为研究中心支板顶角对火箭基组合循环发动机(Rocket Based Combined Cycle,RBCC)进气道的影响,优化RBCC进气道设计方法,利用数值模拟对RBCC进气道开展了研究。分析了中心支板顶角变化对进气道内压缩段最小长度的影响,通过数值模拟对中...为研究中心支板顶角对火箭基组合循环发动机(Rocket Based Combined Cycle,RBCC)进气道的影响,优化RBCC进气道设计方法,利用数值模拟对RBCC进气道开展了研究。分析了中心支板顶角变化对进气道内压缩段最小长度的影响,通过数值模拟对中心支板顶角变化对典型工况下进气道的流场特征和性能影响开展了定量及定性的研究。研究结果表明,增加支板顶角可以减小进气道长度(相比于Strut_1,Strut_2至Strut_5的隔离段长度分别减少47%,62%,70%,75%)和粘性阻力系数(相比于Strut_1,在Ma∞=1.5时Strut_2至Strut_5内压缩段粘性阻力系数分别减少33%,45%,55%,59%;在Ma∞=5.5时Strut_2至Strut_5内压缩段粘性阻力系数分别减少37%,50%,57%和61%),但并不影响进气道流量系数和流动均匀度。同时根据研究结果对进气道进行优化设计,能有效提高进气道的起动能力及其他性能参数,进气道的内、外压缩段阻力系数分别降低13.5%和5.7%,总压恢复系数和循环静温比分别提高2.6%和0.5%。展开更多
A numerical method based on the doublet distribution for calculating the effects of inlet flow on hydrodynamic characteristics of a hydrofoil-strut-pod configuration under the linearized free water surface condition i...A numerical method based on the doublet distribution for calculating the effects of inlet flow on hydrodynamic characteristics of a hydrofoil-strut-pod configuration under the linearized free water surface condition is presented in this paper. Inlet flow condition is represented by a control section 5, in the inlet tube on which the axial velocity is u-niform and determined by a given flowrate. The numerical results for some typical cases are compared with corresponding experimental data. It is found that good agreement between computational and experimental results can be achieved. This numerical method may be applied to the prediction of foilborne performance characteristics of a waterjet propelled hydrofoil craft and to optimization of integrated hydrofoil waterjet propulsion sys-展开更多
针对某包含引射、亚燃两模态（马赫数为0～4．0）的支板式火箭基组合循环（rocket based combinedcycle）发动机地面集成试验，设计了样机用带支板的二元进气道．数值模拟对比分析了在亚燃模态下进气道加入支板前后的性能以及流道内的...针对某包含引射、亚燃两模态（马赫数为0～4．0）的支板式火箭基组合循环（rocket based combinedcycle）发动机地面集成试验，设计了样机用带支板的二元进气道．数值模拟对比分析了在亚燃模态下进气道加入支板前后的性能以及流道内的流动情况，验证了设计的合理性，并且给出了支板位置以及构型的改变引起RBCC发动机进气道性能变化的规律和优化设计结果．展开更多
文摘为研究中心支板顶角对火箭基组合循环发动机(Rocket Based Combined Cycle,RBCC)进气道的影响,优化RBCC进气道设计方法,利用数值模拟对RBCC进气道开展了研究。分析了中心支板顶角变化对进气道内压缩段最小长度的影响,通过数值模拟对中心支板顶角变化对典型工况下进气道的流场特征和性能影响开展了定量及定性的研究。研究结果表明,增加支板顶角可以减小进气道长度(相比于Strut_1,Strut_2至Strut_5的隔离段长度分别减少47%,62%,70%,75%)和粘性阻力系数(相比于Strut_1,在Ma∞=1.5时Strut_2至Strut_5内压缩段粘性阻力系数分别减少33%,45%,55%,59%;在Ma∞=5.5时Strut_2至Strut_5内压缩段粘性阻力系数分别减少37%,50%,57%和61%),但并不影响进气道流量系数和流动均匀度。同时根据研究结果对进气道进行优化设计,能有效提高进气道的起动能力及其他性能参数,进气道的内、外压缩段阻力系数分别降低13.5%和5.7%,总压恢复系数和循环静温比分别提高2.6%和0.5%。
文摘A numerical method based on the doublet distribution for calculating the effects of inlet flow on hydrodynamic characteristics of a hydrofoil-strut-pod configuration under the linearized free water surface condition is presented in this paper. Inlet flow condition is represented by a control section 5, in the inlet tube on which the axial velocity is u-niform and determined by a given flowrate. The numerical results for some typical cases are compared with corresponding experimental data. It is found that good agreement between computational and experimental results can be achieved. This numerical method may be applied to the prediction of foilborne performance characteristics of a waterjet propelled hydrofoil craft and to optimization of integrated hydrofoil waterjet propulsion sys-
文摘针对某包含引射、亚燃两模态（马赫数为0～4．0）的支板式火箭基组合循环（rocket based combinedcycle）发动机地面集成试验，设计了样机用带支板的二元进气道．数值模拟对比分析了在亚燃模态下进气道加入支板前后的性能以及流道内的流动情况，验证了设计的合理性，并且给出了支板位置以及构型的改变引起RBCC发动机进气道性能变化的规律和优化设计结果．
