 and 200, the optimizations consistently converge to
the same optimal tolerance solution for the four-row blade throat areas; within the solution space, to realize performance parameters of the
high-pressure turbine closest to the limit values, the throat area tolerances for the four blade rows should be ±1.02%, ±1.00%, ±1.00%,
±1.01%, respectively. |