对五种不同燃烧室体积的脉冲发动机在小、中和大油门开度三种供油条件下测定其排放物。
The exhaust gas ingredients of pulse engines, with five different combustion chamber volumes, throttle valve at small, middle and wide opening positions respectively, are tested.
本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。
This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
第三代汽油清净剂在保持发动机喷嘴、进气阀清洁的同时，增加了燃烧室沉积物(CCD)，这将增加部分污染物的排放。
Although third generation gasoline detergent additives keep nozzles and intake valves of engines clean, they simultaneously increase combustion chamber deposits (CCD).
对某锥柱形装药固体火箭发动机(SRM)燃烧室和喷管的内流场进行了三维两相一体化计算。
This paper makes a 3-d two-phase flow united calculation of the inner flow field of chamber and nozzle in certain SRM.
固体火箭发动机的点火是一个十分复杂的物理化学过程，包括三个阶段：点火延迟、火焰传播和燃烧室气体充填。
The ignition of the solid rocket motor (SRM) is a very complex physical and chemistry process, which is composed of three component phases: ignition delay, flame spreading and chamber filling.
固体火箭发动机的点火是一个十分复杂的物理化学过程，包括三个阶段：点火延迟、火焰传播和燃烧室气体充填。
The ignition of the solid rocket motor (SRM) is a very complex physical and chemistry process, which is composed of three component phases: ignition delay, flame spreading and chamber filling.
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