OPTIMIZING THE ANGULAR POSITIONING OF A TURBINE NOZZLE AT THE OUTLET FROM A TURBOMACHINE COMBUSTION CHAMBER

  • US 20090266080A1
  • Filed: 04/21/2009
  • Published: 10/29/2009
  • Est. Priority Date: 04/24/2008
  • Status: Active Grant
First Claim
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1. A turbomachine including an annular combustion chamber comprising inner and outer coaxial walls connected together at their upstream ends by an annular chamber end wall, a nozzle comprising an annular row of stationary vanes situated at the outlet from the chamber, and an annular row of fuel injectors having heads in alignment with orifices in the chamber end wall, the number of nozzle vanes being equal to k times the number of injectors, where k is an integer, wherein the head of each injector lies in a plane that contains the axis of the turbomachine and that is half-way between the leading edges of two consecutive nozzle vanes, and that intersects at least one dilution air inlet orifice passing through the inner wall, and/or through at least one dilution air inlet orifice passing through the outer wall, primary air inlet orifices being formed through the chamber walls upstream from the dilution orifices and on either side of the planes passing via the injector heads.

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