Oscillation Characteristics of Pressure in Combustor with Rotary Valve for Solid Rocket Engine

doi:10.3969/j.issn.1000-1093.2021.01.004

Abstract

Abstract: The pressure-coupled response function test system of solid propellant based on rotary valve is difficult to perform the measurement of phase angle, and the analysis of pressure oscillation and internal flow field. A set of cold-flow experimental system with rotary valve was designed, and a corresponding theoretical calculation model of pressure oscillation and a three-dimensional transient flow field simulation model based on dynamic mesh technology were established. Cold flow experiment and theoretical calculation at different exhaust frequencies were made, and the experimental and calculated results were compared with the simulated results. The results show that the periodic swing motion of a single-rotor exhaust duct can replace the unidirectional rotary motion of the multi-rotor exhaust duct in the simulation calculation, and the error is less than 1%. The errors of the exhaust cycle obtained by simulation calculation and experiment are less than 1.2%; the simulated peak-to-peak pressure is smaller than the experimental one, and the difference value is reduced from 0.019 MPa at 20 Hz to 0.001 MPa at 300 Hz, which verifies the effectiveness of the simulation model.

Key words: solidrocketengine, rotaryvalve, pressureoscillation, exhaustarea, transientflowfield, dynamicmesh

CLC Number:

V435⁺.12

XI Yunzhi, WANG Ningfei, LI Junwei, ZHANG Zhihui. Oscillation Characteristics of Pressure in Combustor with Rotary Valve for Solid Rocket Engine[J]. Acta Armamentarii, 2021, 42(1): 33-44.

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