1·Results show that pintle could change the nozzle throat area and thus the motor pressure and thrust, which provided the capability for thrust control.
结果显示喉栓能够有效改变发动机燃烧室压力和推力，满足发动机推力控制要求。
2·The scheme to control launch power is introduced for changeable depth launch of missile. It is to change the aeration area at the nozzle throat of high pressure chamber in launcher.
该文针对导弹变深度发射提出通过改变发射装置高压室喷管喉部的通气面积来实现发射动力可调。
3·The changes of the pressure in puffer chamber and nozzle throat under different base pressure are compared, which shows that base pressure has an influence on the pressure in gas chamber.
分析了压力变化与开断时间的关系，比较了不同基压下压气缸与喷口喉部气体压力特性的变化，说明了基压对断路器灭弧室内压力的影响。
4·The preliminary test result shows that the combustor can be reliably ignited under the condition of large nozzle throat, the combustion process is stable and combustion efficiency is high.
初步研究结果表明，该方案在大喷管条件下点火起动可靠，燃烧过程比较稳定，燃烧效率高。
5·The calculations indicate that the iterating calculation is converged and the calculated throat area of nozzle accords with practicality.
计算结果表明迭代计算是收敛的，算出的喷嘴喉口面积与实际相符。
6·The performance of steamjet ejector was investigated by changing the secondary to the primary throat area ratio and the position of the steam nozzle.
计算并分析了第二喉管与工作蒸汽喷嘴喉管面积比、喷嘴出口截面与混合段入口截面间的距离等几何参数对喷射器操作性能的影响。
7·The motor case is a steel cylinder closed tight at one end. the other end is the open throat and nozzle.
发动机壳体为一个其一端为密封的钢铸圆柱缸体，另一端则为敞口的喉道及喷管。
8·Experiments research were carried out for the throat of nozzle.
本文针对这种情况开展了喷管喉衬的烧蚀试验研究。
9·The local ablation of thermal insulation barrier in nozzle convergence region and of throat insert is analysed.
分析了喷管收敛段绝热层及喉衬的局部烧蚀问题；
10·The results show that throat diameter of the inner nozzle is the most important design parameter influencing structure size of the annular clustered plug nozzle.
结果表明，内喷管喉径是影响环簇式塞式喷管尺寸大小的最主要设计参数；