开式转子发动机具备高效率、高燃油经济性的优点,然而开式转子叶片巨大的噪声辐射是亟待解决的问题。基于非定常涡格法、涡粒子法和Ffowcs-Williams and Hawkings方程,发展了不依赖于空间体网格的开式转子气动-噪声高效预测方法,引入三...开式转子发动机具备高效率、高燃油经济性的优点,然而开式转子叶片巨大的噪声辐射是亟待解决的问题。基于非定常涡格法、涡粒子法和Ffowcs-Williams and Hawkings方程,发展了不依赖于空间体网格的开式转子气动-噪声高效预测方法,引入三维普朗特-葛劳渥法则,进行可压缩性修正。针对NASA(National Aeronautics and Space Administration)SR-7A单排开式转子的起飞工况进行了验证计算,气动结果与NASA试验值和商业软件计算值的误差均小于1%,主要单音噪声与总声压级指向性结果预测误差可低至1 dB以内。在同等研究对象和硬件条件下,本文方法计算所需CPU核时低于通用URANS(Unsteady Reynolds-Averaged Navier-Stokes)计算所需的1%。考虑起飞迎角下的周向不均匀来流畸变,系统研究了SR-7A单排转子在0°~20°来流迎角下的气动参数和噪声特性。结果表明,随着来流迎角的增大,转子的时均推力、功率、效率呈现指数增长趋势,转子桨盘内载荷时均值呈现线性增长趋势。转子各项载荷的非定常波动幅值随着迎角的增大而增加。单个叶片的载荷波动峰谷值与运动相位相比存在17°~56°的相位滞后现象,这与噪声周向指向性结果中的偏转非常相关。在0°~20°迎角内,转子上方总声压级从107 dB降低至99 dB,转子下方位置总声压级从107 dB升高至114 dB。此外,来流迎角与桨盘的相互作用会额外导致最高达73 dB的轴频率单音噪声。针对单排转子的噪声源项解耦分析表明,来流迎角对非定常载荷噪声的增益作用非常显著。本文开发的方法可以用较低成本得到开式转子的非定常气动及噪声特性,并且具备多角度的噪声源解耦能力,为未来低噪声开式转子设计提供了有力工具。展开更多
针对超声速流场智能重构方法存在的复杂波系结构特征丢失、无法有效捕捉非定常流场的时间演化特性,以及共同导致的无法准确辨识激波串前缘位置(shock train leading edge,STLE)等问题,提出基于组合式细节特征增强的神经网络模型。基于...针对超声速流场智能重构方法存在的复杂波系结构特征丢失、无法有效捕捉非定常流场的时间演化特性,以及共同导致的无法准确辨识激波串前缘位置(shock train leading edge,STLE)等问题,提出基于组合式细节特征增强的神经网络模型。基于稀疏压力数据实现密度梯度场的高精度预测,模型通过多层卷积网络串联建立流场的主要波系结构特征,利用残差网络通过跳跃连接将不同尺度感受野的特征进行融合,增强重构流场的细节特征表达能力。基于冲压发动机数值模拟计算构建的数据集进行验证,结果显示,与多层卷积神经网络相比,该方法在整个测试集上的平均峰值信噪比提升了9.5%。重构流场的STLE与数值计算结果高度吻合,进一步证明了所提方法的有效性。展开更多
This study investigates the performance boundaries of ramjet and scramjet engines fueled by boronbased propellant through full-scale engine modeling and three-dimensional computational fluid dynamics simulations.Resul...This study investigates the performance boundaries of ramjet and scramjet engines fueled by boronbased propellant through full-scale engine modeling and three-dimensional computational fluid dynamics simulations.Results show that the performance boundary between ramjets and scramjets occurs near Mach 7.Specifically,at Mach 6,the ramjet exhibits a 1290 m/s higher specific impulse than the scramjet;however,at Mach 7,their performance becomes comparable.The ramjet's higher static temperature promotes boron particle vaporization and B_(2)O_(2) dissociation,limiting the total temperature increase,unlike in scramjets.The boron vapor mass fraction significantly impacts this temperature difference,with ramjets exhibiting values 8.5 and 3.9 times higher than scramjets at Mach 6 and Mach 7,respectively.Despite lower total temperatures,ramjets achieve more efficient boron combustion due to the combined effects of higher pressures and longer particle residence times.These findings offer valuable insights for engine designers in selecting ramjet or scramjet configurations for boron-fueled propulsion systems.展开更多
文摘开式转子发动机具备高效率、高燃油经济性的优点,然而开式转子叶片巨大的噪声辐射是亟待解决的问题。基于非定常涡格法、涡粒子法和Ffowcs-Williams and Hawkings方程,发展了不依赖于空间体网格的开式转子气动-噪声高效预测方法,引入三维普朗特-葛劳渥法则,进行可压缩性修正。针对NASA(National Aeronautics and Space Administration)SR-7A单排开式转子的起飞工况进行了验证计算,气动结果与NASA试验值和商业软件计算值的误差均小于1%,主要单音噪声与总声压级指向性结果预测误差可低至1 dB以内。在同等研究对象和硬件条件下,本文方法计算所需CPU核时低于通用URANS(Unsteady Reynolds-Averaged Navier-Stokes)计算所需的1%。考虑起飞迎角下的周向不均匀来流畸变,系统研究了SR-7A单排转子在0°~20°来流迎角下的气动参数和噪声特性。结果表明,随着来流迎角的增大,转子的时均推力、功率、效率呈现指数增长趋势,转子桨盘内载荷时均值呈现线性增长趋势。转子各项载荷的非定常波动幅值随着迎角的增大而增加。单个叶片的载荷波动峰谷值与运动相位相比存在17°~56°的相位滞后现象,这与噪声周向指向性结果中的偏转非常相关。在0°~20°迎角内,转子上方总声压级从107 dB降低至99 dB,转子下方位置总声压级从107 dB升高至114 dB。此外,来流迎角与桨盘的相互作用会额外导致最高达73 dB的轴频率单音噪声。针对单排转子的噪声源项解耦分析表明,来流迎角对非定常载荷噪声的增益作用非常显著。本文开发的方法可以用较低成本得到开式转子的非定常气动及噪声特性,并且具备多角度的噪声源解耦能力,为未来低噪声开式转子设计提供了有力工具。
文摘针对超声速流场智能重构方法存在的复杂波系结构特征丢失、无法有效捕捉非定常流场的时间演化特性,以及共同导致的无法准确辨识激波串前缘位置(shock train leading edge,STLE)等问题,提出基于组合式细节特征增强的神经网络模型。基于稀疏压力数据实现密度梯度场的高精度预测,模型通过多层卷积网络串联建立流场的主要波系结构特征,利用残差网络通过跳跃连接将不同尺度感受野的特征进行融合,增强重构流场的细节特征表达能力。基于冲压发动机数值模拟计算构建的数据集进行验证,结果显示,与多层卷积神经网络相比,该方法在整个测试集上的平均峰值信噪比提升了9.5%。重构流场的STLE与数值计算结果高度吻合,进一步证明了所提方法的有效性。
基金funded by the National Natural Science Foundation of China(Grant No.U21B2086)。
文摘This study investigates the performance boundaries of ramjet and scramjet engines fueled by boronbased propellant through full-scale engine modeling and three-dimensional computational fluid dynamics simulations.Results show that the performance boundary between ramjets and scramjets occurs near Mach 7.Specifically,at Mach 6,the ramjet exhibits a 1290 m/s higher specific impulse than the scramjet;however,at Mach 7,their performance becomes comparable.The ramjet's higher static temperature promotes boron particle vaporization and B_(2)O_(2) dissociation,limiting the total temperature increase,unlike in scramjets.The boron vapor mass fraction significantly impacts this temperature difference,with ramjets exhibiting values 8.5 and 3.9 times higher than scramjets at Mach 6 and Mach 7,respectively.Despite lower total temperatures,ramjets achieve more efficient boron combustion due to the combined effects of higher pressures and longer particle residence times.These findings offer valuable insights for engine designers in selecting ramjet or scramjet configurations for boron-fueled propulsion systems.
