【摘要】 重型燃气轮机中减少一级静叶的冷气量和降低燃烧室压损，对于提高燃机整体性能具有重要意义。本文以某F级重型燃气轮机第一级透平静叶为基础模型，通过减小燃烧室和静叶前缘轴向距离设计了一体化叶片结构，所得叶片等熵马赫数数值计算与实验结果较为吻合。计算结果表明：相比于分离式叶片结构，燃烧室和透平一体化设计能够降低流体域滞止压力损失系数。同时，当改变进口边界条件时，一体化设计的滞止压力损失系数依然低于分离式叶片。因此，燃烧室和透平一体化设计结构对于提高燃气轮机整体性能具有较高的潜力。更多还原

【Abstract】 It is of great significance to improve the overall performance of the gas turbine by reducing the cooling air of the first vane and pressure loss of the combustor in the heavy-duty gas turbine. In this paper, taking the first stage turbine vane of F-class heavy-duty gas turbine as the base model, an integrated design of combustor and vane is designed by reducing the axial distance between the combustor and the leading edge of the vane. The numerical calculation isentropic Mach number of the integrated design is in good agreement with the experimental results. The calculation results show that compared with the separated vane structure, the integrated design can reduce the stagnation pressure loss coefficient of the fluid domain. At the same time, when the inlet boundary conditions changed, the stagnation pressure loss coefficient of the integrated design is still lower than that of the separated vane structure. Therefore, the integrated design has high potential for improving the overall performance of gas turbine.更多还原