辅助动力装置回流燃烧室设计与性能研究
发布时间：2019-01-25 20:44
【摘要】：随着科技的发展,航空技术发展的越发娴熟,大飞机的发展越来越重要,发动机作为飞机的动力系统必不可少,因而飞机的辅助动力系统也日益受到人们的重视。辅助动力装置的核心部件是燃烧室,燃烧室的性能直接关系到整个辅助动力系统的性能,本文主要针对辅助动力装置回流燃烧室的设计与性能进行研究分析。本文对带头部整流板回流燃烧室模型进行设计改进,并针对火焰筒头部整流板进行设计改进出分段形式整流板、连续形式整流板和分段连续形式整流板三种模型。利用Fluent软件对燃烧室总体性能进行数值计算分析,并在此方法基础上利用经过试验验证的半经验公式方法对燃烧室进行点火、熄火以及污染物排放的性能研究。本文首先基于非预混燃烧模型对带头部整流板回流燃烧室进行性能研究。针对设计出的不同火焰筒头部整流板的回流燃烧室进行数值计算,通过对比分析燃烧室内流场、温度场、出口温度分布以及燃烧室的总体性能,得出火焰筒头部回流区形成的主要原因是内外环主燃孔斜向对冲和火焰筒头部整流板整流的共同作用,其中外环主燃孔的冲击和整流板的整流占主要作用,内环主燃孔起辅助作用。同时由于火焰筒头部整流板的导向作用,可以使气流周向流动,提高燃烧室周向的联焰能力。燃烧室火焰筒头部整流板的改进对燃烧效率影响不大,但对出口温度分布OTDF改善较为明显。接着针对燃烧室点火、熄火以及污染物排放的性能研究,本文采用经过试验验证的半经验公式与数值计算方法对燃烧室的点火、熄火以及污染物排放的性能研究,最终得出点熄火以及污染物排放的半经验公式可以对燃烧室的设计与性能分析进行预估,为燃烧室的设计与试验提供参考。最后针对带头部旋流器回流燃烧室模型的性能研究,通过不同湍流模型对该燃烧室的性能进行对比分析,最终得出大涡模拟方法计算出的燃烧室内部流场可以更好地反映燃烧室内部的流动情况。大涡模拟燃烧室总压恢复系数为0.9753,燃烧室燃烧效率为0.9926,燃烧室出口温度分布为0.32;雷诺时均方法模拟燃烧室总压恢复系数为0.9727,燃烧室燃烧效率为0.9907,燃烧室出口温度分布为0.37。通过对比分析,大涡模拟方法在计算燃烧室总体性能上要优于雷诺平均方法。同时通过大涡模拟方法针对该燃烧室进行点火、熄火以及污染物排放的性能研究。
[Abstract]:With the development of science and technology, the development of aeronautical technology is more and more skillful, the development of large aircraft is more and more important, the engine is indispensable as the aircraft power system, so the auxiliary power system of aircraft has been paid more and more attention. The core component of the auxiliary power device is the combustion chamber. The performance of the combustion chamber is directly related to the performance of the whole auxiliary power system. In this paper, the design and performance of the auxiliary power unit reflux combustor are studied and analyzed. In this paper, the model of reflux combustor with head rectifier plate is designed and improved, and three models of segmented rectifier plate, continuous rectifier board and segmented continuous rectifier board are designed and improved. The overall performance of the combustor was numerically calculated and analyzed by Fluent software. Based on this method, the performance of ignition, flameout and pollutant emission of the combustor was studied by using the semi-empirical formula method verified by the experiment. In this paper, the performance of reflux combustor with head rectifier plate is studied based on non-premixed combustion model. The flow field, temperature field, outlet temperature distribution and the overall performance of the combustor were compared and analyzed by numerical calculation for the designed reflux combustor with rectifier plate at the head of the different flame tube, and the flow field, temperature field, outlet temperature distribution and the overall performance of the combustor were analyzed. It is concluded that the main reason for the formation of the reflux zone at the head of the flame tube is the oblique hedging of the main combustion hole in the inner and outer ring and the common action of the rectifier plate at the head of the flame tube. The main combustion hole in the inner ring plays an auxiliary role. At the same time, because of the guiding action of the rectifier plate at the head of the flame tube, the flow of air can be circumferential and the flaming ability of the combustion chamber can be improved. The improvement of the head rectifier plate of the combustion chamber flame tube has little effect on the combustion efficiency, but it can obviously improve the outlet temperature distribution of OTDF. Then, aiming at the performance research of ignition, flameout and pollutant emission of combustion chamber, this paper uses the semi-empirical formula and numerical calculation method verified by experiment to study the performance of ignition, flameout and pollutant emission of combustion chamber. Finally, the semi-empirical formula of ignition extinguishment and pollutant emission can be used to predict the design and performance analysis of the combustion chamber, which provides a reference for the design and test of the combustion chamber. Finally, the performance of the reflux combustor with head hydrocyclone is studied, and the performance of the combustor is compared and analyzed by different turbulence models. Finally, it is concluded that the flow field in the combustor calculated by the large eddy simulation method can better reflect the flow situation in the combustor. The total pressure recovery coefficient of the combustor is 0.9753, the combustion efficiency of the combustor is 0.9926, and the temperature distribution at the outlet of the combustor is 0.32. The Reynolds time average method simulates the total pressure recovery coefficient of the combustor is 0.9727, the combustion efficiency of the combustor is 0.9907, and the temperature distribution at the outlet of the combustor is 0.37. By comparison and analysis, the large eddy simulation method is superior to the Reynolds average method in calculating the overall performance of the combustor. At the same time, the characteristics of ignition, flameout and pollutant emission of the combustor were studied by means of large eddy simulation.
【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】：V228
本文编号：2415171
[Abstract]:With the development of science and technology, the development of aeronautical technology is more and more skillful, the development of large aircraft is more and more important, the engine is indispensable as the aircraft power system, so the auxiliary power system of aircraft has been paid more and more attention. The core component of the auxiliary power device is the combustion chamber. The performance of the combustion chamber is directly related to the performance of the whole auxiliary power system. In this paper, the design and performance of the auxiliary power unit reflux combustor are studied and analyzed. In this paper, the model of reflux combustor with head rectifier plate is designed and improved, and three models of segmented rectifier plate, continuous rectifier board and segmented continuous rectifier board are designed and improved. The overall performance of the combustor was numerically calculated and analyzed by Fluent software. Based on this method, the performance of ignition, flameout and pollutant emission of the combustor was studied by using the semi-empirical formula method verified by the experiment. In this paper, the performance of reflux combustor with head rectifier plate is studied based on non-premixed combustion model. The flow field, temperature field, outlet temperature distribution and the overall performance of the combustor were compared and analyzed by numerical calculation for the designed reflux combustor with rectifier plate at the head of the different flame tube, and the flow field, temperature field, outlet temperature distribution and the overall performance of the combustor were analyzed. It is concluded that the main reason for the formation of the reflux zone at the head of the flame tube is the oblique hedging of the main combustion hole in the inner and outer ring and the common action of the rectifier plate at the head of the flame tube. The main combustion hole in the inner ring plays an auxiliary role. At the same time, because of the guiding action of the rectifier plate at the head of the flame tube, the flow of air can be circumferential and the flaming ability of the combustion chamber can be improved. The improvement of the head rectifier plate of the combustion chamber flame tube has little effect on the combustion efficiency, but it can obviously improve the outlet temperature distribution of OTDF. Then, aiming at the performance research of ignition, flameout and pollutant emission of combustion chamber, this paper uses the semi-empirical formula and numerical calculation method verified by experiment to study the performance of ignition, flameout and pollutant emission of combustion chamber. Finally, the semi-empirical formula of ignition extinguishment and pollutant emission can be used to predict the design and performance analysis of the combustion chamber, which provides a reference for the design and test of the combustion chamber. Finally, the performance of the reflux combustor with head hydrocyclone is studied, and the performance of the combustor is compared and analyzed by different turbulence models. Finally, it is concluded that the flow field in the combustor calculated by the large eddy simulation method can better reflect the flow situation in the combustor. The total pressure recovery coefficient of the combustor is 0.9753, the combustion efficiency of the combustor is 0.9926, and the temperature distribution at the outlet of the combustor is 0.32. The Reynolds time average method simulates the total pressure recovery coefficient of the combustor is 0.9727, the combustion efficiency of the combustor is 0.9907, and the temperature distribution at the outlet of the combustor is 0.37. By comparison and analysis, the large eddy simulation method is superior to the Reynolds average method in calculating the overall performance of the combustor. At the same time, the characteristics of ignition, flameout and pollutant emission of the combustor were studied by means of large eddy simulation.
【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】：V228
【参考文献】
相关期刊论文 前2条
1 林志勇;颜应文;李井华;朱嘉伟;陈利强;孔祖开;;辅助动力装置环形回流燃烧室数值研究[J];航空动力学报;2012年08期
2 雷雨冰,赵坚行,周峰轮;环形燃烧室性能计算[J];工程热物理学报;2002年05期
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