基于大型结冰风洞的航空发动机结冰与防冰试验技术

航空发动机结冰和防冰过程复杂，数值计算无法对其进行准确模拟，因此试验研究是发动机研究过程中必不可少的手段。我国首座大型结冰风洞已具备开展飞机翼段结冰试验的能力，有必要进一步发展航空发动机结冰与防冰试验技术，以满足下一步我国航空发动机型号设计与适航取证的需求。依托3 m×2 m大型结冰风洞，发展了进气模拟技术和热气供气技术，提出了一套结冰风洞试验流程及方法，并针对某型航空发动机进气部件开展了结冰风洞验证试验。结果表明:试验可真实模拟发动机内外流耦合和压气机引气防冰状态，且提出的结冰风洞试验流程及方法合理可行，实现了试验动态过程监测及进气道内流场压力测量，为下一步我国航空发动机结冰防护系统设计与安全适航符合性验证提供了技术支撑。

Icing and anti-icing test technology of aero-engine based on large-scale icing wind tunnel

The icing and anti-icing process of the aero-engine is complex, which can not be simulated accurately by numerical calculation. As a result, experiment is an indispensable means for the engine research. The first large-scale icing wind tunnel of our country has been built, which has the capacity to carry out icing tests on the aircraft wing section. But further development of the icing and anti-icing test technology is needed to meet the requirement of the next stage model designing and airworthiness certification for aero-engines in our country. Supported by the 3 m×2 m large-scale icing wind tunnel, the inlet gas simulation technology and hot-air supply technology were developed first, then a set of test procedures and methods was put forward, and finally the icing wind tunnel test for the inlet part of an aero-engine was carried out. The results indicate that the system can simulate the internal and external flow coupling of the engine and the anti-icing state of the compressor. The procedures and method of icing wind tunnel test are reasonable and feasible, and the test dynamic process and the flow field pressure in the inlet are successfully measured. It provides a technical support for the design of ice protection system and the verification of airworthiness on aero-engines.