目的 针对某型航空发动机二元尾喷管红外隐身问题,探索在尾喷管内流道面内涂覆兼顾红外辐射抑制与隔热功能的新型热阻涂层的最优方案。方法 建立了某二元喷管的三维可压缩湍流流场-红外辐射耦合计算框架,流场采用Fluent k-ε 湍流模型进行计算,红外辐射强度计算采用NUAA-IR软件,研究波长3~5 μm、探测距离5 000 m、方位角0°~90°内的红外辐射强度。设计了4种涂层涂覆方案：model 0无涂层（壁面发射率ε = 0.9）,model 1仅扩张段内流道面涂敷热阻涂层（ε = 0.12）,model 2仅收敛段涂敷（ε = 0.12）,model 3收敛段与扩张段均涂敷（ε = 0.12）。通过对比光谱辐射强度及辐射强度空间分布,定量评估不同涂覆方案的红外抑制效果。结果 不同方位角下3~5 μm红外辐射强度固体壁面辐射占主导,低发射率涂层显著削弱壁面贡献;其中4.15~4.5 μm主要受CO2的吸收影响,各方案差异较小。相较于model 0、model 1、model 3辐射强度降幅随着方位角增加呈现先增加后减小的趋势,其中方位角为30°时,降幅最大,model l和model 3宽边辐射强度较model 0分别下降19.1%和19.4%,窄边均下降6.9%;方位角增至90°时,四方案辐射强度趋同;model 2因收敛段投影面积趋近于零,辐射强度与model 0几乎重合,红外抑制贡献可忽略。结论 因此,若仅追求红外隐身,只需在扩张段内流道面涂敷低发射率涂层;若同时需要隐身和隔热功能,采用在扩张段涂敷低发射率热阻涂层、收敛段仅涂热阻涂层的组合方案,可在成本增幅有限的条件下获得同等红外抑制效果。
Abstract
Infrared stealth is critical for modern military aircraft to evade detection and tracking by infrared search-and-track systems. While aerodynamic and structural designs of nozzles have been extensively studied, the role of surface emissivity control through coatings remains an area with significant optimization potential. The work aims to systematically evaluate the infrared stealth issue of a certain type of engine aircraft two-dimensional (2D) nozzle and explore the optimal application scheme for a novel thermal resistance coating (TRC) applied inside the nozzle flow path, for balancing stealth performance with practical engineering considerations such as cost, weight, and thermal protection. The coating is designed to simultaneously suppress infrared radiation (in particularly in the 3-5 μm band) and provide thermal insulation for protecting nozzle structures. A three-dimensional compressible turbulent flow field-infrared radiation coupled numerical framework was established for a 2D nozzle. The flow field was solved through ANSYS Fluent with the k-ε turbulence model, while the infrared radiation intensity was subsequently calculated with the in-house software NUAA-IR, which integrated surface radiation, gas radiation (CO2 and H2O), and scattering effects. The analysis focused on the infrared radiation intensity within the 3-5 μm atmospheric window, at a detection distance of 5 000 m, and across azimuth angles from 0° (rear direction) to 90° (side direction). Four distinct coating schemes were designed: model 0 (baseline, no coating), model 1 (TRC applied only on the divergent section of the flow path, emissivity ε = 0.12), model 2 (TRC applied only on the convergent section, ε = 0.12), model 3 (TRC applied on both convergent and divergent sections, ε = 0.12). By comparing spectral radiation curves and spatial distribution of infrared intensity, the suppression effectiveness of each scheme was quantitatively evaluated. Analysis confirmed that solid wall radiation was the dominant contributor to the total infrared intensity in the 3-5 μm band at various azimuth angles. The low emissivity coating significantly reduced wall radiation, especially on surfaces directly visible to the detector. However, within the sub-band 4.15-4.5 μm, where CO2 emission and absorption were strong, differences among the schemes were minimal due to the prevailing gas radiation effects. Compared with model 0, the reduction in radiation intensity for model 1 and model 3 first increased and then decreased with the increasing azimuth angle, reaching its maximum at an azimuth angle of 30°. At an angle of 30°, the wide-side radiation intensity decreased by 19.1% and 19.4% for model 1 and model 3 relative to model 0, respectively, while the narrow-side radiation intensity decreased by 6.9% for both models. When the azimuth angle increased to 90°, the radiation intensities of all four schemes converged to similar values. Model 2 showed almost identical infrared intensity to the baseline model 0 because the convergent section had nearly zero projection area to a rear detector, offering negligible stealth benefit. Thus, for infrared stealth optimization in the rear hemisphere, applying a low emissivity coating solely on the divergent section of the nozzle flow path is sufficient. This scheme achieves most of the achievable radiation reduction without the additional material and weight costs of full internal coating. If both infrared stealth and enhanced thermal insulation are required, for example, to prolong nozzle life or allow higher operating temperatures, a combined strategy is recommended: applying a low emissivity TRC on the divergent section for stealth, and a standard (not necessarily low emissivity) TRC on the convergent section solely for thermal protection. This hybrid approach delivers equivalent infrared suppression to a fully coated nozzle while minimizing cost and complexity.
关键词
发动机 /
二元喷管 /
红外隐身 /
热阻涂层 /
低发射率 /
红外辐射
Key words
engine /
two-dimensional nozzle /
infrared stealth /
TRC /
low emissivity /
infrared radiation
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基金
国家自然科学基金（U2541255,U21B2052）
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