航空发动机风车不平衡适航符合性验证  

Airworthiness Compliance Demonstration for Aeroengine Windmilling Imbalance

作　　者：贾惟[1] 何文博[1] 刘帅[1] 

机构地区：[1]中国民航大学天津市民用航空器适航与维修重点实验室,天津300300

出　　处：《航空发动机》2016年第6期95-101,共7页Aeroengine

基　　金：中国民航大学科研启动基金(2014QD06X)资助

摘　　要：CCAR 25部《运输类飞机适航标准》对航空发动机的持续转动提出明确要求,即航空发动机的持续转动不会危及飞行安全。参考美国联邦航空局(FAA)第25-141号修正案,详细分析了FAR 25.362条款对发动机失效载荷的要求及其适用的符合性验证方法。通过对服役数据进行统计学分析研究了风车不平衡符合性验证条件。结果表明,不平衡量等于1.0与1 h备降时间组合、不平衡量等于1.0与最大不超过3 h备降时间组合可以满足安全性的要求,在此基础上从载荷、强度、耐久性、系统完整性以及人为因素5个方面开展符合性验证。采用完整的飞机模型和发动机模型进行符合性验证是可以接受的。机体结构模型要通过地面振动试验进行校验,发动机模型要通过风扇叶片脱落试验进行校验。CCAR Part 25 presents a clear requirement for aeroengine continued rotation which states that the continued rotation of aeroengine can not jeopardize the safety of the airplane. Requirements of engine failure loads and relevant methods of compliance were both analyzed in details according to FAR 25.362 which was issued by Federal Aviation Administration in amendment 25-141. A compliance demonstration criterion was obtained through statistical analysis of service data. Results show that imbalance design fraction equals to 1.0 combined with windmilling time equals to 1 hour and imbalance design fraction equals to 1.0 combined with windmilling time less than 3 hours meet the requirements of safety targets. Based on these two criteria, compliance demonstration should be carried out from five aspects including loads, strength, durability, system integrity and human factors. A complete integrated airframe and engine analytical model for compliance demonstration are acceptable. Airframe structure model should be validated by ground vibration test and engine structure model should be validated by fan blade off test.

关 键 词：持续转动 风车不平衡 不平衡量 机体结构模型 发动机结构模型 地面振动试验 风扇叶片脱落试验 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]