发动机结构审定的基本原理及其应用

张弓; 何歆; 冯建文; 甄博

doi:10.13224/j.cnki.jasp.20210638

发动机结构审定的基本原理及其应用

doi: 10.13224/j.cnki.jasp.20210638

中国民用航空适航审定中心结构审定室，北京 100102

详细信息

作者简介:
张弓（1983-），男，高级工程师，博士，主要从事发动机结构审定方面的研究。E-mail：zhanggong_acc@caac.gov.cn

通讯作者:
冯建文（1984-），男，高级工程师，博士，主要从事发动机结构审定方面的研究。E-mail：fengjw_acc@caac.gov.cn

中图分类号: V231
计量
- 文章访问数: 762
- HTML浏览量: 559
- PDF量: 72
- 被引次数: 0
出版历程
- 收稿日期: 2021-11-08
- 网络出版日期: 2023-05-12

Principle and application of engine structure certification

Structure Certification Division，Airworthiness Certification Center， Civil Aviation Administration of China，Beijing 100102，China

摘要

摘要:
为了在型号审定中更好地形成从要求制定、验证表明到使用中保持发动机安全性的闭环系统，通过综合失效设计管理、应力-强度干涉、典型结构特征和运行特性研究了发动机结构审定的基本原理，并建立了相应的工作模型。采用工作模型对发动机结构审定所涉及的典型失效模式进行分析，确定了12个条款的全部工作模型关键点，揭示了根据零部件失效后果确定条款适用对象，根据失效模式可控制性确定具体要求的条款内在关联关系。以典型专用条件和豁免为对象说明了限寿件和振动试验条款的安全意图及偏离处理中基本原理的应用。
- 适航 /
- 民用航空发动机 /
- 型号审定 /
- 审定原理 /
- 发动机结构
Abstract:
The basic principle and workflow of civil engine structure certification was established to form a closed-loop system from airworthiness requirement formulation and compliance verification to maintain engine safety in service, by using failure design management, stress-strength interference model, and study of characteristics and operation conditions on typical structure component. Engine part failure modes were analyzed following the established workflow, with the key points of the 12 engine structure regulatory sections identified. Consequence and controllability of each potential failure mode determined the applicable regulatory requirements for each engine part as well as their intrinsic associations. A special condition case and an exemption case were employed as two examples to further discuss the safety intention of the regulatory requirements and application of the principle in deviation treatment.
- airworthiness /
- civil aero-engine /
- type certification /
- certification principle /
- engine structure

HTML

图 1 发动机结构审定的主要工作内容

Figure 1. Main content of engine structure certification

下载: 全尺寸图片幻灯片

图 2 失效管理方法

Figure 2. Failure management method

下载: 全尺寸图片幻灯片

图 3 广义应力-强度干涉模型

Figure 3. Generalized stress-strength interference model

下载: 全尺寸图片幻灯片

图 4 发动机结构审定原理的核心内容

Figure 4. Key elements of engine structural certification principle

下载: 全尺寸图片幻灯片

图 5 涡轴16发动机扭矩管^[38]

Figure 5. Torque tube of WZ16 turboshaft engine^[38]

下载: 全尺寸图片幻灯片

图 6 某型发动机压气机叶片裂纹^[39]

Figure 6. Cracking in a compressor blade of an engine^[39]

下载: 全尺寸图片幻灯片

图 7 某压气机叶片裂纹萌生及扩展机理

Figure 7. Compressor blade crack initiation and propagation mechanism

下载: 全尺寸图片幻灯片

图 8 某型发动机临时豁免的主要验证工作

Figure 8. Verification flowchart for an engine’s temporary deviation

下载: 全尺寸图片幻灯片

表 1 CCAR 33规章风险矩阵

Table 1. Risk matrix in CCAR 33

严重程度	失效概率
严重程度	10⁻³～10⁻⁵ （可能）	10⁻⁵～10⁻⁷ （微小可能）	10⁻⁷～10⁻⁹ （极不可能）
危害性后果	不可接受	不可接受	适用于限寿件
重大后果	不可接受	可接受	可接受
轻微后果	可接受	可接受	可接受

下载: 导出CSV

表 2 发动机结构审定条款的原理工作模型关键点

Table 2. Key point of principle working model on engine structure certification regulation

条款	适用对象	主要失效模式	干涉模型关键点
33.15材料	整机	设计许用值无法满足所需材料性能要求	广义强度一致性
33.17防火	火区内零件	部件的超快速氧化	抗火焰能力
33.19耐用性	整机	多种形式耦合	多个广义应力-广义强度
33.23发动机的安装构件和结构	安装节	屈服/静态断裂	应力-屈服强度/抗拉强度
33.27涡轮、压气机、风扇和涡轮增压器转子	发动机转子	屈服/静态断裂/蠕变	应力-屈服强度/抗拉强度
33.62应力分析	发动机转子	多种形式耦合	多个广义应力-广义强度
33.63振动	整机	高周疲劳断裂	多个广义应力-广义强度
33.64发动机静承压件	静子承压件	屈服/静态断裂/蠕变	应力-屈服强度/抗拉强度
33.70发动机限寿件	限寿件	低循环疲劳/其他	低周应力应变-疲劳强度
33.83振动试验	转子件和流道件	高周疲劳断裂	振动应力/稳态应力-持久极限
33.88发动机超温试验	涡轮部件	屈服/蠕变断裂	应力-屈服强度
33.94叶片包容性和转子不平衡试验	机匣和整机	多种形式耦合	冲击能力-包容能力

下载: 导出CSV

参考文献(43)

[1]	Federal Aviation Administration. ORDER 8000.80A: Aviation safety (AVS) chief scientific and technical advisor (CSTA) and senior technical specialist (STS) program[R]. Washington DC: Federal Aviation Administration, 2010.
[2]	Aviation Rule Making Advisory Committee. Alternate test to 14CFR33.87 endurance test[R]. Washington DC: Aviation Rule Making Advisory Committee, 2017.
[3]	Federal Aviation Administration. Letter to ARAC for endurance test clarification[R]. Washington DC: Federal Aviation Administration, 2020.
[4]	Aviation Rule Making Advisory Committee. Engine harmonization working group. turbofan bird ingestion regulation engine harmonization working group report[R]. Washington DC: Aviation Rule Making Advisory Committee, 2015.
[5]	Federal Aviation Administration. Experimental guidelines for the design of turbine rotor fragment containment rings[R]. Washington DC: Federal Aviation Administration, 1988.
[6]	Federal Aviation Administration. Design procedures and analysis of turbine rotor fragment hazard containment[R]. Washington DC: Federal Aviation Administration, 1996.
[7]	Federal Aviation Administration. FAA T53-L-13L turbine fragment containment test[R]. Washington DC: Federal Aviation Administration, 1998.
[8]	Federal Aviation Administration. Fiber-reinforced structures for turbine engine rotor fragment containment[R]. Washington DC: Federal Aviation Administration, 1999.
[9]	Federal Aviation Administration. Turbine rotor material design[R]. Washington DC: Federal Aviation Administration, 2000.
[10]	Sub-team to the Aerospace Industries Association Rotor Integrity Sub-Committee. The development of anomaly distributions for aircraft engine titanium disk alloys[C]//Proceedings of 38th Structures, Structural Dynamics, and Materials Conference. Reston, US: AIAA, 1997: 2543-2553.
[11]	Federal Aviation Administration. Turbine engine fan disk crack detection test[R]. Washington DC: Federal Aviation Administration, 2004.
[12]	Federal Aviation Administration. Fatigue crack growth database for damage tolerance analysis[R]. Washington DC: Federal Aviation Administration, 2005.
[13]	CORRAN R, GORELIK M, LEHMANN D, et al. The development of anomaly distributions for machined holes in aircraft engine rotors[C]//Proceedings of ASME Turbo Expo: Power for Land, Sea, & Air. Barcelona, US: ASME, 2006: 941-950.
[14]	Federal Aviation Administration. Guidelines to minimize manufacturing induced anomalies in critical rotating parts[R]. Washington DC: Federal Aviation Administration, 2006.
[15]	Federal Aviation Administration. Turbine rotor material design: Phase Ⅱ[R]. Washington DC: Federal Aviation Administration, 2007.
[16]	Federal Aviation Administration. Characterization and structural behavior of braided composites[R]. Washington DC: Federal Aviation Administration, 2009.
[17]	Federal Aviation Administration. Development of a generic gas turbine engine fan blade-out full-fan rig model[R]. Washington DC: Federal Aviation Administration, 2015.
[18]	Federal Aviation Administration. Summary report: joint federal aviation administration-air force workshop on qualification/certification of additively manufactured parts[R]. Washington DC: Federal Aviation Administration, 2016.
[19]	Federal Aviation Administration. Probabilistic integrity and risk assessment of turbine engines[R]. Washington DC: Federal Aviation Administration, 2018.
[20]	Federal Aviation Administration. Probabilistic design for rotor integrity[R]. Washington DC: Federal Aviation Administration, 2018.
[21]	Federal Aviation Administration. The evaluation of cold dwell fatigue in Ti-6242[R]. Washington DC: Federal Aviation Administration, 2018.
[22]	European Commission. Flightpath 2050: Europe’s vision for aviation report of high-level group on aviation research[R]. Brussels, Belgium: European Union, 2011.
[23]	European Aviation Safety Agency. Completeness and timely availability of instructions for continued airworthiness[R]. Cologne, Germany: European Aviation Safety Agency, 2017.
[24]	European Aviation Safety Agency. Critical parts-lifing shortfall[R]. Cologne, Germany: European Aviation Safety Agency, 2017.
[25]	European Aviation Safety Agency. The integrity of nickel powder metallurgy rotating critical parts for gas turbines[R]. Cologne, Germany: European Aviation Safety Agency, 2017.
[26]	European Aviation Safety Agency. Turbine engines: high pressure turbine shaft loss of load and rotor integrity[R]. Cologne, Germany: European Aviation Safety Agency, 2020.
[27]	European Aviation Safety Agency, Federal Aviation Administration. Report of the engine/aircraft certification working group[R]. Cologne, Germany: European Aviation Safety Agency, 2017.
[28]	Federal Aviation Administration. Joint FAA-EASA workshop on qualification and certification of metal additively manufactured parts[R]. Washington DC: Federal Aviation Administration, 2020.
[29]	European Aviation Safety Agency. Notice of proposed amendment 2021-13[R]. Cologne, Germany: European Aviation Safety Agency, 2021.
[30]	丁水汀,张弓,蔚夺魁,等. 航空发动机适航概率风险评估方法研究综述[J]. 航空动力学报,2011,26(7): 1441-1451. doi: 10.13224/j.cnki.jasp.2011.07.011 DING Shuiting,ZHANG Gong,YU Duokui,et al. Review of probabilistic risk assessment on aero-engine airworthiness[J]. Journal of Aerospace Power,2011,26(7): 1441-1451. (in Chinese) doi: 10.13224/j.cnki.jasp.2011.07.011
[31]	王大伟, 邹田春, 王伟, 等. 航空发动机适航标准33.70条款技术解析[C]//航空安全与装备维修技术学术研讨会论文集: 航空安全与装备维修技术. 北京: 国防工业出版社, 2014: 86-94.
[32]	何歆, 张弓. 民用航空发动机适航要求解读(结构审定)[M]. 北京: 航空工业出版社, 2019.
[33]	JOHNSON S B, GORMLEY T J, KESSLER S S, et al. System health management (with aerospace applications)[M]. West Sussex, UK: John Wiley and Sons Limited, 2011.
[34]	MAURYA A, KUMAR D. Reliability of safety-critical systems: a state-of-the-art review[J]. Quality and Reliability Engineering International, 2020, 36(7): 2547-2568.
[35]	高镇同, 熊峻江. 疲劳可靠性[M]. 北京: 北京航空航天大学出版社, 2000.
[36]	陈光. 航空发动机结构设计分析[M]. 北京: 北京航空航天大学出版社, 2006.
[37]	宋兆弘, 航空燃气涡轮发动机强度设计[M]. 北京: 北京航空航天大学出版社, 2008
[38]	张弓, 冯建文, 甄博, 等. 涡轴16发动机结构审定[M]. 北京: 航空工业出版社, 2021.
[39]	Transport Safety Investigation Bureau. Boeing B787, registration 9V-OJF engine failure[R]. Singapore City: Transport Safety Investigation Bureau, 2017.
[40]	NICHOLAS T. High cycle fatigue: a mechanics of materials perspective[M]. Oxford, UK: Elsevier, 2006.
[41]	ARMSTRONG E K,STEVENSON R E. Some practical aspects of compressor blade vibration[J]. The Journal of the Royal Aeronautical Society,1960,64: 117-130.
[42]	ARMSTRONG E K. Recent blade vibration techniques[J]. Journal of Engineering for Power,1967,89(3): 437-444.
[43]	KNAPPETT D,GARCIA J. Blade tip timing and strain gauge correlation on compressor blades[J]. Proceedings of the Institution of Mechanical Engineers: Part G Journal of Aerospace Engineering,2008,222(4): 497-506. doi: 10.1243/09544100JAERO257