南京航空航天大学学报（英文版）2023，Vol.40Issue(1)：1-12,12.
停滞压力对超声速二维塞式喷嘴设计的影响
Stagnation Pressure Effect on the Supersonic Two-Dimensional Plug Nozzle Design
HAMAIDIA Walid 1YAHIAOUI Toufik 2ZEBBICHE Toufik2
作者信息
- 1. Higher School of Aeronautical Techniques, Dar elbeida, Algiers, Algeria
- 2. Institute of Aeronautics and Space Studies, University of Blida 1, BP 270 Blida 09000, Algeria
- 折叠
摘要
Abstract
The aim of this work is to develop a new calculation program to study the stagnation pressure effect of the combustion chamber on the design of the supersonic two-dimensional plug nozzle giving a uniform and parallel flow at the exit section. The model is based on the use of the real gas(RG) approach. The co-volume and the intermolecular interaction effect are taken into account by the use of the Berthelot state equation. The molecular vibration effect is taken into account in our model to evaluate the behavior of the gas at high temperature. The stagnation pressure and the stagnation temperature are important parameters in our model. At the lip, the temperature and the density are given by the resolution of a two nonlinear algebraic equations, which are formulated by an integration of four complex functions. The resolution is made by a new, robust and a fast algorithm. The other parameters are determined by analytical relations. The flow expansion in the nozzle is of the Prandtl Meyer type. The nozzle contour determination is made by discretizing the expansion zone at the nozzle lip by several points. The Mach number, flow deviation, pressure, temperature and density parameters are determined after inversion of the two-variable Prandtl Meyer function. The integration of the functions presented in the calculation is made by the Gauss Legendre quadrature of order 30. The validation of the results is controlled numerically by the convergence of calculated critical sections ratio to that obtained by the theory, because the flow at the throat and the exit section is unidirectional. In this case, the nozzle contour and the flow parameters, like the mass of the nozzle, the length and the thrust coefficient converge automatically to the exact solution. Our new RG model is considered as a generalization to the two perfect gas (PG) and high temperature(HT) models. The two latter can make the design for low stagnation pressure, and do not give any information on the variation of the stagnation pressure. So if the latter is high, it is necessary to correct the results given by the PG and HT models by considering our developed RG model. The plug nozzle has better performances and design parameters compared to other existing nozzles like the minimum length nozzle(MLN). The mass, the length and the thrust coefficient of our plug nozzle for the PG and HT models are corrected by the use of our developed RG model. The application is made for air.关键词
Berthelot状态方程/Gauss Legendre求积/喷嘴质量/最小长度喷嘴/塞式喷嘴/Prandtl Meyer函数/真实气体/停滞压力/停滞气温Key words
Berthelot state equation/Gauss Legendre quadrature/mass of the nozzle/minimum length nozzle (MLN)/plug nozzle/Prandtl Meyer function/real gas(RG)/stagnation pressure/stagnation temperature分类
航空航天引用本文复制引用
HAMAIDIA Walid,YAHIAOUI Toufik,ZEBBICHE Toufik..停滞压力对超声速二维塞式喷嘴设计的影响[J].南京航空航天大学学报（英文版）,2023,40(1):1-12,12.
