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    Three-Dimensional Unsteady Aerodynamic Optimization of a Transonic Compressor Stage Using an Implicit Discrete Adjoint Harmonic Balance Method

    Source: Journal of Turbomachinery:;2024:;volume( 147 ):;issue: 007::page 71016-1
    Author:
    Wu, Hangkong
    ,
    Wang, Dingxi
    ,
    Huang, Xiuquan
    DOI: 10.1115/1.4067290
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The design of high-loading and compact modern turbomachines results in strong unsteady interactions between two adjacent blade rows, which has been found to have a noticeable impact on aerodynamic performances of turbomachines. Therefore, it is necessary to consider unsteady effects arising from blade row interactions in multirow turbomachinery aerodynamic analyses and design optimizations. In this work, three-dimensional multirow unsteady aerodynamic design optimizations of turbomachinery blades are performed using a full-viscosity discrete adjoint solver developed by using the source code transformation automatic differentiation tool—Tapenade. An efficient time domain harmonic balance (HB) method with a complete rotor–stator interface coupling treatment is used to analyze multirow unsteady flow and adjoint fields. To stabilize the solution, the one-step Jacobi iteration combined with the lower–upper symmetric Gauss-Seidel (LU-SGS/one-step Jacobi) method is used for an implicit solution of the HB equation systems. For an efficient sensitivity evaluation, the effect of an adjoint solver’s root-mean-square (RMS) residual convergence levels on adjoint sensitivity accuracy is thoroughly studied to find an adjoint solver’s convergence criterion. The results from a single-stage transonic compressor-NASA Stage 35 reveal that when the adjoint RMS residual is reduced by three orders, accurate sensitivity information can be obtained, leading to a 41% reduction in computational cost compared with a fully converged one. The fully implicit LU-SGS/one-step Jacobi method can stabilize the solution of a multirow discrete adjoint solver while the solution of the semi-implicit LU-SGS equation system diverges quickly. Furthermore, compared with a steady one, the unsteady optimization can achieve more performance gains.
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      Three-Dimensional Unsteady Aerodynamic Optimization of a Transonic Compressor Stage Using an Implicit Discrete Adjoint Harmonic Balance Method

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    http://yetl.yabesh.ir/yetl1/handle/yetl/4305586
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    contributor authorWu, Hangkong
    contributor authorWang, Dingxi
    contributor authorHuang, Xiuquan
    date accessioned2025-04-21T10:08:37Z
    date available2025-04-21T10:08:37Z
    date copyright12/20/2024 12:00:00 AM
    date issued2024
    identifier issn0889-504X
    identifier otherturbo_147_7_071016.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4305586
    description abstractThe design of high-loading and compact modern turbomachines results in strong unsteady interactions between two adjacent blade rows, which has been found to have a noticeable impact on aerodynamic performances of turbomachines. Therefore, it is necessary to consider unsteady effects arising from blade row interactions in multirow turbomachinery aerodynamic analyses and design optimizations. In this work, three-dimensional multirow unsteady aerodynamic design optimizations of turbomachinery blades are performed using a full-viscosity discrete adjoint solver developed by using the source code transformation automatic differentiation tool—Tapenade. An efficient time domain harmonic balance (HB) method with a complete rotor–stator interface coupling treatment is used to analyze multirow unsteady flow and adjoint fields. To stabilize the solution, the one-step Jacobi iteration combined with the lower–upper symmetric Gauss-Seidel (LU-SGS/one-step Jacobi) method is used for an implicit solution of the HB equation systems. For an efficient sensitivity evaluation, the effect of an adjoint solver’s root-mean-square (RMS) residual convergence levels on adjoint sensitivity accuracy is thoroughly studied to find an adjoint solver’s convergence criterion. The results from a single-stage transonic compressor-NASA Stage 35 reveal that when the adjoint RMS residual is reduced by three orders, accurate sensitivity information can be obtained, leading to a 41% reduction in computational cost compared with a fully converged one. The fully implicit LU-SGS/one-step Jacobi method can stabilize the solution of a multirow discrete adjoint solver while the solution of the semi-implicit LU-SGS equation system diverges quickly. Furthermore, compared with a steady one, the unsteady optimization can achieve more performance gains.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleThree-Dimensional Unsteady Aerodynamic Optimization of a Transonic Compressor Stage Using an Implicit Discrete Adjoint Harmonic Balance Method
    typeJournal Paper
    journal volume147
    journal issue7
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.4067290
    journal fristpage71016-1
    journal lastpage71016-16
    page16
    treeJournal of Turbomachinery:;2024:;volume( 147 ):;issue: 007
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
    yabeshDSpacePersian