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The dry gas seal (DGS) is a non-contacting, gas-lubricated mechanical face seal commonly used in rotating machinery. Traditional analyses of DGSs treat the end face as an independent factor by setting the end-face inlet as boundary conditions, but limited attention is focused on the sealing chamber of the DGS. Using the finite volume method and the shear stress transport (SST) k-ω model, the coupling between the millimeter-scale sealing chamber and the micrometer-scale end face are simulated with regard to the real gas effect of CO2. The three-dimensional distributions of velocity, pressure and temperature in the cross-scale flow field are investigated under different working conditions. Moreover, the boundary parameters of the end-face inlet are modified by response surface methodology with a central composite rotatable design. The results demonstrate that the real gas effect of CO2 leads to an increased total inlet flow. When the pressure reaches 10.3 MPa, the relative difference is 51.90% compared to ideal gas. Minor temperature and pressure changes occur in the sealing chamber when the dry gas seal is in operation. However, the inlet temperature of the end face Tf increases and the inlet pressure of the end face pf decreases. These research results provide a reliable reference for engineering practice.

Experiments and numerical simulations were conducted in order to examine the flow field surrounding a flat-faced body impacting on a flat surface. In the experiments impact velocities ranged up to nearly 5 m/s. Visualisation was with a standard z-format schlieren system using a high-speed camera. The associated flow field exhibited ejected gas jets, shed vortices and weak compression waves in the external flow, as well as in the gap depending on pressure differences between the gap and the external field. A computational fluid dynamic simulation (CFD) was undertaken, enabling detailed evaluation of: the flow in the gap, the flow of the emerging jet near the impacting surface, and the development of the wave system and flow on the upper and lower surfaces of the impactor during its descent. It was found that very high pressures are generated in the gap between the impactor and impacting surface and that the jet emerging from the periphery of the impactor can reach supersonic velocities.

When check valve works in long distance or high lift liquid pipeline system, it is often subjected to water hammer. In this study, the UDF program was used to simulate the closing process of an axial flow check valve at the moment of pump shutdown, and the porous media model was applied to simulate the complete closing of the valve disc. It was found that there was local vacuum at the end of the valve disc at the moment when the valve was completely closed. The water hammer and characteristics of the force acting on the valve disc in the whole closing process were also obtained. In order to reduce the pressure surges on the valve disc and seat, a built-in critical damping was designed and added to the to the valve disc drive system. Since the spring force is directly proportional to the movement displacement of the valve disc, the elastic force and the speed of the valve disc reach the peak value when the valve is fully closed, while the damping force is directly proportional to the speed of the valve disc, therefore, the damping force increases gradually with the speed of the valve disc, which only produces the maximum damping force at the moment of fully closing, so as to reduce the slam shut, but has little effect on the closing time, thus adding damping is more effective than reducing the elastic force of spring. The current study provides a possible approach to protect the valve disc and seat of check valves in liquid supply and drainage systems.

A reliable agent addition control is crucial for the foam technology that is prevalent in many industrial fields. The objective of this paper is to reveal the precise quantitative control mechanism and distinctive performance of cavitation jet. The cavitation evolution suction process is analyzed by the vapor appearance order defined. A 5-6 mm vapor-liquid transition interface is found in the cavitation jet with a remarkable mutation in fluid pressure, density and velocity. The vapor region in the jet device decreases and the maximum vapor volume fraction declines from 96.4% to 0 as the pressure ratio increases. The precise quantitative control is realized by the cavitation jet at the negative pressure less than -87 kPa in the suction port. The absorption amount decreases with the absorbed liquid viscosity increasing and a various level of precise quantitative control is achieved by the orifice plate area. The relation between the absorption amount and plate area is quadratic curve. Furthermore, the dust suppression practical was successfully conducted in a coal bunker to verify the effectiveness of foam technology using cavitation jet. Based on the above contribution, it is believed that the proposed precise quantitative control method has a strong applicability and popularization in industrial control field.

Effect of the volute tongue of the multi-blade centrifugal fan on the performance of the machines is significance. The shape and installation angle of the volute tongue affect the circulating internal flow behavior of the volute as well as the energy loss around the volute tongue. In this study, the profile of the leading edge of the owl wing is applied to the volute tongue of a multi-blade centrifugal fan to improve the aerodynamic performance of the fan. The fan models with different volute tongue installation angles are numerically simulated under different flow conditions. The research results show that the proposed design is able to improve the aerodynamic performance of the fan at different flow rate conditions. In addition, an improved method for quantitatively evaluating the level of impeller-volute tongue interaction based on the unsteady simulation result is proposed and it is verified to be effective. Furthermore, the two parameters for evaluating the internal flow circulation which are influenced by the installation angle of the bionic volute tongue are analyzed, namely the recirculated flow coefficient and the reversed flow coefficient. Combined with the analysis of energy loss around the volute tongue, the mechanism of variation of the aerodynamic performance of the multi-blade centrifugal fan with different volute tongue installation angles is explained.