本文用环形不稳定性计算模型计算、分析了FY - 20液体火箭发动机的切向高频燃烧不稳定性。
This paper presents computation and analysis of tangential mode of high frequency combustion instability in FY-20 liquid propellant rocket engine by means of the annular instability model.
为某微型涡喷发动机设计了一个蒸发管环形燃烧室。
An annular combustor with evaporation tubes was designed for certain micro-turbojet engine.
涡轮发动机（10）还包括沿着通过中空环形壁的第一方向的第一流径。
The turbine engine (10) also includes first flow path (72) in a first direction through the hollow annular wall.
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