CAJ | 학술논문

建立了带有波瓣混合器、加力燃烧室及中心锥的涡扇发动排气系统流场计算模型和3~5μm波段红外辐射特性仿真模型，并通过发动机地面辐射特性测试对计算模型进行验证。对降低壁面发射率、部件冷却及两种方案结合三种红外辐射抑制方案开展研究。结果表明：降低壁面发射率能抑制除90°外所有方向的红外辐射；在0°时，发射率每降低0.15，全部涂覆的抑制效果提高约16%；局部涂覆的抑制效果提高约14%；中心锥温度降低300 K，0°~15°的辐射抑制幅度达44%；喷管扩散段温度每降低25 K，在50°方向能产生8%的抑制效果；当两种方案结合时，在0°~5°能够产生80%的抑制效果。在10°~40°产生50%的抑制效果。随着探测角进一步增大，固体辐射所占比例下降，抑制效果降低。
건립료대유파판혼합기、가력연소실급중심추적와선발동배기계통류장계산모형화3~5μm파단홍외복사특성방진모형，병통과발동궤지면복사특성측시대계산모형진행험증。대강저벽면발사솔、부건냉각급량충방안결합삼충홍외복사억제방안개전연구。결과표명：강저벽면발사솔능억제제90°외소유방향적홍외복사；재0°시，발사솔매강저0.15，전부도복적억제효과제고약16%；국부도복적억제효과제고약14%；중심추온도강저300 K，0°~15°적복사억제폭도체44%；분관확산단온도매강저25 K，재50°방향능산생8%적억제효과；당량충방안결합시，재0°~5°능구산생80%적억제효과。재10°~40°산생50%적억제효과。수착탐측각진일보증대，고체복사소점비례하강，억제효과강저。
The flow field and infrared radiation in the 3-5 μm model of an aero-engine exhaust system was built with lobed mixer, afterburner and cone. The calculated model was examined using the aero -engine ground infrared radiation characteristic test. The study of infrared radiation inhibitory schemes was established using low emissivity coating, components cooling, either alone or mixed. The results show that reducing the infrared emissivity of aero-engine wall restrains infrared radiation effectively in all directions except 90° . With emissivity reduces by every 0.15, the infrared radiation of 0° could be reduced by about 16% when all components are coated whereas the inhibitory effect improves about 14% when partly coated. If the temperature of cone decreases by 300 K, the infrared radiation on 0°-15° is reduced by 44%. If the temperature of divergent part of nozzle decreases by 25 K, the signature at 50° reduces by 8%. If combining the two methods, the signature is reduced by 80% on 0°-5° and by 50% on 10°-40°.Along with the increasing angle of detection, the proportion of the solid radiation is found to be declining, and the inhibitory effect is decreasing.