Icing is a phenomenon that poses a serious threat to flight safety. This paper systematically conducts research on engine anti-icing design technology using a newly developed civil turbo-shaft engine as a platform, establishing a complete anti-icing design process for turbo-shaft engines from a forward R&D perspective. It proposes an “mesh screen + hot air anti-icing” composited anti-icing method that combines structure anti-icing with a square-hole curved surface mesh screen and hot-air anti-icing through automatic regulation of bleed air volume via a constant pressure valve. Numerical analysis is performed on the inlet flow field with the mesh screen under icing conditions, the total pressure loss at the inlet, changes in compressor parameters, and the impact of ice chunks on the compressor first rotor blades. The research results indicate that after icing, the total pressure loss at the inlet and the distortion of the compressor inlet flow field increase. Coupled with the temperature distortion effect caused by hot-air anti-icing, compressor efficiency and surge margin decrease, leading to engine performance deterioration. To ensure the anti-icing effectiveness of the engine within the icing envelope, the ground idle condition at -20°C can be used as the design point for hot-air anti-icing, with a bleed air volume of approximately 2.8%. To meet the aircraft's power requirements, performance design should focus on ensuring that the engine retains sufficient power margin under high-altitude icing conditions. To prevent surge during engine acceleration under icing conditions, the control system can adopt a optimized control strategy that automatically reduces the acceleration limit of the gas generator rotor. The research findings have been directly applied to the development of a newly developed civil turboshaft engine, providing important technical support for the engine's airworthiness certification.
[1]F. Ferrigno, P. Vernillo, M. Inverno. NH90 Air Intake Version T700/T6E1 Icing Qualification Tests [J]. AIAA 2005-477 :
[2]Aviation Safety Reporting System[DB/OL]. [S.l.] : Federal Aviation Administra-tion, 2020 [2020-04-18].
https://titan-server.arc.nasa.gov/ASRSPublic Query Wizard/Query Wizard_Filter.aspx.
[3]中国民用航空局. 航空发动机适航规定: CCAR33-R2[S]. 北京: 中国民用航空局, 2011: 22.
Civil Aviation Administration of China. Aeroengine airworthiness regulations: CCAR33-R2[S]. Beijing: Civil Aviation Administration of China, 2011: 22 (in Chinese).
[4]中国民用航空局. 运输类飞机适航标准: CCAR25-R4[S]. 北京: 中国民用航空局, 2011: 22.
Civil Aviation Administration of China. Aero-engine airworthiness regulations: CCAR25-R4[S]. Beijing: Civil Aviation Administration of China, 2011: 22 (in Chinese).
[5]中国民用航空局. 航空发动机审定咨询通告. AC-33-AA-2022-01[S]. 北京. 中国民用航空局航空器适航审定司, 2022
Civil Aviation Administration of China. Aeroengine airworthiness Advisory Circular: AC-33-AA-2022-01 [S]. Beijing: Aircraft airworthiness Certification Department, Civil Aviation Administration of China, 2022
[6]杨军, 张靖周, 郭文,等. 航空发动机进口支板结冰和防冰试验[J]. 航空动力学报, 2014, 29(2): 277-283.
YANG J,ZHANG J Z,GUO W, et al, Experiment of anti-icing and icing on inlet strut of aero-engine[J].Journal of Aerospace Power, 2024, 29(2): 277-283 (in Chinese).
[7]郭文, 陶智, 毛军逵等. 航空发动机空气系统设计[M]. 科学出版社, 2022.
GUO W, TAO Z, MAO J K, et al. Design of Aero-engine Secondary System[M]. Science Press, 2022 (in Chinese).
[8]陆景松. 发动机进气道前缘防冰腔性能研究[D]. 南京: 南京航空航天大学, 2008.
LU J S. Research on the performance of anti-icing cavity at the leading edge of intake of areoengine[D]. Nanjing: Nanjing University of Aeronautics and Astro nautics, 2008(in Chinese).
[9]常士楠, 艾素霄, 毕文明等. 飞机发动机进气道防冰系统的设计计算[J]. 北京航空航天大学学报, 2007, 33(6): 649-652.
CHANG S N,AI S X,BI W M, et al. Design and calculation for the anti-icing system of an aircraft engine let [J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(6): 649-652 (in Chinese).
[10]贺丹, 李杜, 张锦纶,等. 防冰引气对组合压气机性能影响的数值模拟研究[J]. 航空发动机, 2016, 42(4): 63-68.
HE D, Li D, ZHANG J L, et al. Numerical simulation investigation on influence of anti-icing bleed on performance of combined compressor[J]. Aeroengine, 2016, 42(4): 63-38 (in Chinese).
[11]Michael Dvornak. Development of Engine Intake Anti-icing System for LCAC[C]// Proceedings of ASME Turbo Expo 2007: Power for Land, Sea and Air. Canada: ASME, 2007.
[12]Collins O. Ojo, Christine Schwille, Anton Nemet, et al. Optimization of Anti-icing Limits for ALSTOM Gas Turbines Based on Theory of Ice Formation[C]// Proceedings of ASME Turbo Expo 2009: Power for Land, Sea and Air. USA: ASME, 2009.
[13]Alexander Bucknell, Matthew McGilvray, David R. H. Gillespie, et al. Heat Transfer in the Core Compressor under Ice Crystal Icing Conditions[C]// Proceedings of ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. USA: ASME, 2017.
[14]D.M. Farrel, B.V.R.Vittal. Computer simulation of water ingestion for the T800-LHT-801 engine anti-icing test inlet[C]// Joint Propulsion Conference and Exhibit. Lake Buena Vista: AIAA, 1996.
[15]Mark A. Gillan, Roy Farren. Optimal Design of Nacelle Thermal Anti-Icing Exhaust Grills for Enhanced Mixing[C]// AIAA-96-2463-CP. UK: AIAA, 1996
[16]ZHENG Y T, ZHANG F K, WANG D J, et al. Numerical and Experimental Study of Ice Accretion Process and Ice Protection on Turbo-fan Engine Splitter[C]// Proceedings of ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. USA: ASME, 2009.
[17]汪 涛, 王俊琦, 王朝蓬. 直升机进气道防冰试验方法设计与试验[J]. 科学技术与工程, 2017, 17(20): 294-301.
WANG T, WANG J Q, WANG Z P. Method Design of Helicopter Inlet Duct Anti-ice and Experiment[J]. Science Technology and Engineering, 2017, 17(20): 294-301 (in Chinese).
[18]W. Stiefel. Environmental Icing Test of T800 Helicopter Engine with Integral Inlet Particle Separator[C]. AIAA/ASME/SAE/ASEE 52th Joint propulsion Conference,1989,AIAA-89-2324.
[19]唐泉康, 陈代林, 谢寿生. 某型发动机防冰系统的性能改进[J]. 航空维修与工程, 2003, (2), 27-28.
TANG Q K, CHEN D L, XIE S S. [J]. The improvement on the performance of a certain engine’s protection system against the ice[J]. Aviation Maintenance & Engineering, 2003, (2), 27-28 (in Chinese).
[20]Mathioudakis K., Tsalavoutas A. Effects of Anti-icing System Operation on Gas Turbine Performance and Monitoring[C]// Proceedings of ASME Turbo Expo 2010: Louisiana: ASME, 2001.
[21]李概奇, 田骏丹, 吴晶峰等．新研民用涡轴发动机结冰适航试验研究[J]．航空学报, 2025, 46: 131388.
LI G Q, TIAN J D, WU J F, et al. Icing Airworthiness Test Research on a Newly Developing Civil Turbo-shaft Engine[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46: 131399 (in Chinese)
[22]《航空发动机设计手册》总编委会. 航空发动机设计手册－第16册[M]. 北京: 航空工业出版社, 2001.
Aero-engine Design Manual Editorial Board. Aero-engine design manual, Volume 16[M]. Beijing: Aviation Industry Press,2001.(in Chinese).
[23]张丽芬, 韩冰冰, 朱鹏飞等. 航空发动机结冰研究[M]. 科学出版社, 2023.
ZHANG L F, HAN B B, ZHU P F, et al. Aero-engine icing research[M]. Science Press, 2023 (in Chinese).
[24]Kurzke J, Halliwell I. Propulsion and power an exploration of gas turbine performance modeling[M]. Springer, 2018.
[25]李概奇, 马东阳, 李杜等. 某新研民用涡轴发动机起飞状态喘振试验研究[J]. 航空学报, 2023, 44: 628190.
LI G Q, MA D Y, LI D, et al. Surge test research on a newly developing civil turboshaft engine at take-off condition[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44: 628190 (in Chinese). doi:10.7527/S1000-6893.2022.28190
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