一体化加力燃烧室隔热屏冷却特性研究OA
Cooling Characteristics of the Integrated Afterburner Combustor Heat Shield
针对一体化加力燃烧室的气动热力条件,通过数值仿真方法系统地研究了隔热屏气膜冷却主要结构参数对冷却性能的影响.研究结果表明,在相同进出口边界条件下,上游引射器开度的增加,增大了次流流量,将隔热屏与主流燃气分隔开;气膜孔径的增加,增大了射流深度与动量,降低了气膜覆盖的均匀性与延续性,气膜孔倾斜角的增加,降低了气膜的贴壁性;气膜孔轴向间距的增加,强化了气膜的叠加效应,增大了气膜覆盖的范围及均匀性.最佳的结构参数为:孔径d=1.2 mm,孔倾斜角度θ=30°,轴向间距S=10 mm,波纹板高度H=6 mm及采用叉排的排列方式.
Based on the aerodynamic and thermodynamic conditions of the integrated afterburner,the influence of main structural parameters of the insulation screen air film cooling on the cooling performance is systematically studied through numerical simulation methods.This research results indicate that under the same inlet and outlet boundary conditions,an increase in the opening of the upstream injector increases the secondary flow rate,separating the heat shield from the main flow of gas.The increase in the aperture of the gas film increases the depth and momentum of the jet,and reduces the uniformity and continuity of the gas film coverage.The increase in the inclination angle of the gas film hole reduces the wall adhesion of the gas film.The increase in the axial spacing of the gas film holes enhances the superposition effect of the gas film,and increases the coverage range and uniformity of the gas film.The optimal structural parameters are as follows:The aperture of the hole d=1.2 mm,the tilt angle of the hole θ=30°,the axial spacing S=10 mm,and the corrugated plate height H=6 mm.This research uses a forked arrangement for the holes in the screen.
秦贞一;齐海成;王春华;张靖周
南京航空航天大学能源与动力学院,南京 210016中国航发沈阳发动机研究所,沈阳 110015南京航空航天大学能源与动力学院,南京 210016南京航空航天大学能源与动力学院,南京 210016
航空航天
气膜冷却隔热屏引射器开度一体化加力燃烧室数值模拟
film coolingheat shieldejector opening degreeintegrated afterburner combustornumerical simulation
《南京航空航天大学学报(自然科学版)》 2026 (4)
924-935,12
国家科技重大专项(J2019-Ⅲ-0019-0063).
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