随着加力燃烧室进口参数的不断提高，传统结构面临诸多问题，使得一体化设计成为主流趋势，而不同尾缘结构的支板一体化稳定器在非常规参数下的研究目前还较少。因此本文设计了一种加力燃烧室支板稳定器尾缘构型，在进气余旋角-25~25o、来流压力0.1~0.7 MPa、燃油喷射角度30~150o、喷嘴孔径0.5~1.4 mm、液气动量比33~124等工况下研究了其液雾分布特性，并提出了其余7种尾缘构型进行对比，探究尾缘结构对射流雾化的潜在影响性。研究表明：增大来流压力、负进气余旋角（背风侧）时，射流轨迹降低，穿深下降；增大喷嘴直径、90~110o范围内逆向燃油喷射角、0~25o正进气余旋角时，射流穿透深度增大，轨迹升高，空流区尺寸逐渐增大；文中A~I几种尾缘构型对射流外轮廓几乎无影响，而对内边界影响较大；液气动量比对射流穿深起决定作用，韦伯数影响较小

As traditional structures face numerous challenges with the continuous improvement of inlet pa-rameters in afterburners, integrated design has become the mainstream trend. However, research on integrated strut flameholder with trailing edge configurations under unconventional parame-ters is still relatively scarce. Therefore, this study presents a design for trailing edge configura-tion of an integrated strut flameholder used in afterburner. It investigates the characteristics of liquid spray distribution under varied conditions, including inlet cosine rotation angles ranging from -25° to 25°, inlet pressures from 0.1 to 0.7 MPa, fuel injection angles from 30° to 150°, nozzle diameters from 0.5 to 1.4 mm, and liquid-to-air momentum ratios from 33 to 124. Addi-tionally, seven other trailing edge configurations are compared to study their potential influences on jet atomization. The experiments demonstrate that increasing inlet pressure and negative in-let cosine rotation angle (leeward side) result in reduced jet trajectory and penetration depth. Conversely, increasing nozzle diameter and the reverse fuel injection angle between 90o and 110°, along with positive inlet cosine rotation angle below 25o, lead to increased jet penetration depth, higher trajectory, and gradual enlargement of the void area. The different trailing edge configurations in this article named A~I have minimal impact on the outer trajectory of the jet but significantly affect the inner boundary. The liquid-to-air momentum ratio plays a critical role in jet penetration depth, while the Weber number has a less influence