新研民用涡轴发动机整机包容适航试验研究

doi:10.7527/S1000-6893.2026.33945

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

新研民用涡轴发动机整机包容适航试验研究

李概奇¹,王建方¹,冯建文²,马东阳¹,许明文¹,蒋晓炜¹,刘建新¹,刘少戎¹

1. 中国航发湖南动力机械研究所
2. 中国民用航空适航审定中心

收稿日期:2026-05-25 修回日期:2026-08-15 出版日期:2026-08-21 发布日期:2026-08-21
通讯作者: 马东阳
基金资助:
某民用涡轴发动机工程

Research on Whole-Engine Containment Certification Tests for a Newly Developed Civil Turboshaft Engine

Received:2026-05-25 Revised:2026-08-15 Online:2026-08-21 Published:2026-08-21
Contact: Dong-Yang MA

摘要/Abstract

摘要： 整机包容试验是民用航空发动机适航取证中的高难度、高风险、高成本试验项目。本文以某新研民用涡轴发动机为平台，根据适航要求和试验一次成功目标，提出整机包容设计与试验一体化正向研究的技术思路，构建了解决动力涡轮工作叶片脱落转速、脱落截面、机匣包容结构和大冲击载荷下涡轮支承、传力路径、安装节承力等方面技术难点的设计方案；新研了高速自动金刚石切轴装置，提出了燃气发生器恒物理转速闭环控制模式，通过切割动力连接轴让动力涡轮失去负载，成功实现动力涡轮工作叶片在预定转速范围内飞转脱落。发动机在工作叶片脱落后，出现了明显喘振、强烈喷火、动力涡轮转速异常上升等流-固-热-声耦合特殊现象，主、辅安装节载荷和机匣振动幅值急剧增大。发动机分解检查后发现燃气发生器结构完整，但动力涡轮部件受损严重，动力涡轮工作叶片全部脱落，动力涡轮传动轴与中心拉杆之间有明显碰摩痕迹，过渡段支板前、后缘局部出现裂纹，动力涡轮机匣局部变形严重。试验结果表明动力涡轮机匣没有被碎片击穿、安装系统未失效，发动机停车后未发生不可控火情，验证了新研涡轴发动机具有可靠的整机包容能力。

关键词: 涡轴发动机, 动力涡轮, 包容试验, 喘振, 发动机适航

Abstract: The whole engine containment test is a high-difficulty, high-risk, and high-cost test item in the civil aviation airworthiness certification. Based on a newly developed civil turboshaft engine platform, this paper proposes an integrated technical research approach for whole engine containment design and testing from a forward development perspective, according to airworthiness requirements and the goal of a single successful test. It constructs design solutions to address technical challenges such as blade release speed, working blade release cross-section, engine casing containment structure, and support layout under high-impact loads, load paths, and turbine bearing systems. A high-speed automatic diamond cutting shaft device was developed, and a constant physical speed closed-loop control mode for gas generator was proposed. By cutting the power connection shaft to unload the power turbine, working blades of power turbine were successfully released and spun off within the predetermined speed range. After working blades released, the engine exhibited obvious surging, severe flameout, and abnormal rapid increase in power turbine speed. The vibration amplitude of the main and auxiliary mounting loads and the engine casing increased sharply. Post-test inspection after engine disassembly revealed that gas generator structure was intact, the power turbine components suffered severe damage，all blades of power turbine detached, excessive rubbing occurred between power turbine drive shaft and center pull rod, local cracks appeared at the front and rear edges of the transition section support plate, power turbine casing suffered severe deformation. The test results indicate that the power turbine casing was not penetrated by fragments, the mounting system did not fail, and no uncontrollable fire occurred after engine shutdown, verifying that the newly developed turboshaft engine possesses reliable whole engine containment capability.

Key words: turboshaft engine, power turbine, containment test, surge, engine airworthiness

中图分类号:

V231. 3

李概奇王建方冯建文马东阳许明文蒋晓炜刘建新刘少戎. 新研民用涡轴发动机整机包容适航试验研究[J]. 航空学报, doi: 10.7527/S1000-6893.2026.33945.

参考文献

[1]陈光. 航空发动机结构设计分析（第2版）[M]. 北京: 北京航空航天大学出版社, 2014: 1-10.
CHEN G. Structural design and analysis of aero-engines (2nd ed.)[M]. Beijing: Beihang University Press, 2014: 1-10. (in Chinese)
[2]COSME N, CHEVROLET D, BONINI J, et al. Prediction of engine loads and damages due to blade-off event[C]//Proceedings of the 43rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Denver, US: AIAA, 2002: AIAA-2002-1666.
[3]马艳红, 陈璐璐, 张大义, 等. 航空发动机转子系统结构效率评估参数及计算方法[J]. 航空动力学报, 2013, 28(7): 1598-1606.
MA Y H, CHEN L L, ZHANG D Y, et al. Structural efficiency evaluation parameters and calculation method for aero-engine rotor system[J]. Journal of Aerospace Power, 2013, 28(7): 1598-1606. (in Chinese)
[4]Air Accidents Investigation Branch (AAIB). Bell 407, G-CRAZ, uncontained engine failure and forced landing, Long Marston, Warwickshire, 24 June 2020[R/OL]. (2021-09-30). https://www.aaib.gov.uk.
[5]中国民用航空局. 航空发动机适航规定: CCAR-33-R2[S]. 北京: 中国民用航空局, 2012.
CAAC. Airworthiness standards for aircraft engines: CCAR-33-R2[S]. Beijing: Civil Aviation Administration of China, 2012. (in Chinese)
[6]中国民用航空局. 运输类飞机适航标准: CCAR-25-R4[S]. 北京: 中国民用航空局, 2011.
CAAC. Airworthiness standards for transport category airplanes: CCAR-25-R4[S]. Beijing: Civil Aviation Administration of China, 2011. (in Chinese)
[7]中国民用航空局航空器适航审定司. 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, 2022.
CAAC Aircraft Certification Department. Advisory circular for aero-engine certification: AC-33-AA-2022-01[S]. Beijing: Civil Aviation Administration of China, 2022. (in Chinese)
[8]CARNEY K S, LAWRENCE C, CARNEY D V. Aircraft engine blade-out dynamics[C]//Proceedings of the 7th International LS-DYNA Users Conference. Dearborn, US, 2003.
[9]SHMOTIN Y, GABOV D, RYABOV A, et al. Numerical analysis of aircraft engine fan blade-out[C]//Proceedings of the 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Sacramento, US: AIAA, 2006: AIAA-2006-4620.
[10]HUSBAND J B. Developing an efficient FEM structural simulation of a fan blade off test in a turbofan jet engine[D]. Saskatoon: University of Saskatchewan, 2007.
[11]洪杰, 栗天壤, 王永峰, 等. 叶片丢失激励下航空发动机柔性转子系统的动力学响应[J]. 航空动力学报, 2018, 33(2): 257-264.
HONG J, LI T R, WANG Y F, et al. Dynamic response of aero-engine flexible rotor system under blade loss excitation[J]. Journal of Aerospace Power, 2018, 33(2): 257-264. (in Chinese)
[12]魏静, 白培鑫, 杨攀武, 等. 叶片丢失对齿轮涡扇发动机风扇轴振动影响的研究[J]. 振动工程学报, 2018, 31(2): 226-237.
WEI J, BAI P X, YANG P W, et al. Study on vibration characteristics of fan shaft of geared turbofan engine with sudden imbalance caused by blade off[J]. Journal of Vibration Engineering, 2018, 31(2): 226-237. (in Chinese)
[13]彭刚, 李超, 曹冲, 等. 冲击激励转子系统动力学响应及安全性设计[J]. 推进技术, 2018, 39(5): 1111-1121.
PENG G, LI C, CAO C, et al. Dynamic response and safety design of rotor system with impact excitation[J]. Journal of Propulsion Technology, 2018, 39(5): 1111-1121. (in Chinese)
[14]刘璐璐, 赵振华, 陈伟, 等. 叶片丢失后发动机整机响应模拟试验与仿真[J]. 航空动力学报, 2018, 33(2): 290-298.
LIU L L, ZHAO Z H, CHEN W, et al. Simulated test and numerical simulation of aero-engine whole engine response during blade out event[J]. Journal of Aerospace Power, 2018, 33(2): 290-298. (in Chinese)
[15]何庆. 航空发动机机匣包容性机理及数值仿真方法研究[D]. 杭州: 浙江大学, 2012.
HE Q. Research on the mechanism and simulation methodology development for aero-engine casing/blade containment[D]. Hangzhou: Zhejiang University, 2012. (in Chinese)
[16]MARTINO A A, MANGANO G J. AELCEF-A tool to make rotor burst containment a reality[R]. SAE Technical Paper 670332, 1967.
[17]WILBECK J S. Tests of spinning turbine fragment impact on casing models[J]. Nuclear Engineering and Design, 1984, 77(3): 321-329.
[18]GERSTLE J H. Analysis of rotor fragment impact on ballistic fabric engine burst containment shields[J]. Journal of Aircraft, 1975, 12(4): 388-393.
[19]MARTINO A A. Designing rotor burst protection[C]//Proceedings of the ASME International Gas Turbine Conference and Products Show. Houston, US: ASME, 1971: 71-GT-70.
[20]HORSLEY J. The 'Rolls-Royce' way of validating fan integrity[C]//Proceedings of the AIAA/SAE/ASME/ASEE 29th Joint Propulsion Conference and Exhibit. Monterey, US: AIAA, 1993: AIAA-1993-2602.
[21]ROY P A, MEGUID S A. Containment of blade shedding in gas turbine engines: part I-design and development of a scaled down test rig[J]. International Journal of Mechanics and Materials in Design, 2021, 17(1): 3-12.
[22]ROY P A, MEGUID S A. Containment of blade shedding in gas turbine engines: part II-experimental and numerical investigations[J]. International Journal of Mechanics and Materials in Design, 2021, 17(1): 13-24.
[23]SALVINO J T, DELUCIA R A, RUSSO T. Experimental guidelines for the design of turbine rotor fragment containment rings: ADA203557[R]. Fort Belvoir, US: Defense Technical Information Center, 1988.
[24]HE Q, XUAN H J, LIU L L, et al. Perforation of aero-engine fan casing by a single rotating blade[J]. Aerospace Science and Technology, 2013, 25(1): 234-241.
[25]XUAN H J, WU R R. Aeroengine turbine blade containment tests using high-speed rotor spin testing facility[J]. Aerospace Science and Technology, 2006, 10(6): 501-508.
[26]HE Q, XIE Z, XUAN H J, et al. Multi-blade effects on aero-engine blade containment[J]. Aerospace Science and Technology, 2016, 49: 101-111.
[27]刘璐璐, 宣海军, 张娜. 航空发动机复合材料机匣叶片包容性研究[J]. 工程力学, 2013, 30(S1): 314-319.
LIU L L, XUAN H J, ZHANG N. Investigation on blade containment of aero-engine composite case[J]. Engineering Mechanics, 2013, 30(S1): 314-319. (in Chinese)
[28]张晓峰, 宣海军, 吴荣仁. 航空发动机叶片包容模拟试验与数值仿真研究[J]. 航空发动机, 2005, 31(4): 39-42.
ZHANG X F, XUAN H J, WU R R. Experimental investigation and numerical simulation of aeroengine blade containment[J]. Aeroengine, 2005, 31(4): 39-42. (in Chinese)
[29]张伯熹, 宣海军, 吴荣仁. 航空发动机涡轮叶片包容模拟试验研究[J]. 机械工程师, 2006(10): 114-116.
ZHANG B X, XUAN H J, WU R R. Research on aero-engine turbine blade containment experiment[J]. Mechanical Engineer, 2006(10): 114-116. (in Chinese)
[30]宣海军, 洪伟荣, 吴荣仁. 航空发动机涡轮叶片包容试验及数值模拟[J]. 航空动力学报, 2005, 20(5): 762-767.
XUAN H J, HONG W R, WU R R. Aero-engine turbine blade containment tests and numerical simulation[J]. Journal of Aerospace Power, 2005, 20(5): 762-767. (in Chinese)
[31]柴象海, 张晓云, 侯亮, 等. 航空发动机风扇机匣包容性等效试验与分析方法[J]. 振动与冲击, 2016, 35(2): 162-167.
CHAI X H, ZHANG X Y, HOU L, et al. The equivalent test and simulation verification for fan containment case of aero engine[J]. Journal of Vibration and Shock, 2016, 35(2): 162-167. (in Chinese)
[32]YANG B. Blade containment evaluation of civil aircraft engines[J]. Chinese Journal of Aeronautics, 2013, 26(1): 9-16.
[33]白水. 遄达800型风扇叶片包容试验成功[J]. 国际航空, 1994(4): 64.
BAI S. The fan blade containment test of Trent 800 engine was finished successfully[J]. International Aviation, 1994(4): 64. (in Chinese)
[34]宣海军, 陆晓, 洪伟荣, 等. 航空发动机机匣包容性研究综述[J]. 航空动力学报, 2010, 25(8): 1860-1870.
XUAN H J, LU X, HONG W R, et al. Review of aero-engine case containment research[J]. Journal of Aerospace Power, 2010, 25(8): 1860-1870. (in Chinese)
[35]李概奇, 马东阳, 李杜, 等. 新研民用涡轴发动机起飞状态喘振试验[J]. 航空学报, 2023, 44(14): 628190.
LI G Q, MA D Y, LI D, et al. Surge test on newly developing civil turboshaft engine under take-off condition[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628190. (in Chinese)

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

新研民用涡轴发动机整机包容适航试验研究

Research on Whole-Engine Containment Certification Tests for a Newly Developed Civil Turboshaft Engine

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	张悦, 杨刚, 谭慧俊, 张晗天, 庞明池, 张龙芝, 高夏豪. 外并联型进气道模态转换过程中低速通道再起动特性[J]. 航空学报, 2026, 47(6): 132842-132842.
[2]	李概奇, 赵尊盛, 马东阳, 贺丹, 刘建新, 刘少戎, 吴楠. 新研民用涡轴发动机防冰设计技术[J]. 航空学报, 2026, 47(11): 633025-633025.
[3]	周晗, 陈芊, 汪虹余, 史昊蓝, 魏鹏轩, 李嘉诚, 张天宏, 盛汉霖. 含失稳模拟的高通流双变循环发动机动态模型[J]. 航空学报, 2025, 46(14): 131436-131436.
[4]	李概奇, 田骏丹, 吴晶峰, 赵尊盛, 杨洋, 刘梦妮. 新研民用涡轴发动机结冰适航试验[J]. 航空学报, 2025, 46(12): 131388-131388.
[5]	郭振东, 李豪杰, 宋立明, 张华良, 尹钊. 基于自适应稀疏混沌多项式的鲁棒性优化方法[J]. 航空学报, 2024, 45(19): 630273-630273.
[6]	王四季, 张羽薇, 黄开明, 吕彪, 赵海凤, 王虎, 廖明夫. 基于改进粒子群算法的直升机动力涡轮转子系统优化方法[J]. 航空学报, 2024, 45(1): 228608-228608.
[7]	李概奇, 马东阳, 李杜, 刘少戎, 杨艳美. 新研民用涡轴发动机起飞状态喘振试验[J]. 航空学报, 2023, 44(14): 628190-628190.
[8]	刘庭申, 冯立好, 王晋军. S形进气道锤激波的动态特性[J]. 航空学报, 2018, 39(2): 121339-121339.
[9]	伍恒, 李本威, 张赟, 杨欣毅. 基于QPSO-ELM的某型涡轴发动机起动过程模型辨识[J]. 航空学报, 2018, 39(11): 322251-322261.
[10]	李志平, 王孟琦. 进气畸变下航空发动机失速/喘振适航审定方法[J]. 航空学报, 2015, 36(9): 2947-2957.
[11]	王健康, 张海波, 黄向华, 陆波. 基于直升机/涡轴发动机综合仿真平台的发动机非线性模型预测控制[J]. 航空学报, 2012, (3): 402-411.
[12]	孙见忠, 左洪福, 詹志娟, 刘鹏鹏. 涡轴发动机尾气静电监测信号影响因素分析[J]. 航空学报, 2012, (3): 412-420.
[13]	王健康, 张海波, 黄向华, 段姝婧. 基于在线滚动LS-SVR的涡轴发动机混合预测控制[J]. 航空学报, 2012, 33(10): 1755-1764.
[14]	张海波;孙立国;孙健国. 直升机/涡轴发动机综合系统鲁棒抗扰控制设计[J]. 航空学报, 2010, 31(5): 883-892.
[15]	李留刚;谭慧俊;孙姝;张悦. 二元高超声速进气道不起动状态的信号特征及预警[J]. 航空学报, 2010, 31(12): 2324-2331.