Review of design of high-pressure turbine

• Autorzy: Bugała P.

Identyfikatory

DOI

10.5604/01.3001.0010.2796

• Języki publikacji: EN

Abstrakty

EN

The engine manufacturers adopt new measures in order to further improve the characteristics of a turbine engine. They pose new challenges to reduce a fuel consumption and an emission of pollution to the environment (including noise), but also keeping the highest level of reliability. Based on those considerations, current research in propulsion is conducted. Modern turbines are characterised by high inlet temperature. This has implications for engine efficiency, which is expressed with a change of mass, cross-section and fuel consumption. In this article, main trends in the development of turbine engines are presented. This analysis was carried out on the basis of Rolls-Royce engine data. The article presents literature review concerning the analytical methods of high-pressure turbines preliminary design. The aerodynamic design process is highly iterative, multidisciplinary and complex. Due to this, modern gas turbines need sophisticated tools in terms of aerodynamics, mechanical properties and materials. The article depicts simplified model of real turbine engine. As showed in the article, this model gives only a 10% error level in engine thrust value. The calculations may be used for preliminary engine analyses.

Słowa kluczowe

EN

preliminary design; turbomachinery; gas turbine; high-pressure turbine; HPT

PL

projekt wstępny; turbo mechanizm; turbina gazowa; turbina wysokociśnieniowa; HPT

• 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: 2017
• Tom: Vol. 24, No. 1
• Strony: 67--76
• Opis fizyczny: Bibliogr. 16 poz., rys.

Twórcy

autor

Bugała P.

• Institute of Aviation, Department of Aerodynamics and Flight Mechanics Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 359, fax: [phone]

Bibliografia

• [1] Ainley, D. G., Mathieson, G. C. R., A Method of Performance Estimation for Axial-Flow Turbines, Tech. rept. Aeronautical Research Council, London 1951.
• [2] Craig, H. B. M., Cox, H. J. Α., Performance estimation of axial flow turbines, Proc. Inst. Mech. Engrs., 71, Vol. 185 32/71, 1970.
• [3] Craig, H. R. M., Cox, H. J. A., Performance estimation of axial flow turbines, Proc. Inst. Mech. Eng., 185, 32/71, 407-424 , 1971.
• [4] Denton, J. D., Loss mechanisms in turbomachines, Trans. ASME J. Turbomachinery, 115, 621-656, 1993.
• [5] Denton, J. D., Loss mechanisms in turbomachines, Part I – Entropy creation in fluid flows, Part II – Loss generation in turbomachines, VKI LS 1999-02, 1999.
• [6] Dunham, J., Came, P. M., Improvements, to the Ainley-Mathieson method of turbine performance prediction, Trans. ASME, J. Eng. for Power, Series A, No. 3, 252, 1970.
• [7] https://www.rolls-royce.com/products-and-services/defence-aerospace/products/combat-jets/ej200.aspx#engine-specifications.
• [8] Jones, S. M., An Introduction to Thermodynamic Performance Analysis of Aircraft Gas Turbine Engine Cycles Using the Numerical Propulsion System Simulation Code, NASA/TM—2007-214690, 2007.
• [9] Kocker, S. C., Okapuu, V., A mean line prediction method for axial flow turbine efficiency, Trans. ASME, J. Ens. for Power 1, 1982.
• [10] Kurzke, J., How to get component maps for aircraft gas turbine performance calculations, Gas Turbine and Aeroengine Congress & Exhibition, Birmingham 1996.
• [11] Mattingly, J. D., Elements of propulsion: Gas turbines and rockets, Reston, Va: American Institute of Aeronautics and Astronautics, 2006.
• [12] Smith, M. H., A simple correlation of turbine efficiency, Journal of Royal Aeronautical Society, 1965.
• [13] The Jet Engine, Rolls-Royce, 2005.
• [14] Turner, M. G., Merchant, A., Bruna, D., A Turbomachinery Design Tool for Teaching Design Concepts for Axial-Flow Fans, Compressor and Turbines, ASME Turbo Expo GT2006-90105, May 8-11, Barcelona, Spain 2006.
• [15] Turner, M., G., Merchant, A., Bruna D., Turbomachinery Compressor Design (Part of the T-AXI suite of codes), Version 1.1, User manual, 2006.
• [16] Zweifel, O., Optimum Blade Pitch for Turbo-Machines with Special Reference to Blades of Great Curvature, Brown Boveri Review, The Engineer's Digest, 1946. 76

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).