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Gas turbine combustor

  • US 7,954,325 B2
  • Filed: 12/06/2005
  • Issued: 06/07/2011
  • Est. Priority Date: 12/06/2005
  • Status: Active Grant
First Claim
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1. An annular combustor for a gas turbine engine, comprising:

  • a first circumferentially extending liner having a longitudinal axis;

    a second circumferentially extending liner spaced radially outboard of and coaxially circumscribing the first liner; and

    a bulkhead extending between a forward end of the first liner and a forward end of the second liner and cooperating therewith to define a single annular combustion chamber for combusting fuel in air, the bulkhead having a height, H1, and the combustion chamber having an exit height, H3, and a length, L;

    said annular combustor characterized in that the ratio of the bulkhead height to the combustor exit height, H1/H3, has a value in the range from 1.2 to 1.6.

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