CAJ | 학술논문

燃气轮机燃烧室出口燃气温度场分布严重不均匀，其中燃气流的高温核心即热斑会加剧燃气透平内部非定常流动和传热的复杂性，引起叶栅的局部过热甚至烧蚀，从而降低透平的可靠性和寿命。研究并揭示热斑迁移机制对于透平叶栅高效冷却技术及非定常气动优化设计方法的发展至关重要。文中综述了燃气透平进口热斑迁移及其影响机制的研究现状及进展，着重介绍了燃烧室特性参数、叶型结构和冷气对热斑迁移的影响规律。有关热斑现象的研究虽然取得一定进展，但尚需要更深入的试验和数值研究，文中指出：目前试验和数值研究中广泛采用的圆形热斑与实际情况差异较大，需要在燃烧室真实出口温度场下实现透平非定常流场和传热的精确测量；关于燃烧室特性参数对热斑迁移影响的研究未考虑湍流强度和旋流等流场特征的影响且缺乏试验数据；叶型结构对热斑迁移影响的研究才刚刚开始，需要对热斑与叶排间的“时序效应”及其对叶栅热负荷和透平整体性能的影响机制开展深入的试验研究；最后，还需要对冷却气流与热斑干涉作用及其引起的透平非定常气热性能的变化进行试验和数值研究，从而为透平的高效冷却和气动传热优化设计奠定理论基础。
연기륜궤연소실출구연기온도장분포엄중불균균，기중연기류적고온핵심즉열반회가극연기투평내부비정상류동화전열적복잡성，인기협책적국부과열심지소식，종이강저투평적가고성화수명。연구병게시열반천이궤제대우투평협책고효냉각기술급비정상기동우화설계방법적발전지관중요。문중종술료연기투평진구열반천이급기영향궤제적연구현상급진전，착중개소료연소실특성삼수、협형결구화랭기대열반천이적영향규률。유관열반현상적연구수연취득일정진전，단상수요경심입적시험화수치연구，문중지출：목전시험화수치연구중엄범채용적원형열반여실제정황차이교대，수요재연소실진실출구온도장하실현투평비정상류장화전열적정학측량；관우연소실특성삼수대열반천이영향적연구미고필단류강도화선류등류장특정적영향차결핍시험수거；협형결구대열반천이영향적연구재강강개시，수요대열반여협배간적“시서효응”급기대협책열부하화투평정체성능적영향궤제개전심입적시험연구；최후，환수요대냉각기류여열반간섭작용급기인기적투평비정상기열성능적변화진행시험화수치연구，종이위투평적고효냉각화기동전열우화설계전정이론기출。
The temperature profiles of gas flow at the exit of gas turbine combustor are seriously non-uniform, and the high temperature regions at combustor exit are known as hot streaks. The migration of hot streak intensifies the complexity of the unsteady flow and heat transfer in turbine stage and leads to the excessive heating and even erosion of the blade airfoil, thus reducing the turbine operation reliability and life. The understanding of hot streak migration mechanism is important both to the design of airfoil cooling scheme and the development of turbine aerodynamic design optimization method. Studies on hot streak migration in turbine stage was reviewed, which focused on the effects of combustor characteristic parameters, airfoil geometry and cooling flow on the hot streak migration mechanisms. Although research on the effects of hot streak has made some progress, more detailed and systematic numerical and experimental investigations on following topics are urgently needed. The circle hot streak applied in most of the recent studies cannot reflect the combustor exit real temperature distributions well, and experimental measurements should be conducted to reveal the effects of combustor exit real temperature profiles on turbine unsteady aero-thermal performance. The main flow turbulence intensity and inlet swirl are considered by few researchers when investigating the effects of combustor characteristics on hot streak migration, and the experimental data concerning them are still deficiency. Studies on the airfoil geometry effects are just beginning, and the effects of the hot streak and second stage stator clocking positions on the turbine heat load and overall performance should be deeply understood. Also, experimental and numerical studies should be performed to reveal the unsteady interaction mechanisms between hot streak and air coolant, and the effects of the interaction on the turbine aero-thermal performance, thus providing theoretical foundation for the design of cooling scheme and aero-thermal optimization of the turbine blade.