用于超声速飞行器的冲压涡轮发电系统设计研究

发布时间：2018-02-14 03:22

本文关键词： 冲压涡轮涡轮发电总体设计微型涡轮数值模拟试验研究子午流道　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】：近年来超声速飞行器在国防军事领域的地位逐渐升高,对其进行的研究也越来越受到重视。冲压涡轮发电系统由于重量轻、结构简单、综合效能高等优点,成为为超声速飞行器机载设备提供电功率的最佳选择。本文采用数值模拟与试验手段相结合的方法进行了系统设计及核心部件优化等研究。主要内容如下:1、本文首先完成系统的总体方案与总体结构设计。然后详细阐述主要部件的设计过程,包括发电机的磁路结构、冷却润滑装置和主要气动部件,其中在气动部件设计中要考虑各部件之间的匹配。设计的冷却润滑装置高效地解决了发电机的散热以及轴承的润滑问题;设计的扇形节流装置结构紧凑、调节精度高、响应时间短、工作安全可靠。2、采用CFD方法对各气动部件进行数值模拟计算,分析部件的流场情况,得到各部件的工作特性。然后将涡轮与蜗壳进行CFD联算,研究两者的匹配特性;进行涡轮与扇形节流装置的数值模拟联算,为控制策略的选择提供参考。此外还针对扇形节流装置进行特定试验,并与数值模拟结果相对比,验证了数值模拟的准确性。3、对冲压涡轮发电系统进行冷态整机试验。搭建专门的试验台架,制定详备的试验和测量方案,检测系统的振动情况。试验得到系统在低负载状态下的工作特性,验证了部件的结构强度。4、对涡轮进行优化研究。在涡轮出口面积不变的情况下,分析了涡轮转子子午面上下端壁的扩张角组合变化对涡轮性能的影响,结果表明,不同的上下端壁扩张角对涡轮导向器进出口的静压分布、导向器喉道处的Ma分布、转子的进气角以及设计点涡轮出口的激波强度都有一定的影响,且存在一个最佳的上下端壁扩张角的组合使涡轮在设计点及非设计点的性能得到提高,在设计点,最优组合比最差组合等熵效率提高0.7%,功率提高0.465kW。
[Abstract]:In recent years, the status of supersonic vehicle in the field of national defense and military has gradually increased, and the research on it has been paid more and more attention. The ramjet turbine power generation system has the advantages of light weight, simple structure, high comprehensive efficiency and so on. It has become the best choice to provide electric power for supersonic aircraft airborne equipment. The system design and core components optimization are studied by the method of numerical simulation and test. The main contents are as follows: 1, this paper. First, the overall scheme and structure design of the system are completed. Then, the design process of the main components is described in detail. Including generator magnetic circuit structure, cooling lubrication device and main pneumatic components, In the design of pneumatic components, the matching of each component should be considered. The cooling and lubricating device designed can efficiently solve the problems of heat dissipation of generator and lubrication of bearings, and the designed fan throttling device has compact structure and high adjusting precision. The response time is short, the work is safe and reliable. 2. The CFD method is used to simulate and calculate the aerodynamic components, the flow field of the components is analyzed, and the working characteristics of the components are obtained. Then the turbine and the volute are combined with CFD. The matching characteristics of the two are studied, and the numerical simulation of turbine and sector throttle is carried out to provide a reference for the selection of control strategy. In addition, a specific experiment is carried out for the sector throttle, and the results are compared with the results of numerical simulation. The veracity of numerical simulation is verified. 3. The cold test of punching turbine power generation system is carried out. A special test bench is built, and a detailed test and measurement scheme is established. The vibration of the system is detected. The working characteristics of the system under low load are obtained, and the structural strength of the components is verified. 4. The optimization study of the turbine is carried out. When the turbine outlet area is constant, The influence of the expansion angle combination of the upper and lower end wall of the turbine rotor on the turbine performance is analyzed. The results show that the static pressure distribution at the inlet and outlet of the turbine guide and the Ma distribution at the throat of the turbine guide are affected by the expansion angles of the upper and lower end walls of the turbine rotor. The inlet angle of the rotor and the shock intensity at the outlet of the design point have a certain influence, and the performance of the turbine at the design point and non-design point can be improved by the combination of an optimal expansion angle of the upper and lower end wall. Compared with the worst combination, the optimal combination increases the Isentropic efficiency by 0.7 and the power by 0.465kW.
【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】：V242

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