incrementing said ring flame temperature at said first burner dome in said gas turbine engine by a predetermined amount to achieve an incremented ring flame temperature;
recording into memory a plurality of parameters from said plurality of sensors coupled to said gas turbine engine operating at said incremented ring flame temperature; and
repeating said incrementing if said plurality of parameters are within predetermined acoustics and blowout boundaries.
23. The method of claim 1, wherein said adjusting a ring flame temperature at said first burner dome in said gas turbine engine to determine a maximum ring flame temperature operational boundary includes:
incrementing said ring flame temperature at said first burner dome in said gas turbine engine by a predetermined amount to achieve an incremented ring flame temperature;
recording into memory a plurality of parameters from said plurality of sensors coupled to said gas turbine engine operating at said incremented ring flame temperature; and
repeating said incrementing if said plurality of parameters are within predetermined acoustics and blowout boundaries and said ring flame temperature at said first burner dome is less than a predetermined maximum ring flame temperature.