Optimization and Evaluation of Cooling Structure of Stage 1 Blade of Heavy-Duty Gas Turbine

doi:10.12096/j.2096-4528.pgt.24101

Abstract

Abstract:

Objectives The localization of core components of heavy-duty gas turbines holds significant importance for technological innovation, industrial upgrading, and even national security. As a typical hot-end component of heavy-duty gas turbines, the performance of the turbine first-stage rotor blade directly determines the efficiency and reliability of the gas turbine. Therefore, the structure of the first-stage turbine blades of a certain heavy-duty gas turbine was optimized. Methods By increasing the number of bamboo nodes in the blade body, the blade cooling hole structure was optimized, and the thermal barrier coating was used to improve the blade coating. The temperature, stress distribution and aerodynamic efficiency of the blades before and after optimization under the service condition of the blade were compared and analyzed by fluid calculation and finite element calculation. Results Heat transfer efficiency inside the blade is enhanced by optimization of turbulent structure. Under the condition of the same inlet pressure of the cooling air, the surface temperature of the optimized blade is reduced by more than 50 ℃. Since the shape of the blade is not changed, there is little influence on the aerodynamic efficiency. Compared with the blades without optimization, the maximum equivalent stress and equivalent total strain of the optimized blade during service are significantly reduced. Conclusions By optimizing the cooling structure and upgrading the protective coatings, the reliability of the blades in high-temperature can be significantly improved. The research results provide a theoretical basis for the localization of gas turbines.

Key words: gas turbine, turbine blade, structure optimization, coating improvement, cooling hole, fluid calculation, finite element calculation

CLC Number:

TK 14

Wenchang YU, Yang DING, Xuyang WANG, Yonggang CHEN, Ke BI, Zhigang LIU, Xingang SHANGGUAN, Daohuo HUANG, Feng XIAO, Guang LI, Guang WANG, Hanzhang KE, Yasong SUN, Xin WANG. Optimization and Evaluation of Cooling Structure of Stage 1 Blade of Heavy-Duty Gas Turbine[J]. Power Generation Technology, 2024, 45(5): 838-846.

Figures/Tables 19

Fig. 1 Turbulence structures of the blades before and after optimization

Fig. 2 Comparison of blade coating before and after optimization

Fig. 3 Computational model of fluid field

Fig. 4 Fluid domain meshing

Fig. 5 Distribution of Y + in computational domain mesh

Tab. 1 Cooling air parameters of Mark II blade

冷却孔编号	流量/(kg/s)	温度/K
1	0.024 60	342
2	0.023 70	344
3	0.023 80	335
4	0.024 70	336
5	0.023 30	330
6	0.022 80	355
7	0.023 80	335
8	0.007 75	350
9	0.005 11	377
10	0.003 34	387

Fig. 6 Dimensionless temperature distribution in middle cross-section

Tab. 2 Boundary conditions of fluid calculation

热燃气		冷却空气		出口相对静压/Pa	动叶转速/(r/min)
单叶片流量/(kg/s)	温度/℃	流量/(kg/s)	温度/℃	出口相对静压/Pa	动叶转速/(r/min)
4	1 140	0.08	346	600 000	3 000

Fig. 7 Temperature distribution of the blade before optimization

Fig. 8 Temperature distribution of the blade after optimization

Fig. 9 Pressure distribution on the blade before optimization

Fig. 10 Pressure distribution on the blade after optimization

Fig. 11 Total pressure distribution of blade surface before and after optimization

Fig. 12 Constraints of static calculations

Fig.13 Mesh in the middle cross-section

Fig. 14 Equivalent stress of the blade before optimization

Fig. 15 Equivalent stress of the blade after optimization

Fig. 16 Equivalent total strain of the blade before optimization

Fig. 17 Equivalent total strain of the blade after optimization

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