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Cooling structure for recovery-type air-cooled gas turbine combustor

  • US 9,512,781 B2
  • Filed: 08/10/2011
  • Issued: 12/06/2016
  • Est. Priority Date: 09/30/2010
  • Status: Active Grant
First Claim
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1. A cooling structure for a recovery-type air-cooled gas turbine combustor comprising:

  • first cooling passages formed in a downstream wall region of a wall of the gas turbine combustor, the first cooling passages being configured to cool the downstream wall region of the gas turbine combustor by receiving first cooling air bled from a compressed air supply passage and pressurized; and

    second cooling passages formed in an upstream wall region of the wall of the gas turbine combustor, the second cooling passages being configured to cool the upstream wall region of the gas turbine combustor by receiving second cooling air from an inner space of a housing in which the gas turbine is installed, the second cooling air being supplied to the inner space of the housing from the compressed air supply passage,wherein the first cooling air passages are configured so that the first cooling air flows into the first cooling passages and exits into the inner space of the housing,wherein the second cooling air passages are configured so that the second cooling air is introduced from the inner space of the housing into the second cooling passages, andwherein the first cooling air introduced into the first cooling passages for cooling the downstream wall region of the gas turbine combustor is supplied to the gas turbine combustor as combustion air for burning fuel.

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