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System and method for controlling fuel flow to a gas turbine engine

  • US 20030192300A1
  • Filed: 05/20/2003
  • Published: 10/16/2003
  • Est. Priority Date: 09/07/2001
  • Status: Active Grant
First Claim
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1. A system for delivering fuel from a fuel source to a gas turbine engine combustor, comprising:

  • a fuel supply line having an inlet coupled to the fuel source and an outlet coupled to the combustor;

    a metering valve positioned in flow-series in the supply line;

    a bypass flow line coupled between an inlet of the metering valve and the fuel supply line inlet for bypassing a portion of the fuel in the supply line back to the inlet;

    a bypass valve positioned in flow-series in the bypass flow line; and

    a controller operable to selectively adjust one of the metering valve and the bypass valve to control fuel flow rate from the fuel source to the combustor.

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