超声速进气道进发匹配安装性能快速计算方法

推进技术 ›› 2017, Vol. 38 ›› Issue (3): 510-518.

超声速进气道进发匹配安装性能快速计算方法

贾琳渊,陈玉春,解俊琪,蔡飞超

西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072

发布日期:2021-08-15
作者简介:贾琳渊，男，博士生，研究领域为涡轮发动机总体性能仿真与分析。

A Simplified Method to Simulate Supersonic Inlet Installed Performance in Terms of Engine and Inlet Matching

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China and School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究超声速进气道与发动机的匹配特性，改善推进系统的安装性能，结合准一维进气道流场计算方法和基于部件法的发动机总体性能仿真模型，发展了一种考虑进发匹配的超声速进气系统安装性能快速计算方法。该方法能够计算不同飞行条件和不同进气道工况下，超声速进气系统的性能和安装阻力。利用文献中的数据对本文的模型进行了校核，并以两斜一正外压式进气道为例，研究了亚声速飞行时的附加阻力和进气道的调节方法。与文献中数据对比表明，进气道总压恢复和流量系数误差小于1.4%，发动机安装推力计算结果误差小于9%。超声速进气道在亚声速巡航状态下由于发动机节流带来较大的附加阻力，而进气道调节可降低高马赫数下的溢流阻力并增加进气道的稳定裕度。

关键词: 超声速进气道；进发匹配；附加阻力；溢流阻力；变几何进气道

Abstract: To investigate the matching principle between supersonic inlets and gas turbine engines and to improve the installed performance of supersonic propulsion systems，a simplified method to simulate the supersonic inlet installed performance in terms of engine and inlet matching was developed. This method was based on quasi one dimensional simulation of the flow field of supersonic inlets and the component-based gas turbine engine performance simulation model. Consequently，it is capable of simulating the installed drag of supersonic inlets on different flight and working conditions. This method was validated using data from other references before it was used to investigate the matching between ‘2+1’ supersonic inlet and a turbofan engine during subsonic cruise and the performance of a variable supersonic inlet. Results show that，the deviations of inlet pressure recovery and mass flow coefficient are within 1.4%，while the deviations of installed performance of some turbofan engine is within 9%. Noticeable additive drag was detected during subsonic cruise when the engine was working in deep throttle conditions. Variable inlet can reduce the spillage drag and increase the stability of supersonic inlet at high flight Mach numbers.

Key words: Supersonic inlet；Matching of inlets and engines；Additive drag；Spillage drag；Variable inlet

贾琳渊,陈玉春,解俊琪,蔡飞超. 超声速进气道进发匹配安装性能快速计算方法[J]. 推进技术, 2017, 38(3): 510-518.

JIA Lin-yuan,CHEN Yu-chun,XIE Jun-qi,CAI Fei-chao. A Simplified Method to Simulate Supersonic Inlet Installed Performance in Terms of Engine and Inlet Matching[J]. Journal of Propulsion Technology, 2017, 38(3): 510-518.

参考文献

[1] Mattingly J D. Elements of Propulsion: Gas Turbines and Rockets[M]. Virginia: AIAA Press, 2006.
[2] Mattingly J D. Aircraft Engine Design[M]. Virginia: AIAA Press, 2002.
[3] Seddon J, Goldsmith E L. Intake Aerodynamics[M]. Virginia: AIAA Press, 1999.
[4] 朱俊强, 黄国平, 雷志军. 航空发动机进排气系统气动热力学[M]. 上海:上海交大出版社, 2014.
[5] 廉筱纯. 航空发动机原理[M]. 西安:西北工业大学出版社, 2005.
[6] 乐川, 徐大军, 蔡国飙. 超声速溢流条件下二元超声速进气道附加阻力计算[J]. 航空动力学报, 2010, 25(11): 2431-2436.
[7] 王晓蓉. 航空发动机进排气系统特性建模研究[D]. 西安:西北工业大学, 2014.
[8] 刘鹏超, 宋文艳, 骆广琦. 某型飞机发动机的安装推力计算[J]. 航空工程进展, 2010, (3): 268-272.
[9] 钱飞, 宋文艳, 骆广琦. 某型飞机/发动机一体化性能计算[J]. 航空动力学报, 2013, (5): 1112-1118.
[10] Kowaiski E J, Robert A A Jr. A Computer Code for Estimating Installed Performance of Aircraft Gas Turbine Engines[R]. NASA CR 159693, 1979.
[11] 张晓博. 航空发动机多学科耦合设计和优化技术研究[D]. 西安:西北工业大学, 2014.
[12] 周红. 变循环发动机及其与飞机一体化设计研究[D]. 西安:西北工业大学, 2016.
[13] 孙丰勇, 张海波, 叶志锋, 等. 航空发动机超声速巡航性能寻优控制研究[J]. 推进技术, 2015, 36(8): 1248-1256. (SUN Feng-yong, ZHANG Hai-bo, YE Zhi-feng, et al. A Study of Aero-Engine Supersonic Cruise[J]. Journal of Propulsion Technology, 2015, 36(8): 1248-1256.)
[14] 商旭升, 蔡元虎, 李京伟. 某高超声速弹用发动机安装特性分析[J]. 弹箭与制导学报, 2013, (6): 99-102.
[15] 王占学, 乔渭阳, 蔡元虎. 某型弹用涡喷发动机安装性能分析[J]. 推进技术, 2003, 24(1): 12-16. (WANG Zhan-xue, QIAO Wei-yang, CAI Yuan-hu. Analysis of Installation Performance of the Missile Turbojet Engine[J]. Journal of Propulsion Technology, 2003, 24(1): 12-16.)
[16] Moeckel W E. Approximate Method for Predicting Form and Location of Detached Shock Waves Ahead of Plane or Axially Symmetric Bodies[R]. NACA TN 1921, 1949.
[17] Osmon R V. Improved Methods of Spillage Drag Prediction for Two-Dimensional Inlets[J]. Journal of Aircraft, 1968, 5(3): 254-260.
[18] Malan P, Brown E F. Inlet Drag Prediction for Aircraft Conceptual Design[J]. Journal of Aircraft, 2012, 31(3): 616-622.
[19] Hawkins J E, Kirkland F P, Turner R L. Inlet Spillage Drag Tests and Numerical Flow-Field Analysis at Subsonic and Transonic Speeds of a 1/8 Scale, Two-Dimensional, External-Compression, Variable-Geometry, Supersonic Inlet Configuration[R]. NASA-CR-2680.
[20] 贾琳渊, 陈玉春, 黄兴, 等. 1+1/2对转涡轮对双轴混排涡扇发动机整机特性影响的研究[J]. 推进技术, 2013, 34(11): 1459-1465. (JIA Lin-yuan, CHEN Yu-chun, HUANG Xing, et al. Effect of 1+1/2 Counter Rotating Turbine on Twin-Shaft Mixed Turbofan Engine[J]. Journal of Propulsion Technology, 2013, 34(11): 1459-1465.)
[21] 梁振欣. 射流预冷涡轮动力总体性能研究[D]. 西安:西北工业大学, 2011.
[22] 陈玉春, 徐思远, 杨云铠, 等. 改善航空发动机特性计算收敛性的方法[J]. 航空动力学报, 2008, (12): 2242-2248.
[23] 聂恰耶夫 Ю Н. 航空动力装置控制规律与特性[M]. 单凤桐, 程振海,译. 北京:国防工业出版社, 1999.　　　　　　　　　　　　　　收稿日期:2016-09-03；修订日期:2016-11-04。作者简介:贾琳渊,男,博士生,研究领域为涡轮发动机总体性能仿真与分析。E-mail: jlynpu@mail.nwpu.edu.cn(编辑:史亚红)