Patents by Inventor Huu P. Trinh

Huu P. Trinh has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Method for determining optimum injector inlet geometry
    Patent number: 8938974
    Abstract: A 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.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: January 27, 2015
    Assignee: The United States of America as represented by the United States National Aeronautics and Space Administration
    Inventors: Huu P. Trinh, W. Neill Myers
  • Injector element which maintains a constant mean spray angle and optimum pressure drop during throttling by varying the geometry of tangential inlets
    Patent number: 8763362
    Abstract: A 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 tangential inlet area for each throttleable stage is calculated. The correlation between the tangential inlet areas and delta pressure values is used to calculate the spring displacement and variable inlet geometry. An injector designed using the method includes a plurality of geometrically calculated tangential inlets in an injection tube; an injection tube cap with a plurality of inlet slots slidably engages the injection tube. A pressure differential across the injector element causes the cap to slide along the injection tube and variably align the inlet slots with the tangential inlets.
    Type: Grant
    Filed: April 20, 2012
    Date of Patent: July 1, 2014
    Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Huu P. Trinh, William Neill Myers