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A comprehensive aerodynamic-thermalmechanical design method for fast response turbocharger applied in aviation piston engines

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Propulsion and Power Research 2024年第2期13卷 145-165页

作者： Yu Zhou Yue Song Shuai Zhao Xueyu Li longtao shao Huansong Yan Zheng Xu Shuiting Ding Research Institute of Aero-Engine Beihang UniversityBeijing 100083China Aircraft/Engine Integrated System Safety Beijing Key Laboratory Beijing 100083China School of Energy and Power Engineering Beihang UniversityBeijing 100083China School of Transportation Science and Engineering Beihang UniversityBeijing 100083China AVIC Nanjing Engineering Institute of Aircraft Systems Nanjing 210000China Hangzhou International Innovation Institute Beihang UniversityHangzhou 311115China Civil Aviation University of China Tianjin 300300China

Limited by the poor transient response performance of turbochargers,the dynamic performance of aviation piston engines tends to *** a bid to enhance the turbocharger’s acceleration capabilities,this study scrutinizes various factors impacting its *** on the operational principles and transient response process of the turbocharger,three types of in-ertiadnamely,aerodynamic inertia(ADI),thermal inertia(TI),and mechanical inertia(MI)d are identiﬁed and addressed for *** begin,this paper pioneers the innovative deﬁnition of a method for evaluating the transient response performance of the *** method incor-porates the introduction of an ADI parameter,inspired by the deﬁnition of ***,a thin-walled volute design with a low Biot number and a lightweight turbine impeller is introduced to reduce the turbocharger’s TI and *** simulation results of theﬂowﬁeld distribution within the volute and diffuser demonstrate the comprehensive design method’s effectiveness in improving gas pressure and temperature distributions in these ***,the pressure distributionﬂuctuation in the constant moment-of-momentum volute(CMV)is 62.8%lower than that in the constant velocity moment volute(CVMV).The low-TI thin-walled volute not only en-hances the turbocharger’s response speed but also reduces its weight by approximately 40%.The impact of three types of inertia on the engine’s response speed is quantiﬁed as follows:ADI(94%)>MI(5%)>TI(1%).This conclusion has been veriﬁed through test results of both the turbocharger and the *** design method not only signiﬁcantly improves the turbo-charger’s response performance but also offers valuable insights for the optimal design of other blade mechanical systems.

关键词： Turbocharger Fast response design method Aerodynamic inertia Thermal inertia Mechanical inertia

Gas exchange optimization in aircraft engines using sustainable aviation fuel:A design of experiment and genetic algorithm approach

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Energy and AI 2024年第3期17卷 261-280页

作者： Zheng Xu Jinze Pei Shuiting Ding Longfei Chen Shuai Zhao Xiaowei Shen Kun Zhu longtao shao Zhiming Zhong Huansong Yan Farong Du Xueyu Li Pengfei Yang Shenghui Zhong Yu Zhou Hangzhou International Innovation Institute Beihang UniversityHangzhou311115China Research Institute of Aero-Engine Beihang UniversityBeijing102206China Civil Aviation University of China Tianjin300300China Aircraft/Engine Integrated System Safety Beijing Key Laboratory Beijing100083China Aero Engine Academy of China Beijing101304China School of Energy and Power Engineering Beihang UniversityBeijing100083China AVIC Chengdu Aircraft Design and Research Institute Chengdu610091China AVIC Nanjing Engineering Institute of Aircraft Systems Nanjing211106China School of Transportation Science and Engineering Beihang UniversityBeijing100083China Faculty of Science and Engineering University of Nottingham Ningbo ChinaNingbo315100China

The poppet valves two-stroke(PV2S)aircraft engine fueled with sustainable aviation fuel is a promising option for general aviation and unmanned aerial vehicle propulsion due to its high power-to-weight ratio,uniform torque output,and flexible valve ***,its high-altitude gas exchange performance remains unexplored,presenting new opportunities for optimization through artificial intelligence(AI)*** study uses validated 1D+3D models to evaluate the high-altitude gas exchange performance of PV2S aircraft *** valve timings of the PV2S engine exhibit considerable flexibility,thus the Latin hypercube design of experiments(DoE)methodology is employed to fit a response surface model.A genetic algorithm(GA)is applied to iteratively optimize valve timings for varying *** optimization process reveals that increasing the intake duration while decreasing the exhaust duration and valve overlap angles can significantly enhance high-altitude gas exchange *** optimal valve overlap angle emerged as 93°CA at sea level and 82°CA at 4000 m *** effects of operating parameters,including engine speed,load,and exhaust back pressure,on the gas exchange process at varying altitudes are further *** higher engine speed increases trapping efficiency but decreases the delivery ratio and charging efficiency at various *** effect is especially pronounced at elevated *** increase in exhaust back pressure will significantly reduce the delivery ratio and increase the trapping *** study demonstrates that integrating DoE with AI algorithms can enhance the high-altitude performance of aircraft engines,serving as a valuable reference for further optimization efforts.

关键词： Poppet valves two-stroke Design of experiment Genetic algorithm optimization Heavy fuel aircraft engine High altitude gas exchange performance

Numerical and experimental investigation on dynamic performance of bump foil journal bearing based on journal orbit

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Chinese Journal of Aeronautics 2021年第2期34卷 586-600页

作者： Yu ZHOU longtao shao Can ZHANG Fenzhu JI Jiang LIU Guo LI Shuiting DING Qi ZHANG Farong DU School of Transportation Science and Engineering Beijing Key Laboratory for High-efficient Power Transmission and System Control of New Energy Resource VehicleBeihang UniversityBeijing 100083China School of Energy ami Pow er Engineering Aircraft/Engine Integrated System Safety Beijing Key LaboratoryBeihang UniversityBeijing 100083China

Widespread usage of bump-type foil journal bearing(BFJB) in oil-free microturbomachinery requires accurate predictions of dynamic performance characteristics, although it remains a challenging issue because BFJB reflects nonlinear both structurally and *** paper presented a simple experimental method to semi-directly obtain the minimum film thickness and dynamic stiffness of BFJB using the journal orbit. Numerical calculations and simulations are conducted to validate the experimental method. The micro-deformation and interaction of various foils are taken into consideration to improve the model precision. The results from the numerical model regarding the BFJB dynamic characteristics are compared with the experimental results coming from a dedicated test rig, which shows that the experimental results fluctuate obviously and agree not well with the numerical results at the start stage due to the presence of dry friction at that time, nevertheless, they show fantastic agreement as soon as a gas film is gradually generated to separate the shaft from the top foil. Therefore, the proposed experimental method is effective to predict film thickness and dynamic characteristics during the period from the lift-off time to the land-off time. The dynamic characteristics, along with the journal orbits also can be used to rapidly predict the dynamics behavior of rotor-bearing systems.

关键词： Bump-type foil journal bearing Dynamic performance Experimental method Journal orbit Numerical calculation

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重油航空活塞发动机燃油喷射技术

北京航空航天大学学报 2022年第9期48卷 1630-1642页

作者：丁水汀邵龙涛赵帅朱锟杜发荣周煜北京航空航天大学航空发动机研究院北京100083 北京航空航天大学能源与动力工程学院北京100083 中国航空发动机研究院北京101300

燃油喷射技术作为航空活塞发动机的关键技术之一,其结构形式及特性直接影响航空活塞发动机的整机性能,随着通用航空对发动机性能要求的不断提升,燃油喷射技术的发展也在不断延续。综述了当前各种重油航空活塞发动机采用的燃油供给系统,... 详细信息

燃油喷射技术作为航空活塞发动机的关键技术之一,其结构形式及特性直接影响航空活塞发动机的整机性能,随着通用航空对发动机性能要求的不断提升,燃油喷射技术的发展也在不断延续。综述了当前各种重油航空活塞发动机采用的燃油供给系统,对其适用的经典机型进行了梳理,总结了各种燃油供给系统的优缺点。阐述了研究重油喷射技术采用的前沿理论、仿真计算及试验方法,分析了研究重油雾化过程存在的难点,给出了研究重油喷射技术的相关建议。提出了未来重油航空活塞发动机发展思路和关键技术,重点希望对重油航空活塞发动机的正向研制提供技术指导,推动中国通用航空的可持续发展。

关键词：航空活塞发动机重油喷射技术二冲程负碳生物燃料控制策略

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新型热成形-淬火-碳分配工艺

热处理 2016年第5期31卷 45-47页

作者：白洋张明远邵龙涛郑卫刚武汉理工大学能源与动力工程学院湖北武汉430063 武汉理工大学工程训练中心湖北武汉430063

变形与相变和碳分配相结合,即钢在奥氏体区变形以细化晶粒、获得高强度,在淬火过程中钢发生相变和碳分配,可实现对硬相马氏体和软相残留奥氏体的调控,是一种新型热成形-淬火-碳分配工艺。这一工艺方法可使钢获得纳米级位错型马氏体和残... 详细信息

变形与相变和碳分配相结合,即钢在奥氏体区变形以细化晶粒、获得高强度,在淬火过程中钢发生相变和碳分配,可实现对硬相马氏体和软相残留奥氏体的调控,是一种新型热成形-淬火-碳分配工艺。这一工艺方法可使钢获得纳米级位错型马氏体和残留奥氏体的复合组织,在不损害钢的强度的前提下,提高其力学性能。

关键词：热成形淬火碳分配复合组织高强度

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腹板开洞型抗剪连接件力学性能有限元分析

南昌大学学报（工科版） 2024年第1期46卷 53-60页

作者：刘俊辉张龙涛胡淑军黄海邵铁峰南昌大学工程建设学院江西南昌330031

为了提高全装配式混凝土梁柱-钢支撑的受剪性能,提出一种腹板开洞型抗剪连接件。以腹板截面分配方式为参数,设计2个试件进行往复加载试验,研究其力学性能。采用ABAQUS软件进行有限元分析校正,并设计16个分别考虑混凝土强度、腹板宽度高... 详细信息

为了提高全装配式混凝土梁柱-钢支撑的受剪性能,提出一种腹板开洞型抗剪连接件。以腹板截面分配方式为参数,设计2个试件进行往复加载试验,研究其力学性能。采用ABAQUS软件进行有限元分析校正,并设计16个分别考虑混凝土强度、腹板宽度高度和2组腹板组合形式影响的有限元模型进行模拟分析,进而探究各参数对抗剪连接件受剪性能的影响。结果表明:两试件破坏形态基本一致,首先混凝土梁侧面产生斜向裂缝,并向梁正面发展,随后抗剪腹板处出现裂缝,最终在多次循环往复加载下,混凝土被压溃。两滞回曲线走势基本相同,主要包括弹性、弹塑性和破坏3个阶段。提高混凝土强度能有效提高连接件剪切承载能力;腹板截面面积一定时,截面尺寸为15 mm×32 mm的连接件极限承载能力最大;同时改变2组腹板尺寸,截面组合尺寸为18 mm×40 mm和6 mm×40 mm的组合形式抗剪性最好。

关键词：腹板开洞型抗剪连接件力学性能有限元分析破坏形态滞回曲线