Modelling of vane and rotor blade rows in simulations of gas turbine performance

• Autorzy: Sznajder Janusz

Identyfikatory

DOI

10.2478/kones-2019-0022

• Języki publikacji: EN

Abstrakty

EN

A method of modelling of nozzle and rotor blade rows of gas turbine dedicated to simulations of gas turbine performance is proposed. The method is applicable especially in early design stage when many of geometric parameters are yet subject to change. The method is based on analytical formulas derived from considerations of flow theory and from cascade experiments. It involves determination of parameters of gas flow on the mean radius of blade rows. The blade row gas exit angle, determined in turbine design point is a basis for determination of details of blade contour behind the throat position. Throat area is then fixed based on required maximum mass flow in critical conditions. Blade leading edge radius is determined based on flow inlet angle to the blade row in the design point. The accuracy of analytical formulas applied for definition of blade contour details for assumed gas exit angle was verified by comparing the results of analytical formulas with CFD simulations for an airfoil cascade. Losses of enthalpy due to non-isentropic gas flow are evaluated using the analytical model of Craig and Cox, based on cascade experiments. Effects of blade cooling flows on losses of total pressure of the gas are determined based on analytical formulas applicable to film cooling with cooling streams blowing from discrete point along blade surface, including leading and trailing edges. The losses of total pressure due to film cooling of blades are incorporated into the Craig and Cox model as additional factor modifying gas flow velocities.

Słowa kluczowe

EN

aircraft engines; mechanical engineering; engine parts; simulation; modelling

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2019
• Tom: Vol. 26, No. 1
• Strony: 183--190
• Opis fizyczny: Bibliogr. 9 poz., rys.

Twórcy

autor

Sznajder Janusz

• Institute of Aviation Department of Aerodynamics Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 492, fax: [phone]

Bibliografia

• [1] Mattingly, J. D., Elements of Gas Turbine Propulsion (AIAA Education Series), AIAA (American Institute of Aeronautics & Astronautics), 2005.
• [2] Bugała, P., Deviation Angle Models In Off-Design High-Pressure Turbines, Journal of KONES Powertrain and Transport, Vol. 25, No. 2, pp 69-74, 2018, ISSN: 1231-4005, e-ISSN: 2354-0133, DOI: 10.5604/01.3001.0012.2778, 2018.
• [3] Craig, H. R. M., Cox, H. J. A., Performance Estimation of Axial Flow Turbines, Proceedings of the Institution of Mechanical Engineers, Vol. 185 32/71, 1970/71.
• [4] Aronov, B. M., Zhukovskii, M. I., Zhuravlev, B. A., Profilirovanie lopatok aviatsionnih gazovih turbin, Moskva, Mashinostroienie, 1975.
• [5] Dżygadło, Z., Łyżwiński, M., Otyś, J., Szczeciński S., Zespoły wirnikowe silników turbinowych, Warszawa, Wydawnictwo Komunikacji i Łączności, 1982.
• [6] Hylton, L., Mihelc, M. S.., Turner, E. R., Nealy, D. A., York R. E., Analytical and Experimental Evaluation of the Heat Transfer Distribution Over the Surfaces of Turbine Vanes, Detroit Diesel Allison Division of General Motors Company, Final Report prepared for NASA Lewis Research Center, Contract NAS 3-22761, May 1983.
• [7] Mattingly, J. D., Heiser, W. H., Pratt, D. T., Aircraft Engine Design, Second Edition, AIAA Education Series, 2002.
• [8] Hartsel, J. E., Prediction of Effects of Mass Transfer Cooling on the Blade Row Efficiency of Turbine Airfoils, AIAA Paper 72-11, Jan. 1972.
• [9] Lytle, J. K., The Numerical Propulsion System Simulation: A Multidisciplinary Design System For Aerospace Vehicles. NASA/TM—1999-209914, Glenn Research Center, Ohio 1999.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).