Study of Flow and Heat Transfer in an Ejector-Driven Swirl Anti-Icing Chamber  

作　　者：Yi Tu Yuan Wu Yu Zeng 

机构地区：[1]Hunan University of Arts and Sciences,Hunan Key Laboratory of Distributed Electric Propulsion Vehicle Control Technology,Changde,415000,China [2]Liaoning Provincial Key Laboratory of Aircraft Ice Protection,AVIC Aerodynamics Research Institute,Shenyang,110034,China [3]School of Aeronautic Science and Engineering,Beihang University,Beijing,100191,China

出　　处：《Fluid Dynamics & Materials Processing》2024年第5期989-1014,共26页流体力学与材料加工（英文）

基　　金：Shenyang Key Laboratory of Aircraft Icing and Ice Protection,Grant Number XFX20220303;Education Department of Hunan Province,China,Grant Number 23A0504;National Natural Science Foundation of China,Grant Number 52275108.

摘　　要：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.

关 键 词：Swirl anti-icing heat transfer exergy efficiency hot and cold spot aircraft engine 

分 类 号：O35[理学—流体力学]