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LI Jiaxing, LUO Jiaqi, CAO Zhiyuan. Adjoint-based aerodynamic design optimization of transonic turbine cascades considering different constraints[J]. Journal of Aerospace Power, 2021, 36(9): 1986-1998. doi: 10.13224/j.cnki.jasp.20200468
Citation: LI Jiaxing, LUO Jiaqi, CAO Zhiyuan. Adjoint-based aerodynamic design optimization of transonic turbine cascades considering different constraints[J]. Journal of Aerospace Power, 2021, 36(9): 1986-1998. doi: 10.13224/j.cnki.jasp.20200468
shu

Adjoint-based aerodynamic design optimization of transonic turbine cascades considering different constraints

doi: 10.13224/j.cnki.jasp.20200468
  • 1.

    School of Aeronautics and Astronautics，Zhejiang University，Hangzhou 310027，China

  • 2.

    School of Power and Energy，Northwestern Polytechnical University，Xi'an 710129，China

  • Received Date: 2020-11-02
  • Publish Date: 2021-09-28
    Abstract
  • A simplified method based on non-reflecting boundary theory for determining the inlet and outlet boundary conditions of adjoint equations was introduced，by which the aerodynamic design optimization of turbomachinery blade considering different constraints was investigated.The results showed that the simplified adjoint equations strongly coupling with flow under inlet and outlet boundary conditions were sufficiently accurate and applicable in different constrained optimization design.After outlet specific entropy design optimization without constraints，the outlet specific entropy decreased by 0.253%，with varied passage area and outlet flow angle.Considering the constraints of outlet flow angle and passage area separately and the constraints from both of them，the outlet specific entropy after optimization decreased by 0.176%，0.227% and 0.164%，respectively.The aerodynamic performance of the optimized blades was significantly improved，while the optimization constraints were maintained.Moreover，the results demonstrated that changing the curvature of blade profile weakened the shock wave effectively.When the curvature of front portions decreased，the flow velocity decelerated and the outlet flow angle increased，meanwhile when the curvature of front portions changed slightly，the outlet flow angle was constrained better.

     

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    • References(30)
  • [1]
    CHUNG H S,ALONSO J J A.Multidisciplinary design optimization of supersonic business jets using approximation model-based genetic algorithms[D].Palo Alto，US:University of Stanford,2004.
    [2]
    ZHU Z,WANG X,FU H,et al.Aerodynamic optimization design of airfoil and wing[R].AIAA 2004-4367,2004.
    [3]
    SAMAD A,KIM K Y.Multiple surrogate modeling for axial compressor blade shape optimization[J].Journal of Propulsion and Power,2008,24（2）:302-310.
    [4]
    BONAIUTI D,ZANGENEH M.On the coupling of inverse design and optimization techniques for the multiobjective,multipoint design of turbomachinery[J].Journal of Turbomachinery,2009,131（2）:021014.1-021014.16.
    [5]
    LAROCCA F.Multiple objective optimization and inverse design of axial turbomachinery blades[J].Journal of Propulsion and Power,2008,24（5）:1093-1099.
    [6]
    ?ZHAN ?,?BRAHIM S A.Multi-objective aerodynamic optimization of axial turbine blades using a novel multilevel genetic algorithm[J].Journal of Turbomachinery,2010,132（4）:041009.1-041009.19.
    [7]
    JAMESON A.Aerodynamic design via control theory[J].Journal of Scientific Computing,1988,3（3）:233-260.
    [8]
    NADARAJAH S K,JAMESON A.Optimum shape design for unsteady there-dimensional viscous flows using a non-linear frequency domain method[R].AIAA 2006-3455,2006.
    [9]
    NADARAJAH S K,JAMESON A.Optimum shape design of helicopter rotors in forward flight via control theory[R].AIAA 2007-3951,2007.
    [10]
    NADARAJAH S K,JAMESON A.Optimum shape design for unsteady flows with time-accurate continuous and discrete adjoint methods[J].AIAA Journal,2007,45（7）:1478-1500.
    [11]
    IOLLO A,SALAS M D,TA'ASAN S.Shape optimization governed by the quasi 1D Euler equations using an adjoint method[C]∥Fourteenth International Conference on Numerical Methods in Fluid Dynamics.Bangalore,India:Springerlink,1994:274-279.
    [12]
    DREYER J,MARTINELLI L.Hydrodynamic shape optimization of propulsor configurations using continuous adjoint approach[R].AIAA 2001-2580,2001.
    [13]
    YANG S,LIU F.Aerodynamic design of cascades by using an adjoint equation method[R].AIAA 2003-1068,2003.
    [14]
    WU H Y,LIU F,TSAI H M.Aerodynamic design of turbine blades using an adjoint equation method[R].AIAA 2005-1006,2005.
    [15]
    LI H,SONG L,LI Y,et al.2D viscous aerodynamic shape design optimization for turbine blades based on adjoint method[J].Journal of Turbomachinery,2011,133（3）:031014.1-031014.8.
    [16]
    YU J,JI L,LI W,et al.Shape optimization of axial compressor blades using adjoint method with emphasis on thickness distribution[R].ASME Paper GT2015-42232,2015.
    [17]
    PAPADIMITRIOU D I,GIANNAKOGLOU K C.Compressor blade optimization using a continuous adjoint formulatio[R].ASME Paper GT2006-90466,2006.
    [18]
    LUO J,XIONG J,LIU F.Three-dimensional aerodynamic design optimization of a turbine blade by using an adjoint method[J].Journal of Turbomachinery,2011,133（1）:011026.1-11026.11.
    [19]
    LUO J,ZHOU C,LIU F.Multipoint design optimization of a transonic compressor blade by using an adjoint method[J].Journal of Turbomachinery,2014,136（5）:051005.1-051005.10.
    [20]
    LUO J,LIU F.Multi-objective optimization of a transonic compressor rotor by using an adjoint method[J].AIAA Journal,2015,53（3）:797-801.
    [21]
    WANG D,HE L.Adjoint aerodynamic design optimization for blades in multistage turbomachines：Part Ⅰ methodology and verification[J].Journal of Turbomachinery,2010,132（2）:2141-2155.
    [22]
    WALTHER B,NADARAJAH S.Constrained adjoint-based aerodynamic shape optimization of a single-stage transonic compressor[J].Journal of Turbomachinery,2013,135（2）:021017.1-021017.10.
    [23]
    罗佳奇,杨婧.基于伴随方法的单级低速压气机气动设计优化[J].航空学报,2020,41（5）:134-143.
    [24]
    MA C,SU X R,YUAN X.An efficient unsteady adjoint optimization system for multistage turbomachinery[J].Journal of Turbomachinery,2017,139（1）:011003.1-011003.12.
    [25]
    CHEN L,CHEN J.Aerodynamic optimization design for high pressure turbines based on the adjoint approach[J].Chinese Journal of Aeronautics,2015,28（3）:757-769.
    [26]
    GILES M B,PIERCE N A.On the properties of solutions of the adjoint Euler equations[EB/OL].[2020-10-30].http:∥www2.maths.ox.ac.uk/~gilesm/files/icfd_adj.pdf.
    [27]
    罗佳奇.基于伴随方法的三维涡轮叶片气动优化设计[D].西安:西北工业大学,2011.
    [28]
    DENTON J D.Loss mechanisms in turbomachines[J].Journal of Turbomachinery,1993,115（4）:621-656.
    [29]
    JOUINI D B M.Experimental investigation of two transonic linear turbine cascades at off-design conditions[D].Ottawa，Canada:Carleton University,2000.
    [30]
    BALDWIN B S,LOMAX H.Thin layer approximation and algebraic model for separated turbulent flow[R].AIAA 1978-257,1978.
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