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Gas turbine engine having an improved transition duct support

  • US 4,016,718 A
  • Filed: 07/21/1975
  • Issued: 04/12/1977
  • Est. Priority Date: 07/21/1975
  • Status: Expired due to Term
First Claim
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1. In combination in an axial flow gas turbine engine having a combustion section including a plurality of burners disposed circumferentially about the engine axis for receiving and mixing compressed air and fuel in a combustion process to produce propulsive gases which are transmitted from the plurality of burners through a plurality of circumferentially disposed transition ducts between the respective burners and a turbine inlet at the turbine section, the improvement comprising:

  • an outer support ring connected to the plurality of transition ducts and positioned in the engine coaxially of the engine axis, the outer ring circumscribing the transition ducts radially outside of the ducts;

    an inner support ring connected to a plurality of transition ducts and positioned in the engine coaxially of the engine axis, the inner ring extending around the engine axis radially within the circumaxially disposed transition ducts;

    a plurality of struts extending from the outer support ring to the inner support ring, the struts being interdigitated between the transition ducts; and

    one of the support rings being fixedly secured in the engine between the combustion and turbine sections for holding the transition ducts in the engine, and the other of the support rings being suspended in the engine by the struts from said one of the support rings, said other of the support rings thereby being free to expand and contract radially in the engine with the transition ducts.

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