THERMAL SCIENCE
International Scientific Journal
OPTIMIZATION OF BLADE PROFILE FOR GOVERNING STAGE IN PEAK REGULATING CONDITION
ABSTRACT
Blade loss seriously affects the stage efficiency of steam turbine. The genetic algorithm is used to optimize the NURBS curve of blade profile in governing stage. With the maximum value of the function composed of total pressure loss coefficient, steam flow Angle and static pressure ratio, the optimized blade profile in peak regulating condition is obtained. The flow pattern of internal flow field, the load distribution of blade and the development law of cascade losses are studied before and after blade profile optimization. The results show that after blade profile optimization, larger rotor blade leading edge diameter can effectively reduce the influence of steam attack angle on the flow field when the volume flow rate is small. The smoother suction surface and thinner trailing edge can reduce the end wall loss in the cascade passage, which leads to the reduction of the influence area of secondary flow, the effective restraint of the boundary-layer thickness on the blade surface, the reduction of blade loss, and the improvement of flow efficiency of the governing stage after optimization. The optimized blade not only improves the performance in the peak regulating condition, but also has good performance in the design condition.
KEYWORDS
PAPER SUBMITTED: 2024-06-07
PAPER REVISED: 2024-07-26
PAPER ACCEPTED: 2024-07-29
PUBLISHED ONLINE: 2024-08-31
THERMAL SCIENCE YEAR
2025, VOLUME
29, ISSUE
Issue 2, PAGES [849 - 860]
- Oyama, A., et al., Transonic Axial-Flow Blade Optimization: Evolutionary Algorithms and 3-D Navier-Stokes Solver, Journal of Propulsion and Power, 20 (2012), 4, pp. 612-619
- Danish, S. N., et al., Effect of Tip Clearance and Rotor-Stator Axial Gap on the Efficiency of a Multistage compressor, Applied Thermal Engineering, 99 (2016), Apr., pp. 988-995
- Masters, D. A., et al., Geometric Comparison of Aerofoil Shape Parameterization Methods, 53rd AIAA Journal, 55 (2015), 5, pp. 1575-1589
- Obayashi, S., et al., Multi-Objective Genetic Algorithm Applied to Aerodynamic Design of Cascade Airfoils, IEEE Transactions on Industrial Electronics, 47 (2000), 1, pp. 211-216
- Chao, S. M., et al., Optimization of a Total Internal Reflection Lens By Using A Hybrid Taguchi-Simulated annealing algorithm, Optical Review, 21 (2014), 2, pp. 153-161
- Li, H. L., et al.,. State Variable and Optimization Potential-Based Multi-Objective Optimization Method and Application in Compressor Blade Airfoil Design, Structural and Multidisciplinary Optimization, 66 (2023), 7, pp. 165-173
- Wahid, S. G., Temesgen, T. M., Optimal Geometric Representation of Turbomachinery Cascades Using NURBS, Inverse Problems in Science and Engineering, 11 (2003), 2, pp. 359-373
- Cheng, J., et al., Multi-Objective Optimization of Incidence Features for Cascade, Journal of Aerospace Power, 32 (2017), 12, pp. 3064-3072
- Cheng, Y., et al., Efficient Aerodynamic Optimization of Turbine Blade Profiles: An Integrated Approach with Novel HDSPSO Algorithm, Multidiscipline Modelling in Materials and Structures, 20 (2024), 4, pp. 725-745
- Georgia, N. K., et al., A Software Tool for Parametric Design of Turbomachinery Blades, Advances in Engineering Software, 40 (2009), 1, pp. 41-51
- Wang, W., et al., Optimization Design on Cascade Profile Based on Entropy Generation Theory (in Chinese), Journal of Huazhong University of Science and Technology, 49 (2021), 9, pp. 52-58
- Song, P., et al., Blade Shape Optimization oor Transonic Axial Flow Fan (in Chinese), Journal of Mechanical Science and Technology, 29 (2015), 3, pp. 931-938
- Yu, J., et al., Adjoint Optimization of Multistage Axial Compressor Blades with Static Pressure Constraint at Blade Row Interface, International Journal of Turbo and Jet-Engines, 33 (2016), 2, pp. 105-118
- Yang, J., et al., Design Optimization of a Supersonic through-Flow Fan Rotor Based on the Blade Profiles, International Journal of Turbo and Jet Engines, 40 (2023), 4, pp. 503-517
- Juri, B., et al., Numerical and Experimental Investigation of Axial Gap Variation in High-pressure Steam Turbine Stages, Journal of Engineering for Gas Turbines and Power, 139 (2017), 5, 052603