本研究项目以高超声速超燃发动机设计为背景，提出并研究了适用于超声速燃烧室内三维"燕尾形"凹槽火焰稳定器。通过理论、数值和实验方法该类型凹槽火焰稳定器在促进凹槽流与超声速主流之间的流动交换作用和基本流动机理。研究结果表明，三维"燕尾形"凹槽火焰稳定器通过凹槽内三维漩涡的运动和组织，在凹槽内形成向横向下游方向的抽吸流动作用，在凹槽中心区将主流边界层吸入，在凹槽两侧端部将低速凹槽流排出。通过对相同对称面形状的二维凹槽和三维凹槽的性能评估，三维凹槽结构能够提升凹槽与外部气流交换率达98.5%。带氢气射流的化学反应流动模拟结果显示，采用凹腔火焰稳定器的超声速燃烧室流场是比较典型的超燃/亚燃混合流场，这种混合流场会导致燃烧室严重的总压损失。.本项研究的成果为为克服超燃发动机推力不足的问题提供新的思路，为我国自行研发高效、低阻超燃推进技术，实现吸气时高超声速飞行技术提供给出科学和应用技术支持。

A new three-dimensional "swallowtail-type" cavity as the flameholder the was proposed and studies to support the design of a Scramjet engine. The flow features and the basic mechanism of mixing enhancement between the cavity flow and the supersonic main fow in a supersonic chamber were studied. The results show that three-dimension vortex movement exist in the three-dimensional "swallowtail-type" cavity which induces the transverse flow in the cavit, helps to suck the boudary layer at the cavity head and exhausts the cavity flow in the lateral ends of the cavity. A comparason between the two-dimensional cavity and the new type cavity with the same shape in the symmetric plane shows that the new type cavity can improve the mass exchange between the cavity flow and supersonic flow up to 98.5%. When Hydrogen fuel jet and chemical reaction are considered, the flowfield of supersonic combustor is typically supersonic/subsonic combustion blending, which results in the serious total pressure loss of the superonsic combustor. .The result of this project will provide new idea for overcome the problem of low thrust of current Scramjet engine. Such a research work will support the devlopment of high-performance, low-drag Scramjet propulsion technology of and help to realize the air-breathing hypersonic aviation of our country.

本研究项目以高超声速超燃发动机设计为背景，提出并研究了适用于超声速燃烧室内三维"燕尾形"凹槽火焰稳定器。通过理论、数值和实验方法该类型凹槽火焰稳定器在促进凹槽流与超声速主流之间的流动交换作用和基本流动机理。研究结果表明，三维"燕尾形"凹槽火焰稳定器通过凹槽内三维漩涡的运动和组织，在凹槽内形成向横向下游方向的抽吸流动作用，在凹槽中心区将主流边界层吸入，在凹槽两侧端部将低速凹槽流排出。通过对相同对称面形状的二维凹槽和三维凹槽的性能评估，三维凹槽结构能够提升凹槽与外部气流交换率达98.5%。带氢气射流的化学反应流动模拟结果显示，采用凹腔火焰稳定器的超声速燃烧室流场是比较典型的超燃/亚燃混合流场，这种混合流场会导致燃烧室严重的总压损失。本项研究的成果为为克服超燃发动机推力不足的问题提供新的思路，为我国自行研发高效、低阻超燃推进技术，实现吸气时高超声速飞行技术提供给出科学和应用技术支持。