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TWO-SHAFT GAS TURBINE CONTROL SYSTEM

  • US 3,638,422 A
  • Filed: 06/26/1970
  • Issued: 02/01/1972
  • Est. Priority Date: 06/26/1970
  • Status: Expired due to Term
First Claim
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1. In a control system for a gas turbine power plant having a compressor high-pressure turbine unit and a load turbine unit, the compressor high-pressure turbine unit discharging motive fluid through an adjustable nozzle to the load turbine unit, said units being mechanically independent and also having servo means to control fuel flow to the combustion chambers in accordance with a fuel control signal, the combination comprising:

  • a plurality of closed loop control means, each arranged to supply a respective fuel control signal for controlling a respective operating condition, at least one of said control means being continuously responsive to a temperature condition of the gas turbine and comparing said condition to a temperature setting, gating means connected to be responsive to said loop control means and enabling only one of said fuel control signals representing the least fuel to control said fuel flow servo means, nozzle control means responsive to shaft speed and temperature signals such that the adjustable nozzle is normally positioned to hold the exhaust temperature substantially constant over a portion of the load range, and biasing means connected to augment the temperature setting of the closed loop control means responsive to temperature so that when additional load is called for, fuel can be added quickly allowing temperature to increase to the new temperature limit.

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