Shock System Model of Highly Loaded Turbine Cascade
Publication: Journal of Aerospace Engineering
Volume 33, Issue 1
Abstract
To support the design of a two-dimensional turbine blade profile with reduced shock loss, an efficient model for shock system with separation shock in highly loaded turbine cascade needed to be established to realize parameterized shock losses prediction and analysis. The discussions on the model demonstrate that the effect of base pressure on shock losses can be achieved by controlling the width of the base region (the region between the pressure surface and suction surface trailing edge separation points). Increasing the trailing-edge wedge angle can increase the base pressure as well as the width of the base region, thus reducing the shock losses. Moreover, the pressure change caused by reducing the suction surface curvature downstream of the throat can reduce the loss caused by the reflected shock.
Get full access to this article
View all available purchase options and get full access to this article.
References
Denton, J. D. 1993. “Loss mechanisms in turbomachines.” Trans. ASME J. Turbomach. 115 (4): 621–656. https://doi.org/10.1115/1.2929299.
Denton, J. D., and L. Xu. 1990. “The trailing edge loss of transonic turbine blades.” J. Turbomach. 112 (2): 277–285. https://doi.org/10.1115/1.2927648.
Dorney, D. J., L. W. Griffin, and F. W. Huber. 2000. “A study of the effects of tip clearance in a supersonic turbine.” J. Turbomach. 122 (4): 674–683. https://doi.org/10.1115/1.1290400.
Giel, P. W. 2008. “NASA/GE highly-loaded turbine research program.” In Proc., NASA Fundamental Aeronautics 2007 Annual Meeting. Washington, DC: National Aeronautics and Space Administration.
Gong, J. B., J. Q. Zhu, H. W. Zhang, and C. Q. Nie. 2009. “Profile losses prediction of transonic turbine cascades.” Turbine Technol. 51 (2): 81–84. https://doi.org/10.3969/j.issn.1001-5884.2009.02.001.
Ji, L., J. Yu, W. Li, and W. Yi. 2016. “Study on aerodynamic optimal super/transonic turbine cascade and its geometry characteristics.” Proc. Inst. Mech. Eng. Part G: J. Aerosp. Eng. 231 (3): 435–443. https://doi.org/10.1177/0954410016638875.
Ji, L. C., W. T. Ma, and F. J. Feng. 2015. “Research on the shock wave structure and its evolution in turbine cascades.” Trans. Beijing Ins. Technol. 35: 571–575. https://doi.org/10.15918/j.tbit1001-0645.2015.06.005.
Jiang, Z. L., and D. J. Ling. 2007. “The base pressure influence on the trailing edge loss of transonic turbine cascade.” Gas Turbine Exp. Res. 20 (3): 23–27. https://doi.org/10.3969/j.issn.1672-2620.2007.03.006.
Kacker, S. C., and U. Okapuu. 1982. “A mean line prediction method for axial flow turbine efficiency.” ASME J. Eng. Power 104 (1): 111–119. https://doi.org/10.1115/1.3227240.
Min, D., and X. Ai. 1989. “Experimental research on two-dimensional transonic cascades of an 850-mm steam turbine blade.” J. Turbomach. 111 (3): 231–235. https://doi.org/10.1115/1.3262260.
Senoo, S., and H. Ono. 2013. “Development of design method for supersonic turbine aerofoils near the tip of long blades in steam turbines. 1: Overall configuration.” In Vol. 6 of Proc., ASME Turbo Expo 2012: Turbine Technical Conf. and Exposition, 355–365. New York: ASME.
Sieverding, C. H., M. Stanislas, and J. Snoeck. 1980. “The base pressure problem in transonic turbine cascades.” J. Eng. Power 102 (3): 711–718. https://doi.org/10.1115/1.3230330.
Sonoda, T., T. Arima, M. Olhofer, B. Sendhoff, F. Kost, and P. A. Gieß. 2006. “A study of advanced high-loaded transonic turbine airfoils.” J. Turbomach. 128 (4): 650–657. https://doi.org/10.1115/1.2221325.
Wang, Y. F., F. B. Wen, S. T. Wang, and S. W. Chen. 2013. “Research on the effects of negative curvature design of blade suction side on shock wave intensity in gas turbine cascade.” Energy Conserv. Technol. 31 (5): 404–408. https://doi.org/10.3969/j.issn.1002-6339.2013.05.005.
Xu, L. 1991. “An inviscid model for the base pressure of transonic turbine cascade.” Acta Mech. Sin. 7 (1): 39–45. https://doi.org/10.1007/BF02486594.
Xu, L., and J. D. Denton. 1988. “The base pressure and loss of a family of four turbine blades.” J. Turbomach. 110 (1): 9–17. https://doi.org/10.1115/1.3262174.
Yasa, T., G. Paniagua, and A. Bussolin. 2007. “Performance analysis of a transonic high-pressure turbine.” Proc. Inst. Mech. Eng. Part A: J. Power Energy 221 (6): 769–778. https://doi.org/10.1243/09576509JPE467.
Zhao, W., W. Luo, Q. Zhao, and J. Xu. 2016. “Investigation on the reduction of trailing edge shock losses for a highly loaded transonic turbine.” In Proc., ASME Turbo Expo 2016: Turbomachinery Technical Conf. and Exposition, 10. New York: ASME.
Zhou, K. 2014. “Investigations of aerodynamic design techniques for counter-rotating turbine in adaptive cycle engine.” Ph.D. dissertation, School of Energy and Power Engineering, Beihang Univ.
Нечаев, Ю. ., and P. . Федоров. 1979. The theory of aircraft gas turbine: Moscow mechanical engineering. Sofia, Bulgaria: Bulgarian Telecommunications Company.
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 33 • Issue 1 • January 2020
Copyright
©2019 American Society of Civil Engineers.
History
Received: Aug 7, 2018
Accepted: Jul 9, 2019
Published online: Oct 31, 2019
Published in print: Jan 1, 2020
Discussion open until: Mar 31, 2020
Authors
Metrics & Citations
Metrics
Citations
Download citation
If you have the appropriate software installed, you can download article citation data to the citation manager of your choice. Simply select your manager software from the list below and click Download.