Load spectrum correction method considering performance degradation

Sisi YUAN; Xuming NIU; Zhigang SUN; Yingdong SONG

doi:10.7527/S1000-6893.2024.31312

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2025 , Vol. 46 >Issue 12: 231312 - 231312

DOI: https://doi.org/10.7527/S1000-6893.2024.31312

Solid Mechanics and Vehicle Conceptual Design

Load spectrum correction method considering performance degradation

Sisi YUAN ,
Xuming NIU ,
Zhigang SUN ,
Yingdong SONG

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^1.College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 　210016，China
^2.Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 　210016，China
^3.Key Laboratory of Aero-Engine Thermal Environment and Structure of Ministry of Industry and Information Technology，Nanjing 　210016，China
^4.Wuxi Research Institute，Nanjing University of Aeronautics and Astronautics，Wuxi 　213300，China

E-mail： szg_mail@nuaa.edu.cn

Received date: 2024-10-08

Revised date: 2024-11-01

Accepted date: 2024-11-13

Online published: 2024-11-18

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Abstract

Engine performance degradation often causes changes of performance parameters， which leads to the change of load spectrum in completing the same mission and affects life prediction of the engine structure. At present， the above factors have not been considered in the process of compiling the load spectrum of the whole machine life test， resulting in a large error between life prediction results and field test results. To address this problem， based on the construction of a turbofan engine model that integrates overall performance degradation and dynamic performance correction is constructed， mainly analyzing dynamic correction of engine performance by tip clearance prediction method considering wear and creep. On this basis， a load spectrum correction method for turbofan engine considering performance degradation is proposed. The engine load spectrum for the typical flight mission profile is calculated. The results show that after 3 000 cycles of engine operation， the inlet temperature of the high-pressure turbine corrected with the model proposed in this paper is 0.69% higher than that with the traditional model. Compared with the original spectrum， the corrected load spectrum has a 4.90% reduction in the high-pressure shaft speed at the maximum state， a 2.95% increase in inlet temperature of the high-pressure turbine， and a 21.05% increase in duration of the maximum state. The goal of load spectrum correction considering performance degradation is shown to be achieved.

Key words： turbofan engine; performance degradation; load spectrum correction; tip clearance; wear; creep

Cite this article

Sisi YUAN , Xuming NIU , Zhigang SUN , Yingdong SONG . Load spectrum correction method considering performance degradation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(12) : 231312 -231312 . DOI: 10.7527/S1000-6893.2024.31312

References

[1]	马双员，张永峰. 航空发动机载荷谱综述［J］. 现代机械， 2011（5）： 15-17， 35.
	MA S Y， ZHANG Y F. Overview of aeroengine loading spectrum［J］. Modern Machinery， 2011（5）： 15-17， 35 （in Chinese）.
[2]	牛序铭，赵旭，王飞飞，等. 基于损伤等效的航空发动机加速任务试车谱编制方法［J］. 推进技术， 2023， 44（2）： 237-245.
	NIU X M， ZHAO X， WANG F F， et al. Compiling method of aero-engine acceleration mission test spectrum based on damage equivalence［J］. Journal of Propulsion Technology， 2023， 44（2）： 237-245 （in Chinese）.
[3]	史海秋，赵福星. 某型发动机承力机匣疲劳载荷谱研究［J］. 燃气涡轮试验与研究， 2005， 18（1）： 41-44.
	SHI H Q， ZHAO F X. Research on fatigue load spectra of an engine supporting-case［J］. Gas Turbine Experiment and Research， 2005， 18（1）： 41-44 （in Chinese）.
[4]	ARNOLD S， KELLY P G. Recent turbine engine accelerated mission testing accomplishments at AEDC［C］∥ 2018 Aerodynamic Measurement Technology and Ground Testing Conference. Reston： AIAA， 2018.
[5]	NAEEM M， SINGH R， PROBERT D. Implications of engine’s deterioration upon an aero-engine HP turbine blade’s thermal fatigue life［J］. International Journal of Fatigue， 2000， 22（2）： 147-160.
[6]	RATH N， MISHRA R K， KUSHARI A. Aero-engine health monitoring， diagnostics and prognostics for condition-based maintenance： An overview［J］. International Journal of Turbo & Jet-Engines， 2024， 40（s1）： s279-s292.
[7]	SUN J Z， YAN Z C， HAN Y， et al. Deep learning framework for gas turbine performance digital twin and degradation prognostics from airline operator perspective［J］. Reliability Engineering & System Safety， 2023， 238： 109404.
[8]	郭庆，黄启廉，陈金亮. 基于部件特性图优化的民航发动机性能退化建模［J/OL］. 北京航空航天大学学报， 2023： 1-14. （2023-08-22）. .
	GUO Q， HUANG Q L， CHEN J L. Performance degradation modeling of civil aviation engine based on component characteristic map optimization［J/OL］. Journal of Beijing University of Aeronautics and Astronautics， 2023： 1-14. （2023-08-22）. （in Chinese）.
[9]	WANG C J， TAO H Y， XU P Y， et al. The effect of changing the combustion chamber head structure on turbine blades under thermal shock test［J］. International Journal of Thermal Sciences， 2024， 205： 109260.
[10]	KHANI N， SEGOVIA C， NAVARATNE R， et al. Towards development of a diagnostic and prognostic tool for civil aero-engine component degradation［C］∥ASME 2012 Gas Turbine India Conference. New York： ASME， 2013： 803-814.
[11]	WANG C S， ZHU Z H， LU N Y， et al. A data-driven degradation prognostic strategy for aero-engine under various operational conditions［J］. Neurocomputing， 2021， 462： 195-207.
[12]	李业波，李秋红，黄向华，等. 航空发动机性能退化缓解控制技术［J］. 航空动力学报， 2012， 27（4）： 930-936.
	LI Y B， LI Q H， HUANG X H， et al. Performance deterioration mitigation control of aero-engine［J］. Journal of Aerospace Power， 2012， 27（4）： 930-936 （in Chinese）.
[13]	LI Y F， CHEN Y， HU Z C， et al. Remaining useful life prediction of aero-engine enabled by fusing knowledge and deep learning models［J］. Reliability Engineering & System Safety， 2023， 229： 108869.
[14]	KURZ R， BRUN K. Degradation in gas turbine systems［J］. Journal of Engineering for Gas Turbines and Power， 2001， 123（1）： 70-77.
[15]	肖俊峰，伍赫，高松，等. 叶顶间隙对多级轴流压气机性能退化的影响［J］. 动力工程学报， 2024， 44（9）： 1353-1360.
	XIAO J F， WU H， GAO S， et al. Effects of blade tip clearance on performance degradation of the multi-stage axial compressor［J］. Journal of Chinese Society of Power Engineering， 2024， 44（9）： 1353-1360 （in Chinese）.
[16]	ZHANG X D， XIONG Y W， HUANG X， et al. Dynamic modeling of rotary blade crack with regard to three-dimensional tip clearance［J］. Journal of Sound and Vibration， 2023， 544： 117414.
[17]	LATTIME S， STEINETZ B. Turbine engine clearance control systems： Current practices and future directions［C］∥38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2002.
[18]	宋丙新，侯朝山. 某型航空发动机HPT转子叶片叶尖间隙对涡轮流场及性能的影响分析［J］. 航空维修与工程， 2024（2）： 27-30.
	SONG B X， HOU C S. Analysis on the influence of clearance between HPT rotor blade tip and casing on flow field and performance for a certain aero-engine［J］. Aviation Maintenance & Engineering， 2024（2）： 27-30 （in Chinese）.
[19]	TENG F， ZHANG X D， XIE S Y. Research on variation mechanism of three-dimensional blade tip clearance of aero-engine［C］∥2016 13th International Conference on Ubiquitous Robots and Ambient Intelligence （URAI）. Piscataway： IEEE Press， 2016： 1-6.
[20]	MA H， TAI X Y， HAN Q K， et al. A revised model for rubbing between rotating blade and elastic casing［J］. Journal of Sound and Vibration， 2015， 337： 301-320.
[21]	杨梓佟. 基于热-固耦合的航空发动机碰摩动力学分析［D］. 天津：中国民航大学， 2023.
	YANG Z T. Aero-engine rubbing dynamics analysis based on thermo-structure coupling［D］. Tianjin： Civil Aviation University of China， 2023 （in Chinese）.
[22]	YANG Y， MAO J K， CHEN P T， et al. Prediction and analysis of transient turbine tip clearance using long short-term memory neural network［J］. Journal of Engineering for Gas Turbines and Power， 2024， 146（10）： 101011.
[23]	SHENG H L， LIU T， ZHAO Y， et al. New model-based method for aero-engine turbine blade tip clearance measurement［J］. Chinese Journal of Aeronautics， 2023， 36（8）： 128-147.
[24]	何辉，毛军逵，刘方圆，等. 考虑发动机性能退化的涡轮叶尖间隙预估方法研究［J］. 推进技术， 2020， 41（10）： 2283-2291.
	HE H， MAO J K， LIU F Y， et al. Method of turbine tip clearance prediction considering engine performance degradation［J］. Journal of Propulsion Technology， 2020， 41（10）： 2283-2291 （in Chinese）.
[25]	WANG Z， WANG Y， WANG X， et al. A novel digital twin framework for aeroengine performance diagnosis?［J］. Aerospace， 2023， 10（9）：789.
[26]	YE M L， HE K， YAN X. Influence of wear damages on aerodynamic and heat transfer performance in squealer tip gap?［J］. Applied Thermal Engineering， 2019， 159： 113976.
[27]	徐田镇. 航空发动机退化状态参数估计与控制技术研究［D］. 南京：南京航空航天大学， 2017.
	XU T Z. Research on degradation aero-engine’s parameters estimation and control technology?［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2017 （in Chinese）.
[28]	郑玺龙. 基于战斗机飞行任务的涡扇发动机参数设计研究［D］. 南京：南京航空航天大学， 2018.
	ZHENG X L. Research of turbofan parameter design based on fighter flight missions［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2018 （in Chinese）.
[29]	VERBIST M L D. Gas path analysis for enhanced aero-engine condition monitoring and maintenance?［D］. Delft： Delft University of Technology， 2017.
[30]	LITT J S， PARKER K I， CHATTERJEE S. Adaptive gas turbine engine control for deterioration compensation due to aging［C］∥16th International Symposium on Airbreathing Engines. 2003.
[31]	KRATZ J L， CHAPMAN J W. Active turbine tip clearance control trade space analysis of an advanced geared turbofan engine［C］∥2018 Joint Propulsion Conference. Reston： AIAA， 2018.
[32]	JAVIER K A. A reduced model for prediction of thermal and rotational effects on turbine tip clearance［R］. Washington， D.C.： NASA， 2023.
[33]	SALLEE G P. Performance deterioration based on existing （historical） data； JT9D jet engine diagnostics program： NASA-CR-135448［R］. Washington， D.C.： NASA， 1978.
[34]	全昌彪，廖明夫，米栋，等. 基于θ映射法的燃气涡轮叶片高温蠕变变形分析［J］. 燃气涡轮试验与研究， 2018， 31（6）： 25-29， 55.
	QUAN C B， LIAO M F， MI D， et al. High temperature creep deformation analysis of gas turbine blade based on θ-projection method［J］. Gas Turbine Experiment and Research， 2018， 31（6）： 25-29， 55 （in Chinese）.
[35]	CHAPMAN J W， GUO T H， KRATZ J L， et al. Integrated turbine tip clearance and gas turbine engine simulation［C］∥52nd AIAA/SAE/ASEE Joint Propulsion Conference. Reston： AIAA， 2016.
[36]	NAEEM M. Implications of aero-engine deterioration for a military aircraft’s performance?［D］. Cranfield： Cranfield University， 1999.
[37]	JAY A. TODD E S. Effect of steady flight loads on JT9D-7 performance deterioration： NASA-CR-135407 ［R］. Washington， D.C.： NASA， 1978.
[38]	聂志强. 短寿涡轮叶片和轮盘的强度分析与寿命预测［D］. 哈尔滨：哈尔滨工程大学， 2023.
	NIE Z Q. Strength analysis and life prediction of short-life turbine blades and disks［D］. Harbin： Harbin Engineering University， 2023 （in Chinese）.
[39]	《中国航空材料手册》委员会. 中国航空材料手册. 第2卷，变形高温合金铸造高温合金［M］. 北京：中国标准出版社， 2002.
	Committee on Chinese Aeronautical Materials Manual.Manual of Chinese aeronautical materials. Volume 2， Deformation superalloys casting superalloys［M］. Beijing： Standards Press of China， 2002 （in Chinese）.
[40]	陆山，唐俊星，赵明，等. 航空发动机结构强度设计与分析［M］. 北京：科学出版社， 2022.
	LU S， TANG J X， ZHAO M， et al. Structural strength design and analysis of aircraft engines［M］. Beijing： Science Press， 2022 （in Chinese）.
[41]	SAKANE M， HIRANO A， HAMADA N， et al. Multiaxial inverse stress analysis for indentation creep［C］∥MATEC Web of Conferences. 2019.
[42]	ZHAO X， NIU X M， SONG Y D， et al. A novel damage constitutive model for creep deformation and damage evolution prediction［J］. Fatigue & Fracture of Engineering Materials & Structures， 2023， 46（3）： 798-813.
[43]	高丽敏，王浩浩，黄维娜，等. 压气机叶片加工偏差的不确定性效应研究进展［J］. 航空学报， 2024， 45（19）： 630386.
	GAO L M， WANG H H， HUANG W N， et al. Research progress on uncertainty effect of compressor blade machining deviation［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（19）： 630386 （in Chinese）.

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