混合排氣二元收斂噴管氣動與紅外隱身綜合設(shè)計方法研究.pdf

1、南京航空航天大學(xué)博士學(xué)位論文混合排氣二元收斂噴管氣動與紅外隱身綜合設(shè)計方法研究姓名：李娜申請學(xué)位級別：博士專業(yè)：工程熱物理指導(dǎo)教師：吉洪湖2011-03混合排氣二元收斂噴管氣動與紅外綜合設(shè)計方法研究 II Abstract The objective of this thesis is to develop the design method of two-dimensional convergent nozzle of mixed f

2、low turbofan engine to meet aerodynamic and infrared stealth requirements. Configuration design method for two-dimensional convergent nozzle is studied. The effect of geometric parameters on internal performance and infr

3、ared (IR) signatures of two-dimensional convergent nozzle is calculated and compared. Matching method for core and bypass mass flux is researched. Integration design method for internal performance and infrared stealth o

4、f mixed flow two-dimensional convergent nozzle is explored and verified by numerical simulation and experiments. The main results are as follows: (1) Configuration design method for two-dimensional convergent nozzle base

5、d on super-ellipse cross-section or a rectangle cross-section with filleted corner is developed. Controling parameters for these two kinds of cross-section are analysed. Variation functions of the cross-section controlin

6、g parameters are constructed based on polynomial functions. Restricting relationship between cross- section controling parameters and the variation functions is analysed and pointed out. The cross section controling para

7、meters and the variation functions choosing criterion for high performance two-dimensional convergent nozzle are concluded. (2) The effect of geometric parameters on internal performance and IR signatures of two-dimensio

8、nal convergent nozzle is obtained. The configuration of nozzle has some effect on internal performance, but little on the IR signatures. Aspect ratio of nozzle exit, nozzle length, and throate area have masurable effect

9、on internal performance. Nozzle inlet section position has little effect on internal performance. The effect of aspect ration on IR signatures is of the most significance, but nozzle length, throate area, and nozzle inle

10、t section position have less effect on the IR. (3) Matching method for core and bypass mass flux base on 3-D viscous numerical simulation is proposed. Non-linear dimensionless mass flux matching equations for core and by

11、pass channel with 2D nozzle are formulated. Solving procedure of the nolinear equations is presented. Numerical simulation and matching results for some nozzle cases indicate that the method for solving the non-linear ma

12、ss flux equations is effective. (4) Integration design procedures for internal performance and IR stealth of two-dimensional mixed flow convergent nozzle are proposed. Based on the requirements for the nozzle, a nozzle s