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Fuel flow information for gas turbine engines is measured…

  • A
    in the line between the booster pump and the engine.
  • B
    in the inlet of the high-pressure fuel pump.
  • C
    in the line between the fuel control unit and the engine burners.
  • D
    at the outlet of the high pressure fuel pump.
Refer to figure.
The fuel system is designed to supply fuel flow into the combustion chamber, servo fuel for some fuel-actuated systems, and fuel for engine oil cooling. The fuel is ducted from the fuel tanks initially by a LP fuel pump to the fuel-oil heat exchangers. It is then filtered and pressurized under high pressure (by a HP pump) and delivered a number of fuel nozzles that will atomize the fuel into the combustion chamber. Between the fuel control unit and the fuel nozzles, a fuel flow transmitter measures the instant fuel flow and send this information to the cockpit instruments as a reference for the pilots.

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