Patent ID: 8707704

Claim:
A method of assembling a turbine engine, said method comprising: coupling a first chamber in flow communication with a plurality of fuel nozzles and a plurality of air streams, such that the first chamber premixes fuel from the plurality of fuel nozzles with air from the plurality of air streams, wherein the fuel is at least one of natural gas, fuel oil, process gas, and synthetic gas; defining a second chamber configured to combust the premixed fuel and air into a combustion gas stream having a temperature of at least approximately 1100 degrees Celsius, wherein a centerline extends through the second chamber; and coupling the first chamber in flow communication with the second chamber using at least one venturi device coupled between the two chambers, wherein the at least one venturi device includes at least one first wall substantially parallel to the centerline, at least one second wall oriented with a predetermined venturi step angle that is greater than approximately 48 degrees as defined by the at least one second wall and a line extending substantially parallel to the centerline, and at least one third wall oriented at an oblique angle with respect to the centerline and coupled at an apex to said at least one second wall, and wherein the predetermined venturi step angle facilitates the formation of recirculation zones within the second chamber such that a nitrogen oxide concentration in the combustion gas stream is maintained below about 3 ppmvd, and such that the at least one venturi device defines a cooling fluid plenum and a plurality of cooling fluid passages coupled in flow communication via a plurality of cooling fluid openings, and wherein the plenum is radially outward from the apex and configured to receive cooling fluid through an aperture defined radially outward from and adjacent to the plenum.