轴对称矢量喷管内流特性的模型试验

Experimental investigation of static internal performance for an axisymmetric vectoring thrust nozzle

在喷管落压比1.5～17的情况下,对3组不同几何尺寸的轴对称矢量喷管模型试验件内流特性进行了试验.结果表明:气动矢量角与几何矢量角呈正比关系;当落压比小于设计落压比时,气动矢量角会出现大于几何矢量角的峰值,并随落压比的增加而逐渐趋近几何矢量角,推力系数并不随几何矢量角增加而显著下降,且与非矢量状态相当;矢量状态下,推力系数与面积比呈正比关系,而对喉道面积的变化不敏感.

An investigation was conducted with 3 scale models to determine the static internal performance of an axisymmetric vectoring thrust nozzle (AVEN) simulating the nozzle pressure ratio (NPR = 1.7-17) of practical engine. The results indicate that the relationship between the resultant vector angle and the geometric vector angle has direct ratio and while the NPR is less than design pressure ratio, a peak resultant vector angle which is greater than the geometric vector angle occurs and the resultant vector angle is close to a constant slightly larger than the geometric vector angle with the increase of NPR. The thrust coefficient has not decreased distinctly compared with existing no-vectoring convergent-divergent exhaust nozzles with the increase of nozzle geometric vector angle and means that vectoring of the exhaust flow could be achieved with no addition turning losses within nozzle design pressure ratio. The thrust coefficient has direct relationship with the area ratio of nozzle and is independent of the area of nozzle throat.