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高压涡轮动叶内部冷却结构的改进设计
引用本文:郭文,吉洪湖,蔡毅,江和甫,刘玉芳.高压涡轮动叶内部冷却结构的改进设计[J].南京航空航天大学学报,2006,38(4):408-412.
作者姓名:郭文  吉洪湖  蔡毅  江和甫  刘玉芳
作者单位:1. 南京航空航天大学能源与动力学院,南京,210016
2. 中国燃气涡轮研究院,成都,610500
摘    要:对某型高压涡轮动叶的内部冷却结构进行了详细的分析,提出了具体的改进方案,并利用有限元方法对改进前后的方案进行了叶片温度分布计算分析。结果表明,在相同冷却空气流量比的条件下,叶片尖截面表面最高温度降低了33°C,截面温差减小了131°C,改进效果明显。同时,改进后的冷却结构有效降低了叶片进口压力,提高了预旋喷嘴压比,减轻了高压涡轮转子的重量,达到了增加发动机推重比,减少冷却空气泄漏量,改善发动机性能的目的。

关 键 词:涡轮  转子叶片  冷却结构  改进设计
文章编号:1005-2615(2006)04-0408-05
收稿时间:2005-05-13
修稿时间:2006-01-23

Optimized Design Approach for Internal Cooling Structure in Turbine Blades
Guo Wen,Ji Honghu,Cai Yi,Jiang Hefu,Liu Yufang.Optimized Design Approach for Internal Cooling Structure in Turbine Blades[J].Journal of Nanjing University of Aeronautics & Astronautics,2006,38(4):408-412.
Authors:Guo Wen  Ji Honghu  Cai Yi  Jiang Hefu  Liu Yufang
Abstract:The high pressure(HP) turbine blade is an important part in the aeroengine and withstands high temperature and high centrifugal load.To ensure the blade safety and reliability,and to improve the engine performance and the thrust-weight ratio,many measures are considered,such as using high efficiency cooling structure to reduce the temperature of the blade,and reasonably distributing cooling air flow to decrease the section temperature difference and thermal stresses,etc.This paper analyzes a internal cooling structure in a high pressure turbine blade,and presents the optimized design.Then an investigation about the flow and the heat thansfer in the internal cooling passages of the turbin blade is completed.Results show that the optimized design improves the temperature distribution of the blade and reduces the temperature difference in the blade remarkably,and the weight of the high pressure turbine rotor is reduced by using a simpled seal structure.
Keywords:turbine  blade  cooling structure  optimized design
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