基于体积力模型的大S弯进气道与风扇耦合计算研究
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摘要
为理解超紧凑大S弯进气道与风扇的耦合效应,基于体积力模拟方法开展了一体化计算研究。研究的进气道长径比为2.5,使用Rotor 67进行耦合分析,体积力模型与冻结转子计算得到的总压比、总温比和等熵效率分别相差4.49%,0.26%和2.38%。流场分析表明,风扇对入口段流场影响较为明显,主要体现为畸变区的顺向偏转与微弱衰减;进气道出口畸变经过风扇叶片后得到改善,大低压区和反向旋流基本消失;而流体在叶片的前后缘旋流角与轴向速度的综合改变量越大,风扇对气流做功越多。总的来说,超紧凑大S弯进气道与风扇之间耦合比较明显,需要在设计时进行详细的考察。
Towards understanding the coupling effect between ultra-compact S-shaped inlet and fan,integrated simulation study was carried out using body force modeling method. The inlet model has a length to diameter ratio of 2.5 and Rotor 67 was used for the coupling analysis. The differences between body force modeling and frozen rotor simulation are 4.49%,0.26% and 2.38% respectively for total pressure ratio,total temperature ratio and isentropic efficiency. Flow field analysis shows that,in the entrance part,the fan has a significant influence on the distorted flow which is co-rotated with the fan and attenuated slightly. The distortion is holistically improved after the fan blades where the large low pressure region and counter-rotating swirl disappear. The more the swirl angle and axial velocity between the leading and trialing edges change,the higher the fan works. In summary,the coupling between the ultra-compact S-shaped inlet and fan is significant and needs to be examined in details.
Towards understanding the coupling effect between ultra-compact S-shaped inlet and fan,integrated simulation study was carried out using body force modeling method. The inlet model has a length to diameter ratio of 2.5 and Rotor 67 was used for the coupling analysis. The differences between body force modeling and frozen rotor simulation are 4.49%,0.26% and 2.38% respectively for total pressure ratio,total temperature ratio and isentropic efficiency. Flow field analysis shows that,in the entrance part,the fan has a significant influence on the distorted flow which is co-rotated with the fan and attenuated slightly. The distortion is holistically improved after the fan blades where the large low pressure region and counter-rotating swirl disappear. The more the swirl angle and axial velocity between the leading and trialing edges change,the higher the fan works. In summary,the coupling between the ultra-compact S-shaped inlet and fan is significant and needs to be examined in details.
引文
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[16]徐诸霖,达兴亚,范召林.基于五孔探针的大S弯进气道旋流畸变研究[J].航空学报,2017,38(12).
[17]徐诸霖,达兴亚,范召林,等.一种适用于进气道/风扇一体化计算的体积力模型[J].推进技术,2019,40(4).(XU Zhu-lin,DA Xing-ya,FAN Zhao-lin,et al.A Body Force Model for the Computation of Inlet and Fan Integration[J].Journal of Propulsion and Technology,2019,40(4).)
[18]Marble F E.Three-Dimensional Flow in Turbomachines[C].Princeton:High Speed Aerodynamics and Jet Propulsion,1964.
[19]Gong Y,Tan C,Gordon K.A Computational Model for Short Wavelength Stall Inception and Development in Multi-Stage Compressors[J].Journal of Turbomachinery,1999,121(4):726-734.
[2]Jirasek A.Example of Integrated CFD and Experimental Studies:Design of Flow Control in the FOI-EIC-01 Inlet[J].Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering,2009,223(4):369-377.
[3]Sheoran Y,Bouldin B,Krishnan P M.Compressor Performance and Operability in Swirl Distortion[J].Journal of Turbomachinery,2012,134(4).
[4]Aulehla F.Intake Swirl-a Major Disturbance Parameter in Engine/Intake Compatibility[C].Seattle:Proceedings of the 13th Congress of ICAS/AIAA,1982.
[5]Smith L.The Radial Equilibrium Equation of Turbomachinery[J].Journal of Engineering for Power,1966,88(1):1-12.
[6]SAE AIR 5686-2010.A Methodology for Assessing Inlet Swirl Distortion[S].
[7]Arend D J,Castner R S,Frate F C.Low Cost,Compact and Versatile Rig for Integrated Inlet and Propulsion Systems Research[R].AIAA 2006-1313.
[8]Chima R V,Arend D J,Castner R S,et al.CFD Models of a Serpentine Inlet,Fan and Nozzle[R].AIAA 2010-0033.
[9]Nichols R H,Klepper J B,McDaniel D R,et al.Firebolt c2.0-Unstructured Grid Navier Stokes Code for Airframe/Propulsion Integration[R].AIAA 2015-0043.
[10]Pardo A C,Mehdi A,Pachidis V,et al.Numerical Study of the Effect of Multiple Tightly-Wound Vortices on a Transonic Fan Stage Performance[R].ASME GT2014-26481.
[11]Gunn E J,Tooze S E,Hall C A,et al.An Experimental Study of Loss Sources in a Fan Operating with Continuous Inlet Stagnation Pressure Distortion[J].Jounal of Turbomachinery,2012,135(5).
[12]Rademakers R,Bindl S,Niehuis R,et al.Effects of Flow Distortions as They Occur in S-Duct Inlets on the Performance and Stability of a Jet Engine[J].Journal of Engineering for Gas Turbines and Power,2015,138(2).
[13]刘雷,宋彦萍,陈焕龙,等.S弯进气道优化对其内流场及性能影响研究[J].工程热物理学报,2015,36(1):50-54.
[14]许开富,乔渭阳,罗华玲.畸变进气条件下风扇三维非定常流动数值模拟[J].热能动力工程,2009,24(5):571-576.
[15]Da X Y,Fan Z L,Fan J C,et al.Microjet Flow Control in an Ultra-Compact Serpentine Inlet[J].Chinese Journal of Aeronautics,2015,28(5):1381-1390.
[16]徐诸霖,达兴亚,范召林.基于五孔探针的大S弯进气道旋流畸变研究[J].航空学报,2017,38(12).
[17]徐诸霖,达兴亚,范召林,等.一种适用于进气道/风扇一体化计算的体积力模型[J].推进技术,2019,40(4).(XU Zhu-lin,DA Xing-ya,FAN Zhao-lin,et al.A Body Force Model for the Computation of Inlet and Fan Integration[J].Journal of Propulsion and Technology,2019,40(4).)
[18]Marble F E.Three-Dimensional Flow in Turbomachines[C].Princeton:High Speed Aerodynamics and Jet Propulsion,1964.
[19]Gong Y,Tan C,Gordon K.A Computational Model for Short Wavelength Stall Inception and Development in Multi-Stage Compressors[J].Journal of Turbomachinery,1999,121(4):726-734.