Abstract
In this paper, a novel engineering platform for throughflow analysis based on streamline curvature approach is developed for the research of a 5-stage compressor. The method includes several types of improved loss and deviation angle models, which are combined with the authors’ adjustments for the purpose of reflecting the influences of three-dimensional internal flow in high-loaded multistage compressors with higher accuracy. In order to validate the reliability and robustness of the method, a series of test cases, including a subsonic compressor P&W 3S1, a transonic rotor NASA Rotor 1B and especially an advanced high pressure core compressor GE E3 HPC, are conducted. Then the computation procedure is applied to the research of a 5-stage compressor which is designed for developing an industrial gas turbine. The overall performance and aerodynamic configuration predicted by the procedure, both at design- and part-speed conditions, are analyzed and compared with experimental results, which show a good agreement. Further discussion regarding the universality of the method compared with CFD is made afterwards. The throughflow method is verified as a reliable and convenient tool for aerodynamic design and performance prediction of modern high-loaded compressors. This method is also qualified for use in the further optimization of the 5-stage compressor.
Article PDF
Similar content being viewed by others
Avoid common mistakes on your manuscript.
References
Gümmer V, Wenger U, Kau H P. Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressors. J Turbomach, 2001, 123: 40–48
Song Y, Gu C W. Effects of curvature continuity of compressor blade profiles on their performances. ASME Turbo Expo 2014, Düsseldorf, 2014, GT2014-25804
Cumpsty N A. Some lessons learned. J Turbomach, 2010, 132: 041018.1–7
Gbadebo S A, Cumpsty N A, Hynes T P. Three-dimensional separations in axial compressors. Jurbomach, 2005, 127: 331–339
Huang D G, Wu G Q. Preliminary study on the aerodynamic characteristics of an adaptive reconfigurable airfoil. Aerosp Sci Technol, 2013, 27: 44–48
Wang Y, Sun X J, Dai Y J, et al. Numerical investigation of drag reduction byheat-enhanced cavitation. Appl Therm Eng, 2015, 75: 193–202
Lichtfuss H J. Customized profiles—The beginning of an era: a short history of blade design. ASME Turbo Expo 2004, Vienna, 2004, GT2004-53742
Hao Z, Gu C, Song Y. Discontinuous galerkin finite element methods for numerical simulations of thermoelasticity. J Therm Stresses, 2015, 38: 983–1004
Denton J, Dawes W. Computational fluid dynamics for turbomachinery design. P I Mech Eng C-J Mec, 1998, 213: 107–124
Cumpsty N A. Compressor aerodynamics. London: Longman Scientific & Technical, 1989, 93–131
Boyer K M. An improved streamline curvature approach for offdesign analysis of transonic compression systems. Dissertation of Doctor Degree. Blacksburg: Virginia Polytechnic Institute and State University, 2001
Wu C H. A general theory of three-dimensional flow in subsonic and supersonic turbomachines of axial-, radial, and mixed-flow types. NACA-TN-2604. NACA, 1952
Smith L. The radial-equilibrium equation of turbomachinery. J Eng Power, 1966, 88: 1–11
Swan W. A practical method of predicting transonic-compressor performance. J Eng Power, 1961, 83: 322–330
Novak R. Streamline curvature computing procedures for fluid-flow problems. J Eng Power, 1967, 89: 478–490
Bryans A, Miller M. Computer program for design of multistage axial- flow compressors. NASA-CR-54530, NASA, 1967
Hirsch C, Warzee G. A finite-element method for through flow calculations in turbomachines. J Fluid Eng, 1976, 98: 403–415
Miller G R, Hartmann M J. Experimental shock configurations and shock losses in a transonic-compressor rotor at design speed. NACA RM-E58A14B. NACA, 1958
Oldham R K. Some design data for double circular arc compressor blading. NGTE Note NT. 589, 1965
Creveling H F, Carmody R H. Axial flow compressor computer program for calculating off-design performance (Program IV). NASA-CR-72427, NASA, August 1968
Koch C, Smith L. Loss sources and magnitudes in axial-flow compressors. J Eng Power, 1976, 98: 411–424
Adkins G G, Smith L H. Spanwise mixing in axial-flow turbomachines. J Eng Power, 1982, 104: 97–110
Gallimore S J, Cumpsty N. Spanwise mixing in multistage axial flow compressors. II: Throughflow calculations including mixing. J Turbomach, 1986; 108: 2–16
Lieblein S. Loss and stall analysis of compressor cascades. ASME J Basic Eng, 1959, 81: 387–400
Cetin M, Uecer A, Hirsch C, et al. Application of modified loss and deviation correlations to transonic axial compressors. AGARD-R-745, Advisory Group For Aerospace Research and Development Neuilly-Sur-Seine (Fran Ce), 1987
Konig W, Hennecke D, Fottner L. Improved blade profile loss and deviation angle models for advanced transonic compressor bladings. 1. A model for subsonic flow. J Turbomach, 1996, 118: 73–80
Konig W, Hennecke D, Fottner L. Improved blade profile loss and deviation angle models for advanced transonic compressor bladings. 2. A model for supersonic flow. J Turbomach, 1996, 118: 81–87
Pachidis V, Pilidis P, Templalexis I, et al. An iterative method for blade profile loss model adaptation using streamline curvature. J Eng Gas Turb Power, 2008, 130: 011702.1–8
Li H B, Gu C, Song Y. Through-flow calculation with a cooling model for cooled turbines. P I Mech Eng A-J Pow, 2015, doi: 0957650915594294
Turner M G, Merchant A, Bruna D. A turbomachinery design tool for teaching design concepts for axial-flow fans, compressors, and turbines. ASME Turbo Expo 2006, Barcelona, 2006, GT2006-90105
Petrovic M V, Wiedermann A, Banjac M B. Development and validation of a new universal through flow method for axial compressors. P I Mech Eng A-J Pow, 2010, 224: 869–880
Song Y, Gu C W, Xiao Y B. Numerical and theoretical investigations concerning the continuous-surface-curvature effect in compressor blades. Energies, 2014, 7: 8150–5177
Song Y, Gu C W, Ji X X. Development and validation of a full-range performance analysis model for a three-spool gas turbine with turbine cooling. Energy, 2015, 89: 545–557
Wang J, Gu C, Sunden B A. Conjugated heat transfer analysis of a film cooling passage with different rib configurations. Int J Numer Method H, 2015, 25: 841–860
Lieblein S, Roudebush W H. Theoretical loss relations for low-speed two-dimensional-cascade flow. NACA TN 3662, NACA, 1956
Petrovic M V, Wiedermann A, Banjac M B. Development and validation of a new universal through flow method for axial compressors. ASME Turbo Expo 2009, Orlando, 2009, GT2009-59938
Carter A. The low speed performance of related aerofoils in cascade. ARC CP29, His Maj. Stat. Office, 1950
Creveling H F, Carmody R H. Axial flow compressor computer program for calculating off-design performance. NASA-CR-72472, NASA, 1968
Hearsey R M. Program HT0300 NASA 1994 version. D6-81569TN, 1994
Howell A. Fluid dynamics of axial compressors. P I Mech Eng, 1945, 153: 441–452
Fouflias D, Gannan A, Ramsden K, et al. Experimental investigation of the influence of fouling on compressor cascade characteristics and implications for gas turbine engine performance. P I Mech Eng A-J Pow, 2010, 224: 1007–1018
Eftari M, Jouybari H J, Shahhoseini M R, et al. Performance prediction modeling of axial-flow compressor by flow equations. J Mech Res Appl, 2011, 3: 49–55
Lakshminarayana B. Methods of predicting the tip clearance effects in axial flow turbomachinery. J Basic Eng, 1970, 92: 467–482
Miller G R, Lewis G W, Hartmann M J. Shock losses in transonic compressor blade rows. J Eng Power, 1961, 83: 235–242
Bloch G S, Copenhaver W W, O’Brien W F. A shock loss model for supersonic compressor cascades. J Turbomach, 1999, 121: 28–35
Boyer K M O’Brien W F. An improved streamline curvature approach for off-design analysis of transonic axial compression systems. ASME Turbo Expo 2002, Amsterdam, 2002, GT2002-30444
Moeckel W E. Approximate method for predicition form and location of detached shock waves ahead of plane or axially symmetric bodies, NACA TN 1921, NACA, 1949
Howard M, Gallimore S. Viscous throughflow modeling for multistage compressor design. J Turbomach, 1993, 115: 296–304
Koch C. Stalling pressure rise capability of axial flow compressor stages. J Eng Power, 1981, 103: 645–656
Burdsall E A, Canal E, Lyons K A. Core compressor exit stage study-1: Aerodynamic and mechanical design. NASA CR-159714, NASA, 1979
Behlke R F, Burdsall E A, Canal E, et al. Core compressor exit stage study-2: Final Report. NASA CR-159812, NASA, 1979
Seyler D, Smith L. Single stage experimental evaluation of high Mach number compressor rotor blading, part 1: Design of rotor blading. NASA CR-54581, NASA, 1967
Seyler D, Gestolow J. Single stage experimental evaluation of high Mach number compressor rotor blading, part 2: Performance of Rotor 1B. NASA CR-54582, NASA, 1967
Wisler D, Koch C, Smith L. Preliminary design study of advanced multistage axial flow core compressors. NASA CR-135133, NASA, 1977
Holloway P, Koch C, Knight G, et al. Energy efficient engine. High pressure compressor detail design report. NASA CR-165558, NASA, 1982
Author information
Authors and Affiliations
Corresponding author
Rights and permissions
About this article
Cite this article
Li, B., Gu, C., Li, X. et al. Development and application of a throughflow method for high-loaded axial flow compressors. Sci. China Technol. Sci. 59, 93–108 (2016). https://doi.org/10.1007/s11431-015-5947-4
Received:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s11431-015-5947-4