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    Influences of Design Parameters on a Double Serpentine Convergent Nozzle

    Source: Journal of Engineering for Gas Turbines and Power:;2016:;volume( 138 ):;issue: 007::page 72301
    Author:
    Sun, Xiao
    ,
    Wang, Zhan
    ,
    Zhou, Li
    ,
    Liu, Zeng
    ,
    Shi, Jing
    DOI: 10.1115/1.4032338
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Serpentine nozzles are supplied in stealth bombers and unmanned aerial vehicles (UAVs) to evidently suppress the infrared radiation signatures (IRSs) emitted by engine exhausts. It is commonly known that excessive geometric parameters are included in the double serpentine nozzle design and, as a result, the aim of this paper is to study the influences of the design parameters on the performance of double serpentine nozzle. To this end, the design method of the serpentine nozzle was concisely introduced, and the qualifications to completely shield turbine were given. Simulations using six different turbulence models were conducted and compared to the experimental data in order to determine the suitable turbulence model for serpentine duct simulations. Then, the effects of geometric design parameters at the first serpentine paragraph exit (the dimensionless width of W1/D, area of A1/Ain, and offset distance of خ”Y1/L1) on the flowfield, and the performance of double serpentine nozzle was investigated numerically. The validation study shows that the simulations with shearstress transport (SST) خ؛–د‰ turbulence model adopted can accurately predict the flux rate, the axial thrust, and the static pressure of the experimental nozzle, and therefore, SST خ؛–د‰ turbulence model is the most suitable turbulence model in the selected six turbulence models to be used for the simulation of the double serpentine nozzles. The numerical results show that friction loss increases with the increment of W1/D due to the increased wetted perimeter, but small value of W1/D would lead to large secondary flow loss; even the shock loss appears because of the steep curvature of the second turning. Small area of the first serpentine duct A1/Ain induces high flow velocity in the first duct, which corresponds to large friction loss. Steep offset distance of the first serpentine duct خ”Y1/L1 induces high local losses. As the geometric design parameters of the double serpentine nozzle interact mutually with the qualifications to completely shield the turbine, the range of design parameters should be synthetically chosen during the design progress. Thus, the width of the first serpentine duct W1/D is recommended to be from 1.0 to 1.3. The area of the first serpentine duct A1/Ain should be as large as possible, and the offset distance of the first serpentine خ”Y1/L1 should be small in the permission range of the design parameters.
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      Influences of Design Parameters on a Double Serpentine Convergent Nozzle

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    contributor authorSun, Xiao
    contributor authorWang, Zhan
    contributor authorZhou, Li
    contributor authorLiu, Zeng
    contributor authorShi, Jing
    date accessioned2017-05-09T01:28:36Z
    date available2017-05-09T01:28:36Z
    date issued2016
    identifier issn1528-8919
    identifier othergtp_138_07_072301.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/161127
    description abstractSerpentine nozzles are supplied in stealth bombers and unmanned aerial vehicles (UAVs) to evidently suppress the infrared radiation signatures (IRSs) emitted by engine exhausts. It is commonly known that excessive geometric parameters are included in the double serpentine nozzle design and, as a result, the aim of this paper is to study the influences of the design parameters on the performance of double serpentine nozzle. To this end, the design method of the serpentine nozzle was concisely introduced, and the qualifications to completely shield turbine were given. Simulations using six different turbulence models were conducted and compared to the experimental data in order to determine the suitable turbulence model for serpentine duct simulations. Then, the effects of geometric design parameters at the first serpentine paragraph exit (the dimensionless width of W1/D, area of A1/Ain, and offset distance of خ”Y1/L1) on the flowfield, and the performance of double serpentine nozzle was investigated numerically. The validation study shows that the simulations with shearstress transport (SST) خ؛–د‰ turbulence model adopted can accurately predict the flux rate, the axial thrust, and the static pressure of the experimental nozzle, and therefore, SST خ؛–د‰ turbulence model is the most suitable turbulence model in the selected six turbulence models to be used for the simulation of the double serpentine nozzles. The numerical results show that friction loss increases with the increment of W1/D due to the increased wetted perimeter, but small value of W1/D would lead to large secondary flow loss; even the shock loss appears because of the steep curvature of the second turning. Small area of the first serpentine duct A1/Ain induces high flow velocity in the first duct, which corresponds to large friction loss. Steep offset distance of the first serpentine duct خ”Y1/L1 induces high local losses. As the geometric design parameters of the double serpentine nozzle interact mutually with the qualifications to completely shield the turbine, the range of design parameters should be synthetically chosen during the design progress. Thus, the width of the first serpentine duct W1/D is recommended to be from 1.0 to 1.3. The area of the first serpentine duct A1/Ain should be as large as possible, and the offset distance of the first serpentine خ”Y1/L1 should be small in the permission range of the design parameters.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleInfluences of Design Parameters on a Double Serpentine Convergent Nozzle
    typeJournal Paper
    journal volume138
    journal issue7
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.4032338
    journal fristpage72301
    journal lastpage72301
    identifier eissn0742-4795
    treeJournal of Engineering for Gas Turbines and Power:;2016:;volume( 138 ):;issue: 007
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
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