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Method for Determining Optimum Injector Inlet GeometryA method for determining the optimum inlet geometry of a liquid rocket engine swirl injector includes obtaining a throttleable level phase value, volume flow rate, chamber pressure, liquid propellant density, inlet injector pressure, desired target spray angle and desired target optimum delta pressure value between an inlet and a chamber for a plurality of engine stages. The method calculates the tangential inlet area for each throttleable stage. The method also uses correlation between the tangential inlet areas and delta pressure values to calculate the spring displacement and variable inlet geometry of a liquid rocket engine swirl injector.
Document ID
20150003443
Acquisition Source
Headquarters
Document Type
Other - Patent
Authors
Trinh, Huu P.
Myers, W. Neill
Date Acquired
March 20, 2015
Publication Date
January 27, 2015
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
Patent Application Number: US-Patent-Appl-SN-14/282,890
Patent Number: US-Patent-8,938,974
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-8,938,974
Patent Application
US-Patent-Appl-SN-14/282,890

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