Abstract
Recently, a large side thrust was observed during start-up and shutdown sequences in the nozzle of the LE-7A rocket engine. The objective of the present paper is to clarify the mechanism producing the large side thrust during start-up sequence. In the present paper, unsteady numerical simulation is performed. The flow field is assumed to be two dimensional planer flow as the first step of the study. This is because full three-dimensional simulation needs huge computational time, and axial symmetry field never show the asymmetry flow. The results show that the movement of separation point is discontinuous at the film cooling injection step on the nozzle wall. In a certain range of Nozzle Pressure Ratio (NPR), the separation point is trapped at the step. When the NPR reached a certain value, the separation point moves to nozzle exit rapidly. This phenomenon occurs non-simultaneously on both walls and cause the large side load.
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