Design and verification of airworthiness compliance of equivalent endurance test cycle of turbofan engine
-
摘要:
为优化涡扇发动机的持久试车谱,减少试验过程中的三红线构型改装次数,对持久试车谱的等效设计与符合性验证方法进行研究。分析了持久原始试车谱及其不同阶段的损伤特征,以发动机零部件的等效损伤为原则,以减少三红线构型改装次数为目的,提出一种基于等效损伤原则的等效持久试车谱适航符合性设计与验证方法,并以某型发动机高压涡轮叶片为例提出模拟特征试验件设计方案。所提方法可作为整机持久适航取证试验试车谱优化工作的参考,所提方案可支撑模拟特征试验件的等效损伤试验。
Abstract:In order to optimize the endurance test cycle of the turbofan engine and reduce the number of triple red-line configuration modifications during the test, the equivalent design and compliance verification method of the endurance test cycle were studied. The damage characteristics of the original endurance test cycle and endurance test cycle at different stages were analyzed, and a design and verification method for the airworthiness compliance of the equivalent endurance test cycle based on the principle of equivalent damage was proposed to reduce the number of triple red-line configuration modifications. A simulated characteristic test piece was designed by taking the high-pressure turbine blade of a certain engine as an example. The proposed design and verification method for the airworthiness compliance of the equivalent endurance test cycle of a turbofan engine can be used as a reference for the optimization of the test cycle of the endurance airworthiness certification test of the whole engine, and the proposed design scheme of the simulated characteristic test piece can support the equivalent damage test of the simulated characteristic test piece.
-
Key words:
- airworthiness /
- endurance test /
- test cycle /
- equivalent damage /
- triple red-line
-
表 1 持久试验三红线状态运行时间
Table 1. Triple red-line operation time in endurance test
分段 三红线
时间/min循环数 MTO三红线
总时间/minMCT三红线
总时间/min三红线
总时间/minA 30 25 750 0 750 B1 30 15 0 450 450 B2 30 10 300 0 300 C 90 25 0 2250 2250 D 0 25 0 0 0 E 3 25 75 0 75 -
[1] 中国民用航空局. 航空发动机适航规定: CCAR-33R2[S]. 北京: 中国民用航空局, 2011.Civil Aviation Administration of China. Aircraft engine airworthiness regulations: CCAR-33R2 [S]. Beijing: Civil Aviation Administration of China, 2011(in Chinese). [2] Civil Aeronautics Board. Aircraft engine airworthiness: CAR13[S]. Washington, D. C. : Civil Aeronautics Board, 1952: 4. [3] 王晓明, 綦蕾. 民用航空涡轮发动机持久试验条款发展历程[J]. 航空动力学报, 2021, 36(2): 431-439.WANG X M, QI L. Development history of civil turbine engine endurance test requirements[J]. Journal of Aerospace Power, 2021, 36(2): 431-439(in Chinese). [4] Federal Aviation Administration. Airworthiness standards: Aircraft engines FAR Part 33 amendment 33-32[S]. Washington, D.C.: Federal Aviation Administration, 2012. [5] MOSKOVIC R, LINGHAM I J, CROCKER A G, et al. An experimental and theoretical consideration of the effect of prior creep damage on the heat affected zone fracture toughness of CrMoV steel[J]. Engineering Fracture Mechanics, 2004, 71(4-6): 587-599. [6] KAFTELEN H, BALDAN A. Comparative creep damage assessments using the various models[J]. Journal of Materials Science, 2004, 39(13): 4199-4210. [7] CHATZIIOANNOU K, KARAMANOS S A, HUANG Y E. Coupled numerical simulation of low-cycle fatigue damage in metal components[J]. Engineering Structures, 2021, 229: 111536. [8] JEONG I H, PARK Y M, BAE M K, et al. Low-cycle fatigue characteristics of SNCM 420H steel used to fabricate ships’ engines[J]. Modern Physics Letters B, 2019, 33(14/15): 1940035. [9] 许罗鹏, ZHOU M, 王清远. DZ125合金超高周疲劳微观裂纹萌生机制[J]. 工程科学与技术, 2018, 50(6): 245-250.XU L P, ZHOU M, WANG Q Y. Micro-crack initiation mechanism of DZ125 Ni-based alloy during very high cycle fatigue[J]. Advanced Engineering Sciences, 2018, 50(6): 245-250(in Chinese). [10] MATSUZAKI T, SUGIURA R, NAGUMO Y, et al. Crack growth characteristic and damage evaluation under creep-fatigue interactive condition for W-added high-Cr steel[J]. Materials Transactions, 2013, 54(12): 2215-2224. [11] XU L Y, ZHAO L, GAO Z F, et al. A novel creep–fatigue interaction damage model with the stress effect to simulate the creep–fatigue crack growth behavior[J]. International Journal of Mechanical Sciences, 2017, 130: 143-153. [12] Federal Aviation Administration. Engine over-torque test, calibration test, endurance test, and teardown inspection for turbine engine certification (33.84, 33.85, 33.87, 33.93): AC 33.87-1A [R]. Washington, D. C. : Federal Aviation Administration, 2015. [13] 白国娟, 侯乃先, 杨坤, 等. 粉末高温合金涡轮盘初始缺陷概率模型研究[J]. 机械设计与制造, 2021, 360(2): 252-256.BAI G J, HOU N X, YANG K, et al. Study on the initial defect probability model of powdered high temperature alloy turbine disc[J]. Mechanical Design and Manufacture, 2021, 360(2): 252-256(in Chinese). [14] 由于, 徐健, 燕群, 等. 涡轮叶片耦合疲劳寿命预测与试验验证[J]. 航空动力学报, 2022, 37(5): 946-953.YOU Y, XU J, YAN Q, et al. Combined fatigue life prediction and experiment verification for turbine blade[J]. Journal of Aerospace Power, 2022, 37(5): 946-953(in Chinese). [15] 雷世英, 孙见忠, 刘赫. 涡轮叶片累积损伤指数模型及服役可靠性评估[J]. 航空学报, 2022, 43(3): 244-260.LEI S Y, SUN J Z, LIU H. Cumulative damage index model and service reliability evaluation of turbine blade[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(3): 244-260(in Chinese). [16] 何庆富, 迟重然, 臧述升. 几何损伤导致涡轮静叶气动衰减的CNN预测[J]. 工程热物理学报, 2022, 43(12): 3219-3224.HE Q F, CHI C R, ZANG S S. CNN prediction of aerodynamic decay of turbine static blades due to geometric damage[J]. Journal of Engineering Thermophysics, 2022, 43(12): 3219-3224(in Chinese). -


下载: