- Dissertation
- 10.31274/td-20240329-56
An experimental study of icing physics and anti-/de-icing techniques for aero-engine icing mitigation
- Jan 01, 2021
- Linchuan Tian
Aero-engine icing, which occurs due to the impingement and subsequent freezing of airborne, super-cooled water droplets in clouds on the exposed surfaces of aero-engine inlet components, such as fan blades and inlet guide vane (IGV), has been widely recognized as a significant hazard to aviation safety in cold weathers. Typical glaze and rime icing process on such aero-engine components would fast change the surface roughness and even the designed geometry, which would degrade the performance of the jet engine and even jeopardize the engine stability. In addition, the potential shedding of large ice chunk would also be a threat to downstream components when be sucked into the core component, for example, the high-pressure compressor. Such impinged ice chunk would significantly distort the incoming flow condition and even cause the blades mechanical vibration. Therefore, the ice accretion process is considered to be one of the most hazardous icing incidents due to the potentially fatal penalties of the surge, stall, and even flameout of aero-engines. By leveraging the Icing Research Tunnel of Iowa State University (ISU-IRT in short), a series of experimental campaigns were conducted to investigate the dynamic icing process over the rotating engine fan and static inlet guide vane model. While different anti-/de-icing strategies were also applied to achieve ice mitigation for the aero-engine rotor and the stator. Firstly, the dynamic icing process of the aero-engine fan was studied using the high-speed imaging system and the digital image projection (DIP) based 3D scanning system, to reveal and quantify the transient ice accretion process over the rotation engine fan model and its performance degradation. Then, three anti-icing coatings, based on different working mechanisms, were also applied to the aero-engine fan model to study the surface wettability effect on the dynamic icing process and to achieve ice mitigation. For the IGV icing and anti-/de-icing study, an experimental campaign was conducted to investigate the IGV icing process under both wet glaze and dry rime icing conditions. While a parametric study was also conducted to study each operating parameter of the hot-air anti-/de-icing system on its anti-/de-icing performance. Finally, a theoretical heat transfer model based on mass and energy conservation was built to study the energy budget during the icing and anti-/de-icing process. During the experiment, an infrared (IR) imaging system, combined with thermocouples and heat flux sensors, was then applied to quantify the energy stored in the control volume and dissipated to the surrounding environment, which would be used to explain the phenomena related to the icing and anti-/de-icing process. The results from this paper would provide a better understanding of the aero-engine components icing physics pertinent to both jet engine rotor and stator. While the explorative study of each anti-/de-icing strategy also helps the design of more effective and robust anti-/de-icing strategies tailored for aero-engine fan and the IGV. Such improvement would fulfill the fast raised standard of the modern aviation industry for a high efficiency and safety aero-engine even operating in cold weather.
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