The formation of ice on the leading edge of aircraft engines is a serious issue,as it can have catastrophic consequences.The Swirl Anti-Icing(SAI)system,driven by ejection,circulates hot fluid within a 360°annula...The formation of ice on the leading edge of aircraft engines is a serious issue,as it can have catastrophic consequences.The Swirl Anti-Icing(SAI)system,driven by ejection,circulates hot fluid within a 360°annular chamber to heat the engine inlet lip surface and prevent icing.This study employs a validated Computational Fluid Dynamics(CFD)approach to study the impact of key geometric parameters of this system on flow and heat transfer characteristics within the anti-icing chamber.Additionally,the entropy generation rate and exergy efficiency are analyzed to assess the energy utilization in the system.The research findings indicate that,within the considered flow range,reducing the nozzle specific areaφfrom 0.03061 to 0.01083 can enhance the ejection coefficient by over 60.7%.This enhancement increases the air circulating rate,thereby intensifying convective heat transfer within the SAI chamber.However,the reduction inφalso leads to a significant increase in the required bleed air pressure and a higher entropy generation rate,indicating lower exergy efficiency.The nozzle angleθnotably affects the distribution of hot and cold spots on the lip surface of the SAI chamber.Increasingθfrom 0°to 20°reduces the maximum temperature difference on the anti-icing chamber surface by 60 K.展开更多
Icing on the surface of aircraft will not only aggravate its quality and affect flight control,but even cause safety accidents,which is one of the important factors restricting all-weather flight.Bio-inspired anti-ici...Icing on the surface of aircraft will not only aggravate its quality and affect flight control,but even cause safety accidents,which is one of the important factors restricting all-weather flight.Bio-inspired anti-icing surfaces have gained great attention recently due to their low-hysteresis,non-stick properties,slow nucleation rate and low ice adhesion strength.These bio-inspired anti-icing surfaces,such as superhydrophobic surfaces,slippery liquid-infused porous surfaces and quasi-liquid film surfaces,have realized excellent anti-icing performance at various stages of icing.However,for harsh environment,there are still many problems and challenges.From the perspective of bioinspiration,the mechanism of icing nucleation,liquid bounce and ice adhesion has been reviewed together with the application progress and bottleneck issues about anti-icing in view of the process of icing.Subsequently,the reliability and development prospect of active,passive and active-passive integrated anti-icing technology are discussed,respectively.展开更多
针对飞机除冰液加热,设计了一种基于GPRS(通用分组无线服务)网络的远程监控系统。它可以实现对设备的实时监控,及时有效地完成飞机地面除冰。该系统由上位机和下位机两部分组成:PLC作为下位机的控制系统,对执行机构进行控制输出,并且由...针对飞机除冰液加热,设计了一种基于GPRS(通用分组无线服务)网络的远程监控系统。它可以实现对设备的实时监控,及时有效地完成飞机地面除冰。该系统由上位机和下位机两部分组成:PLC作为下位机的控制系统,对执行机构进行控制输出,并且由A/D转换模块采集加热设备管道内的物理参数;远程控制中心作为上位机的监控系统,包括两种方式:一是利用数据服务中心作为远程控制中心,二是利用组态软件设计系统的操作界面作为远程控制中心。GPRS DTU(data transfer unit)通信模块通过GPRS网络完成与远程控制中心的无线通信,实现上位机与下位机之间的数据交互。展开更多
基金Shenyang Key Laboratory of Aircraft Icing and Ice Protection,Grant Number XFX20220303Education Department of Hunan Province,China,Grant Number 23A0504National Natural Science Foundation of China,Grant Number 52275108.
文摘The formation of ice on the leading edge of aircraft engines is a serious issue,as it can have catastrophic consequences.The Swirl Anti-Icing(SAI)system,driven by ejection,circulates hot fluid within a 360°annular chamber to heat the engine inlet lip surface and prevent icing.This study employs a validated Computational Fluid Dynamics(CFD)approach to study the impact of key geometric parameters of this system on flow and heat transfer characteristics within the anti-icing chamber.Additionally,the entropy generation rate and exergy efficiency are analyzed to assess the energy utilization in the system.The research findings indicate that,within the considered flow range,reducing the nozzle specific areaφfrom 0.03061 to 0.01083 can enhance the ejection coefficient by over 60.7%.This enhancement increases the air circulating rate,thereby intensifying convective heat transfer within the SAI chamber.However,the reduction inφalso leads to a significant increase in the required bleed air pressure and a higher entropy generation rate,indicating lower exergy efficiency.The nozzle angleθnotably affects the distribution of hot and cold spots on the lip surface of the SAI chamber.Increasingθfrom 0°to 20°reduces the maximum temperature difference on the anti-icing chamber surface by 60 K.
基金financially supported by the National Natural Science Foundation of China(Nos.T2121003,51725501,51935001,52205297).
文摘Icing on the surface of aircraft will not only aggravate its quality and affect flight control,but even cause safety accidents,which is one of the important factors restricting all-weather flight.Bio-inspired anti-icing surfaces have gained great attention recently due to their low-hysteresis,non-stick properties,slow nucleation rate and low ice adhesion strength.These bio-inspired anti-icing surfaces,such as superhydrophobic surfaces,slippery liquid-infused porous surfaces and quasi-liquid film surfaces,have realized excellent anti-icing performance at various stages of icing.However,for harsh environment,there are still many problems and challenges.From the perspective of bioinspiration,the mechanism of icing nucleation,liquid bounce and ice adhesion has been reviewed together with the application progress and bottleneck issues about anti-icing in view of the process of icing.Subsequently,the reliability and development prospect of active,passive and active-passive integrated anti-icing technology are discussed,respectively.
基金supported by the National Natural Science Foundation of China (No.12072213)the National Science and Technology Major Project from Ministry of Science and Technology of China (No.J2019-Ⅲ-00100054)the National Numerical Windtunnel from China Aerodynamics Research and Center (No. NNW2019JT01-023)。
文摘针对飞机除冰液加热,设计了一种基于GPRS(通用分组无线服务)网络的远程监控系统。它可以实现对设备的实时监控,及时有效地完成飞机地面除冰。该系统由上位机和下位机两部分组成:PLC作为下位机的控制系统,对执行机构进行控制输出,并且由A/D转换模块采集加热设备管道内的物理参数;远程控制中心作为上位机的监控系统,包括两种方式:一是利用数据服务中心作为远程控制中心,二是利用组态软件设计系统的操作界面作为远程控制中心。GPRS DTU(data transfer unit)通信模块通过GPRS网络完成与远程控制中心的无线通信,实现上位机与下位机之间的数据交互。
