Hostname: page-component-848d4c4894-pjpqr Total loading time: 0 Render date: 2024-06-25T18:29:14.742Z Has data issue: false hasContentIssue false
  • English
  • Français

Aerodynamic design of a high-efficiency two-stage axial turbine, using streamline curvature method and performance optimisation by clocking of stator blades

Published online by Cambridge University Press:  01 February 2024

R. Taghavi Zenouz Open the ORCID record for R. Taghavi Zenouz [Opens in a new window]  and
S.M.M. Abiri Open the ORCID record for S.M.M. Abiri [Opens in a new window]
R. Taghavi Zenouz*
Affiliation:
Aerodynamics and compressible Turbomachine Research Laboratory, School of Mechanical Engineering, Iran University of Science and Technology, Tehran, 16846-13114, Iran
S.M.M. Abiri
Affiliation:
Aerodynamics and compressible Turbomachine Research Laboratory, School of Mechanical Engineering, Iran University of Science and Technology, Tehran, 16846-13114, Iran
*
Corresponding author: R. Taghavi Zenouz; Email: taghavi@iust.ac.ir
Get access Rights & Permissions [Opens in a new window]

Abstract

Aerodynamic design of a high-efficiency two-stage axial turbine is carried out using a hybrid method through implantation of a two-step design procedure. In the first step, the well-known streamline curvature (SLC) and free vortex (FV) methods are properly combined to establish three-dimensional geometries of the blades at each row and to obtain the flow field properties. The second step is provided to obtain the highest aerodynamic efficiency by optimum clocking of the second stator blades relative to the first ones through executing steady and unsteady computational fluid dynamics (CFD) of three-dimensional viscous flow. Slight discrepancies were observed between gas dynamics results of the SLC and those of CFD. Total pressure and temperature at the turbine outlet, obtained from SLC method, differed from those obtained by 3D-CFD technique by 13.06% and 1.88% respectively. Aerodynamic efficiency of the turbine is obtained about 91.83%, based on 3D-CFD. Time-averaged results showed that under the optimum clocking of the second row stator blades, inlet total pressure and output power of the second rotor increase by 0.23%, and 0.93%, respectively, in comparison to the worst clocking case. These augmentations resulted in increased total to total efficiency of the second stage by 0.444%. Additionally, the total output power of the two stages increased by 0.71% through the optimum clocking. Modeling the unsteady wake flow trajectory within the blades passages confirmed that all of these beneficial effects happen if the upstream wake impinges on the leading edge region of the second stator blades.

Keywords

axial turbinestreamline curvature methodfree vortex methodstator blades clockingwake flow trajectory
Type
Research Article
Information
The Aeronautical Journal , First View , pp. 1 - 30
Check for updates
Copyright
© The Author(s), 2024. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Wu, C.-H. A general theory of three-dimensional flow in subsonic and supersonic turbomachines of axial, radial, and mixed-flow types, Trans. Amer. Soc. Mech. Eng., 1952, 74, (8), pp 1363–1380. https://doi.org/10.1115/1.4016114 CrossRefGoogle Scholar
Novak, R. Streamline curvature computing procedures for fluid-flow problems, J. Eng. Power, 1967, 89, (4), pp 478–490. https://doi.org/10.1115/1.3616716 CrossRefGoogle Scholar
Denton, J. Throughflow calculations for transonic axial flow turbines, J. Eng. Gas Turbines Power, 1978, 100, (2), pp 212–218. https://doi.org/10.1115/1.3446336 CrossRefGoogle Scholar
Aungier, R.H. Axial-Flow Compressors: A Strategy for Aerodynamic Design and Analysis. American Society of Mechanical Engineers, New York, 2003. ISBN:0-7918-0192-6.CrossRefGoogle Scholar
Korakianitis, T. and Zou, D. Through-flow analysis for axial-stage design including streamline-slope effects, Turbo Expo: Power Land, Sea Air, 1993, 78880, p V001T003A024. https://doi.org/10.1115/93-GT-056 Google Scholar
Wennerstrom, A.J. On the treatment of body forces in the radial equilibrium equation of turbomachinery, Traupel Commemorative Volume.(A 75-19051 06-02) Zurich, Juris-Verlag AG, 1974, 1974, pp 351–367. https://ntrl.ntis.gov/NTRL/dashboard/searchResults/titleDetail/ADA008127.xhtml Google Scholar
Wennerstrom, A.J. Design of Highly Loaded Axial-Flow Fans and Compressors. Concepts Eti, White River Junction, Vt, 2000. ISBN:0933283113Google Scholar
Boyer, K.M. and O’Brien, W.F. An improved streamline curvature approach for off-design analysis of transonic axial compression systems, ASME. J. Turbomach., 2003, 125, (3), pp 475–481. https://doi.org/10.1115/1.1565085 CrossRefGoogle Scholar
Templalexis, I., Pilidis, P., Pachidis, V. and Kotsiopoulos, P. Development of a two-dimensional streamline curvature code, ASME. J. Turbomach., 2011, 133, (1), p 011003. https://doi.org/10.1115/1.2720877 CrossRefGoogle Scholar
Zhu, X.C., Hu, J.F., Ou-Yang, H., Tian, J., Qiang, X.Q. and Du, Z.H. The off-design performance prediction of axial compressor based on a 2D approach, J. Theor. Appl. Mech., 2013, 51, (3), pp 523–531. https://www.ptmts.org.pl/jtam/index.php/jtam/article/view/v51n3p523/32 Google Scholar
Pachidis, V., Pilidis, P., Templalexis, I., Korakianitis, T. and Kotsiopoulos, P. Prediction of engine performance under compressor inlet flow distortion using streamline curvature, ASME. J. Eng. Gas Turbines Power, 2007, 129, (1), pp 97–103. https://doi.org/10.1115/1.2363414 CrossRefGoogle Scholar
Abbasi, S., Pirnia, A. and Taghavi-Zenouz, R. Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method, J. Theor. Appl. Mech., 2018, 56, (4), pp. 1005–1015. https://doi.org/10.15632/jtam-pl.56.4.1005 CrossRefGoogle Scholar
Kim, S., Kim, K. and Son, C. A study on the through-flow analysis for a multi-stage axial turbine considering leakage flows, J. Korean Soc. Propul. Eng., 2018, 22, (5), pp 1–12. https://doi.org/10.6108/KSPE.2018.22.5.001 Google Scholar
Ainley, D. and Mathieson, G. A method of performance estimation for axial-flow turbines. In Aeronautical Research Council Reports and Memoranda, (Vol. Reports and Memoranda No. 2 9 74). London: Library Royal Aircraft Establishment Bedford, 1951.Google Scholar
Hodson, H.P. and Howell, R.J. The role of transition in high-lift low-pressure turbines for aeroengines, Prog. Aerosp. Sci., 2005b, 41, (6), pp 419–454. https://doi.org/10.1016/j.paerosci.2005.08.001 CrossRefGoogle Scholar
Wisler, D.C. The technical and economic relevance of understanding boundary layer transition in gas turbine engines, In Minnowbrook II, 1997 Workshop on Boundary Layer Transition in Turbomachines, pp 53–64, 1998. https://doi.org/114603952 Google Scholar
Gaetani, P. Stator-rotor interaction in axial turbine: flow physics and design perspective, Aircr. Technol., 2018. https://doi.org/10.5772/intechopen.76009 Google Scholar
Tucker, P. Computation of unsteady turbomachinery flows: Part 1—Progress and challenges, Prog. Aerosp. Sci., 2011, 47, (7), pp 522–545. https://doi.org/10.1016/j.paerosci.2011.06.004 CrossRefGoogle Scholar
Halstead, D.E., Wisler, D.C., Okiishi, T.H., Walker, G.J., Hodson, H.P. and Shin, H.-W. Boundary layer development in axial compressors and turbines: part 1 of 4—composite picture, J. Turbomach., 1997, 119, (1), pp 114–127. https://doi.org/10.1115/1.2841000 CrossRefGoogle Scholar
König, S., Stoffel, B. and Taher Schobeiri, M. Experimental investigation of the clocking effect in a 1.5-stage axial turbine—part i: time-averaged results, J. Turbomach., 2009, 131, (2), 12 pages. https://doi.org/10.1115/1.2948968 Google Scholar
Arnone, A., Marconcini, M., Del Greco, A.S. and Spano, E. Numerical investigation of three-dimensional clocking effects in a low pressure turbine, J. Turbomach., 2004, 126, (3), pp 375–384. https://doi.org/10.1115/1.1740780 CrossRefGoogle Scholar
Hodson, H.P. and Howell, R.J. Bladerow interactions, transition, and high-lift aerofoils in low-pressure turbines, Ann. Rev. Fluid Mech., 2005a, 37, (1), pp 71–98. https://doi.org/10.1146/annurev.fluid.37.061903.175511 CrossRefGoogle Scholar
Smith, L.H. Wake dispersion in turbomachines, J. Basic Eng., 1966, 88, (3), pp 688–690. https://doi.org/10.1115/1.3645942 CrossRefGoogle Scholar
Huber, F., Johnson, P., Sharma, O., Staubach, J. and Gaddis, S. Performance improvement through indexing of turbine airfoils: part 1—experimental investigation, J. Turbomach., 1996, 118, (4), pp 630–635. https://doi.org/10.1115/1.2840918 CrossRefGoogle Scholar
Arnone, A., Marconcini, M., Pacciani, R., Schipani, C. and Spano, E. Numerical investigation of airfoil clocking in a three-stage low-pressure turbine, J. Turbomach., 2002, 124, (1), pp 61–68. https://doi.org/10.1115/1.1425810 CrossRefGoogle Scholar
Reinmöller, U., Stephan, B., Schmidt, S. and Niehuis, R. Clocking effects in a 1.5 stage axial turbine—steady and unsteady experimental investigations supported by numerical simulations, J. Turbomach., 2002, 124, (1), pp 52–60. https://doi.org/10.1115/1.1425811 CrossRefGoogle Scholar
Jouini, D., Little, D., Bancalari, E., Dunn, M., Haldeman, C. and Johnson, P. Experimental investigation of airfoil wake clocking impacts on aerodynamic performance in a two stage turbine test rig, ASME Turbo Expo: Power Land, Sea Air, 2003, 36894, pp 351–358. https://doi.org/10.1115/GT2003-38872 Google Scholar
Bohn, D., Ausmeier, S. and Ren, J. Investigation of the optimum clocking position in a two-stage axial turbine, Int. J. Rotat. Mach., 2005, 2005, (3), pp 202–210. https://doi.org/10.1155/IJRM.2005.202 CrossRefGoogle Scholar
Sobczak, K., Smolny, A. and Blaszczak, J. Quasi-unsteady simulations of the clocking phenomena in the two-stage turbine, Mech. Mech. Eng., 2008, 12, (2), pp 111–124. https://doi.org/bwmeta1.element.baztech-article-LOD9-0012-0010 Google Scholar
Zhu, Y., Luo, J. and Liu, F. Numerical investigation of stator clocking effects on the downstream stator in a 1.5-stage axial turbine, In Proceedings of the ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, Volume 2D: Turbomachinery, 26–30, 2017. https://doi.org/10.1115/GT2017-63273 CrossRefGoogle Scholar
Ghenaiet, A. and Touil, K. Characterization of component interactions in two-stage axial turbine, Chin. J. Aeronaut., 2016, 29, (4), pp 893–913. https://doi.org/10.1016/j.cja.2016.06.007 CrossRefGoogle Scholar
Touil, K. and Ghenaiet, A. Blade stacking and clocking effects in two-stage high-pressure axial turbine, Aircr. Eng. Aerosp. Technol., 2019. https://doi.org/10.1108/AEAT-03-2018-0110 CrossRefGoogle Scholar
Yahya, S. Turbines Compressors and Fans. Tata McGraw-Hill Education, 2010. ISBN: 9780070707023.Google Scholar
Aungier, R.H. Turbine Aerodynamics: Axial-Flow and Radial-Inflow Turbine Design and Analysis. American Society of Mechanical Engineers, New York, 2006. ISBN: 0791802418.Google Scholar
Kacker, S. and Okapuu, U. A mean line prediction method for axial flow turbine efficiency. ASME. J. Eng. Power, 1982, 140, (1), pp 111–119. https://doi.org/10.1115/1.3227240 CrossRefGoogle Scholar
Rhie, C.M. and Chow, W.-L. Numerical study of the turbulent flow past an airfoil with trailing edge separation, AIAA J., 1983, 21, (11), pp 1525–1532. https://doi.org/10.2514/3.8284 CrossRefGoogle Scholar
Langtry, R.B. and Menter, F.R. Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes, AIAA J., 2009, 47, (12), pp 2894–2906. https://doi.org/10.2514/1.42362 CrossRefGoogle Scholar
Wilcox, D.C. Turbulence Modeling for CFD (Vol. 2). DCW industries La Canada, CA, 1998. ISBN: 0963605151.Google Scholar
Van Driest, E. and Blumer, C. Boundary layer transition-freestream turbulence and pressure gradient effects. AIAA J., 1963, 1, (6), pp 1303–1306. https://doi.org/10.2514/3.1784 CrossRefGoogle Scholar
Abu-Ghannam, B. and Shaw, R. Natural transition of boundary layers—the effects of turbulence, pressure gradient, and flow history, J. Mech. Eng. Sci., 1980, 22, (5), pp 213–228. https://doi.org/10.1243/JMES_JOUR_1980_022_043_02 CrossRefGoogle Scholar
Mayle, R.E. The role of laminar-turbulent transition in gas turbine engines, In Proceedings of the ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award; General. Orlando, Florida, USA, 1991. https://doi.org/10.1115/91-GT-261 CrossRefGoogle Scholar
Menter, F.R., Smirnov, P.E., Liu, T. and Avancha, R. A one-equation local correlation-based transition model, Flow, Turbul. Combust., 2015, 95, (4), pp 583–619. https://doi.org/10.1007/s10494-015-9622-4 CrossRefGoogle Scholar
Farokhi, S. (2014). Aircraft Propulsion: John Wiley and Sons. ISBN: 1118806778.Google Scholar
Mattingly, J.D., Boyer, K.M. and von Ohain, H. Elements of Propulsion: Gas Turbines and Rockets. American Institute of Aeronautics and Astronautics, Reston, VA, 2006. ISBN: 1563477793.CrossRefGoogle Scholar
Stieger, R.D. and Hodson, H.P. The unsteady development of a turbulent wake through a downstream low-pressure turbine blade passage, In ASME Turbo Expo 2004: Power for Land, Sea, and Air, Volume 5: Turbo Expo 2004, Parts A and B, pp 121–129. https://doi.org/10.1115/gt2004-53061 Google Scholar