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Gas turbine engine combustion chambers

  • US 4,373,327 A
  • Filed: 06/27/1980
  • Issued: 02/15/1983
  • Est. Priority Date: 07/04/1979
  • Status: Expired due to Term
First Claim
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1. A gas turbine engine combustion system comprising:

  • an annular housing defined by inner and outer annular walls;

    a plurality of combustion chambers equi-spaced apart and circumferentially arranged within said annular housing, each of said combustion chambers having an upstream and a downstream end;

    a diffusion passage upstream of the upstream ends of said combustion chambers, said diffusion passage including inner and outer annular walls connected respectively to said inner and outer annular walls of said annular housing, said inner and outer walls of said diffusion passage converging in an upstream direction and arranged to receive a flow of compressed air; and

    a plurality of aerodynamic struts extending between said inner and outer walls of said diffusion passage, each of said struts being adjacent to and upstream of and in alignment with a respective one of said combustion chambers, each of said struts being wedge-shaped in plan form and having an upstream apex, a downstream base spaced from the upstream apex of the respective one of said combustion chambers and sidewalls extending the full height of said diffusion passage, each of said struts having a circumferential width and radial height increasing from the apex thereof in a downstream direction to the base thereof whereby said diffusion passage increases in radial height and decreases in circumferential width in a downstream direction so as to decrease diffuser area ratio.

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