Supersonic Two-Dimensional Minimum Length Nozzle Design at High Temperature. Application for Air

When the stagnation temperature of a perfect gas increases, the specific heat ratio does not remain constant any more, and start to vary with this temperature. The gas remains perfect, its state equation remains always valid, except it will name in more calorically imperfect gas or gas at High Temperature. The goal of this work is to trace the profiles of the supersonic Minimum Length Nozzle with centered expansion when the stagnation temperature is taken into account, lower than the threshold of dissociation of the molecules and to have for each exit Mach number several nozzles shapes by changing the value of the temperature. The method of characteristics is used with a new form of the Prandtl Meyer function at high temperature. The resolution of the obtained equations is done by the second order of fmite differences method by using the predictor corrector algorithm. A study on the error given by the perfect gas model compared to our model is presented. The comparison is made with a calorically perfect gas for goal to give a limit of application of this model. The application is for the air.

Flow Characteristics in Compact Thermal Spray Coating Systems with Minimum Length Nozzle

In this study, numerical analysis is performed to adopt the equivalence ratio on the high velocity oxygen fuel （HVOF） thermal spray coating systems equipped with a minimum length nozzle. The analysis is applied to investigate the axisymmetric, steady-state, turbulent, and chemically combusting flow both within the torch and in a free jet region between the torch and the substrate to be coated. The combustion is modeled using a single-step and eddy-dissipation model which assumes that the reaction rate is limited by the turbulent mixing rate of the fuel and oxidant. As the diameter of the nozzle throat is increased, the location of the Mach shock disc moves backward from the nozzle exit. As the throat diameter and the divergent portion are 6 mm and 8 mm, respectively, the pressure in the HVOF system is the lowest at the chamber and the expanding gas is steadily maintained with both high velocity and high temperature for different equivalence ratios. Thus, relatively minor amendments of the equivalence ratio and the geometry of HVOF can lead to improved control over coating characteristics.

Performances analysis of asymmetric minimum length nozzles

Two-dimensional(2D)and axisymmetric minimum length nozzles(MLNs)with constant and variable specific heat were strictly designed using the method of characteristics(MOCs).MOC is a numerical technique which has great advantages in accuracy and efficiency for solving hyperbolic partial differential equations.According to previous MLN designs,violent vibrations of upper wall discrete points at the inlet were observed for 2D nozzles.Meanwhile,slight compressions could be observed in the flow field of axisymmetric nozzles designed by those methods.We proposed a novel technique in which the inlet grid is intensified to overcome the limitations mentioned above.Inviscid numerical simulations by CFD revealed that the proposed nozzle could meet the requirements for exit Mach number and flow field uniformity.Additionally,asymmetric MLNs could be used to hypersonic vehicles.The preliminary performances of 2D asymmetric nozzle with constant specific heat were investigated.