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Operation and Turndown of a Segmented Annular Combustion System

  • US 20170276359A1
  • Filed: 03/21/2017
  • Published: 09/28/2017
  • Est. Priority Date: 03/25/2016
  • Status: Active Grant
First Claim
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1. A method for operating a segmented annular combustion system, comprising:

  • injecting a first combustible mixture into a primary combustion zone defined between a pair of circumferentially adjacent integrated combustor nozzles of the segmented annular combustion system via a fuel nozzle;

    burning the first combustible mixture in the primary combustion zone to produce a flow of combustion gases;

    flowing compressed air into a first premixing channel defined within a first integrated combustor nozzle of the pair of circumferentially adjacent integrated combustor nozzles;

    injecting fuel into the first premixing channel such that the fuel mixes with the compressed air to provide a second combustible mixture;

    injecting the second combustible mixture from the first premixing channel into a secondary combustion zone downstream from the primary combustion zone, the second combustible mixture burning in the secondary combustion zone and combining with the flow of combustion gases from the primary combustion zone; and

    accelerating the flow of combustion gases toward a plurality of turbine blades, via a turbine nozzle portion of each integrated combustor nozzle.

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