超临界机组末级叶片典型截面的叶型设计

推进技术 ›› 2009, Vol. 30 ›› Issue (3): 314-317.

超临界机组末级叶片典型截面的叶型设计

杨其国,韩万金,黄家骅,宋勇

哈尔滨工业大学能源科学与工程学院;哈尔滨汽轮机有限责任公司;哈尔滨工业大学能源科学与工程学院;二炮驻31所军代表室;二炮驻31所军代表室

发布日期:2021-08-15

Optimization design of typical blade profile of long blade in ultra-supercritical steam turbine

School of Energy Science and Engineering,Harbin Inst.of Technology,Harbin 150001,China;Harbin Turbine Company Limited,Harbin 150001,China;School of Energy Science and Engineering,Harbin Inst.of Technology,Harbin 150001,China;The Second Artillery Representative Office in the 31st Research Inst.,Beijing 100074,China;The Second Artillery Representative Office in the 31st Research Inst.,Beijing 100074,China

Published:2021-08-15

摘要/Abstract

摘要： 针对超临界机组末级长叶片的设计特点,采用遗传算法和人工神经网络,提出对长叶片典型截面叶型进行分区优化设计思想,并对原型与改型进行了多工况点的数值计算,结果表明,将叶型吸力侧后半段由直线型改为内凹型,能够显著降低超声速叶型在超声速工况范围内的叶型损失。对叶型前缘以及压力侧的局部优化设计能够改善超声速叶型在临界马赫数工况下的气动性能。优化设计最大程度地减小了样本空间,提高了优化效率。

关键词: 超声速流;叶片;气动特性;优化设计

Abstract: Based on genetic algorithm and neutral network,a multi-segment optimization design method was proposed for the typical blade profile of an ultra-supercritical steam turbine.Optimization under multiple operating conditions was performed for the original and optimized blade profiles.The result showed that the concaving design for the suction side of blade profile reduced the energy loss under high Mach number conditions.Synthetically with the subsonic design technique for the blade leading edge and pressure side,the aerodynamic character of the blade profile was increased under conditions from critical to high Mach number.The optimization method decreased sample number and improved optimization effectiveness.

Key words: Supersonic flow;Blade;Aerodynamic characteristic;Optimization design

杨其国,韩万金,黄家骅,宋勇. 超临界机组末级叶片典型截面的叶型设计[J]. 推进技术, 2009, 30(3): 314-317.