Flow Analysis and Orifice Plate Design for Oxygen Chamber of a Liquid Propellant Rocket Engine

The oxygenchamber flow in thrust chamber of a liquid propellant rocket engine is numerically simulated using NavierStokes solver.The total/static pressure distributions and pressure distortion on the throttle plate are analyzed.A method to improve the flowuniforming orificeplate design is developed based on the calculated pressure distortion,and the new orifice plate is designed via several analysisdesign cycles.Finally numerical and experimental validations are performed for the newly designed case,the analysis and validation show that the pressure distortion on the throttle plate is reduced 30.4% in new design.This improves the uniformity evidently,thus the combustion efficiency can be significantly improved.