热斑在船用燃气轮机高低压涡轮中迁移路径分析  

Migration path of a hot streak in high-pressure and lowpressure turbines of a marine gas turbine

作　　者：牛夕莹 郑群[1] 林枫 李国强 高春祥 高杰[1] 李翔宇 NIU Xiying;ZHENG Qun;LIN Feng;LI Guoqiang;GAO Chunxiang;GAO Jie;LI Xiangyu(College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China;No.703 Research Institute of CSSC,Harbin 150078,China;National Engineering Laboratory for Ship and Marine Engineering Power System-Marine Engineering Gas Turbine Laboratory,Harbin 150078,China)

机构地区：[1]哈尔滨工程大学动力与能源学院,黑龙江哈尔滨150001 [2]中国船舶集团有限公司第七〇三研究所,黑龙江哈尔滨150078 [3]船舶与海洋工程动力系统国家工程实验室-海洋工程燃气轮机实验室,黑龙江哈尔滨150078

出　　处：《推进技术》2025年第3期80-90,共11页Journal of Propulsion Technology

基　　金：国家自然科学基金“叶企孙”科学基金(U2241251)。

摘　　要：为了探索船用燃气轮机燃烧室出口热斑在涡轮叶栅内的迁移路径和规律,并为叶片冷却设计、热防护和温度测量提供参考,本研究分析了某船用燃气轮机高、低压涡轮中热斑的迁移路径,并考虑了冷却空气的影响,揭示了高低压涡轮导叶和动叶通道内热斑的演变过程。结果表明,燃烧室出口的热斑在通过高低压涡轮导叶和动叶通道时逐渐被“切割”,其强度也随之减弱。虽然热斑核心的径向位置基本保持在35%叶高处不变,但其周向沿旋转方向的偏移逐渐增加,在通过高、低压涡轮后,偏移角度约为37°。高、低压涡轮动叶进口最大温差分别达到200℃,150℃,叶片设计时应留有一定的温度裕度。本文的结果不仅为确定燃气发生器涡轮出口处总温热电偶的周向和径向位置提供了依据,也为监测燃烧室的工作情况、评估燃气轮机的总体性能和涡轮叶片冷却设计提供了参考。To explore the migration paths and patterns of hot streaks at the exit of a marine gas turbine com⁃bustion chamber within turbine cascades,and to provide references for blade cooling design,thermal protection,and temperature measurement,this study analyzes the migration path of hot streaks in both the high-pressure and low-pressure turbines of a marine gas turbine,taking into account the effects of cooling air.The evolution of hot streaks within the passages of both the guide vanes and rotor blades for both the high-pressure and low-pressure turbines was determined and revealed.The analysis revealed that hot streaks exiting the combustion chamber are gradually"cut"and their intensity weakens as they traverse the passages of both the guide vanes and rotor blades in the high-pressure and low-pressure turbines.Notably,while the radial position of the hot streaks’core,at ap⁃proximately 35%of the blade height,remains essentially unchanged,they undergo a gradual lateral shift in the direction of rotation,with an estimated deflection angle of 37°after passing through both turbines.The maximum inlet temperature difference for high-pressure and low-pressure turbine rotor blades reached 200℃and 150℃,respectively,indicating the necessity for blades to be designed with an adequate temperature margin.The find⁃ings not only establish a basis for the circumferential and radial positioning of total temperature thermocouples at the exit of the gas generator turbine but also aid in monitoring the combustion chamber’s operating conditions,as⁃sessing the overall performance of gas turbine engines,and guiding turbine blade cooling design.

关 键 词：船用燃气轮机 高低压涡轮 热斑 迁移路径 三维非定常 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]