涡轮叶片综合冷却效果模拟试验方法研究

发布时间：2018-01-02 17:46

本文关键词：涡轮叶片综合冷却效果模拟试验方法研究　出处：《南京航空航天大学》2016年硕士论文　论文类型：学位论文

【摘要】：涡轮叶片是航空发动机的重要部件,它的冷却性能直接影响发动机的正常工作。综合冷却效果是涡轮叶片冷却性能的核心评价指标,对涡轮叶片进行综合冷却效果试验是必不可少的。目前综合冷效果试验包括高温高压试验和中温中压模拟试验,后者具有试验周期短,费用低等优势,被广泛应用,而正确、合理的试验方法是进行模拟试验的关键。因此,本文针对涡轮叶片综合冷却效果模拟试验方法开展了理论、数值模拟和试验研究。首先,建立了涡轮叶片流动换热理论模型,然后在相似理论指导下,对控制方程和边界条件无量纲化,得到了涡轮叶片流动与换热问题的主要影响因素和准则数,推导得出涡轮叶片综合冷却效果准则参数的一般表达式,进而提出了涡轮叶片综合冷却效果模拟试验方法。然后,数值研究了各个无量纲准则数对综合冷效的影响规律,研究结果表明,在本文研究参数范围内,叶片中截面平均综合冷效对主流雷诺数变化不敏感,随欧拉数增加而小幅下降,随着流量比的增加而上升,随着温比的增加而下降,随着毕渥数的增加而下降。另外,对比分析了不同模化状态下的叶片中截面平均综合冷效,结果表明,各模化状态下叶片中截面平均综合冷效基本一致,最大差距在2.5%左右,证明本文提出的涡轮叶片综合冷却效果模拟试验方法可靠。最后,对叶片综合冷效开展试验研究,结果表明试验与数值计算结果在变化趋势上保持一致,说明数值计算得出的规律是可靠的。此外,对比了相对较高和相对较低状态下的叶片综合冷却效果,结果表明,两个状态下的综合冷效基本一致,进一步验证了本文提出的涡轮叶片综合冷却效果模拟试验方法是可靠的。
[Abstract]:The turbine blade is an important component of aero engine cooling performance, which directly affect the normal operation of the engine. The cooling effect is the core of the performance evaluation index of turbine blade cooling test, comprehensive cooling effect is essential for turbine blades. The comprehensive effect of cold test of high temperature and high pressure test and temperature and pressure in the simulation test, the latter has the test cycle is short, low cost advantages, has been widely used, and the correct, reasonable test method is the key to carry out a simulation test. Therefore, the cooling effect of turbine blade comprehensive simulation test method was carried out in theory, numerical simulation and experimental research. First of all, the establishment of the turbine blade flow and heat transfer model, and then the similarity theory under the guidance of the governing equations and boundary conditions dimensionless, the main effect of turbine blade flow and heat transfer problems of the factors and criteria are The general expression, criterion of turbine blade cooling effect parameters are integrated, and then put forward the effect of comprehensive simulation test method for cooling turbine blade. Then, a numerical study of the impact of various rules of the dimensionless number of cooling effect, the results of the study show that, in the research range of parameters, leaf section average comprehensive cooling effect of the mainstream the Reynolds number is not sensitive to changes, but slightly decreased with the increase of the Euler number, with increase of flow ratio increases, decreases with the temperature increasing, and decreased with increase of the Biot number. In addition, comparative analysis of the different modeling section of the blade under the condition of average comprehensive cooling efficiency, results show that the model of state under the leaves of section average comprehensive cooling effect is basically the same, the biggest gap between the 2.5%, that the turbine blade cooling effect of the proposed comprehensive simulation test method is reliable. Finally, the integrated cooling blade Carry out experimental research of effect, results show that the results of tests and numerical calculation are consistent in the trend, that the conclusion of numerical calculation is reliable. In addition, compared to the relatively high and low state of the blade cooling effect, the results show that the two state of the integrated cooling effect is consistent, further verified turbine blade cooling effect of the proposed comprehensive simulation test method is reliable.

【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V231.1

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