This paper presents two optimized rotors. The first rotor is as part of a 3-blade row optimization (IGV-rotor-stator) of a high-pressure compressor. It is based on modifying blade angles and advanced control of curvature of the airfoil camber line. The effects of these advanced blade techniques on the performance of the transonic 1.5-stage compressor were calculated using a 3D Navier-Stokes solver combined with a vortex/vorticity dynamics diagnosis method. The first optimized rotor produces a 3-blade row efficiency improvement over the baseline of 1.45% while also improving stall margin. The throttling range of the compressor is expanded largely because the shock in the rotor tip area is further downstream than that in the baseline case at the operating point. Additionally, optimizing the 3-blade row block while only adjusting the rotor geometry ensures good matching of flow angles allowing the compressor to have more range. The flow diagnostics of the rotor blade based on vortex/vorticity dynamics indicate that the boundary-layer separation behind the shock is verified by on-wall signatures of vorticity and skin-friction vector lines. In addition, azimuthal vorticity and boundary vorticity flux (BVF) are shown to be two vital flow parameters of compressor aerodynamic performance that directly relate to the improved performance of the optimized transonic compressor blade. A second rotor-only optimization is also presented for a 2.9 pressure ratio transonic fan. The objective function is the axial moment based on the BVF. An 88.5% efficiency rotor is produced.
References
[1]
Shang, E.B., Wang, Z.Q., et al. (1991) A Perspective and Effective Way to Improve the Compressor Cascade Performance. IGTC-13, Yokohama Int. Gas Turbine Congress.
[2]
Deich, M.E., Gubalev, A.B., Filippov, G.A. and Wang, Z.Q. (1962) A New Method of Profiling the Guide Vane Cascade of Stage with Small Ratios Diameter to Length. Teplienergetika, 8, 42-46.
[3]
Filippov, G.A. and Wang, Z.Q. (1963) The Calculation of Axial Symmetric Flow in an Turbine Stage with Small Ratio of Diameter to Blade Length. Journal of Moscow Power Institute, 47, 63-78.
[4]
Wang, Z.Q., Su, J.X. and Zhong, J. (1994) The Effect of the Pressure Distribution in a Three-Dimensional Flow Field of a Cascade on the Type of Curved Blade. ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition, Hague, 13-16 June 1994, No. 94-GT-400.
http://proceedings.asmedigitalcollection.asme.org/proceeding.aspx?articleid=2143638
https://doi.org/10.1115/94-gt-409
[5]
Bliss, D.B., Hayden, R.P. and Murry, B.S. (1976) Design Considerations for Novel Low Source Noise Transonic Fan Stage. 3rd Aeroacoustics Conference, Palo Alto, 20-22 July 1976, AIAA Paper No. 76-577. https://doi.org/10.2514/6.1976-577
[6]
Lucas, J., Woodward, R. and Mackinnon, M. (1978) Acoustic Evaluation of a Novel Swept Rotor Fan. 11th Fluid and Plasma Dynamics Conference, Seattle, AIAA Paper No. 78-1121. https://doi.org/10.2514/6.1978-1121
[7]
Wennerstrom, A.J. and Frost, G.R. (1976) Design of a 1500ft/sec, Transonic, High-through-Flow, Single-Stage Axial-Flow Compressor with Low Hub/Tip Ratio. Air Force Aero Propulsion Lab, Wright-Patterson AFB, No. AFARL-TR-76-59.
[8]
Frank, B.J. and King, P.I. (1994) Effects of Leading Edge Sweep on Stall Inception in a High-Speed Single-Stage Compressor. 30th Joint Propulsion Conference and Exhibit, Joint Propulsion Conferences, AIAA Paper No. 94-2696.
https://doi.org/10.2514/6.1994-2696
[9]
Boger, K.M., King, P.I. and Copenhaver, W.W. (1993) Stall Inception in Single Stage High-Speed Compressor with Straight and Swept Leading Edges. 29th Joint Propulsion Conference and Exhibit, Joint Propulsion Conferences, AIAA 93-1870.
[10]
Benini, E. (2004) Three-Dimensional Multi-Objective Design Optimization of a Transonic Compressor Rotor. Journal of Propulsion and Power, 20, 559-565.
https://www.researchgate.net/publication/235642689_Three-Dimensional_Multi-Objective_Design_Optimization_of_a_Transonic_Compressor_Rotor
https://doi.org/10.2514/1.2703
[11]
Jang, C.M., Li, P. and Kim, K.Y. (2005) Optimization of Blade Sweep in a transonic Axial Compressor Rotor. JSME International Journal Series B, 48, 793-801.
https://www.researchgate.net/publication/245396662_Optimization_of_Blade_Sweep_in_a_ Transonic_Axial_Compressor_Rotor
https://doi.org/10.1299/jsmeb.48.793
[12]
Lian, Y. and Liou, M.S. (2005) Multi-Objective Optimization of Transonic Compressor Blade Using Evolutionary Algorithm. Journal of Propulsion and Power, 21, 979-987. https://doi.org/10.2514/1.14667
[13]
Ellbrant, L., Eriksson, L.E. and Martensson, H. (2013) Balancing Efficiency and Stability in the Design of Transonic Compressor Stages. Proceedings of ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, San Antonio, 3-7 June 2013, GT2013-94838.
http://proceedings.asmedigitalcollection.asme.org/proceeding.aspx?articleid=1776564&resultClick=3
[14]
Siddappaji, K., Turner, M.G. and Merchant, A. (2012) General Capability of Parametric 3D Blade Design Tool for Turbomachinery. Proceedings of ASME Turbo Expo 2012, Copenhagen, 11-15 June 2012, GT2012-69756.
http://proceedings.asmedigitalcollection.asme.org/proceeding.aspx?articleid=1695055&resultClick=3
[15]
Nemnem, A.F., Turner, M.G., Siddappaji, K. and Galbraith, M. (2014) A Smooth Curvature-Defined Meanline Section Option for a General Turbomachinery Geometry Generator. Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, Düsseldorf, 16-20 June 2014, GT2014-26363.
http://proceedings.asmedigitalcollection.asme.org/proceeding.aspx?articleid=1907506&resultClick=3
[16]
Nemnem, A.F. (2014) A General Multidisciplinary Turbomachinery Design Optimization System Applied to a Transonic Fan. Ph.D. Thesis, University of Cincinnati, Cincinnati.
[17]
Wu, J.Z., Ma, H.Y. and Zhou, M.D. (2006) Vorticity and Vortex Dynamics. Springer Science & Business Media, New York, Printed in Germany.
https://doi.org/10.1007/978-3-540-29028-5
[18]
Wu, J.Z., Tramel, R.W., Zhu, F.L., et al. (2000) A Vorticity Dynamics Theory of Three-Dimensional Flow Separation. Physics of Fluids (1994-Present), 12, 1932-1954. http://aip.scitation.org/doi/abs/10.1063/1.870442
https://doi.org/10.1063/1.870442
[19]
Wu, J.Z., Lu, X.Y., Yang, Y.T., et al. (2010) Vorticity Dynamics in Complex Flow Diagnosis and Management. Proceedings of the 13th Asian Congress of Fluid Mechanics, Dhaka, 17-21 December 2010, 1-22.
https://www.researchgate.net/publication/266891986_Vorticity_Dynamics_in_Complex_Flow_ Diagnosis_and_Management
[20]
Yang, Y., Wu, H., Li, Q., et al. (2008) Vorticity Dynamics in Axial Compressor Flow Diagnosis and Design. Journal of Fluids Engineering, 130, 041102.
http://fluidsengineering.asmedigitalcollection.asme.org/article.aspx?articleid=1478110
https://doi.org/10.1115/1.2903814
[21]
Li, Q., Wu, H., Guo, M., et al. (2010) Vorticity Dynamics in Axial Compressor Flow Diagnosis and Design—Part II: Methodology and Application of Boundary Vorticity Flux. Journal of Fluids Engineering, 132, 011102.
http://meetings.aps.org/Meeting/DFD07/Event/72001
https://doi.org/10.1115/1.4000650
[22]
Fox, R.W., McDonald, A.T. and Pritchard, P.J. (2004) Introduce to Fluid Mechanics. 6th Edition, John Wiley & Sons, Inc., Hoboken.
[23]
Chen, H.L. and Turner, M.G. (2016) Vorticity Dynamics Based Flow Diagnosis for a 1.5-Stage High Pressure Compressor with an Optimized Transonic Rotor. ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, Seoul, 13-17 June 2016, GT-56682.
http://proceedings.asmedigitalcollection.asme.org/proceeding.aspx?articleid=2554633&resultClick=1
Holloway, P., Knight, G., Koch, C. and Shaffer, S. (1982) Energy Efficient Engine High Pressure Compressor Detail Design Report. General Electric Company, Tech. Rep., NASA CR-165558.
[28]
Turner, M.G., Merchant, A. and Bruna, D. (2011) A Turbomachinery Design Tool for Teaching Design Concepts for Axial-Flow Fans, Compressors, and Turbines. Journal of Turbomachinery, 133. http://www.asme.org/about-asme/terms-of-use
https://doi.org/10.1115/1.4001240
[29]
Mahmood, S.-H., Turner, M.G., Siddappaji, K. and Balasubramanian, K. (2016) Flow Characteristics of an Optimized Axial Compressor Rotor Using Smooth Design Parameters. Proceedings of ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, Seoul, GT2016-57028.
http://proceedings.asmedigitalcollection.asme.org/solr/searchresults.aspx?q=Flow%20 Characteristics%20of%20an%20Optimized%20Axial%20Compressor%20Rotor%20using%20Smooth% 20Design%20Parameters&f_ContentType=Proceedings&SearchSourceType=3
https://doi.org/10.1115/gt2016-57028
