Energy deposition at the interface of explosive welding is analyzed by symmetrical impaction model of uneompressible liquid. Equation of energy in the flow field of explosive welding is deduced and the distribution of...Energy deposition at the interface of explosive welding is analyzed by symmetrical impaction model of uneompressible liquid. Equation of energy in the flow field of explosive welding is deduced and the distribution of temperature in the flow field is solved by finite difference method on the basis that the adiabatic compression is considered. The results show that the temperature rise increases with the increasing of the velocity of approaching flow and impact angle, under appropriate velocity of approaching flow and impact angle the temperature rise near the welding interface will be higher than the melting point of the material and the thin melted layer is localized on the region near welding interface.展开更多
This paper is an eye opening to the new horizon of the design of operational Compressors in our jet engines. That are compressors usually perform an operation called isentropic process and which levitate the pressure ...This paper is an eye opening to the new horizon of the design of operational Compressors in our jet engines. That are compressors usually perform an operation called isentropic process and which levitate the pressure and temperature to the optimum level which require for effective ignition. Basically, our compressors have several sets of blades to perform this function, more precisely saying Rotor and stator blades. Where rotor blade provides air molecule to push at very high velocity to the Stationary blade and when the air Enders to the Stator, the stator races its pressure to move on to the next stage. And we call this set of Stator and rotor as a stage ref [1]. However, in this work, I consider the geometry of the incoming air molecule and how it transforms its physical quantities such as Pressure and temperature ref [2]. For that I tie the concept of Thermodynamic and mechanics on the platform of Tensor analysis ref [3]. That is, I consider the quantities like Pressure, Temperature and rate of flow are their corresponding vector spaces and energy related quintets like heat, work as the scaling elements on the above vector space. And quantities such as entropy enthalpy and specific heat capacity are corresponding physics of it. Considering the advantages, one of the important advantages of this approach is the applicability of results of this work to the formulation of blade less compression Example: Ram and Scram jet engine. Again, the relevant upgrading which is essential for future hypersonic air crafts can achieve from this study and this will be a mile stone for bright air and space travel. To conclude, this approach will be a great transformation on the conventional idea for realization of compression for operational Scram and Ram jet engines ref [4] [5].展开更多
基金Support of this research is provided by National Natural Science Foundation of China (No.10172025).
文摘Energy deposition at the interface of explosive welding is analyzed by symmetrical impaction model of uneompressible liquid. Equation of energy in the flow field of explosive welding is deduced and the distribution of temperature in the flow field is solved by finite difference method on the basis that the adiabatic compression is considered. The results show that the temperature rise increases with the increasing of the velocity of approaching flow and impact angle, under appropriate velocity of approaching flow and impact angle the temperature rise near the welding interface will be higher than the melting point of the material and the thin melted layer is localized on the region near welding interface.
文摘This paper is an eye opening to the new horizon of the design of operational Compressors in our jet engines. That are compressors usually perform an operation called isentropic process and which levitate the pressure and temperature to the optimum level which require for effective ignition. Basically, our compressors have several sets of blades to perform this function, more precisely saying Rotor and stator blades. Where rotor blade provides air molecule to push at very high velocity to the Stationary blade and when the air Enders to the Stator, the stator races its pressure to move on to the next stage. And we call this set of Stator and rotor as a stage ref [1]. However, in this work, I consider the geometry of the incoming air molecule and how it transforms its physical quantities such as Pressure and temperature ref [2]. For that I tie the concept of Thermodynamic and mechanics on the platform of Tensor analysis ref [3]. That is, I consider the quantities like Pressure, Temperature and rate of flow are their corresponding vector spaces and energy related quintets like heat, work as the scaling elements on the above vector space. And quantities such as entropy enthalpy and specific heat capacity are corresponding physics of it. Considering the advantages, one of the important advantages of this approach is the applicability of results of this work to the formulation of blade less compression Example: Ram and Scram jet engine. Again, the relevant upgrading which is essential for future hypersonic air crafts can achieve from this study and this will be a mile stone for bright air and space travel. To conclude, this approach will be a great transformation on the conventional idea for realization of compression for operational Scram and Ram jet engines ref [4] [5].
