Patent ID: 8938974
Filing Date: 2015-01-27
Classification: F02K,F05D,F23D,G01B,G01F,G01L,G01N

Abstract:
1. A method for determining the optimum inlet geometry of a liquid rocket engine swirl injector comprised of the steps of: obtaining a first throttleable level phase value (TLPV); obtaining a first measured value for a volume flow rate; obtaining a first measured value for a chamber pressure; obtaining a first measured value for a density of liquid propellant; obtaining a first measured value for an inlet injector pressure; obtaining a first desired target spray angle θ between 60 and 90 degrees; obtaining a first desired target optimum delta pressure value between an inlet and a chamber; calculating a first tangential inlet area; repeating said steps of obtaining a throttleable level phase value, obtaining a measured value for a volume flow rate, obtaining a measured value for a chamber pressure, obtaining a measured value for an inlet injector pressure, obtaining a desired target spray angle θ between 60 and 90 degrees, obtaining a desired target optimum delta pressure value between an inlet and a chamber, and calculating a tangential inlet area; establishing a correlation between said calculated tangential inlet areas and said obtained optimum delta pressure values; calculating a spring constant; determining a spring displacement value for said obtained throttleable level phase values; establishing a correlation between said spring displacement values and said obtained optimum delta pressure values; establishing a relationship between said tangential inlet areas and said spring displacement values to qualitatively determine the shape of a variable inlet slot; wherein the shape of the variable inlet slot has a shape selected from a group of geometric slot shapes consisting of polygon, irregular polygon and oval; wherein each of said geometric slot shapes has a geometric shape predetermined geometric effectiveness coefficient value d wherein d wherein r