فناوری در مهندسی هوافضا

فناوری در مهندسی هوافضا

بررسی اثر فرسودگی بر عمر خزشی پره‌های توربین موتور جت‌ مدل 250-C20

نوع مقاله : علمی پژوهشی

نویسندگان
1 استادیار، دانشکده مهندسی هوافضا، دانشگاه علوم و فنون هوایی شهید ستاری، تهران، ایران
2 استاد، دانشکده مهندسی هوافضا، دانشگاه علوم و فنون هوایی شهید ستاری، تهران، ایران
3 دانشجو دکتری، دانشکده مهندسی هوافضا، دانشگاه علوم و فنون هوایی شهید ستاری، تهران، ایران
چکیده
پره‌های ثابت و متحرک توربین‌ها در بخش گرم موتورهای جت و توربوشفت، به دلیل تحمل تنش‌های شدید در دمای بالا، همواره در معرض آسیب‌ها و خرابی‌های مختلف از قبیل خوردگی داغ، اکسیداسیون، آسیب‌های خزشی، فرسایش، خستگی، برخورد جسم خارجی و ایجاد ترک قرار دارند. از طرفی یکی از چالش‌های مهندسین در حوزه موتور‌های توربینی، یافتن راهی برای تخمین عمر قطعات به‌ویژه پره‌های توربین است. در این مقاله، تحلیل عددی یک نمونه پره ردیف اول توربین موتور 250-C20  به همراه پوشش‌های سد حرارتی آن، در نرم‌افزار اجزای محدود آباکوس انجام شده، و توزیع تنش و کرنش در بازه زمان، مشخص گردید و بر اساس آن، مناطق دارای بیشترین خزش استخراج شده است و سپس با در نظر گرفتن میزان کرنش گسیختگی پره توربین، عمر خزشی پره تخمین زده شده است. برای اعتبارسنجی عمر تخمین زده شدۀ توربین، نتایج عددی مستخرجه با نتایج تجربی سه نمونه پره توربین مقایسه شده‌است.
کلیدواژه‌ها
موضوعات

عنوان مقاله English

Investigating the Effect of Wear on the Creepage Life of Jet Engine Turbine Blades Model 250-C20

نویسندگان English

Mostafa Livani 1
Hamid Reza Zarei 2
Seyed Mohammad Kamali 3
1 Department of Aerospace Engineering, Shahid Sattari Aeronautical University of Science and Technology, Tehran, Iran
2 Department of Aerospace Engineering, Shahid Sattari Aeronautical University of Science and Technology, Tehran, Iran
3 Department of Aerospace Engineering, Shahid Sattari Aeronautical University of Science and Technology, Tehran, Iran
چکیده English

The stationary and rotating blades of jet engines and turboshaft turbines, particularly in the hot section, are subjected to extreme stresses at high temperatures. Consequently, they are constantly exposed to various forms of damage and failure, including hot corrosion, oxidation, creep damage, erosion, fatigue, foreign object damage, and cracking. A key challenge in turbine engine maintenance is the accurate estimation of the lifespan of critical components, particularly turbine blades. This study used finite element analysis in ABAQUS software to conduct a numerical analysis of a first-row turbine blade from the C20-250 engine, including its thermal barrier coatings. The stress and strain distribution over the operational period were determined, highlighting the areas most susceptible to creep failure. Based on the rupture strain of the turbine blade material, the creep life of the blade was estimated. The numerical results were compared with experimental data from three turbine blade samples to validate the estimated creep life. These findings provide crucial insights for predictive maintenance strategies, enhancing the durability and cost-effectiveness of turbine engines.

کلیدواژه‌ها English

Turbine blade
thermal protective coating
finite element modeling
creep
stress
creep life estimation
1] T. J. Carter, "Common failures in gas turbine blades," Engineering Failure Analysis, vol. 12, no. 2, pp. 237-247, 2005, https://doi.org/10.1016/j.engfailanal.2004.07.004.
[2] R. B. Spector, "A method of evaluating life cycle costs of industrial gas turbines," Journal of Engineering for Gas Turbines and Power, vol. 111, no. 4, pp. 637-641, 1989, https://doi.org/10.1115/1.3240304.
[3] D. Dye, A. Ma, and R. C. Reed, "Numerical modelling of creep deformation in a CMSX-4 single crystal superalloy turbine blade," Superalloys, pp. 911-919, 2008, Art. no. e919, https://doi.org/10.7449/2008/SUPERALLOYS_2008_911_919.
[4] E. Barzkar and M. Forouzan, "Creep life assessment of repaired turbine blade from two substances," Journal of Aerospace Mechanics, vol. 8, no. 1, pp. 29-41, 2012, (in Persian).
[5] Z. Mazur, G. D. Ortega-Quiroz, and R. García-Illescas, "Evaluation of creep damage in a gas turbine first stage blade," in 20th International Conference on Nuclear Engineering and the ASME 2012 Power Conference, Anaheim, California, USA, 2012, pp. 531-536, https://doi.org/10.1115/ICONE20-POWER2012-55087.
[6] L. Donghuan, H. Li, and Y. Liu, "Numerical simulation of creep damage and life prediction of superalloy turbine blade," Mathematical Problems in Engineering, vol. 015, no. 1, 2015, Art. no. 732502, http://dx.doi.org/10.1155/2015/732502.
[7] J. Zhao, A. K. Koul, and A. Banerjee, "An investigation on the effect of creep shakedown on the creep behavior of an industrial gas turbine blade," in ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, Quebec, Canada, 2015, Peper V006T21A014, https://doi.org/10.1115/GT2015-43844.
[8] P. Brandão, V. Infante, and A. M. Deus, "Thermo-mechanical modeling of a high-pressure turbine blade of an airplane gas turbine engine," Procedia Structural Integrity, vol. 1, pp. 189-196, 2016, https://doi.org/10.1016/j.prostr.2016.02.026.
[9] A. Karimi, H. Yarmohammad, M. M. Barjesteh, M. Noori, and H. Mohammad Karimi Yazdi, "Remaining creep life assessment of gas turbine blade made of IN 792 ‎nickel-base superalloy," Iranian Journal of Mechanical Engineering Transactions of ISME, vol. 18, no. 3, pp. 6-18, 2016.
[10] T. Sadowski and P. Golewski, Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades: An Experimental Research and Numerical Modeling, Springer, 2016, http://dx.doi.org/10.1007/978-981-10-0919-8.
[11] Z. Xu et al., "Creep behaviour investigation of additively manufactured IN738LC superalloy based on Materials Genome approach," Materials Science and Engineering, vol. 163, Art. no. 100914, 2025, https://doi.org/10.1016/j.mser.2024.100914.
[12] A. Soleimani, S. Shahraki, M. Sherafati, and H. Bisadi, "Fatigue and creep analysis of the first row of turbine blades of microturbine TRI60," Journal of Modeling in Engineering, vol. 15, no. 51, pp. 251-265, 2017, https://doi.org/10.22075/jme.2017.2694.
[13] B. Mohammadi and S. A. Hashemitabar, " Developing a cdm based model for creep-fatigue life assessment of a gas turbine blade," Amirkabir Journal of Mechanical Engineering, vol. 52, no. 10, pp. 2951-2966, 2021, https://doi.org/10.22060/mej.2019.15921.6229.
[14] M. Spodniak, K. Semrád, and K. Draganová, "Turbine blade temperature field prediction using the numerical methods," Applied Sciences, vol. 11, no. 6, 2021, https://doi.org/10.3390/app11062870.
[15] L. Yang, Q. X. Liu, Y. C. Zhou, W. G. Mao, and C. Lu, "Finite element simulation on thermal fatigue of a turbine blade with thermal barrier coatings," Journal of Materials Science and Technology, vol. 30, no. 4, pp. 371-380, 2014, https://doi.org/10.1016/j.jmst.2013.11.005.
[16] Z. Mazur, R. García-Illescas, and J. Porcayo-Calderón, "Last stage blades failure analysis of a 28MW geothermal turbine," Engineering Failure Analysis, vol. 16, no. 4, pp. 1020-1032, 2009, https://doi.org/10.1016/j.engfailanal.2008.05.012.
[17] W. Zhu, L. Yang, J. W. Guo, Y. C. Zhou, and C. Lu, "Numerical study on interaction of surface cracking and interfacial delamination in thermal barrier coatings under tension," Applied Surface Science, vol. 315, pp. 292-298, 2014, https://doi.org/10.1016/j.apsusc.2014.07.142.
[18] J. Rösler, M. Bäker, and K. Aufzug, "A parametric study of the stress state of thermal barrier coatings: Part I: Creep relaxation," Acta Materialia, vol. 52, no. 16, pp. 4809-4817, 2004, https://doi.org/10.1016/j.actamat.2004.06.046.
[19] Z. Huda, "Development of heat-treatment process for a P/M superalloy for turbine blades," Materials and Design, vol. 28, no. 5, pp. 1664–1667, 2007, http://dx.doi.org/10.1016/j.matdes.2006.03.026.
[20] G. VanDrunen and J. Liburdi, "Rejuvenation of used turbine blades by hot isostatic processing,", in 6th Turbomachinery Symposium, Texas A&M University, Gas Turbine Laboratories, 1977, pp. 55-60.
 

  • تاریخ دریافت 27 مهر 1402
  • تاریخ بازنگری 20 آذر 1402
  • تاریخ پذیرش 03 دی 1402
  • تاریخ اولین انتشار 04 بهمن 1402