Aerospace Science and Technology最新文献_第3页

Corrigendum to “Three-dimensional fault-tolerant cooperative guidance law with constraints on relative impact velocity and attack angle” [AESCTE, 168 (2026) 111003] “具有相对冲击速度和攻角约束的三维容错协同制导律”的勘误表[AESCTE， 168 (2026) 111003]

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-09 DOI: 10.1016/j.ast.2026.111848

Zhanpeng Gao, Jun Liu, Jian Huang, Wenwen Wang, Wenjun Yi, Shusen Yuan

引用次数: 0

Aerodynamic performance of a cross-flow fan for VTOL and its multi-objective optimization 垂直起降横流风机气动性能及其多目标优化

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-09 DOI: 10.1016/j.ast.2026.111872

Yasuyuki Nishi , Masafumi Fukuyama , Naofumi Saeki , Kotaro Ohashi , Takao Oku

The objective of this study is to propose a cross-flow fan for VTOL applications, evaluate its aerodynamic performance, and enhance its performance through a multi-objective optimization design method. Following an investigation into a three-dimensional CFD analysis approach for assessing the fan’s aerodynamic performance, a multi-objective optimization framework that simultaneously optimizes the rotor and casing by integrating CFD analysis and a deep neural network was developed and implemented. Based on CFD-derived performance metrics, the optimized fan demonstrated a thrust-shaft power ratio approximately 12.4 % lower than that of the original fan, while achieving a thrust increase of approximately 78.1 %. This substantial improvement in thrust was attributed to elevated flow velocity and flow rate at the fan outlet. Additionally, the thrust coefficient of the cross-flow fan was shown to be more than one order of magnitude greater than that of a conventional propeller fan. Performance validation using a scaled-down model further confirmed the effectiveness of the optimization method: although the thrust-shaft power ratio of the optimized fan was approximately 3.0 % lower than the original fan, its thrust increased by approximately 64.2 %. These findings underscore the potential of the proposed optimization approach not only for high-performance fan design but also for advancing the development of next-generation VTOL aircraft.

本研究的目的是提出一种用于垂直起降的横流风扇，评估其气动性能，并通过多目标优化设计方法提高其性能。研究了用于风机气动性能评估的三维CFD分析方法，开发并实现了将CFD分析与深度神经网络相结合，同时优化转子和机匣的多目标优化框架。基于cfd导出的性能指标，优化后的风扇的推轴功率比比原风扇低约12.4%，而推力增加约78.1%。推力的显著提高归功于风扇出口的流速和流量的提高。此外，横流风扇的推力系数比传统的螺旋桨风扇高出一个数量级以上。缩小模型的性能验证进一步证实了优化方法的有效性：优化后风机的推轴功率比比原风机低约3.0%，但推力提高约64.2%。这些发现强调了所提出的优化方法的潜力，不仅可以用于高性能风扇设计，还可以用于推进下一代垂直起降飞机的开发。

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引用次数: 0

Experimental investigation on improving the electro-thermal efficiency of a novel GLARE leading-edge deicing structure 提高新型眩光前缘除冰结构电热效率的实验研究

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-09 DOI: 10.1016/j.ast.2026.111881

Chao Tang, Yang Yan, Rongtao Wang, Zhixiong Cen, Zonghong Xie

Ice accretion poses a significant challenge to the aerodynamic performance of aircraft wings and wind turbine blades, while traditional deicing methods are hampered by high weight and energy consumption. Carbon nanotube films offer a promising alternative, yet research is lacking on their integration into high-performance, damage-tolerant hybrid laminates like GLARE (GLAss fiber REinforced aluminum) and their direct performance comparison against traditional heaters. This study, therefore, develops a novel GLARE structure with an embedded CNT film, systematically comparing its performance to an identical structure using a conventional resistance wire. The two structures were comparatively evaluated in a recirculating icing wind tunnel, using thermography and thermocouple data to assess transient thermal dynamics under ambient and cold (dry) conditions, and phenomenological deicing effectiveness under representative icing (wet) conditions. The results demonstrated the FCL(Fiber Carbon-nano Laminated) heater's superior transient performance, achieving 18.91-26.67% faster heating rates under ambient conditions and 5.13-9.23% faster rates under cold (dry) conditions, alongside significantly better thermal uniformity (ΔTmaxsof 4.6°C vs. 7.8°C). In deicing tests, the FCL heater achieved 20.00-25.86% faster deicing rates, translating to a quantified energy saving of 16.67-20.55%. Critically, the FCL heater achieved complete ice removal in 35 seconds at 15 kW/m², a performance level the RWL(Resistance Wire Laminated) heater only reached at 18 kW/m², demonstrating the FCL system can provide the same performance-on-demand with 16.67% less power input. These findings validate the significant potential of FCL heaters for efficient, lightweight deicing in next-generation aerospace and renewable energy applications.

冰积对飞机机翼和风力涡轮机叶片的气动性能提出了重大挑战，而传统的除冰方法由于重量大、能耗大而受到阻碍。碳纳米管薄膜提供了一种很有前途的替代方案，但缺乏将其集成到高性能、耐损伤的混合层压板（如眩光（玻璃纤维增强铝））中以及与传统加热器直接性能比较的研究。因此，本研究开发了一种具有嵌入式碳纳米管薄膜的新型眩光结构，并系统地将其性能与使用传统电阻丝的相同结构进行了比较。在循环结冰风洞中对两种结构进行了对比评估，利用热成像和热电偶数据评估了环境和冷（干）条件下的瞬态热动力学，以及代表性结冰（湿）条件下的现象除冰效果。结果表明，FCL（纤维碳纳米层压）加热器具有优越的瞬态性能，在环境条件下加热速度提高18.91-26.67%，在冷（干）条件下加热速度提高5.13-9.23%，同时热均匀性显著提高（ΔTmaxsof 4.6°C vs. 7.8°C）。在除冰测试中，整箱加热器的除冰率提高了20.00-25.86%，量化节能为16.67-20.55%。关键的是，FCL加热器在35秒内以15 kW/m²的速度完全除冰，而RWL（电阻丝层压）加热器的性能水平仅达到18 kW/m²，这表明FCL系统可以在减少16.67%的功率输入的情况下提供相同的性能。这些发现验证了FCL加热器在下一代航空航天和可再生能源应用中高效、轻质除冰的巨大潜力。

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引用次数: 0

Fire suppression of recirculation zone flames in aircraft nacelles: effects of blockage ratio and crossflow on extinction thresholds and mixing time 飞机机舱内再循环区火焰的灭火：堵塞比和横流对熄灭阈值和混合时间的影响

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-09 DOI: 10.1016/j.ast.2026.111883

Qiyong Zhou, Song Lu, Hui Shi, Heping Zhang, Rui Chen

The recirculation zone flame is typical of the flame structure in aircraft nacelle. Based on a transient extinguishing agent injection experiment apparatus, the combustion and extinguishing of recirculation zone flame under the influence of blockage ratio and wind velocity were studied, and the fire extinguishing concentration in free flow and recirculation zone were measured. A modeling study was conducted on the dynamic evolution of the flame in the recirculation zone. The critical extinguishing concentration, fire extinguishing time, and characteristic mixing time (τ) were determined and correlated with flow parameters. Results show that obstacles increase local concentrations but also stabilize flames, raising the extinction threshold. Through analysis of the mean flame length, a dynamic evolution prediction model suitable for the mean flame length in the recirculation zone has been established. A revised correlation for τ was obtained,

τ = 36.6 (h_{s} / U_{a}^{*})

, which exceeds values reported under non-combustion conditions and highlights the stronger coupling between mixing and reactive processes. Application to aircraft nacelle scenarios indicates that, due to short discharge durations and obstruction effects, the required free flow concentration of HFC-125 exceeds nominal design specifications to ensure effective suppression in recirculation zones. This methodology provides a quantitative basis for performance evaluation of HFC-125 systems in safety-critical applications, supporting system safety assessments during early design and certification stages.

再循环区火焰是飞机机舱内典型的火焰结构。基于瞬态灭火剂注入实验装置，研究了阻塞比和风速对再循环区火焰燃烧和灭火的影响，并测量了自由流动区和再循环区的灭火浓度。对循环区内火焰的动态演化进行了模拟研究。确定了临界灭火浓度、灭火时间和特征混合时间（τ），并将其与流量参数相关联。结果表明，障碍物增加了局部浓度，但也稳定了火焰，提高了熄灭阈值。通过对平均火焰长度的分析，建立了适用于再循环区平均火焰长度的动态演化预测模型。修正后的相关系数τ=36.6(hs/Ua*)，超过了非燃烧条件下报道的值，突出了混合和反应过程之间更强的耦合。在飞机机舱场景的应用表明，由于排放持续时间短和阻塞效应，HFC-125所需的自由流动浓度超过了公称设计规范，以确保在再循环区域有效抑制。该方法为安全关键应用中HFC-125系统的性能评估提供了定量基础，支持早期设计和认证阶段的系统安全评估。

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引用次数: 0

Thermal model test and multi-scale simulation method for the lattice-structured air rudder of hypersonic flight vehicle 高超声速飞行器格构空气舵热模型试验及多尺度仿真方法

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-09 DOI: 10.1016/j.ast.2026.111885

Long Zhang, Wenlin Liao, Bowen Liu, Song Feng, Juntao Fan

This paper conducts experimental investigation and multi-scale simulation for the thermal-vibration characteristics of lattice-structured air rudders, aiming to provide a comprehensive understanding of how these complex structures behave under combined thermal and vibration loads. Firstly, a quartz infrared radiation heater device with independent control tunnels is designed and fabricated to produce thermal gradient loads on the air rudder in accordance with flight service condition. On this basis, thermal model test is performed on the rudder. In order to simulate the thermal-vibration behaviour, an orthotropic temperature-dependent material model is established, where in-situ samples of different directions have been printed simultaneously with the rudder and tested under various temperature conditions to fit the material model parameters. Afterwards, a multi-scale simulation method, which is capable of linking the mesoscopic lattice structures with the macroscopic material properties, is developed to simulate the thermal model test. The maximum absolute relative error between the simulated and tested natural frequencies is within 5.0%, and the simulated and tested mode shapes are in good agreement with each other, which proves that the developed method possesses good capability for computing natural frequencies and mode shapes of the lattice-structured air rudder under complicated thermal conditions. This combined approach enables a more thorough investigation of the thermal-vibration characteristics, leading to improved design and performance of lattice-structured air rudders.

本文对栅格结构空气舵的热振动特性进行了实验研究和多尺度模拟，旨在全面了解这些复杂结构在热振动复合载荷作用下的性能。首先，根据飞行服役条件，设计制作了具有独立控制通道的石英红外辐射加热装置，对气动舵产生热梯度载荷。在此基础上，对舵机进行了热模型试验。为了模拟方向舵的热振动行为，建立了正交各向异性温度相关的材料模型，并在不同的温度条件下对不同方向的原位样品进行了打印，以拟合材料模型参数。随后，提出了一种能够将介观晶格结构与宏观材料性能联系起来的多尺度模拟方法来模拟热模型试验。仿真与试验固有频率的最大绝对相对误差在5.0%以内，模态振型与试验模态振型吻合较好，证明该方法具有较好的计算复杂热工况下格构空气舵固有频率和模态振型的能力。这种结合的方法可以更彻底地研究热振动特性，从而改进栅格结构空气舵的设计和性能。

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引用次数: 0

Analysis of the effects of expansion ratio on the structure and infrared radiation characteristics of engine under-expanded plume under different altitudes 不同高度下膨胀比对发动机欠膨胀羽流结构及红外辐射特性的影响分析

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-09 DOI: 10.1016/j.ast.2026.111880

ZeYang Xiao, Bijiao He, Lihui Liu, Yatao Chen, Kuo Li, Guobiao Cai

The exhaust plume ejected from a rocket engine exhibits high temperature and pressure, leading to intense infrared radiation signals. Variations in expansion ratio and ambient pressure influence the plume’s flow field structure, which in turn affects these signals. This study investigates the effects of the expansion ratio, which ranges from under-expanded (2.78) to the optimal state (5.65), and the flight altitude, varying from 0 km to 30 km, on the flow field and infrared radiation (IR) characteristics of the exhaust plume. The exhaust plume flow field is numerically solved using the Computational Fluid Dynamics (CFD) method, while its radiative transfer is modeled using the Backward Monte Carlo method. Additionally, the gas radiative properties in the radiative transfer process are computed using the line-by-line method. The simulation results show that plume diffusion increases significantly with altitude, but it is less sensitive to changes in expansion ratios at a given altitude. At the lower altitudes, such as 0 km and 5 km, the difference in total radiation intensity due to varying expansion ratios is minimal. However, as altitude increases, the disparity in total radiation intensity among different expansion ratios grows noticeably. At an altitude of 30 km, the radiation increment caused by the expansion ratio exceeds threefold compared to that at 0 km. This is attributed to the smaller expansion ratio intensifying the afterburning reactions and promoting the formation of strongly radiative species, such as H2O and CO2.

从火箭发动机喷出的排气羽流表现出高温高压，导致强烈的红外辐射信号。膨胀比和环境压力的变化会影响羽流的流场结构，进而影响这些信号。研究了未充分膨胀比（2.78）至最佳膨胀比（5.65）、飞行高度（0 ~ 30 km）对排气羽流场和红外辐射特性的影响。采用计算流体力学（CFD）方法对排气羽流场进行了数值求解，并采用后向蒙特卡罗方法对其辐射传递进行了建模。此外，采用逐行方法计算了辐射传递过程中气体的辐射特性。模拟结果表明，羽流扩散随高度的增加而显著增加，但在一定高度下，羽流扩散对膨胀比的变化不太敏感。在较低的海拔高度，如0公里和5公里，由于不同的膨胀比，总辐射强度的差异是最小的。但随着海拔高度的增加，不同膨胀比之间的总辐射强度差异明显增大。在30 km高度，膨胀比引起的辐射增量是0 km高度的3倍以上。这是由于较小的膨胀比加剧了加力反应，促进了强辐射物质的形成，如H2O和CO2。

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引用次数: 0

Compressor cascade cross flow control via endwall passage vortex generator 利用端壁通道涡发生器控制压气机叶栅横流

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-09 DOI: 10.1016/j.ast.2026.111888

Huiling Zhu, Ling Zhou, Xin Li, Chenhao Zhao, Tongtong Meng, Lucheng Ji

Endwall cross flow is a critical factor in inducing corner separation in compressors, substantially influencing their aerodynamic performance. To address this issue at its source, this study investigates the application of vortex generators (VGs) to the endwall of the compressor cascade passage, positioned between the leading and trailing edges. Two configurations—single VG and double VG—are designed and analyzed. Using a combination of experimental and numerical methods, the study evaluates the effectiveness of the endwall passage VG technique in mitigating endwall cross flow and controlling corner separation. In addition, it uncovers the underlying flow control mechanisms and provides design guidelines. Experimental results show that both the single VG and double VG schemes effectively suppress endwall cross flow near the suction side of the compressor cascade, thereby controlling corner separation and markedly enhancing aerodynamic performance. Under an inlet Mach number of 0.6 and an incidence angle of −7°, the single VG scheme reduces the total pressure loss coefficient of the compressor cascade by 9.0%. The success of the endwall passage VG technique lies in its dual action: the direct blocking effect of the VG on the endwall cross flow, and the suppression of endwall cross flow by the concentrated vortex it generates. Together, these mechanisms constitute the key to effectively controlling corner separation in compressor cascades. Moreover, this concentrated vortex further weakens the passage vortex, thereby improving the endwall flow field.

端壁横流是压气机产生转角分离的关键因素，对压气机的气动性能有重要影响。为了从源头上解决这一问题，本研究研究了在压气机叶栅通道端壁（位于前后缘之间）安装涡发生器（vg）的方法。设计并分析了单VG和双VG两种配置。采用实验与数值相结合的方法，对端壁通道VG技术在缓解端壁横流和控制转角分离方面的效果进行了评价。此外，它还揭示了底层流控制机制并提供了设计指南。实验结果表明，单涡扇和双涡扇方案均能有效抑制压气机叶栅吸力侧附近的端壁横流，从而控制转角分离，显著提高气动性能。在进口马赫数为0.6、入射角为- 7°时，单VG方案可使压气机叶栅总压损失系数降低9.0%。端壁通道涡发生器技术的成功在于其双重作用：涡发生器对端壁横流的直接阻断作用，以及涡发生器产生的集中涡对端壁横流的抑制作用。这些机制共同构成了有效控制压气机叶栅转角分离的关键。这种集中涡进一步削弱了通道涡，从而改善了端壁流场。

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引用次数: 0

Accelerating adjoint-based aerodynamic shape optimization through integrating reduced-order modeling and active learning 通过集成降阶建模和主动学习加速基于自伴随的气动形状优化

IF 5.6 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-08 DOI: 10.1016/j.ast.2026.111876

Wengang Chen, Weixiang Gao, Jiaqing Kou, Wenkai Yang, Hongyu Zheng, Baoling Lu

Owing to its computational efficiency in gradient evaluation, the adjoint method has emerged as a cornerstone in the field of aerodynamic shape optimization. However, the efficiency of the adjoint-based aerodynamic shape optimization relies on the cost of solving adjoint equations, which still remains time-consuming. In this paper, the adjoint method is accelerated by constructing efficient dynamic Reduced-Order Models (ROMs) enhanced by the active learning strategy. During each adjoint optimization step, the query function, i.e., also the objective function, is introduced to obtain relevant additional samples for updating the dynamic ROM. The updated ROM then predicts an improved initial guess for the adjoint solver, enabling faster convergence and accelerating the overall optimization process. The proposed Active Learning ADjoint (ALAD) method does not require additional simulation for model update, and is easy to combine with other acceleration methods. The efficiency of the proposed method is verified by airfoil shape optimization in both transonic inviscid and subsonic laminar flow regimes. Results indicate that the proposed ROM significantly reduces the initial residual of pseudo-time iterations, thus significantly decreasing the iteration numbers required by adjoint optimization. Finally, we combine ALAD with the dynamic mode decomposition (DMD) acceleration method, showing that this approach can be combined with other methods to further enhance the optimization efficiency. The proposed method holds great promise for a wide range of applications in aerospace engineering.

伴随方法由于其在梯度计算方面的效率高，已成为气动形状优化领域的基石。然而，基于伴随方程的气动形状优化的效率依赖于求解伴随方程的成本，而求解伴随方程仍然很耗时。本文通过构造有效的动态降阶模型（ROMs）来加速伴随方法，并采用主动学习策略进行增强。在每个伴随优化步骤中，引入查询函数（即目标函数）来获取相关的附加样本，用于更新动态ROM。更新后的ROM预测伴随求解器的改进初始猜想，从而加快收敛速度，加快整体优化过程。提出的主动学习伴随方法（ALAD）不需要额外的仿真来进行模型更新，并且易于与其他加速方法相结合。通过跨声速无粘流和亚声速层流两种流型的翼型优化，验证了该方法的有效性。结果表明，所提出的ROM显著降低了伪时间迭代的初始残差，从而显著减少了伴随优化所需的迭代次数。最后，我们将ALAD与动态模态分解（DMD）加速方法相结合，表明该方法可以与其他方法相结合，进一步提高优化效率。该方法在航空航天工程中具有广泛的应用前景。

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引用次数: 0

Effects of icing and flight factors on surface temperature and heating time on composite electrothermal protection system 结冰和飞行因素对复合电热保护系统表面温度和加热时间的影响

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-08 DOI: 10.1016/j.ast.2026.111877

Yijing An , Huajie Xiong , Zengpei Liu , Yuxuan Gao , Zhihong Zhou

Timing control of electro-thermal anti-icing systems for aircraft and aero-engines often rely on empirical methods, leading to excessive energy consumption or insufficient heating that compromises flight safety. This study identifies stagnation point temperature as the key parameter for analysis and investigates the effects of environmental temperature, velocity, liquid water content (LWC), and medium volume diameter (MVD) on anti-icing performance. Quantitative relationships between these parameters and the timing control of anti-icing are derived. Additionally, the study explores the coupled effects of these parameters, introducing the icing influence factor

α_{E}

, as a novel metric. A multiphysics-coupled simulation method was developed through secondary development in CFD, integrating airflow, droplet impingement, and transient heat conduction models. The accuracy of this numerical approach was validated by comparison with icing wind tunnel experiments. A mathematical model linking this factor to the timing control process is established, offering valuable insights that can inform design and optimization of electro-thermal anti-icing systems.

飞机和航空发动机电热防冰系统的定时控制往往依赖于经验方法，导致能量消耗过多或加热不足，危及飞行安全。本研究将驻点温度作为分析的关键参数，探讨了环境温度、速度、液态水含量（LWC）和介质体积直径（MVD）对防冰性能的影响。推导了这些参数与防冰定时控制之间的定量关系。此外，研究探讨了这些参数的耦合效应，引入结冰影响因子αE作为一个新的度量。通过对CFD的二次开发，结合气流、液滴撞击和瞬态热传导模型，提出了一种多物理场耦合模拟方法。通过与结冰风洞实验的对比，验证了该数值方法的准确性。建立了将该因素与定时控制过程联系起来的数学模型，为电热防冰系统的设计和优化提供了有价值的见解。

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引用次数: 0

Investigation of impingement-film composite anti-icing on a rotating spinner 旋转纺丝机冲击膜复合防冰性能研究

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2026-02-08 DOI: 10.1016/j.ast.2026.111878

Yaping Hu , Weiliang Zheng , Chen Wu , Yuxin Fan , Yaxin Du , Haoyu Yuan , Tianyi Zhang , Shuliang Jing

The impingement-film composite anti-icing provides higher heating efficiency and significant application potential for aircraft compared to conventional hot-air anti-icing. While prior studies have focused on stationary components, this study investigates the anti-icing performance of a full-scale rotating spinner via a combined experimental and numerical approach at high rotational speeds. Surface temperature was measured using a calibrated infrared thermal imager, while water film flow and ice evolution were captured with a high-speed camera. The numerical model couples external and internal airflow, heat transfer, surface water film dynamics with phase change, and solid conduction. Results indicate that the surface temperature initially rises slightly and then decreases, peaking near the fourth row of film holes. Predicted surface temperatures agree well with the experimental data within the uncertainty bands, yielding a mean absolute error of 1.5°C. The composite anti-icing mechanism is attributed to the combined effects of internal hot-air impingement heating and an external protective film formed by the ejected hot air, which simultaneously heats the surface and suppresses droplet impingement. Under the studied conditions, the rotating spinner remains fully protected at freestream temperatures slightly above −10°C. At −20°C, a continuous annular runback ice layer forms downstream of the film-hole region, with a maximum thickness of approximately 15 mm. In contrast, a stationary spinner under identical conditions exhibits an average surface temperature about 2.3°C lower, a larger ice accretion area, and a maximum ice thickness of 20 mm.

与传统的热空气防冰相比，冲击膜复合防冰具有更高的热效率和巨大的应用潜力。虽然之前的研究主要集中在固定部件上，但本研究通过实验和数值相结合的方法研究了全尺寸旋转旋流器在高转速下的防冰性能。表面温度通过校准的红外热成像仪测量，而水膜流动和冰的演变用高速摄像机捕捉。数值模型耦合了内外气流、传热、表面水膜相变动力学和固体传导。结果表明：表面温度呈先上升后下降的趋势，在第4排膜孔附近达到峰值；在不确定度范围内，预测的地表温度与实验数据吻合良好，平均绝对误差为1.5°C。复合防冰机理是由于内部热空气撞击加热和喷出热空气形成的外部保护膜的共同作用，同时加热表面并抑制液滴撞击。在研究条件下，旋转纺丝器在略高于- 10°C的自由流温度下仍能得到充分保护。在- 20°C时，膜孔区域下游形成连续的环状回流冰层，最大厚度约为15 mm。相比之下，在相同条件下，静止旋转器的平均表面温度低约2.3℃，冰的吸积面积更大，冰的最大厚度为20 mm。

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引用次数: 0