The accurate prediction of the aeroheating performance of hypersonic vehicles requires more detailed modeling of the catalysis process,rather than merely employing a catalytic coefficient.In this paper,the theoretical...The accurate prediction of the aeroheating performance of hypersonic vehicles requires more detailed modeling of the catalysis process,rather than merely employing a catalytic coefficient.In this paper,the theoretical modeling,as well as the direct simulation Monte Carlo method,is used to preliminarily study the incomplete chemical energy accommodation effects,that is,only a part of the potential energy released in the heterogenous recombination reaction is transferred to the surface,while the remaining is retained as the vibrational energy of the desorbed molecule.An integrated model is proposed to describe the contribution of each energy mode in the rarefied nonequilibrium heat and mass transfer process.Based on the model and several Damko?hler numbers,an analytical formula is derived,and is also shown to compare well with the numerical results.On account of the incomplete accommodations of the chemical and vibrational energy on the wall,a variation up to 20%is observed in predicting the stagnation point heat flux under typical nonequilibrium flow conditions.This study could enrich our understanding of the nonequilibrium heat transfer phenomenon and also shows a potential practical value.展开更多
Gasdynamic flow features in an electrothermal arcjet thruster with a mixture of 1：2 nitrogen/hydrogen as the working gas have been studied by a two-temperature numerical simulation.Seven species and 17 kinetic proces...Gasdynamic flow features in an electrothermal arcjet thruster with a mixture of 1：2 nitrogen/hydrogen as the working gas have been studied by a two-temperature numerical simulation.Seven species and 17 kinetic processes are included in the chemical kinetic model used to represent dissociation, ionization, and the corresponding recombination reactions in this nitrogen/hydrogen mixture system. Based on the gas flow characteristics inside the arcjet nozzle,a new method is introduced to define the edge of the cold boundary layer, which is more convenient to analyze the evolution and development of plasma flow in an arcjet thruster. The results show that the arcjet thruster performance is determined largely by the exchange of energy and momentum between the low-density, high-temperature arc region and the high-density, coolflow region near the nozzle wall. A significant thermal nonequilibrium is found in the cold boundary layer in the expansion portion of the nozzle. The important chemical kinetic processes determining the distribution of hydrogen and nitrogen species in different flow regions are presented. It has been shown that the reaction rate of hydrogen species ionization impacted by electrons is much higher than that of nitrogen species ionization in the center of the constrictor of the arcjet thruster. This indicates that hydrogen species is very important in the conversion of applied electric energy into thermal energy in the constrictor region of the arcjet thruster.展开更多
We applied the method of Thermomechanical Dynamics (TMD) to a low-temperature Stirling engine, and the dissipative equation of motion and time-evolving physical quantities are self-consistently calculated for the firs...We applied the method of Thermomechanical Dynamics (TMD) to a low-temperature Stirling engine, and the dissipative equation of motion and time-evolving physical quantities are self-consistently calculated for the first time in this field. The thermomechanical states of the heat engine are in Nonequilibrium Irreversible States (NISs), and time-dependent thermodynamic work W(t), internal energy E(t), energy dissipation or entropy Q<sub>d</sub>(t), and temperature T(t), are precisely studied and computed in TMD. We also introduced the new formalism, Q(t)-picture of thermodynamic heat-energy flows, for consistent analyses of NISs. Thermal flows in a long-time uniform heat flow and in a short-time heat flow are numerically studied as examples. In addition to the analysis of time-dependent physical quantities, the TMD analysis suggests that the concept of force and acceleration in Newtonian mechanics should be modified. The acceleration is defined as a continuously differentiable function of Class C<sup>2</sup> in Newtonian mechanics, but the thermomechanical dynamics demands piecewise continuity for acceleration and thermal force, required from physical reasons caused by frictional variations and thermal fluctuations. The acceleration has no direct physical meaning associated with force in TMD. The physical implications are fundamental for the concept of the macroscopic phenomena in NISs composed of systems in thermal and mechanical motion.展开更多
A novel capillary array model is proposed to shed light on the development of themaldistribution of cocurrent downward gas-liquid flow and the hysteretic performance behavior in apacked column.The model is based on th...A novel capillary array model is proposed to shed light on the development of themaldistribution of cocurrent downward gas-liquid flow and the hysteretic performance behavior in apacked column.The model is based on the principle of nonequilibrium thermodynamics and incombination with lateral random walk of elemental liquid rivulets.The liquid distribution over aone-dimensional array of capillaries is simulated and the basic features of gas-liquid flow in packedbeds are demonstrated.With proper correspondence of hysteresis branches with nonuniformity of flowdistribution assumed,the experimentally observed hysteresis in pressure drop,liquid holdup and masstransfer rate can be qualitatively simulated.Strenuous efforts are still required for further developingthis model into a predictive tool for the evaluation of performance of packed-bed type devices.展开更多
为准确高效地模拟高压CO_(2)管道泄漏的瞬态特性,基于Fluent仿真平台,利用用户自定义真实气体模型(User Defined Real Gas Model,UDRGM)和用户自定义函数(User Defined Function,UDF),结合查表法和双线性插值法建立CO_(2)的真实气体模型...为准确高效地模拟高压CO_(2)管道泄漏的瞬态特性,基于Fluent仿真平台,利用用户自定义真实气体模型(User Defined Real Gas Model,UDRGM)和用户自定义函数(User Defined Function,UDF),结合查表法和双线性插值法建立CO_(2)的真实气体模型,并将压力驱动的Lee模型通过用户自定义函数嵌入Fluent求解器来模拟CO_(2)的非平衡相变过程,建立了高压CO_(2)管道泄漏的非平衡相变数值模型。通过与Botros等的试验数据进行对比分析,验证了该模型的准确性。在此基础上,对比了上述模拟方法与编译S-W(Span-Wagner)状态方程模拟方法的精度和效率,最后使用本模型研究了不同初始压力对高压CO_(2)管道泄漏瞬态特性的影响。结果表明:两种模拟方法精度接近,最大相差为7.37%,但提出的模拟方法效率明显优于编译S-W状态方程的模拟方法,计算时间相较缩短约86.9%;初始压力为11.27 MPa的最大总出口质量流量比4.36 MPa的大7.24 kg/s,而对应的气相CO_(2)出口质量流量却低0.14 kg/s;初始压力为11.27 MPa和4.36 MPa对应的近场最大射流流速分别为155.12 m/s和175.50 m/s;管内初始压力越低,泄漏后到达亚稳态时过热度越大,管内及泄漏口附近相变程度越剧烈,气相出口质量流量越大,近场射流峰值速度越大。这项研究可为工业规模管道泄漏的模拟和管道泄漏的三维模拟提供更高效的方式。展开更多
This paper systematically reviews the mathematical modeling based on the computational fluid dynamics(CFD)method of equilibrium and nonequilibrium hypersonic flows.First,some physicochemical phenomena in hypersonic fl...This paper systematically reviews the mathematical modeling based on the computational fluid dynamics(CFD)method of equilibrium and nonequilibrium hypersonic flows.First,some physicochemical phenomena in hypersonic flows(e.g.,vibrational energy excitation and chemical reactions)and the flow characteristics at various altitudes(e.g.,thermochemical equilibrium,chemical nonequilibrium,and thermochemical nonequilibrium)are reviewed.Second,the judgment rules of whether the CFD method can be applied to hypersonic flows are summarized for accurate numerical calculations.This study focuses on the related numerical models and calculation processes of the CFD method in a thermochemical equilibrium flow and two nonequilibrium flows.For the thermochemical equilibrium flow,the governing equations,chemical composition calculation methods,and related research on the thermodynamic and transport properties of air are reviewed.For the nonequilibrium flows,the governing equations that include one-,two-,and three-temperature models are reviewed.The one-temperature model is applied to a chemical nonequilibrium flow,whereas the two-and three-temperature models are applied to a thermochemical nonequilibrium flow.The associated calculations and numerical models of the thermodynamic and transport properties,chemical reaction sources,and energy transfers between different energy modes of the three models are presented in detail.Finally,the corresponding numerical models of two special wall boundary conditions commonly used in hypersonic flows(i.e.,slip boundary conditions and catalytic walls)and related research,are reviewed.展开更多
基金supported by the National Natural Science Foundation of China (Nos. 11672292 and 12072343)the Youth Innovation Promotion Association of Chinese Academy of Sciences (No. 2017490)the Strategic Priority Research Program (B) of Chinese Academy of Sciences (No. XDB22040202)
文摘The accurate prediction of the aeroheating performance of hypersonic vehicles requires more detailed modeling of the catalysis process,rather than merely employing a catalytic coefficient.In this paper,the theoretical modeling,as well as the direct simulation Monte Carlo method,is used to preliminarily study the incomplete chemical energy accommodation effects,that is,only a part of the potential energy released in the heterogenous recombination reaction is transferred to the surface,while the remaining is retained as the vibrational energy of the desorbed molecule.An integrated model is proposed to describe the contribution of each energy mode in the rarefied nonequilibrium heat and mass transfer process.Based on the model and several Damko?hler numbers,an analytical formula is derived,and is also shown to compare well with the numerical results.On account of the incomplete accommodations of the chemical and vibrational energy on the wall,a variation up to 20%is observed in predicting the stagnation point heat flux under typical nonequilibrium flow conditions.This study could enrich our understanding of the nonequilibrium heat transfer phenomenon and also shows a potential practical value.
基金Supported by National Natural Science Foundation of China(Grant Nos.11575019,11275021)
文摘Gasdynamic flow features in an electrothermal arcjet thruster with a mixture of 1：2 nitrogen/hydrogen as the working gas have been studied by a two-temperature numerical simulation.Seven species and 17 kinetic processes are included in the chemical kinetic model used to represent dissociation, ionization, and the corresponding recombination reactions in this nitrogen/hydrogen mixture system. Based on the gas flow characteristics inside the arcjet nozzle,a new method is introduced to define the edge of the cold boundary layer, which is more convenient to analyze the evolution and development of plasma flow in an arcjet thruster. The results show that the arcjet thruster performance is determined largely by the exchange of energy and momentum between the low-density, high-temperature arc region and the high-density, coolflow region near the nozzle wall. A significant thermal nonequilibrium is found in the cold boundary layer in the expansion portion of the nozzle. The important chemical kinetic processes determining the distribution of hydrogen and nitrogen species in different flow regions are presented. It has been shown that the reaction rate of hydrogen species ionization impacted by electrons is much higher than that of nitrogen species ionization in the center of the constrictor of the arcjet thruster. This indicates that hydrogen species is very important in the conversion of applied electric energy into thermal energy in the constrictor region of the arcjet thruster.
文摘We applied the method of Thermomechanical Dynamics (TMD) to a low-temperature Stirling engine, and the dissipative equation of motion and time-evolving physical quantities are self-consistently calculated for the first time in this field. The thermomechanical states of the heat engine are in Nonequilibrium Irreversible States (NISs), and time-dependent thermodynamic work W(t), internal energy E(t), energy dissipation or entropy Q<sub>d</sub>(t), and temperature T(t), are precisely studied and computed in TMD. We also introduced the new formalism, Q(t)-picture of thermodynamic heat-energy flows, for consistent analyses of NISs. Thermal flows in a long-time uniform heat flow and in a short-time heat flow are numerically studied as examples. In addition to the analysis of time-dependent physical quantities, the TMD analysis suggests that the concept of force and acceleration in Newtonian mechanics should be modified. The acceleration is defined as a continuously differentiable function of Class C<sup>2</sup> in Newtonian mechanics, but the thermomechanical dynamics demands piecewise continuity for acceleration and thermal force, required from physical reasons caused by frictional variations and thermal fluctuations. The acceleration has no direct physical meaning associated with force in TMD. The physical implications are fundamental for the concept of the macroscopic phenomena in NISs composed of systems in thermal and mechanical motion.
文摘A novel capillary array model is proposed to shed light on the development of themaldistribution of cocurrent downward gas-liquid flow and the hysteretic performance behavior in apacked column.The model is based on the principle of nonequilibrium thermodynamics and incombination with lateral random walk of elemental liquid rivulets.The liquid distribution over aone-dimensional array of capillaries is simulated and the basic features of gas-liquid flow in packedbeds are demonstrated.With proper correspondence of hysteresis branches with nonuniformity of flowdistribution assumed,the experimentally observed hysteresis in pressure drop,liquid holdup and masstransfer rate can be qualitatively simulated.Strenuous efforts are still required for further developingthis model into a predictive tool for the evaluation of performance of packed-bed type devices.
文摘为准确高效地模拟高压CO_(2)管道泄漏的瞬态特性,基于Fluent仿真平台,利用用户自定义真实气体模型(User Defined Real Gas Model,UDRGM)和用户自定义函数(User Defined Function,UDF),结合查表法和双线性插值法建立CO_(2)的真实气体模型,并将压力驱动的Lee模型通过用户自定义函数嵌入Fluent求解器来模拟CO_(2)的非平衡相变过程,建立了高压CO_(2)管道泄漏的非平衡相变数值模型。通过与Botros等的试验数据进行对比分析,验证了该模型的准确性。在此基础上,对比了上述模拟方法与编译S-W(Span-Wagner)状态方程模拟方法的精度和效率,最后使用本模型研究了不同初始压力对高压CO_(2)管道泄漏瞬态特性的影响。结果表明:两种模拟方法精度接近,最大相差为7.37%,但提出的模拟方法效率明显优于编译S-W状态方程的模拟方法,计算时间相较缩短约86.9%;初始压力为11.27 MPa的最大总出口质量流量比4.36 MPa的大7.24 kg/s,而对应的气相CO_(2)出口质量流量却低0.14 kg/s;初始压力为11.27 MPa和4.36 MPa对应的近场最大射流流速分别为155.12 m/s和175.50 m/s;管内初始压力越低,泄漏后到达亚稳态时过热度越大,管内及泄漏口附近相变程度越剧烈,气相出口质量流量越大,近场射流峰值速度越大。这项研究可为工业规模管道泄漏的模拟和管道泄漏的三维模拟提供更高效的方式。
基金Key Laboratory of Hypersonic Aerodynamic Force and Heat Technology of the AVIC Aerodynamics Research Institute,National Natural Science Foundation of China(Grant Nos.31371873,31000665,51176027,and 31300408)Special Program for Applied Research on Super Computation of the NSFC-Guangdong Joint Fund(the second phase)of China and CAST-BISEE(Beijing Institute of Spacecraft Environment Engineering)innovation fund.
文摘This paper systematically reviews the mathematical modeling based on the computational fluid dynamics(CFD)method of equilibrium and nonequilibrium hypersonic flows.First,some physicochemical phenomena in hypersonic flows(e.g.,vibrational energy excitation and chemical reactions)and the flow characteristics at various altitudes(e.g.,thermochemical equilibrium,chemical nonequilibrium,and thermochemical nonequilibrium)are reviewed.Second,the judgment rules of whether the CFD method can be applied to hypersonic flows are summarized for accurate numerical calculations.This study focuses on the related numerical models and calculation processes of the CFD method in a thermochemical equilibrium flow and two nonequilibrium flows.For the thermochemical equilibrium flow,the governing equations,chemical composition calculation methods,and related research on the thermodynamic and transport properties of air are reviewed.For the nonequilibrium flows,the governing equations that include one-,two-,and three-temperature models are reviewed.The one-temperature model is applied to a chemical nonequilibrium flow,whereas the two-and three-temperature models are applied to a thermochemical nonequilibrium flow.The associated calculations and numerical models of the thermodynamic and transport properties,chemical reaction sources,and energy transfers between different energy modes of the three models are presented in detail.Finally,the corresponding numerical models of two special wall boundary conditions commonly used in hypersonic flows(i.e.,slip boundary conditions and catalytic walls)and related research,are reviewed.
