Aerodynamic design and flow field analysis of integrated combustion vanes in heavy-duty gas turbines
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摘要:
提出一种整体造型、局部细修的设计方法，针对某重型燃气轮机开展了燃烧室与第一级涡轮导向器一体化气动设计研究，并采用三维流场数值模拟，分析了不同单元体数量及前缘截断长度下的气动性能。结果显示，前缘结构对出口气流参数无显著影响，截断长度增加可显著降低总压损失系数至5%以下，证明了设计方法的有效性。流场分析揭示，燃喷联合体构型流道呈现轴向收缩、周向扭转、径向斜流的复合特征，叶片与端壁协同主导气流加速与转向。与传统导向器相比，其不存在前缘冲击滞止流动及马蹄涡结构，尾迹涡主导的周期性涡对演化成为主要二次流特征。
Abstract:A design method of combining overall configuration with local refinement for the integrated aerodynamic design of the combustor and the first-stage turbine guide vanes in a heavy-duty gas turbine was proposed. Three-dimensional numerical simulations were conducted to analyze the aerodynamic performance under different numbers of unit bodies and leading-edge truncation lengths. The results showed that the leading-edge structure had no significant effect on the outlet flow parameters, while increasing the truncation length effectively reduced the total pressure loss coefficient to below 5%, thus validating the effectiveness of the proposed method. Flow field analysis revealed that the integrated combustion vanes exhibited compound characteristics of axial contraction, circumferential swirl, and radial skewed flow, with blades and endwalls jointly governing flow acceleration and turning. Compared with conventional guide vanes, the integrated design eliminated the mechanisms of leading-edge impingement stagnation and horseshoe vortex formation, while wake-vortex-dominated periodic vortex pairs became the primary secondary flow structures.
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Key words:
- combustor /
- turbine /
- integrated design /
- aerodynamic performance /
- vortex structure
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图 1 燃喷联合体构型气动设计结果
Figure 1. Aerodynamic design results of the integrated combustion vanes
图 6 叶片表面等熵马赫数分布（Case 1，10%叶高）
Figure 6. Isentropic Mach number distribution on blade surface （Case 1, 10% span）
图 7 叶片表面等熵马赫数分布（Case 1，50%叶高）
Figure 7. Isentropic Mach Number distribution on blade surface （Case 1, 50% span）
图 8 叶片表面等熵马赫数分布（Case 1，90%叶高）
Figure 8. Isentropic Mach Number distribution on blade surface （Case 1, 90% span）
图 13 吸力面（竖面）和下端面（横面）近壁处流体速度的发展
Figure 13. Development of near-wall fluid velocity on suction surface （vertical plane） and lower endwall （horizontal plane）
图 15 尾迹区湍动能瞬态变化
Figure 15. Transient variation of turbulent kinetic energy in the wake region
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