نوع مقاله : علمی- ترویجی

نویسندگان

1 دانشــیار، مجتمــع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران ، ایران

2 دانشـجوی کارشناسـی ارشـد، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالـک اشتر ، تهران، ایران

چکیده

تخمین اولیة وزن در مرحلة طراحی مفهومی موتور توربوفن، یکی از مهمترین مراحل طراحی موتورهای توربین‌گاز  است. از این‌رو، در این مقاله به بررسی روش‌های تخمین اولیة وزن موتور توربوفن و سپس پارامترهای مورد نیاز برای اجرای هر روش پرداخته شده است. در ادامه جامعة آماری که در آن اطلاعات مربوط به وزن 64 موتور توربوفن تدوین شده است، معرفی می‌شود. بنابراین، رو‌ش‌های مختلف تخمین اولیة وزن موتور استفاده از اطلاعات وزنی حاصل از پردازش آماری، مقایسه و وزن موتورها محاسبه می‌شوند. در نهایت، نتایج حاصل از این آزمایش با وزن واقعی موتور مقایسه شده است. براساس نتایج به‌دست آمده در میان روش‌های مختلف در صد خطای کمترین خطا مربوط به روش تخمین وزن ناسا است که درحدود 8/4 درصد است. در ادامه براساس نمودارهای حاصل از این مقایسه به بررسی تأثیر پارامترهای مختلف بر وزن موتور توربوفن پرداخته شده است (تخمین اولیة وزن به روش وزن موتور برای حالتی که موتور ثابت است ولی طراحی هواپیما تغییر می‌کند، مطرح می‌شود). در روش تخمین اولیة وزن براساس اجزای موتور امکان طراحی و وزن هر جزء به طور جداگانه میسر است، از این‌رو در طراحی موتورهای جدید بیشتر از آن استفاده می‌شود.

کلیدواژه‌ها

[1]  Ravi, B., Deo, J., Starnes, H., Richard, Jr., and Holzwarth, C., "Low-Cost Composite Materials and Structures for Aircraft Applications," Paper presented at the RTO AVT Specialists’ Meeting on “Low Cost Composite Structures”, held in Loen, Norway, 7-11 May 2001.
[2]  Lolis, P., Development of a Preliminary Weight Estimation Method for Advanced Turbofan Engines, (Ph.D. Thesis), University of Craneld, 2014.
[3]  Whitehead, L. T.  and  Brown.,  J., “A mechanical design for a lightweight turbo-jet engine and the variation of engine weight with size, “National gas turbine establishment, Memorandum M.177, August 1953.
[4]  Pennington, W.A., “Choice of engines for aircraft”, Shell Aviation News, January 1959,  pages 14-19.
[5]  Guha, A., Boylan, D. and Gallagher, P., “Determination of optimum specic thrust for civil aero gas turbine engines: A multidisciplinary design synthesis and optimisation”, Part G: Journal of Aerospace Engineering, Vol. 227, No.3, 2012.
[6]  Svoboda, C., “Turbofan engine database as a preliminary design tool”, Journal of Aircraft design, Vol.3, 2000, pp.17-31.
[7]  Raymer, D. P., “Aircraft design: A conceptual approach”, AIAA, 1989.
[8]  Jenkinson, L. R., Simpkin, P. and Rhodes, D., Civil Jet Aircraft Design, Butterwoth-Heinemann, 1999.
[9]  Daly, M., editor. Jane's aero-engines. 28 rd Ed, IHS Janes, September 2010.
[10]  Torenbeek., E., “Synthesis of Subsonic Airplane Design”, Martinus Nijhoff publishers, 1975.
[11]  Clavier, J., Aero gas turbine engine design project (AVIC). Ultra high bypass ratio (12-14) study, (Master's Thesis), University of Craneld, 2008.
[12]  Gerend, R. P. and Roundhill, J. P., "Correlation of gas turbine engine weights and dimensions," In Propulsion Joint Specialist Conference, AIAA,Vol. 669, 1970, pages 1-7.
[13]  Colmenares Quintero, R.F.,  Techno-economic and enviromental risk assessment of innovative propulsion systems for short-range civil aircraft, (Ph.D. Thesis), University of Craneld, April 2009.
[14]  Sagerser, D. A., Lieblein, S. and Krebs,  R. P., “Empirical expressions for estimating length and weight of axial-ow components of VTOL powerplants," Technical Report TM X-2406, NASA, December 1971.
[15]  Pera, R.J., Onat, E., Klees, G. W. and Tjonneland, E., “A method to estimate weight and dimensions of aircraft gas turbine engines." Vol. 1, Method of analysis nal report Technical Report NASA-CR-135170, NASA, 1977.
[16]  G. W. Klees and L. Fishbach, H., “Aircraft engine weight estimation method," Proceedings of the thirty-seventh annual conference of the Society of Allied Weight Engineers, number 1248. SAWE, May 1978.
[17]  Onat, E. and Tolle, F.F.,  “An extension of engine weight estimation techniques to compute engine production cost ,“Technical Report N62269-78-C-0286, Naval Air Development Center, 1979.
[18]  Hale, P.L., “A method to estimate weight and dimensions of small aircraft propulsion gas turbine engines ,“Technical Report NASA-CR-168049, NASA - Garrett turbine engine company, 1982.
[19]  Tong, M.T., Halliwell, I. and Ghosn, L. J., “A computer code for gas turbine engine weight and disk life estimation, “Journal of Engineering for Gas Turbines and Power, Vol.126, No. 2, 2004, pp.265-270.
[20]  Tong, M. T. and Naylor, B. A., “An object-oriented computer code for aircraft engine weight estimation," In Proceedings of the ASME Turbo Expo, Vol. 1, 2008, pages 1-7.
[1]  Ravi, B., Deo, J., Starnes, H., Richard, Jr., and Holzwarth, C., "Low-Cost Composite Materials and Structures for Aircraft Applications," Paper presented at the RTO AVT Specialists’ Meeting on “Low Cost Composite Structures”, held in Loen, Norway, 7-11 May 2001.
[2]  Lolis, P., Development of a Preliminary Weight Estimation Method for Advanced Turbofan Engines, (Ph.D. Thesis), University of Craneld, 2014.
[3]  Whitehead, L. T.  and  Brown.,  J., “A mechanical design for a lightweight turbo-jet engine and the variation of engine weight with size, “National gas turbine establishment, Memorandum M.177, August 1953.
[4]  Pennington, W.A., “Choice of engines for aircraft”, Shell Aviation News, January 1959,  pages 14-19.
[5]  Guha, A., Boylan, D. and Gallagher, P., “Determination of optimum specic thrust for civil aero gas turbine engines: A multidisciplinary design synthesis and optimisation”, Part G: Journal of Aerospace Engineering, Vol. 227, No.3, 2012.
[6]  Svoboda, C., “Turbofan engine database as a preliminary design tool”, Journal of Aircraft design, Vol.3, 2000, pp.17-31.
[7]  Raymer, D. P., “Aircraft design: A conceptual approach”, AIAA, 1989.
[8]  Jenkinson, L. R., Simpkin, P. and Rhodes, D., Civil Jet Aircraft Design, Butterwoth-Heinemann, 1999.
[9]  Daly, M., editor. Jane's aero-engines. 28 rd Ed, IHS Janes, September 2010.
[10]  Torenbeek., E., “Synthesis of Subsonic Airplane Design”, Martinus Nijhoff publishers, 1975.
[11]  Clavier, J., Aero gas turbine engine design project (AVIC). Ultra high bypass ratio (12-14) study, (Master's Thesis), University of Craneld, 2008.
[12]  Gerend, R. P. and Roundhill, J. P., "Correlation of gas turbine engine weights and dimensions," In Propulsion Joint Specialist Conference, AIAA,Vol. 669, 1970, pages 1-7.
[13]  Colmenares Quintero, R.F.,  Techno-economic and enviromental risk assessment of innovative propulsion systems for short-range civil aircraft, (Ph.D. Thesis), University of Craneld, April 2009.
[14]  Sagerser, D. A., Lieblein, S. and Krebs,  R. P., “Empirical expressions for estimating length and weight of axial-ow components of VTOL powerplants," Technical Report TM X-2406, NASA, December 1971.
[15]  Pera, R.J., Onat, E., Klees, G. W. and Tjonneland, E., “A method to estimate weight and dimensions of aircraft gas turbine engines." Vol. 1, Method of analysis nal report Technical Report NASA-CR-135170, NASA, 1977.
[16]  G. W. Klees and L. Fishbach, H., “Aircraft engine weight estimation method," Proceedings of the thirty-seventh annual conference of the Society of Allied Weight Engineers, number 1248. SAWE, May 1978.
[17]  Onat, E. and Tolle, F.F.,  “An extension of engine weight estimation techniques to compute engine production cost ,“Technical Report N62269-78-C-0286, Naval Air Development Center, 1979.
[18]  Hale, P.L., “A method to estimate weight and dimensions of small aircraft propulsion gas turbine engines ,“Technical Report NASA-CR-168049, NASA - Garrett turbine engine company, 1982.
[19]  Tong, M.T., Halliwell, I. and Ghosn, L. J., “A computer code for gas turbine engine weight and disk life estimation, “Journal of Engineering for Gas Turbines and Power, Vol.126, No. 2, 2004, pp.265-270.
[20]  Tong, M. T. and Naylor, B. A., “An object-oriented computer code for aircraft engine weight estimation," In Proceedings of the ASME Turbo Expo, Vol. 1, 2008, pages 1-7.