An experimental study was conducted to characterize the dynamic ice accretion process over the surface of a typical aeronautic Pitot probe model under different icing conditions. The experimental study was conducted in the Icing Research Tunnel available at Iowa State University. While a high-speed imaging system was used to record the dynamic ice accretion process, a three-dimensional (3D) scanning system was also used to measure the 3D shapes of the ice layers accreted on the test model. While opaque and grainy ice structures were found to accrete mainly along the wedge-shaped lip of the front port and over the front surface of the probe holder under a dry rime icing condition, much more complicated ice structures with transparent and glazy appearance were observed to cover almost entire surface of the Pitot probe under a wet glaze icing condition. While a flower-like ice structure was found to grow rapidly along the front port lip, multiple irregular-shaped ice structures accreted over the probe holder under a mixed icing condition. The characteristics of the icing process under different icing conditions were compared in terms of 3D shapes of the ice structures, the profiles of the accreted ice layers, the ice blockage to the front port, and the total ice mass on the Pitot probe model. The acquired ice accretion images were correlated with the 3D ice shape measurements to elucidate the underlying icing physics.
{"title":"Experimental Study of Dynamic Icing Process on a Pitot Probe Model","authors":"Haiyang Hu, Faisal Al-Masri, L. Tian, Hui Hu","doi":"10.2514/1.t6782","DOIUrl":"https://doi.org/10.2514/1.t6782","url":null,"abstract":"An experimental study was conducted to characterize the dynamic ice accretion process over the surface of a typical aeronautic Pitot probe model under different icing conditions. The experimental study was conducted in the Icing Research Tunnel available at Iowa State University. While a high-speed imaging system was used to record the dynamic ice accretion process, a three-dimensional (3D) scanning system was also used to measure the 3D shapes of the ice layers accreted on the test model. While opaque and grainy ice structures were found to accrete mainly along the wedge-shaped lip of the front port and over the front surface of the probe holder under a dry rime icing condition, much more complicated ice structures with transparent and glazy appearance were observed to cover almost entire surface of the Pitot probe under a wet glaze icing condition. While a flower-like ice structure was found to grow rapidly along the front port lip, multiple irregular-shaped ice structures accreted over the probe holder under a mixed icing condition. The characteristics of the icing process under different icing conditions were compared in terms of 3D shapes of the ice structures, the profiles of the accreted ice layers, the ice blockage to the front port, and the total ice mass on the Pitot probe model. The acquired ice accretion images were correlated with the 3D ice shape measurements to elucidate the underlying icing physics.","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":" ","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43295425","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
R. Hidki, L. El moutaouakil, M. Boukendil, Z. Charqui, Z. Zrikem
{"title":"Mixed-Convection Coupled with Thermal-Radiation in a Ventilated Horizontal Channel Containing Different Electronic Components","authors":"R. Hidki, L. El moutaouakil, M. Boukendil, Z. Charqui, Z. Zrikem","doi":"10.2514/1.t6659","DOIUrl":"https://doi.org/10.2514/1.t6659","url":null,"abstract":"","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":" ","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-01-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42982969","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
In this paper, magnetohydrodynamics natural convection inside an annulus equipped with fins is studied numerically. The impact of various parameters such as the angle of the fin, length of the fin, and the Hartmann number on the flow and heat transfer characteristics are studied. The governing equations are discretized using a finite volume technique at a fixed value of the Rayleigh number ([Formula: see text]), while the Hartmann number is in the range of 0–100. The results show that increasing the angle of the fin ([Formula: see text]) for a specific value of the fin length ([Formula: see text]) results in decreasing the heat transfer except [Formula: see text] due to some created small vortices. Moreover, the Nusselt number is reduced by increasing the Hartmann number. For all ranges of the Hartmann number from 0 to 100, the change in the Nusselt number is at maximum when [Formula: see text].
{"title":"Magnetohydrodynamics Natural Convection Inside an Annulus Equipped with Fins","authors":"Ahad Abedini Esfahlani, H. Kargarsharifabad","doi":"10.2514/1.t6696","DOIUrl":"https://doi.org/10.2514/1.t6696","url":null,"abstract":"In this paper, magnetohydrodynamics natural convection inside an annulus equipped with fins is studied numerically. The impact of various parameters such as the angle of the fin, length of the fin, and the Hartmann number on the flow and heat transfer characteristics are studied. The governing equations are discretized using a finite volume technique at a fixed value of the Rayleigh number ([Formula: see text]), while the Hartmann number is in the range of 0–100. The results show that increasing the angle of the fin ([Formula: see text]) for a specific value of the fin length ([Formula: see text]) results in decreasing the heat transfer except [Formula: see text] due to some created small vortices. Moreover, the Nusselt number is reduced by increasing the Hartmann number. For all ranges of the Hartmann number from 0 to 100, the change in the Nusselt number is at maximum when [Formula: see text].","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":" ","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-01-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48051489","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Melting processes of phase change material (PCM) confined in a rectangular cavity with an isothermal vertical wall are investigated to quantify the transition criterion between different melting regimes. A series of numerical simulations are conducted via the phase-change lattice Boltzmann method, and the results show that the temperature field in the liquid PCM region changes from the structure with two thermal boundary layers to the structure with two thermal boundary layers plus a convection region. Moreover, the results also indicate that the heat transfer mechanism undergoes a transition from conduction to convection when the relative thickness between the convention region and the thermal boundary reaches a critical value. This value (transition criterion) can be quantified by the critical melted volume fraction, and its dependence on Rayleigh number, Prandtl number, and aspect ratio of cavity is theoretically derived in this study. Then, based on the transition criterion, a piecewise correlation of melted volume fraction is proposed, which considers the effect of different melting regimes and is proven to predict the literature’s result.
{"title":"Melting Processes of Phase Change Material in Sidewall-Heated Cavity","authors":"Y. Li, G. Su","doi":"10.2514/1.t6705","DOIUrl":"https://doi.org/10.2514/1.t6705","url":null,"abstract":"Melting processes of phase change material (PCM) confined in a rectangular cavity with an isothermal vertical wall are investigated to quantify the transition criterion between different melting regimes. A series of numerical simulations are conducted via the phase-change lattice Boltzmann method, and the results show that the temperature field in the liquid PCM region changes from the structure with two thermal boundary layers to the structure with two thermal boundary layers plus a convection region. Moreover, the results also indicate that the heat transfer mechanism undergoes a transition from conduction to convection when the relative thickness between the convention region and the thermal boundary reaches a critical value. This value (transition criterion) can be quantified by the critical melted volume fraction, and its dependence on Rayleigh number, Prandtl number, and aspect ratio of cavity is theoretically derived in this study. Then, based on the transition criterion, a piecewise correlation of melted volume fraction is proposed, which considers the effect of different melting regimes and is proven to predict the literature’s result.","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":" ","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-01-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45305105","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Tingting Wu, C. Zhang, H. Ji, Yupeng Zhang, C. Tao, J. Qiu
Aerodynamic heating measurement of reusable hypersonic vehicles has always been an important aspect of hypersonic vehicle design. In this paper, a mechanistic-model-based heat flux identification method with artificial neural network (ANN) compensation is established to determine the spatially distributed heat flux of the aircraft structure. A one-dimensional heat conduction model is used to estimate heat flux by a robust and efficient algorithm integrating Tikhonov regularization with Levenberg–Marquardt method. The one-dimensional estimated heat flux has large errors for not considering multidimensional heat conduction effects. The proposed mechanistic-model-based method is then utilized to compensate the multidimensional heat conduction by ANN. The performance of the proposed method will be assessed by the determination of the heat flux of a two-dimensional plate and aircraft structure. Results show that compared with the one-dimensional inversion results, ANN compensation method can significantly improve the accuracy of estimated heat flux and is also applicable for larger levels of heat flux. The proposed compensation method is an effective technique to identify the nonuniform surface heat flux of multidimensional structures.
{"title":"Heat Flux Identification of Aircraft Structure with Artificial Neural Network Compensation","authors":"Tingting Wu, C. Zhang, H. Ji, Yupeng Zhang, C. Tao, J. Qiu","doi":"10.2514/1.t6680","DOIUrl":"https://doi.org/10.2514/1.t6680","url":null,"abstract":"Aerodynamic heating measurement of reusable hypersonic vehicles has always been an important aspect of hypersonic vehicle design. In this paper, a mechanistic-model-based heat flux identification method with artificial neural network (ANN) compensation is established to determine the spatially distributed heat flux of the aircraft structure. A one-dimensional heat conduction model is used to estimate heat flux by a robust and efficient algorithm integrating Tikhonov regularization with Levenberg–Marquardt method. The one-dimensional estimated heat flux has large errors for not considering multidimensional heat conduction effects. The proposed mechanistic-model-based method is then utilized to compensate the multidimensional heat conduction by ANN. The performance of the proposed method will be assessed by the determination of the heat flux of a two-dimensional plate and aircraft structure. Results show that compared with the one-dimensional inversion results, ANN compensation method can significantly improve the accuracy of estimated heat flux and is also applicable for larger levels of heat flux. The proposed compensation method is an effective technique to identify the nonuniform surface heat flux of multidimensional structures.","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":"1 1","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-01-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"69688775","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Yifeng Zhang, Yong Cao, Yu Feng, Deming Zhang, J. Qin
Efficient utilization of chemical heat sinks and enhancement of heat transfer are key issues for the thermal protection of advanced hypersonic flight vehicles. However, the influences of residence time on the pyrolysis and convection heat transfer of hydrocarbon fuel are different, which is important for the design and optimization of cooling systems. Therefore, a multidimensional numerical simulation model based on a molecular reaction model of aviation kerosene, RP-3, is established. This model reveals that the residence time has a great influence on the heat sink and heat transfer characteristics under the supercritical condition. With the increase of the residence time, the chemical heat sink and physical heat sink increase, whereas the convective heat transfer coefficient decreases. The heat transfer is not only affected by flow structures but also by the ratio of the chemical heat sink to the physical heat sink. With the increase of the residence time, this ratio first increases and then decreases. It has a maximum value, and the residence time corresponding to this maximum value is exactly the residence time when the total chemical heat sink rate reaches the maximum. A correlation predicting the maximum heat sink ratio is proposed based on these data.
{"title":"Investigation into Effect of Residence Time on Cooling Characteristics of RP-3","authors":"Yifeng Zhang, Yong Cao, Yu Feng, Deming Zhang, J. Qin","doi":"10.2514/1.t6556","DOIUrl":"https://doi.org/10.2514/1.t6556","url":null,"abstract":"Efficient utilization of chemical heat sinks and enhancement of heat transfer are key issues for the thermal protection of advanced hypersonic flight vehicles. However, the influences of residence time on the pyrolysis and convection heat transfer of hydrocarbon fuel are different, which is important for the design and optimization of cooling systems. Therefore, a multidimensional numerical simulation model based on a molecular reaction model of aviation kerosene, RP-3, is established. This model reveals that the residence time has a great influence on the heat sink and heat transfer characteristics under the supercritical condition. With the increase of the residence time, the chemical heat sink and physical heat sink increase, whereas the convective heat transfer coefficient decreases. The heat transfer is not only affected by flow structures but also by the ratio of the chemical heat sink to the physical heat sink. With the increase of the residence time, this ratio first increases and then decreases. It has a maximum value, and the residence time corresponding to this maximum value is exactly the residence time when the total chemical heat sink rate reaches the maximum. A correlation predicting the maximum heat sink ratio is proposed based on these data.","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":" ","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-01-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47683486","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
A numerical solver is developed for the modeling of electric discharges in high-speed flows. For the formulation of the physicochemical model, common electric discharge modeling approaches are combined with detailed models for nonequilibrium aerothermodynamics and finite-rate chemical kinetics. The physicochemical model is based on the single-fluid assumption and takes into account the thermal and chemical nonequilibria in the gas mixture. For the numerical implementation, the finite-volume-based open-source CFD software package OpenFOAM is used. The verification of the calculation models for thermodynamic and transport properties as well as finite-rate chemical kinetics is carried out by means of one-dimensional simulations. The first validation of the solver is carried out by means of a three-dimensional simulation of an electric discharge with a constant input power of 10 kW generated on the surface of a wedge in a supersonic nitrogen flow. The numerically obtained results are compared with corresponding experimental measurements and theoretical calculations and show a fair agreement. The numerically calculated maximum temperature values, for example, are 20–40% above the measured values. However, it should be noted that the experimentally obtained values represent a spatial integration over the entire measurement volume and therefore do not indicate maximum temperature values.
{"title":"Numerical Modeling of Electric Discharges Generated in Supersonic Flows","authors":"Alexander Nekris, P. Gnemmi, C. Mundt","doi":"10.2514/1.t6509","DOIUrl":"https://doi.org/10.2514/1.t6509","url":null,"abstract":"A numerical solver is developed for the modeling of electric discharges in high-speed flows. For the formulation of the physicochemical model, common electric discharge modeling approaches are combined with detailed models for nonequilibrium aerothermodynamics and finite-rate chemical kinetics. The physicochemical model is based on the single-fluid assumption and takes into account the thermal and chemical nonequilibria in the gas mixture. For the numerical implementation, the finite-volume-based open-source CFD software package OpenFOAM is used. The verification of the calculation models for thermodynamic and transport properties as well as finite-rate chemical kinetics is carried out by means of one-dimensional simulations. The first validation of the solver is carried out by means of a three-dimensional simulation of an electric discharge with a constant input power of 10 kW generated on the surface of a wedge in a supersonic nitrogen flow. The numerically obtained results are compared with corresponding experimental measurements and theoretical calculations and show a fair agreement. The numerically calculated maximum temperature values, for example, are 20–40% above the measured values. However, it should be noted that the experimentally obtained values represent a spatial integration over the entire measurement volume and therefore do not indicate maximum temperature values.","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":" ","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-01-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44417420","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The efficient and accurate prediction of the aeroheating performance of hypersonic vehicles is a challenging task in the thermal protection system structure design process, which is greatly affected by grid distribution, numerical schemes, and iterative steps. From the inspiration of the theoretical analysis and machine learning strategy, a new wall heat flux prediction framework is proposed first by establishing the relationship between the wall heat flux and the flow variables at an extreme temperature point (ETP) in the normal direction of the corresponding wall grid cell, which is named the machine learning (ML)-ETP method. In the training phase, the flow properties and their gradients at the ETP and the distance from the ETP normal to the wall are employed as feature values, and the accurate wall heat flux predicted by the converged fine grid is regarded as the tag value. With the assistance of the trained regression model, the heat flux of the same configuration with a coarse grid in the wall-normal direction could be predicted accurately and efficiently. Moreover, test cases of different configurations and inflow conditions with a coarse grid are also carried out to assess the model’s generalization performance. All comparison results demonstrate that the ML-ETP strategy could predict wall heat flux more rapidly and accurately than the traditional numerical method due to its nonstrict grid distribution requirements. The improvement of the predictive capability of the coarse-graining model could make the ML-ETP method an effective tool in hypersonic engineering applications, especially for unsteady ablation simulations or aerothermal optimizations.
{"title":"Machine Learning Strategy for Wall Heat Flux Prediction in Aerodynamic Heating","authors":"Gang Dai, Wenwen Zhao, Shaobo Yao, Weifang Chen","doi":"10.2514/1.t6675","DOIUrl":"https://doi.org/10.2514/1.t6675","url":null,"abstract":"The efficient and accurate prediction of the aeroheating performance of hypersonic vehicles is a challenging task in the thermal protection system structure design process, which is greatly affected by grid distribution, numerical schemes, and iterative steps. From the inspiration of the theoretical analysis and machine learning strategy, a new wall heat flux prediction framework is proposed first by establishing the relationship between the wall heat flux and the flow variables at an extreme temperature point (ETP) in the normal direction of the corresponding wall grid cell, which is named the machine learning (ML)-ETP method. In the training phase, the flow properties and their gradients at the ETP and the distance from the ETP normal to the wall are employed as feature values, and the accurate wall heat flux predicted by the converged fine grid is regarded as the tag value. With the assistance of the trained regression model, the heat flux of the same configuration with a coarse grid in the wall-normal direction could be predicted accurately and efficiently. Moreover, test cases of different configurations and inflow conditions with a coarse grid are also carried out to assess the model’s generalization performance. All comparison results demonstrate that the ML-ETP strategy could predict wall heat flux more rapidly and accurately than the traditional numerical method due to its nonstrict grid distribution requirements. The improvement of the predictive capability of the coarse-graining model could make the ML-ETP method an effective tool in hypersonic engineering applications, especially for unsteady ablation simulations or aerothermal optimizations.","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":" ","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42871072","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
S. Gimelshein, Jesse W. Streicher, Ajay Krish, R. Hanson, I. Wysong
The direct simulation Monte Carlo (DSMC) method is used to model transient thermal and chemical relaxation behind reflected shock waves in oxygen–argon and air mixtures under conditions reproducing earlier shock-tube experiments. Two vibration–translation and three popular DSMC chemical reaction models are tested. Where possible, model parameters are adjusted to match equilibrium and nonequilibrium [Formula: see text] relaxation times and reaction rates. A number of factors that impact relaxation and reaction model validation are examined, including gas–surface interactions, time-varying freestream properties, location of the observation point, electronic excitation, and nonequilibrium populations of vibrational states probed in the experiments. Comparison of numerical and experimental results has demonstrated that the reflected shock configuration is a platform very convenient for validation and analysis of high-temperature chemical reaction models. Computations have shown that the Bias reaction model is superior to the total collision energy and quantum kinetic models, providing reasonable agreement with measured absorbance time histories and [Formula: see text] vibrational temperatures in oxygen–argon mixtures and pure [Formula: see text]. There are some modeling-versus-experiment differences observed for air that may warrant additional studies focused on Zeldovich reaction rates and oxygen–nitrogen vibrational excitation and nonequilibrium dissociation rate.
{"title":"Application of Reflected Shock Wave Configuration to Validate Nonequilibrium Models of Reacting Air","authors":"S. Gimelshein, Jesse W. Streicher, Ajay Krish, R. Hanson, I. Wysong","doi":"10.2514/1.t6630","DOIUrl":"https://doi.org/10.2514/1.t6630","url":null,"abstract":"The direct simulation Monte Carlo (DSMC) method is used to model transient thermal and chemical relaxation behind reflected shock waves in oxygen–argon and air mixtures under conditions reproducing earlier shock-tube experiments. Two vibration–translation and three popular DSMC chemical reaction models are tested. Where possible, model parameters are adjusted to match equilibrium and nonequilibrium [Formula: see text] relaxation times and reaction rates. A number of factors that impact relaxation and reaction model validation are examined, including gas–surface interactions, time-varying freestream properties, location of the observation point, electronic excitation, and nonequilibrium populations of vibrational states probed in the experiments. Comparison of numerical and experimental results has demonstrated that the reflected shock configuration is a platform very convenient for validation and analysis of high-temperature chemical reaction models. Computations have shown that the Bias reaction model is superior to the total collision energy and quantum kinetic models, providing reasonable agreement with measured absorbance time histories and [Formula: see text] vibrational temperatures in oxygen–argon mixtures and pure [Formula: see text]. There are some modeling-versus-experiment differences observed for air that may warrant additional studies focused on Zeldovich reaction rates and oxygen–nitrogen vibrational excitation and nonequilibrium dissociation rate.","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":" ","pages":""},"PeriodicalIF":2.1,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45775329","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Yaru Sun, Jiadong Ji, Zisen Hua, Runmiao Gao, Chengjun Wang
A novel hollow shell-and-tube heat exchanger with helical elastic coiled tubes was designed to improve the overall heat transfer performance. Different numbers of helical baffles installed on the hollow helical elastic tubes (HHETs) heat exchanger were compared with the HHET heat exchanger without a baffle. The fluid–solid coupling method was provided to study the effects of the entrance velocity and baffle number on the performances of heat transfer and vibration-enhanced heat transfer. Based on the numerical results, the performances of vibration and heat transfer become more obvious by increasing the entrance velocity. Compared with the HHET heat exchanger without a baffle, adding a baffle or baffles on the HHET heat exchanger can remarkably make the fluid flow more consistent. Whereas a higher number of baffles can weaken the vibration and heat transfer performance of the novel heat exchange, the performance evaluation criteria of the HHET heat exchanger with one baffle, two baffles, and four baffles is improved by 2.04, 4.37, and 2.3%, respectively. It indicates that adding a baffle or baffles to the novel heat exchanger can effectively improve the overall thermal and hydraulic characteristics of the novel heat exchanger.
{"title":"Flow-Induced Vibration and Heat Transfer Analysis for a Novel Hollow Heat Exchanger","authors":"Yaru Sun, Jiadong Ji, Zisen Hua, Runmiao Gao, Chengjun Wang","doi":"10.2514/1.t6588","DOIUrl":"https://doi.org/10.2514/1.t6588","url":null,"abstract":"A novel hollow shell-and-tube heat exchanger with helical elastic coiled tubes was designed to improve the overall heat transfer performance. Different numbers of helical baffles installed on the hollow helical elastic tubes (HHETs) heat exchanger were compared with the HHET heat exchanger without a baffle. The fluid–solid coupling method was provided to study the effects of the entrance velocity and baffle number on the performances of heat transfer and vibration-enhanced heat transfer. Based on the numerical results, the performances of vibration and heat transfer become more obvious by increasing the entrance velocity. Compared with the HHET heat exchanger without a baffle, adding a baffle or baffles on the HHET heat exchanger can remarkably make the fluid flow more consistent. Whereas a higher number of baffles can weaken the vibration and heat transfer performance of the novel heat exchange, the performance evaluation criteria of the HHET heat exchanger with one baffle, two baffles, and four baffles is improved by 2.04, 4.37, and 2.3%, respectively. It indicates that adding a baffle or baffles to the novel heat exchanger can effectively improve the overall thermal and hydraulic characteristics of the novel heat exchanger.","PeriodicalId":17482,"journal":{"name":"Journal of Thermophysics and Heat Transfer","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136296832","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：