发动机复合材料导向叶片防冰性能研究
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摘要
飞机在负温云层中飞行时，云层中的过冷水滴撞击到其迎风表面后会冻结而发生结冰现象。飞机结冰会破坏飞机迎风面的气动外形和影响外置传感器的正常工作，是导致飞行事故的主要原因之一。为提高飞机飞行的安全性，需要采取防护措施以应对飞机结冰，因此飞机的结冰机理和防/除冰方法得到了广泛研究。复合材料具有比强度高、重量轻等特点，在现代飞机上得到了广泛应用，由于复合材料和金属材料的物性有较大差异，因此对复合材料部件的防/除冰性能进行研究势在必行。本文采用数值模拟和冰风洞试验的方法对某型复合材料发动机导向叶片的防冰性能进行了研究。
本文工作主要有以下几个方面：
1）概述了飞机结冰的原因、危害和防护方法，介绍了飞机结冰、防/除冰研究的方法和现状，分析了复合材料在飞机上的应用及对复合材料部件进行防/除冰性能研究的必要性。2）采用蒸发循环制冷机组和冷却涡轮组联合制冷获得冷却空气，由气/液二流体喷嘴获得小尺寸雾化水滴，建立了研究用小型直流冰风洞系统；讨论了冰风洞模拟的结冰气象条件中各参数的测量方法，结合数值模拟对冰风洞的水滴撞击和结冰进行了运行调试。3）设计制作了复合材料导向叶片的电加热防冰结构，在小型冰风洞中进行了单区加热状态下的防冰试验，根据试验结果分析了不同来流风速、结冰气象条件、防冰方式对电加热防冰结构的防冰性能影响；在相同来流速度和结冰气象条件下，对单区加热和双区加热两种加热方式进行了防冰试验，分析了对复合材料而言两种电加热方式的优缺点；数值模拟了冰风洞试验工况下导向叶片的防冰性能，将计算结果与试验结果进行了对比分析，验证了数值模拟方法的可行性，为设计真实发动机工况下导向叶片的电热防冰结构打下了基础。4）采用数值模拟方法对原发动机导向叶片热气防冰结构内流动与换热以及外部水滴撞击特性进行了分析；在此基础上对导向叶片热气防冰结构进行了改进，采用前缘冲击射流结合微小防冰通道的换热结构提高结冰区的防冰性能，改变防冰排气孔形式以增强排气形成的气膜对溢流水膜和外部过冷水滴的吹袭；对改进前后的热气防冰结构的防冰性能进行了对比分析。5）设计制作了改进后的复合材料导向叶片热气防冰结构，在冰风洞中对其防冰性能和排气气膜对溢流水膜的吹袭效果进行了测试，分析了不同供气参数对热气防冰系统的影响。6）总结了本文的研究工作，对后续的研究工作提出了展望。
When aircraft fly under icing condition, the impingement of super-cooled droplets in the cloudson the exposed surfaces of aircraft may cause ice accretion. Accreted ice on the aircraft has severelyadverse effects on flight safety, like changing the aerodynamic shape of aircraft and causing errors tothe sensors, and has been one of the main reasons of aircraft disasters. Anti-icing or de-icing systemmust be equipped to ensure flying safety. Efforts have been made on the research of theory of aircrafticing and methods of de-icing and anti-icing.
Composite has been widely used on modern aircraft. Though many differences betweencomposite and metal meterails, there lacks research of composite assembly anti-icing and de-icingsystem where potential damage exists. To evaluate composite engine inlet vane anti-icing system,icing wind tunnel experiments and numerical simulation were carried out in this paper.
The followings are the the main works in this thesis:1) The cause, hazards of aircraft icing andmethods of protection and the application of composite on aircraft were introduced, the ways ofinvestigation and the state-of-art of icing and anti-,de-cing, and the necessity of research of anti-icingof composite assembly were summarized.2) A small open-circuit icing wind tunnel based on highpressure air source was built, in which the air source is the air compressor sets and the refrigerantsystem is a combination of Freon refrigerator and air turbines. The spray systems were consisted ofair/fluid nozzles. The measurement of the icing condition parameters of the icing wind tunnel wasdiscussed. The running tests of impingment and icing were carried out and the results were vadidatedby numecial simulation.3) Electro-thermal anti-icing structure on a composite engine inlet vane wasdesigned. Anti-icing experiments of the structure were run in the small open-circuit icing wind tunnel.Single zone heating tests were carried out to evaluate the influence of flying and meteorologicconditions and different anti-icing modes. Two-zones heating tests were carried out and comparedwith single zones heating tests to evaluate the influence of heating methods to the temperaturedistribution of vane. Impingement characters of engine inlet vane under small icing wind tunnelcondition were calculated and the influence of flying and meteorologic condition was analized; theanti-icing thermal load under test conditions was calculated. Electro-thermal anti-icing of compositeengine inlet vane under tests conditions was numerical simulated. The results were validated bycompare with the experiment results and indicate the capability of the design of electro-thermalanti-icing system under real engine condition.4) A new hot-air anti-icing structure of composite engine inlet vane was developed after the analysis of original system by numerical simulation of itsinner flow and heat transfer and super-cooled droplets impingement microchannels and jets were usedto enhance the heat transfer characteristics of leading edge.A narrow gap was opened and assigned onthe vane surface at the rear end of the anti-icing tunnels, and the exhaust hot-air was released from thegap to form an air film on the outside surface, which was supposed to prevent the droplets fromimpinging to the surface and sweep the droplets and running back water away. The thermodynamicanalysis of the original and newly developed anti-icing structure was presented to compare the effectsto heat transfer and droplet impingment.5) Experiments of the developed hot-air anti-icing structurewere run in the icing wind tunnel to evaluate the effects of microchannels and jets to anti-icing, andair film to sweep the running back water.6) The work in this theis was summarized and some newideas were presented
本文工作主要有以下几个方面：
1）概述了飞机结冰的原因、危害和防护方法，介绍了飞机结冰、防/除冰研究的方法和现状，分析了复合材料在飞机上的应用及对复合材料部件进行防/除冰性能研究的必要性。2）采用蒸发循环制冷机组和冷却涡轮组联合制冷获得冷却空气，由气/液二流体喷嘴获得小尺寸雾化水滴，建立了研究用小型直流冰风洞系统；讨论了冰风洞模拟的结冰气象条件中各参数的测量方法，结合数值模拟对冰风洞的水滴撞击和结冰进行了运行调试。3）设计制作了复合材料导向叶片的电加热防冰结构，在小型冰风洞中进行了单区加热状态下的防冰试验，根据试验结果分析了不同来流风速、结冰气象条件、防冰方式对电加热防冰结构的防冰性能影响；在相同来流速度和结冰气象条件下，对单区加热和双区加热两种加热方式进行了防冰试验，分析了对复合材料而言两种电加热方式的优缺点；数值模拟了冰风洞试验工况下导向叶片的防冰性能，将计算结果与试验结果进行了对比分析，验证了数值模拟方法的可行性，为设计真实发动机工况下导向叶片的电热防冰结构打下了基础。4）采用数值模拟方法对原发动机导向叶片热气防冰结构内流动与换热以及外部水滴撞击特性进行了分析；在此基础上对导向叶片热气防冰结构进行了改进，采用前缘冲击射流结合微小防冰通道的换热结构提高结冰区的防冰性能，改变防冰排气孔形式以增强排气形成的气膜对溢流水膜和外部过冷水滴的吹袭；对改进前后的热气防冰结构的防冰性能进行了对比分析。5）设计制作了改进后的复合材料导向叶片热气防冰结构，在冰风洞中对其防冰性能和排气气膜对溢流水膜的吹袭效果进行了测试，分析了不同供气参数对热气防冰系统的影响。6）总结了本文的研究工作，对后续的研究工作提出了展望。
When aircraft fly under icing condition, the impingement of super-cooled droplets in the cloudson the exposed surfaces of aircraft may cause ice accretion. Accreted ice on the aircraft has severelyadverse effects on flight safety, like changing the aerodynamic shape of aircraft and causing errors tothe sensors, and has been one of the main reasons of aircraft disasters. Anti-icing or de-icing systemmust be equipped to ensure flying safety. Efforts have been made on the research of theory of aircrafticing and methods of de-icing and anti-icing.
Composite has been widely used on modern aircraft. Though many differences betweencomposite and metal meterails, there lacks research of composite assembly anti-icing and de-icingsystem where potential damage exists. To evaluate composite engine inlet vane anti-icing system,icing wind tunnel experiments and numerical simulation were carried out in this paper.
The followings are the the main works in this thesis:1) The cause, hazards of aircraft icing andmethods of protection and the application of composite on aircraft were introduced, the ways ofinvestigation and the state-of-art of icing and anti-,de-cing, and the necessity of research of anti-icingof composite assembly were summarized.2) A small open-circuit icing wind tunnel based on highpressure air source was built, in which the air source is the air compressor sets and the refrigerantsystem is a combination of Freon refrigerator and air turbines. The spray systems were consisted ofair/fluid nozzles. The measurement of the icing condition parameters of the icing wind tunnel wasdiscussed. The running tests of impingment and icing were carried out and the results were vadidatedby numecial simulation.3) Electro-thermal anti-icing structure on a composite engine inlet vane wasdesigned. Anti-icing experiments of the structure were run in the small open-circuit icing wind tunnel.Single zone heating tests were carried out to evaluate the influence of flying and meteorologicconditions and different anti-icing modes. Two-zones heating tests were carried out and comparedwith single zones heating tests to evaluate the influence of heating methods to the temperaturedistribution of vane. Impingement characters of engine inlet vane under small icing wind tunnelcondition were calculated and the influence of flying and meteorologic condition was analized; theanti-icing thermal load under test conditions was calculated. Electro-thermal anti-icing of compositeengine inlet vane under tests conditions was numerical simulated. The results were validated bycompare with the experiment results and indicate the capability of the design of electro-thermalanti-icing system under real engine condition.4) A new hot-air anti-icing structure of composite engine inlet vane was developed after the analysis of original system by numerical simulation of itsinner flow and heat transfer and super-cooled droplets impingement microchannels and jets were usedto enhance the heat transfer characteristics of leading edge.A narrow gap was opened and assigned onthe vane surface at the rear end of the anti-icing tunnels, and the exhaust hot-air was released from thegap to form an air film on the outside surface, which was supposed to prevent the droplets fromimpinging to the surface and sweep the droplets and running back water away. The thermodynamicanalysis of the original and newly developed anti-icing structure was presented to compare the effectsto heat transfer and droplet impingment.5) Experiments of the developed hot-air anti-icing structurewere run in the icing wind tunnel to evaluate the effects of microchannels and jets to anti-icing, andair film to sweep the running back water.6) The work in this theis was summarized and some newideas were presented
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