25 November 2025, Volume 46 Issue 12

    

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  Research Progress and Prospects of Turbine-based Rotating Detonation

  LI Yinghong, WU Yun, SONG Feilong, CHEN Xin, GUO Shanguang, WANG Jiaojiao, YANG Zhao

  Journal of Engineering Thermophysics. 2025, 46(12): 3851-3877.

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  Detonation engines, compared with traditional aviation engines that adopt the Brayton cycle, have higher unit thrust and lower fuel consumption rate, and thus have broad application prospects. Rotating detonation engines have attracted significant attention in the global aerospace field in recent years due to their advantages such as high operating frequency, single ignition and low start Mach number. The funding intensity and engineering application progress of various countries in this research field are all in a state of rapid development. In view of this, this paper conducts a comprehensive review of the research progress of rotating detonation in the international community. It analyzes the current research status of multiple key technical problems in turbine-based rotating detonation engines, and elaborately describes the breakthrough progress made by our research team in these fields. Finally, it looks forward to the future development of turbine-based rotating detonation engines and puts forward development suggestions for each research direction. The subsequent research work on turbine-based rotating detonation engines will focus on three application directions: internal/external afterburning detonation and turbine-ramjet rotating detonation combined engines. Key technical challenges such as reliable initiation of combustor over a wide range, modulation and propagation stabilization of detonation wave modes, optimization of combustor and injection structures, suppression of pressure feedback, efficient thermal protection of combustor, and stable matching of engine will be overcome to accelerate the engineering application of rotating detonation engines.
  
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  Transition Mechanism for Separated Shear Layers on Compressor Blades at Low Reynolds Numbers

  ZHU Junqiang, WANG Mingyang, LU Xingen, ZHAO Shengfeng, HAN Ge, YANG Chengwu

  Journal of Engineering Thermophysics. 2025, 46(12): 3878-3890.

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  When Reynolds number decreases to near the critical value (approximately 2×10⁵), the separation-transition process on the surface of compressor blade/endwall induces strong turbulent fluctuations, leading to a sharp degradation in efficiency and stability margin. However, the transition mechanisms and the spatio-temporal evolution of multi-scale vortex structures under different Reynolds numbers remain unclear, making it difficult to accurately identify the core factors responsible for the performance degradation of compressors. In this study, a high-subsonic compressor cascade is selected to explore the instability of separated shear layers and vortex dynamics under various Reynolds numbers, thereby clarifying the mechanism of performance variation. The results indicate that disturbances in the separated shear layer initially exhibit exponential growth, followed by nonlinear effects that trigger the onset of transition. As the Reynolds number decreases from 4.5×10⁵ to 1.5×10⁵, the disturbance growth rate in the shear layer declines, nonlinear effects are delayed, and the transition onset and end locations shift significantly downstream, with the separation bubble length increasing by 122%. Concurrently, the vortex shedding frequency in the shear layer decreases, while the roll-up and breakdown intensity of three-dimensional hairpin vortices at the late transition stage intensify, leading to a rapid expansion of high-level Reynolds shear stress regions and a 241% increase in loss. A rapid increase in the pressure gradient at the separation point under low Reynolds numbers is identified. Then, a correlation model between the pressure gradient at the separation point and the separation scale/boundary layer growth rate under different Reynolds numbers is established, which accurately pinpoints the key sensitive parameters responsible for performance degradation. This provides direct theoretical support for compressor blade design and flow control strategies under low Reynolds number conditions。
  
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  Investigation of Two-dimensional Through-flow Method and Its Application in Axial Compressors

  WANG Xiaochen, REN Xiaodong, LI Xuesong, GU Chunwei

  Journal of Engineering Thermophysics. 2025, 46(12): 3891-3905.

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  Two dimensional through-flow method and its application in multi-compressor seriesparallel system are investigated based on an in-house streamline curvature tool. Aimed at the limitation of classical transonic corrections, a simplified model of expansion before shock is proposed considering the shock effect, and a deviation is developed combining analysis of continuity and force equilibrium. Good agreement is shown between model predictions and test data of a transonic cascade and a 1.5-stage transonic compressor, and the prediction accuracy exceeds that of classical models. Correction models of loss, deviation and blockage are proposed for low Reynolds number effects based on theoretical analysis of cascade tests of NACA65 and C4 airfoils. These models evaluate effectively the influences of low Reynolds number on the matching performances of a 3-stage axial compressor, where the predictions agree well with the CFD results. Through-flow matching analysis method is established for multi-compressor series-parallel systems. It provides accurate predictions of the compressor component, and supports the matching operation strategy for optimum system efficiency without stall risk under a critical loading condition.
  
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  Study of Formation, Propagation and Dissipation of Complex Acoustic Modes Under Swirling Flow Conditions

  QIN Lei, ZHANG Guangyu, WANG Xiaoyu, SUN Xiaofeng

  Journal of Engineering Thermophysics. 2025, 46(12): 3906-3918.

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  With the advancement of high-bypass-ratio turbofan engines, it is crucial to conduct a comprehensive investigation into the effects of swirling flows within their nacelles on acoustic propagation characteristics and the impedance design of perforated liners. Based on the linearized Euler equations, we established an eigenvalue equation to systematically analyze the acoustic propagation characteristics and acoustic transmission loss in an impedance duct under swirling flow conditions. The results show that an increase of frequency causes the acoustic wave to move away from the cut-off frequency, resulting in a reduction in acoustic transmission loss for both upstream and downstream waves. Additionally, the circumferential velocity component of the swirling flow suppresses the acoustic transmission loss of counter-propagating acoustic waves while amplifying the acoustic transmission loss of co-propagating acoustic waves. The presence of swirling flows also leads to a shift in the optimal acoustic resistance of the perforated liner; specifically, the optimal acoustic resistance decreases for modes propagating with the swirl and increases for modes propagating against it. This study elucidates the multidimensional mechanisms of swirling flows on duct acoustics, thereby providing a theoretical foundation for the design of perforated liners in advanced aero-engine nacelles.
  
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  Parametric Study on the Head Profile of Five-hole Probe Under Different Flow Conditions

  KAN Xiaoxu, SUO Licheng, ZHONG Jingjun

  Journal of Engineering Thermophysics. 2025, 46(12): 3919-3929.

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  The five-hole aerodynamic probe has been widely used in the measurement of shipboard gas turbines due to its convenient and reliable characteristics. In this paper, the probe head profile is parameterized, and the influence of different probe head shapes on the flow field is analyzed by numerical calculation in order to design a probe suitable for subsonic, transonic, and supersonic conditions. The research results show that by adjusting the parameters x_h, D and q of the parameterized equation, a variety of probe head shapes can be generated according to requirements. It can be seen from the shock function of the probe head that the closer the probe head is to a semicircle, the less the influence on the flow field in subsonic and transonic conditions, while the opposite is true in supersonic conditions. The distribution of aerodynamic parameters near the wall shows that Probe02 has the smallest overall abrupt changes in total pressure and Mach number, and the least impact on the near-wall flow field. The Mach number of Probe02 calculated from the five pressure measurement holes has a measurement error of about 1.03% compared with the real incoming flow under subsonic conditions, about 1.47% during transonic processes, and about 5.15% under supersonic 
  conditions. Considering the compatibility under different incoming flow conditions, Probe02 is a better measurement scheme.
  
  
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  Uncertainty Analysis of Impact of Geometric Deviations on Low-pressure Turbine Stall Margins

  WANG Xiaojing, CHEN Hao, JIANG Qifeng, ZOU Zhengping

  Journal of Engineering Thermophysics. 2025, 46(12): 3930-3937.

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  Random geometric deviations introduce significant variability in the aerodynamic performance of low-pressure turbines, which is further intensified under high loading conditions. In this study, the influence of geometric deviations on boundary layer separation on the suction side of turbine blades is compared across various loading levels and incidences. The consequent uncertainty impact on operating margins is quantified. To improve sample efficiency and reduce data requirements, the stall condition is simplified as a binary classification, and an active transfer learning strategy is employed. The results reveal that geometric deviations lead to substantial scatter in the operating margins of turbines, narrowing the available high-efficiency operating range and increasing the risk of stall. This uncertainty impact should therefore be carefully considered in the practical aerodynamic design of low-pressure turbines.
  
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  Influence of Circumferential Distortion on Compressor Vortex Structures and Stall-triggering Mechanism

  YAN Jiandong, PAN Tianyu, SONG Yong, HE Guozhong, LI Qiushi

  Journal of Engineering Thermophysics. 2025, 46(12): 3938-3951.

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  This paper uses multi-wavelet spatial mode decomposition, dynamic mode decomposition method and vortex identification technology to conduct an in-depth study on the vortex structure evolution and instability triggering mechanism of the transonic rotor under circumferential distortion. The stall-related vortex structures are identified as: the leakage vortex initiated from the tip clearance and the separation vortex initiated from the leading edge of the suction surface. The instability triggering event is identified as: the low-order spatial mode in the compression system rotating at 0.24 times the rotor passing frequency. This spatial mode is dominated by the 1^st wavenumber. The leading edge separation vortex is first affected by this spatial mode. The leading edge separation vortex structure distribution in different passages is concordant with the wavelet shape of spatial mode. The leading edge separation vortex intensity in the passages around the spatial mode phase location become intensified each rotation period. Eventually, with the combination vortexes of the leading edge separation vortex and the tip leakage vortex, rotating stall cell is formed, leading the entire compressor into stall.
  
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  Data-driven Prediction Method for Film Cooling Based on Deep Learning 

  LIU Yi, CUI Hao, LI Xueying, REN Jing

  Journal of Engineering Thermophysics. 2025, 46(12): 3952-3960.

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  The fully three-dimensional conjugate heat transfer analysis of air-cooled turbine vanes faces dual challenges in both accuracy and efficiency. This study constructs a two-dimensional film cooling dataset based on experimental and numerical methods and develops a film cooling effectiveness prediction model using a deep convolutional conditional generative adversarial network (DCCGAN), enabling rapid prediction of single-hole film cooling effectiveness. This study applies the prediction model to the film cooling effectiveness prediction on the surface of turbine vanes and develops a data-driven three-dimensional heat transfer analysis method. The results show that the proposed prediction method reduces the average relative error of three-dimensional vane computations to 3.1% and shortens the computation time by 57.2%, achieving simultaneous improvements in both accuracy and efficiency.
  
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  PIV Experiment Research of Leakage Flow in Open Clearance Compressor Cascade

  ZHANG Gangduo, ZHU Mingmin, HE Zhaoyu, YUAN Yixi, HE Xiao, JIANG Hongmei, TENG Jinfang

  Journal of Engineering Thermophysics. 2025, 46(12): 3961-3969.

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  To investigate the flow mechanism of leakage in an open clearance environment of a small core engine compressor blade cascade and to provide reliable calibration data for high-precision numerical simulation methods under such conditions, Particle image velocimetry (PIV) was employed to conduct experimental research on a compressor blade cascade with tip clearance. The experiments were performed in a low-turbulence high-speed wind tunnel using a single camera to capture the flow field. Technical validation was carried out at various inlet Mach numbers, and through experimental measurements and data processing, the time-averaged two-dimensional velocity distribution within the gap plane was obtained. The results demonstrate that, under the current experimental conditions, PIV technology is capable of measuring the detailed flow field inside the open tip clearance, successfully capturing complex flow phenomena such as leakage flow, wake, and suction-side trailing edge separation. This not only enhances the understanding of internal flow mechanisms in small core engine clearances but also provides a robust PIV experimental research framework for applications in turbomachinery environments.
  
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  Impeller Type Influence on Performance of Transcritical CO₂ Centrifugal Compressors

  GAO Xinyi, GONG Wuqi, WANG Kaixin, LIU Zhe

  Journal of Engineering Thermophysics. 2025, 46(12): 3970-3978.

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  The centrifugal compressor, as the core component in a transcritical CO₂ heat pump system, plays a dominant role in the performance of the system. In this paper, numerical calculations are used to study the characteristics of the centrifugal compressor of transcritical CO₂ heat pump with unshrouded and shrouded centrifugal impellers, the tip gap leakage characteristics and the shroud labyrinth seal leakage characteristics are investigated respectively. The study shows that compared with the unshrouded centrifugal impeller, the shrouded impeller centrifugal compressor has better performance, its isentropic efficiency reaches 85.34% under the designed condition, and the pressure ratio reaches 1.97; the range of stable operating conditions of the shrouded impeller compressor has a tendency to shift to the left, which is due to the backflow of leakage flow from the shroud labyrinth seal which reduces the effective flow rate of the compressor, and results in the reduction of compressor stall and blockage flow rate. And an impeller shroud labyrinth seal leakage characteristic prediction formula for CO₂ is proposed, and the difference between the predicted value and the numerical calculation value is less than 5.0%.
  
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  Investigation on the Performance Simulation and Design for a Vaneless Counter-rotating Air Turbo Rocket

  ZHAO Qingjun, ZHAO Wei, XIANG Xiaorong, HU Bin, LIU Binbin, LUO Weiwei, XU Jianzhong

  Journal of Engineering Thermophysics. 2025, 46(12): 3979-3984.

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  In order to optimize the thermodynamic cycle and component matching for a vaneless counter rotating Air Turbo Rocket (ATR) engine, the Gibbs minimum free energy principle is used to solve the chemical equilibrium and components of working fluid, and the engine thermodynamic cycle model considering the changes of working fluid components and physical properties is established. The design criteria of compressor pressure ratio and turbine expansion ratio at the ground design point of the engine are proposed. A method is introduced to determine the similarity conditions at the inlet of the downstream rotor based on the upstream rotor speed, inter-stage total temperature and total pressure. The performance maps of the vaneless counter rotating compressor and counter rotating turbine are established by using the combined upstream and downstream stage corrected speed lines. The process of the engine component matching under off-design working conditions is presented based on the maps. The thrust and specific impulse characteristics of typical operating points in the engine flight envelope are then obtained. It is pointed out that the engine has the advantages of small thrust degradation in the acceleration flight phase and high specific impulse in the cruise flight phase. Through the analysis of the weight proportion of engine components, it is pointed out that the thrust weight ratio of the engine can be increased by 15%∼20% with the vaneless counter rotating compressor and turbine.
  
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  Cooling and Loss Mechanism of Anti-vortex Hole in the Middle of the Gill Region of the Turbine Blade

  LI Nianqiang, LI Guoqing, BAI Xiaohui, LIU Jialin, LU Xingen

  Journal of Engineering Thermophysics. 2025, 46(12): 3985-3994.

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  Aiming at the problem that the gill region of the turbine blade is easy to be detached from the wall, a new type of the anti-vortex hole of large and small holes is proposed, mixing loss mechanism is compared and analyzed using numerical simulation based on the transonic HS1A type high-pressure turbine blade. In this study, the open area of large hole is 4 times and mass flow rate is 3 times that of small hole, the exit velocity of small hole is larger. The results show that the anti-vortex hole can inhibit the development of kidney-shaped vortex through mutual interference between the holes. The average adiabatic cooling of the anti-vortex hole improves about 24%, the cooling uniformity improves about 37.6%, and the net heat flux reduction (NHFR) improves about 54.2% compared with cylindrical hole, the anti-vortex hole has very superior comprehensive cooling characteristics compared with cylindrical hole in M=0.4. In addition, the anti-vortex hole leads to some increase in the total mixing loss. Overall, the anti-vortex hole improves film cooling characteristics in gill region of the turbine blade.
  
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  Integrated Design Optimization of Blade and Casing Treatment Based on Transformer and Reinforcement Learning

  FAN Zhonggang, WU Yueteng, BA Dun, WANG Yangyang, ZHANG Min, DU Juan

  Journal of Engineering Thermophysics. 2025, 46(12): 3995-4004.

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  A platform for integrated optimization of blade and casing treatment based on Transformer and reinforcement learning was developed for a low-speed axial compressor. The platform comprehensively considers stall margin and efficiency. The agent continuously improves its strategy during interaction with the environment, ultimately achieving a 13.1% stall margin improvement without peak efficiency penalty. For the optimal design, the aerodynamic performance analysis was conducted. The study found that the tip blockage was significantly reduced after the integrated blade and casing treatment design, delaying the spillage of the interface between the main flow and the tip leakage flow. Additionally, the entropy generation induced by secondary tip leakage flow was significantly reduced, which offset the negative impact of casing treatment on efficiency .
  
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  Comparative Study on Loss Decomposition Methods for Transonic Turbine Cascades

  WEI Wei, LI Xuesong, LI Yan, LI Yuhong

  Journal of Engineering Thermophysics. 2025, 46(12): 4005-4014.

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  To address the issue of loss decompositions in transonic turbine cascades, the energy loss coefficient and power loss methods are employed to quantitatively decompose the Reynolds-averaged Navier-Stokes (RANS) flow field loss into laminar boundary layer losses, turbulent losses, shock losses, and trailing edge wake mixing losses. The characteristics of these two methods in loss representation and decomposition are compared. The results indicate that the power loss method offers additive loss properties, effectively identifying high-loss regions caused by the interaction between the trailing edge shock and wakes. This method provides advantages in both quantitative and qualitative loss analysis. The decomposition results reveal that shock loss in the studied turbine cascade contribute to 8.6%∼19.4% of the total loss. Both the power loss method and the energy loss coefficient method have their respective strengths, making them complementary for loss analysis.
  
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  Numerical Investigation of Stall Inception and Deep Stall in a Centrifugal Compressor With Vaned Diffuser

  ZHAO Yang, ZHAO Tianhao, XI Guang

  Journal of Engineering Thermophysics. 2025, 46(12): 4015-4024.

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  To deeply elucidate the flow mechanism of the diffuser stall in a centrifugal compressor with vaned diffuser, a full-domain three-dimensional numerical simulation is performed to investigate the dynamic characteristics of diffuser stall inception and deep stall. Firstly, this paper presents the dynamic development of stall disturbances at the critical stall point. It is found that the diffuser rotating stall is triggered by hub-corner separation within the diffuser passage near the volute tongue. The stall disturbances, characterized by short-wavelength of static pressure fluctuation, occupy 2∼3 diffuser passages. Furthermore, the flow mechanism of the circumferential propagation of stall cells is thoroughly analyzed. Subsequently, the dynamic evolution of stall cells under deep stall conditions is analyzed in detail. It is demonstrated that stall cells undergo a sequential process of generation, merging, and dissipation, with the number of stall cells dynamically varying between 1 and 3.
  
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  High-precision Numerical Study on Influences of Roughness and Vibration on Boundary Layer Transition of Low Re Number Compressor Cascade

  WANG Zhiheng, XI Guang, LING Weihao, HUANG Wenlin, GAO Song

  Journal of Engineering Thermophysics. 2025, 46(12): 4025-4035.

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  This study employs a spectral element-based direct numerical simulation (DNS) solver to investigate the boundary layer transition of low-Reynolds-number compressor cascades subjected to surface roughness elements and blade vibration. The roughness elements or rough surfaces are represented using an embedded boundary method, while the vibration-induced body force is introduced via a moving coordinate system. We examine the transitional boundary layer flow over a flat plate with favorable–adverse pressure gradients and localized three-dimensional roughness, as well as over the suction surface of a cascade blade featuring a random cylindrical roughness array and its coupling with blade-normal vibration. The effects of different effective slopes, skewness, and streamwise locations of the roughness on the near-wall drag characteristics and downstream transitional flow features are quantified, and the transition mechanisms on the suction surface of compressor cascade blades are elucidated. The results show that, roughness elements trigger distinct transition mechanisms on the suction surface of the blade, depending on whether they are located in the favorable or adverse pressure gradient region. Under the coupling of vibration, the boundary layer becomes thinner, the high-loss region is reduced, and in the outer region of the turbulent wedge, the wall-normal vortex tilting term in the vorticity equation plays a dominant role in the generation of streamwise vortices.
  
  
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  Study on Unsteady Flow Characteristics in Hump Region of a Pump-turbine

  LIANG Ao, ZHANG Wenwu, YAO Zhifeng, WANG Fujun

  Journal of Engineering Thermophysics. 2025, 46(12): 4036-4042.

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  To investigate the unsteady flow characteristics in the hump region of a pump-turbine, unsteady numerical simulations were conducted using the SST k-ω turbulence model on a pumpturbine model with the guide vane opening of 19 mm. Hydraulic losses in different flow passage regions were analyzed, and pressure fluctuation characteristics and unstable flow characteristics in the runner and guide vane were studied under the hump region conditions. The results show that large vortices near the band side at the runner inlet under 0.90Q_BEP operating condition sharply increase the total hydraulic loss, becoming the main factor for the formation of hump region. Under hump region operating conditions, the pressure fluctuation frequencies within the runner primarily include the rotational frequency of fn and its harmonics, as well as rotor-stator interaction frequency of 20f_n; within the guide vane, the frequencies mainly include the rotor-stator interaction frequency of 7f_n and the rotating stall frequencies of 0.1f_n and 0.15f_n. As flow rate decreases, backflow from the guide vane outlet extends to the inlet, squeezing the runner outlet flow and affecting the internal flow state within the runner.
  
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  Study on the Aeroelastic Instability of the 100-meter-class Wind Turbine Blade With Bend-twist Design

  ZHOU Le, SHEN Xin, MA Lu, WANG Su, LI Yijia, OUYANG Hua, DU Zhaohui

  Journal of Engineering Thermophysics. 2025, 46(12): 4043-4050.

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  In this paper, the effects of the unbalanced layup design of the carbon fibers at the spar cap on the structural characteristics of the IEA-15MW wind turbine blade are studied, and the aerodynamic instability of the wind turbine after bend-twist coupling design is discussed. The results show that with the increase of the off-axis angle of the carbon fibers, the flapwise stiffness and tensile stiffness of the blade decrease significantly, and the bend-twist coupling factor increases first and then decreases. When the off-axis angle of the carbon fibers is equal to 25°, the blade has the best bend-twist coupling effect. As the flapwise stiffness of the blade is reduced by the unbalanced layup design, the work done by aerodynamic force on the blade in the flapwise direction increases significantly. As a result, the unbalanced layup blade with an off-axis angle of 25° exhibits pronounced aeroelastic instability at the rated operation point of the wind turbine.
  
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  Mechanism of Unsteady Cavitation Suppression by Spanwise Obstacles Near the Trailing Edge

  WANG Lu, WANG Pengzhong, HUANG Bin, WU Peng, WU Dazhuan

  Journal of Engineering Thermophysics. 2025, 46(12): 4051-4058.

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  Cavitation is a critical factor that constrains the stable operation of hydraulic machinery. Effective cavitation suppression methods are of significant importance for ensuring the safe operation of hydraulic machinery. This study focuses on the cavitation suppression method using spanwise obstacles near the trailing edge. Based on numerical simulations of cavitation flow around NACA66 and NACA63820 hydrofoils equipped with spanwise obstacles near the trailing edge, Lagrangian coherent structures (LCSs) were used to extract the vortex structures during the cavitation development process, revealing the mechanism by which spanwise obstacles near the trailing edge suppress unsteady cavitation development. Experimental validation further confirmed the effectiveness of this method. The results demonstrate that the presence of trailing-edge spanwise obstacles induces complete vortex structures extending from the downstream side of the obstacles to the hydrofoil trailing edge. This vortex formation modifies the flow path around the hydrofoil and suppresses flow separation near the leading edge, thereby effectively controlling the development of unsteady cavitation on the hydrofoil surface.
  
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  Review on High-efficiency Energy Conversion and Key Technologies of Wind-to-heat Systems

  SUN Xiangyu, ZHONG Xiaohui, LI Qingan, XU Jianzhong

  Journal of Engineering Thermophysics. 2025, 46(12): 4059-4074.

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  The wind-to-heat system, comprising a wind turbine subsystem and a heat pump subsystem connected via a transmission chain, represents an innovative approach to wind energy heating. It achieves energy conversion through a streamlined process of wind energy → mechanical energy → thermal energy. With advantages such as minimized energy conversion stages and high energy conversion efficiency, this technology has garnered increasing attention. However, challenges arise from the fluctuating input of wind energy at the front end and the hysteresis in load response at the terminal. To elucidate the energy conversion pathways of wind-to-heat systems and enhance their efficiency, researchers have conducted studies from multiple perspectives, including high-precision performance simulations, optimized design of critical components, efficient control strategies, and prototype experimentation and application analysis. These efforts establish a theoretical foundation and scientific framework for ensuring high-efficiency, high-reliability, and cost-effective operation of wind-to-heat systems, as well as enabling holistic system optimization. This research holds significant scientific value and engineering potential for expanding wind energy integration and advancing clean heating solutions.
  
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  Research on Wind Tunnel Test Method of Physical-Numerical Coupling Model for Floating Offshore Wind Turbines

  ZHANG Pan, ZHANG Hairui, LUO Tianxiao, LI Zhixun, WU Guangxing

  Journal of Engineering Thermophysics. 2025, 46(12): 4075-7086.

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  The dynamic response characteristics of floating offshore wind turbines (FOWTs) are of vital importance to their safety, stability, and efficiency. Model tests are an important means to verify the design performance of FOWTs. However, traditional full-physical model tests have the problem of mismatch between aerodynamic and hydrodynamic forces. In this paper, a wind tunnel experimental system of a physical-numerical coupling model for the real-time measurement of the aerodynamic forces of the wind turbine rotor and the real-time calculation of the motion response of the floater is developed. A real-time measurement method for the dynamic aerodynamic forces of the wind turbine rotor based on the pressure on the blade surface is proposed, which solves the problem that the force measurement method using a balance cannot accurately identify the dynamic aerodynamic forces. The accuracy of the experimental system is verified by comparing it with the calculation results of the normal operating conditions of OpenFAST.
  
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  Achieving Flow Control in Vertical Axis Wind Turbine Under Extreme Gust Conditions Based on Adaptive Flap

  PAN Yurun, MIAO Weipao, LI Chun, ZHANG Qiang, LIU Ke, YUE Minnan

  Journal of Engineering Thermophysics. 2025, 46(12): 4087-4095.

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  Vertical axis wind turbine (VAWT) suffer notable aerodynamic performance losses under extreme gusts compared to steady-state winds. Inspired by the adaptive lift of bird wings to mitigate flow separation, adaptive flaps were installed at the trailing edge of the suction side of VAWT blades. A self-developed program was used to construct a gust model, and computational fluid dynamics simulations were conducted to evaluate the aerodynamic performance under both steady and extreme gust conditions. Results show that adaptive flap effectively enhance flow control under extreme gusts, leading to increased power and torque coefficients and improved overall aerodynamic performance. The adaptive flap mitigate flow separation by dividing the separated flow region into multiple smallscale vortices, promoting flow reattachment.
  
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  Solar-driven Photo-Thermo-Electric Coupling for Hydrogen Production: Material Development and System Integration

  ZHANG Jinjie, GUAN Xiangjiu, DING Yani, XIANG Junfeng, GUO Liejin

  Journal of Engineering Thermophysics. 2025, 46(12): 4096-4109.

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  Solar-driven water/seawater splitting for hydrogen production is an important pathway to achieve the goal of carbon neutrality. However, single technologies such as photocatalysis are limited by issues including insufficient solar spectrum utilization, low energy conversion efficiency, and interference from complex components in seawater, making it difficult to meet the application requirements for large-scale hydrogen production. In this paper, the basic principles and performance optimization strategies of solar-driven hydrogen-production technologies such as photocatalysis, photothermal catalysis and photovoltaic-electrolysis are systematically reviewed; the synergistic mechanism of broad spectral absorption, optimization of the local thermal field and integrated design of devices in the photothermal coupled decomposition of water/seawater system is analyzed at the levels of material development, device design and system integration; and the strategies of corrosionresistant catalytic material design, optimization of interface engineering and regulation of reaction pathway in seawater hydrogen-production system are also discussed. Moreover, the future research trends, technological challenges and application prospects of solar-driven hydrogen production from seawater are proposed.
  
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  Design of a Full-spectrum-driven CO₂ to Chemicals System Based on Photo-thermo-electro-coupled Utilization

  WU Junxiang, LIU Ya, WANG Feng, GUO Liejin

  Journal of Engineering Thermophysics. 2025, 46(12): 4110-4115.

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  Solar-driven CO₂ reduction to chemicals technology enables both carbon emission recycling and stable solar energy storage, representing a green negative-carbon solution for achieving national “Dual Carbon” goals. However, conventional single-path approaches like photothermal, photoelectric or photocatalytic CO₂ reduction exhibit limited the full-spectrum utilization efficiency due to their wavelength-dependent mechanisms. Based on the concentrated photovoltaic/thermal system, this study proposes a novel full-spectrum utilization by transferring thermal energy to the photoelectric chemical reactor to enhance CO₂ conversion. Through multiphysics modeling analysis of the proposed photothermal coupling system, the optical, thermal, and flow field distributions as well as its operational behavior were characterized, and the thermal output efficiency reaches 80% under 30× solar concentration. Outdoor experiments show that compared to traditional PV/electrolysis, the Faraday efficiency of the reduction product CO is improved from 90% to more than 95% because of photo-thermo-electric coupling utilization while maintaining high stability, and the daily output of CO can reach 26.31 L.
  
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  Progress in the Application of Artificial Intelligence in Energy Storage Technologies

  YIN Zhao, XU Yujie, ZHANG Hualiang, XU Dehou, WEI Lu, LENG Zhiyi, YE Jia, ZHAO Xinyu, SHI Zhuoqun, CHAI Xingzai, SUN Baozuo, CHEN Haisheng

  Journal of Engineering Thermophysics. 2025, 46(12): 4116-4140.

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  Energy storage technology plays a crucial role in advancing the development of renewable energy, promoting carbon peak and carbon neutrality, and enhancing the quality of power systems. Facing complex and variable electricity supply and demand scenarios, artificial intelligence (AI) powerfully drives energy storage technology towards development in the directions of high efficiency, economy, reliability, and environmental friendliness. This paper first classifies artificial intelligence into categories such as algorithms (intelligent prediction, intelligent optimization, intelligent decision), tasks (predictive AI, generative AI, computer vision, embodied AI, agents), and scale (small models, large models), elaborating on relevant cases. Subsequently, it introduces the application of artificial intelligence across various stages of energy storage technology, encompassing design, experiment, manufacture, operation, fault diagnosis, and decommissioning & recycling. Following this, it proposes future development directions and summarizes the application system of artificial intelligence in energy storage technology. Through the above work, the paper aims to further promote a more comprehensive, orderly, and in-depth cross-integration of ”AI + Energy Storage”.
  
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  Reconstructing Multi-scale Low-carbon Thermal Energy Systems Enabled by Heat Pumps

  LÜ Haotian, DONG Yixiu, WANG Ruzhu

  Journal of Engineering Thermophysics. 2025, 46(12): 4141-4156.

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  As a highly efficient technology for both heating and cooling, heat pumps play a pivotal role in the global transition toward low-carbon energy systems. This paper presents a systematic review of the evolution of heat pump technology, tracing its development from early-stage refrigeration applications to emerging high-temperature industrial uses. It examines the deployment and performance characteristics of heat pumps across residential, commercial, and industrial sectors, highlighting their potential for integrated heating and cooling and cross-scale energy integration. The study identifies three key challenges currently constraining heat pump development: limited high-temperature heating capability, the urgent need for environmentally friendly low-GWP refrigerant alternatives, and the complexity of load matching, control, and economic feasibility. In response, the paper explores several cutting-edge strategies, including fifth-generation district heating and cooling (5GDHC), integration with thermal energy storage systems, and the application of Carnot batteries. These integrated approaches demonstrate significant potential to enhance primary energy efficiency, reduce operating costs, and markedly decrease greenhouse gas emissions in industrial processes. Finally, the paper underscores the necessity of technological innovation, policy refinement, and cross-sectoral collaboration to advance the widespread adoption of heat pump technologies and accelerate progress toward carbon neutrality and a sustainable energy future.
  
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  Research Progress and Prospects of Transpiration Cooling Technology for Extreme Heat Flux Thermal Protection

  DU Shen, LI Dong, HE Yaling

  Journal of Engineering Thermophysics. 2025, 46(12): 4157-4166.

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  The high efficiency and less coolant requirement characteristics of transpiration cooling provide significant application potential for thermal protection under extreme heat-flux environments, making it a crucial safety guarantee for reusable hypersonic vehicles engaged in long-duration, high-frequency space-to-space and space-to-ground missions. Based on the long-term exploration of transpiration cooling by the author’s team, this review focuses on the mechanisms and applications of transpiration cooling. First, experimental studies on flow and heat transfer characteristics of transpiration cooling were systematically reviewed, along with a summary of research findings on the property characterization of porous materials and cooling performance of the system. Second, differences in two-phase heat transfer models within porous media during transpiration cooling were compared, and recent advances in coupled algorithms for cross-velocity-domain and multi-scale inner/outer field interactions were discussed. Third, application strategies of transpiration cooling technology were reviewed focusing on structural configuration optimization and system regulation techniques. Finally, the future development prospects of transpiration cooling are outlined.
  
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  Study on Modal Characteristics of Coherent Structures in Integrated Combustor-turbine Flow Fields

  WANG Tianyi, XUAN Yimin

  Journal of Engineering Thermophysics. 2025, 46(12): 4167-4178.

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  In the integrated combustor-turbine flow field, there exist numerous recurring ordered motion patterns with spatial or temporal correlations, known as turbulent coherent structures, which significantly influence turbulent combustion stability and turbine aerodynamic efficiency. This study employs high-fidelity numerical simulations combined with multiple modal analysis methods to investigate the flow characteristics of the combustor-turbine integrated flow field and reveals the spatiotemporal evolution mechanisms of its coherent structures. The results demonstrate that spectral proper orthogonal decomposition (SPOD) more efficiently extracts the amplitude-frequency joint characteristics of coherent structures in the integrated flow field compared to proper orthogonal decomposition (POD) and dynamic mode decomposition (DMD). Modal analysis reveals that the flow fluctuation characteristics in the mainstream region near the combustor exit are dominated by the superposition effect of coherent structures from swirling flow and jet from dilution holes, while the unsteady fluctuations near the sidewalls originate from coherent structures formed by coolant-main flow mixing. The modal features of these two regions exhibit significant spatial heterogeneity. The conclusions of this study provide theoretical and technical support for combustor-turbine integrated design and reliability analysis.
  
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  Review on Regenerative Cooling of Hydrocarbon Fuels in Ramjet Engines

  ZHU Yinhai1, 2 TIAN Dongfeng1 CHENG Yuxiang1 JIANG Peixue1

  Journal of Engineering Thermophysics. 2025, 46(12): 4179-4211.

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  Ramjet engines serve as the primary propulsion system for hypersonic vehicles. During flight, the engine walls endure an extreme thermal environment, necessitating effective thermal protection via regenerative cooling. The core challenges of regenerative cooling involve convective heat transfer, thermal cracking, and coking of hydrocarbon fuels at supercritical pressures. This review comprehensively summarizes recent advances in these areas globally. First, the characteristics of supercritical convective heat transfer of hydrocarbon fuels in circular tubes, rectangular channels, and under rotating conditions are elucidated, along with relevant heat transfer correlations. Subsequently, it outlines measurement techniques, reaction mechanisms, and models for fuel cracking. The patterns, mechanisms, models, and suppression methods of coking are also addressed. Furthermore, the effects of thermal cracking and coking on heat transfer is analyzed. Additionally, structural optimization design methods for regenerative cooling channels are elaborated. Finally, future research directions for regenerative cooling are proposed. This review provides theoretical support for performance prediction and optimized design of regenerative cooling systems in ramjet engines.
  
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  Experimental Study of Enhanced Heat Transfer in Manifold-type LHP

  CHEN Chaowei, LIU Yang, CHEN Yan, OU Denglong, XIN Gongming

  Journal of Engineering Thermophysics. 2025, 46(12): 4212-4217.

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  In this work, a novel loop heat pipe with a manifold evaporator cavity and a flat-plate loop heat pipe with an insulating block were designed and fabricated, and capillary cores with composite porosity and thermal conductivity adapted to these two types of loop heat pipes were prepared by using nickel-foam and copper-foam. A heat transfer experimental platform was set up to characterize the heat transfer properties of the two types of loop heat pipes. The results show that the manifold evaporator cavity design can significantly enhance the liquid transport capacity of the capillary core. Compared with the traditional flat-plate loop heat pipe, the critical failure heat load of manifold loop heat pipe has been increased by more than 100%, while its thermal resistance has been reduced by 33.6% and the maximum temperature difference at the bottom surface of the evaporator has been reduced by 16.4◦C. This study can provide new solutions for the study of the enhancement of heat transfer of loop heat pipes and their applications in aerospace and chip thermal management, etc.
  
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  Investigation on Air Carrier Characteristics of Liquid Effluent Based on Low-pressure Atomization Technology

  DENG Zhenpeng, YAN Jindong, CHEN Hua, WANG Shuo, CHENG Wenlong

  Journal of Engineering Thermophysics. 2025, 46(12): 4218-4226.

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  In the nuclear industry, liquid effluents generated during reprocessing are typically discharged using air carrier technology. The heat transfer characteristics of droplet evaporation within the humidification tower are critical factors influencing the effectiveness and safety of air carrier discharge. This study establishes a numerical model for heat transfer and evaporation of fine mist droplets in a humidification tower and constructs an experimental atomization humidification system. The system employs a self-developed low-pressure atomization nozzle, and the accuracy of the model is validated by comparing simulated and experimental results of outlet air temperature and humidity. Further analysis based on this model evaluates the outlet temperature, humidity, humidification efficiency, and humidification capacity of liquid effluent discharge under various parameters. The results indicate that the nozzle atomization requires a liquid supply pressure of less than 1 MPa, with a short atomization distance and droplet sizes below 25 µm. Reducing the initial droplet diameter enhances the gas-liquid contact area, significantly improving discharge performance. When the droplet diameter decreases from 100 µm to 10 µm, the humidification capacity increases by 223.6%, and the height required for complete droplet evaporation decreases by 98.8%. The conclusions of this study provide valuable insights for the design of air carrier liquid effluent discharge systems.
  
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  Investigation of the Flame Morphology Transitions in Swirl Spray Flames at Elevated Pressures and Temperatures

  FENG Xiaoxing, YIN Shengming, DU Hui, GAO Xianzhi, WANG Shaojie, HU Weifan, YAO Jiaxin, WANG Guoqing, XU Liangliang, XIA Xi, GU Mingming, QI Fei

  Journal of Engineering Thermophysics. 2025, 46(12): 4227-4235.

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  The flame morphology of aircraft engines significantly impacts combustion efficiency, stability, and emissions. This study examined centrally staged swirl combustors with different mainstage swirl numbers under near-real conditions (1.3 MPa, 780 K) using OH* chemiluminescence and OH-PLIF diagnostics. Key parameters—flame angle, luminescence intensity, and flame height—were analyzed to assess the effects of fuel-air ratios and main-stage fuel splits. Results showed that higher fuel-air ratios enlarged flame angles, reduced luminescence intensity, and lowered flame heights, indicating intensified mixing-zone reactions and upstream flame shifts. Main-stage fuel splits influenced flame height, luminescence, and radial expansion, highlighting the interplay between nozzle design and operating conditions. These findings aid in optimizing combustor design for improved efficiency.
  
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  Review on Research Progress of the Instability and Engineering Application of Rotating Detonation Combustion

  HE Xiaojian, LIU Peilin, SUN Qi, ZHANG Xiangjun, HOU Yuechen, MA Zhuang, WANG Jianping

  Journal of Engineering Thermophysics. 2025, 46(12): 4236-4251.

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  Compared to traditional deflagration-based engines, rotating detonation engines offer advantages such as a wide speed range, high thermal cycle efficiency, self-suppression, and rapid heat release. These features have gradually attracted increasing attention worldwide and are considered a new type of aerospace propulsion that can further enhance propulsion performance. These engines fall within the scope of “new quality productivity” that China is strongly advocating for development at this stage. This paper briefly reviews the research progress of the common instability phenomena and engineering applications of rotating detonation engines. The instability phenomena discussed include multi-wave phenomena, wave bifurcation, and longitudinal pulse detonation, etc; the engineering applications are categorized into three forms: rocket-, ramjet-, and turbine- rotating detonation engines.
  
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  Research Progress in Modeling Techniques for Spray Combustion Processes

  ZOU Jianfeng, ZHAO Ziting, ZHENG Yao, TAN Gao, HAO Yunfei, SUN Jiaqi, KONG Linghao

  Journal of Engineering Thermophysics. 2025, 46(12): 4252-4269.

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  The spray evaporation and combustion behavior of liquid fuels directly impact the efficiency and pollutant emission characteristics of aero-engines. Developing efficient and highly reliable predictive technologies and tools for spray combustion is crucial for the optimal design of low-emission combustors. This review systematically summarizes the research progress on mainstream modeling methods for liquid fuel spray combustion, with particular emphasis on progress of spray process modeling techniques. Although liquid fuel spray combustion involves the application of turbulent combustion models, their detailed discussion is beyond the scope of this paper due to the complexity and breadth of the subject, as well as space limitations. This article provides a detailed analysis of the advantages and disadvantages of three core methodologies: 1) The widely applied Eulerian-Lagrangian method suffers from limitations in accuracy and practicality due to the poor universality of its atomization models and their reliance on experimental tuning. 2) Direct numerical simulation (DNS) of gas-liquid two-phase flow, while capable of precisely capturing interface evolution, incurs prohibitively high computational costs and is thus mainly suitable for mechanistic studies of initial instability processes near the nozzle. 3) Among multi-scale hybrid modeling approaches, the near-field DNS method eliminates the need for empirical models but requires detailed resolution of the primary breakup process, leading to enormous computational demands that hinder engineering applications. In contrast, the full-field Large Eddy Simulation (LES) method coupled with a sub-grid scale (SGS) atomization model significantly reduces mesh resolution requirements by modeling rather than directly resolving the near-field liquid ligament/droplet generation process, offering feasibility for simulating turbulent atomization and spray combustion under high Reynolds and Weber number conditions typical of real engine combustors. Current predictive models commonly face bottlenecks such as weak generalization capability of empirical atomization submodels, excessive resource demands for direct simulations, and unclear cross-scale coupling mechanisms. Key future research directions include: 1) Developing adaptive mesh and large-scale parallel computing technologies to dynamically optimize resolution in critical flow regions and enhance computational efficiency; 2) Exploring machine learning-based methods for constructing atomization submodels to overcome the generalization limitations of traditional empirical correlations and efficiently learn complex nonlinear relationships within high-dimensional parameter spaces; 3) Deepening research on the reliability of SGS atomization modeling theories and advancing the engineering application and validation of SGS atomization models. This review aims to provide theoretical references and technical perspectives for the design optimization of high-performance, low-emission aero-engine combustors