现有的研究多采用零维仿真模型对辅助动力装置（Auxiliary Power Unit, APU）进行总体性能仿真，而忽略了不同工况下进/排气系统总压损失变化对APU总体性能的影响。为提高计算结果的准确性，基于完全耦合的维度缩放方法将高精度的三维计算流体力学（Computational Fluid Mechanics, CFD）计算模型与低精度的零维仿真模型相结合，建立了零维仿真模型（APU Zero-dimensional Steady Model, AZSM）与多精度仿真模型（APU Multi-dimensional Steady Model, AMSM），实现了APU进/排气系统与APU本体性能的一体化计算。基于上述方法，本文对典型工况点进行计算分析，与常用商用软件Gasturb的计算结果进行对比，进而分析高度和速度变化对各参数的影响。结果表明，工况点1下（地面静止状态）AZSM、AMSM的计算结果精度均提升了0.02%；工况点2下（三万英尺高空飞行状态）AZSM的计算结果精度提升了12.75%，AMSM计算结果精度提升了19.42%；工况点3下（四万英尺高空飞行状态）AZSM的计算结果精度提升了8.54%，AMSM的计算结果精度提升了24.271%，多维度仿真模型AMSM可更准确地计算不同工况下APU的总体性能参数。
Most existing studies employ zero-dimensional simulation models for the overall performance simulation of the Auxiliary Power Unit (APU), while ignoring the impact of total pressure loss changes in the intake/exhaust system on the overall performance of the APU under different operating conditions. To improve the accuracy of calculation results, a zero-dimensional simulation model AZSM (APU Zero-dimensional Steady Model) and a multi-fidelity simulation model AMSM (APU Multi-dimensional Steady Model) were established. These models were achieved by integrating a high-fidelity three-dimensional Computational Fluid Dynamics (CFD) flow field calculation model with a low-fidelity zero-dimensional simulation model via a fully coupled dimensional scaling method, enabling the integrated calculation of the performance of the APU intake/exhaust system and the APU itself. Based on the aforementioned method, this study conducts computational analysis on typical operating points, compares the results with those from the commonly used commercial software Gasturb, and further analyzes the impact of altitude and speed variations on various parameters. The results show that: at Operating Point 1 (ground static state), the calculation accuracy of both AZSM and AMSM increased by 0.02% compared with the results from Gasturb; at Operating Point 2 (flight state at 30,000 ft altitude), the calculation accuracy of AZSM increased by 12.75%, while that of AMSM increased by 19.42%; at Operating Point 3 (flight state at 40,000 ft altitude), the calculation accuracy of AZSM increased by 8.54%, and that of AMSM increased by 24.271%. These results confirm that the multi-dimensional simulation model AMSM can more accurately calculate the overall performance parameters of the APU under different operating conditions.
[1]王浩, 杨恒辉, 卢玉芳.飞机第二动力系统技术综述[J].[J].信息系统工程, 2014(4):38-39., :-
[2]WANG H, YANG H H, LU Y F.A Technical Review of Aircraft Secondary Power Systems[J]. Information Systems Engineering, 2014(4):38-39 (in Chinese).
[3]马强, 田宏星.战斗机用辅助动力装置的发展[J]. 航空动力, 2019(2):20-22.
[4]MA Q, TIAN H X.The Development of Auxiliary Power Units for Fighter Jets[J]. Aerospace Power, 2019(2):20-22 (in Chinese).
[5]Sijie, Chen, et al.“Research on the architecture of auxiliary energy system for future fighter.” 2016 IEEE International Conference on Aircraft Utility Systems (AUS) (2016): 189-192.
[6]赵运生, 胡骏, 吴铁鹰, 等.大型民用飞机辅助动力装置性能仿真[J].航空动力学报, 2011, 26(7):1590-1598
[7]ZHAO Y S, HU J, WU T Y, et al.Performance Simulation of Auxiliary Power Units for Large Civil Aircraft[J].Journal of Aerospace Power, 2011, 26(7):1590-1598
[8]刘然.辅助动力装置与空气涡轮起动机一体化建模与计算研究[D]. 南京：南京航空航天大学, 2020.
[9]LIU R.Integrated Modeling and Calculation Research on Auxiliary Power Unit and Air Turbine Starter[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2020 (in Chinese).
[10]常博博, 苏三买, 刘铁庚, 等.辅助动力装置建模及数值仿真[J].航空动力学报, 2011, 26(09):2122-2127
[11]CHANG B B, SU A M, LIU T G, et al.Modeling and Numerical Simulation of Auxiliary Power Units[J].Journal of Aerospace Power, 2011, 26(09):2122-2127
[12]苏三买, 孙牧桥, 田宏星, 等.飞机辅助动力装置引气特性计算方法[J].推进技术, 2013, 34(04):439-444
[13]SU S M, SUN M Q, TIAN H X, et al.Calculation Method for Bleed Air Characteristics of Aircraft Auxiliary Power Units[J].Propulsion Technology, 2013, 34(04):439-444
[14]袁昌坤, 刘娇, 刘火星, 等.第二动力系统建模及性能分析[J].航空动力学报, 2024, 39(10):344-353
[15]YUAN C H, LIU J, LIU H X, et al.Modeling and Performance Analysis of the Secondary Power System[J].Journal of Aerospace Power, 2024, 39(10):344-353
[16]智文静, 李国材, 徐颖, 等.基于的某型进气管道的流场数值分析[J].液压与气动, 2023, 47(10):119-126
[17]ZHI W J, LI G C, XU Y, et al.Numerical Analysis of Flow Field in a Certain Type of APU Inlet Pipe Based on Fluent[J].Hydraulics and Pneumatics, 2023, 47(10):119-126
[18]邓智亮, 唐宏刚, 张乃昌, 等.APU进气管道口尺寸比例对进气性能影响研究[J]. 科技信息, 2011, (22):446-447+449.
[19]DENG Z L, TANG H G, ZHANG N C, er al.Study on the Influence of Size Ratio of APU Inlet Pipe Opening on Intake Performance[J]. Scientific and technological information, 2011, (22):446-447+449 (in Chinese).
[20]王虎山, 汪明生.带多孔板的进气系统气动性能研究[J].推进技术, 2013, 34(07):865-872
[21]WANG S H, WANG M S.Study on Aerodynamic Performance of APU Intake System with Perforated Plates[J].Propulsion Technology, 2013, 34(07):865-872
[22]Pilet J，Lecordix J L，Nicolas G R，et al.Towards a Ful?ly Coupled Component Zooming Approach in Engine Per?formance Simulation［R］. ASME GT 2011-46320.
[23]Templalexis I，Alexiou A，Pachicis V，et al.Direct Cou?pling of a Turbofan Engine Performance Simulation［R］.ASME GT 2016-56617.
[24]Joachim K.How to Get Component Maps for Aircraft Gas Turbine Performance Calculation［R］. ASME 96-GT-164.
[25]倪勤，王正盛，刘皞等.数值计算方法[M]. 北京:高等教育出版社, 2012:45~46.
[26]NI Q, WANG Z S, LIU H, et al.Numerical Calculation Method[M].Beijing:Higher Education Press, 2012:45~46. (in Chinese).
[27]刘伟, 田宏星, 陈玉春, 等.航空发动机空气起动系统性能匹配计算方法[J].推进技术, 2020, 41(02):277-284
[28]LIU W, TIAN H X, CHEN Y C, et al.Calculation Method for Performance Matching of Aeroengine Air Start System[J].Propulsion Technology, 2020, 41(02):277-284
[29]宋甫, 周莉, 王占学, 等.不同维度缩放方法在航空发动机总体仿真中的应用[J].推进技术, 2020, 41(05):974-983
[30]SONG F, ZHOU L, WANG Z X, et al.Application of Different Dimension Scaling Methods in Overall Simulation of Aero-Engines[J].Propulsion Technology, 2020, 41(05):974-983
[31]宋甫, 周莉, 王占学, 等.部件三维仿真模型与发动机循环参数分析的耦合方法研究[J].推进技术, 2022, 43(07):85-92
[32]SONG F, ZHOU L, WANG Z X, et al.Research on Coupling Method between Component 3D Simulation Model and Engine Cycle Parameter Analysis[J].Propulsion Technology, 2022, 43(07):85-92
[33]Basoglu O，Yalcin L，Yilmaz A E.Computational study on the design parameters of S-type subsonic inlets．AIAA 2008—73，2008
[34]Jovanovic V J．Taskinoglu E S，Knight D D.Experimental investigation of a submerged subsonic inlet．AIAA，2004—2649，2004
[35].李学来，任三星，王琴芳，等．埋入式进气道的流场畸变．福州大学学报(自然科学版)，2002; 30(2): 250—253
[36]LI X L, REN S X, WANG Q F, et al.Flow Field Distortion of Embedded Inlet. Journal of Fuzhou University (Natural Science Edition), 2002; 30(2): 250—253 (in Chinese).
CJA