新研民用涡轴发动机整机包容适航试验研究

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

doi:10.7527/S1000-6893.2026.33945

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DOI: https://doi.org/10.7527/S1000-6893.2026.33945

新研民用涡轴发动机整机包容适航试验研究

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

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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

网络出版日期: 2026-08-21

基金资助

某民用涡轴发动机工程

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

LI Gai-Qi ,
WANG Jian-Fang ,
FENG Jian-Wen ,
MA Dong-Yang ,
XU Ming-Wen ,
JIANG Xiao-Wei ,
LIU Jian-Xin ,
LIU Shao-Rong

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Received date: 2026-05-25

Revised date: 2026-08-15

Online published: 2026-08-21

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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

本文引用格式

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, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33945

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

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