Combustor hot streak alignment for gas turbine engine

A method for improving vane durability in a turbine engine having a plurality of fuel nozzles, a plurality of first stage vane airfoils downstream of said fuel nozzles, a plurality of rotating blades downstream of said first stage vane airfoils, and a plurality of second stage vane airfoils downstream of said rotating blades, comprising:

• selecting a second stage hot operating temperature condition when said turbine engine generates a second stage hot temperature flow condition at said second stage vane airfoils;
• said second hot temperature flow condition able to generate vane distress;
• mapping a second stage circumferential temperature distribution of said second stage hot temperature flow condition;
• determining a plurality of second stage hot zones and a plurality of second stage cool zones circumferentially at an inlet plane of said second stage vane airfoils;
• and
• aligning said second stage vane airfoils circumferentially in between said second stage hot zones according to said second stage circumferential temperature distribution.

A method for improving vane durability in a turbine engine having a plurality of fuel nozzles, a plurality of first stage vane airfoils downstream of said fuel nozzles, a plurality of rotating blades downstream of said first stage vane airfoils, and a plurality of second stage vane airfoils downstream of said rotating blades, comprising:

• determining a plurality of first stage centerlines defined by two adjacent first stage vane airfoils, said first stage centerlines being separated from each other by a first stage angular distance circumferentially;
• producing a plurality of hot streaks from said fuel nozzles, said hot streaks being characterized by a plurality of hot streak fields having center hot zones;
• directing said hot streaks between said first stage vane airfoils such that said center hot zones are aligned with said first stage centerlines;
• wherein said center hot zones avoid impingement with said first stage vane airfoils.

A method for improving hot section vane durability in a turbine engine having N number of fuel nozzles and N number of first stage vane airfoils, comprising:

• selecting a hot operating temperature condition when said turbine engine is expected to generate a hot temperature flow condition at said first stage vane airfoils;
• said hot operating temperature flow condition able to generate vane distress;
• mapping a circumferential temperature distribution at said hot temperature flow condition to determine a plurality of hot zones and a plurality of cool zones circumferentially at an inlet plane of said first stage vane airfoils;
• aligning said first stage vane airfoils circumferentially in between said hot zones according to said circumferential temperature distribution;
• determining an average angular distance of said first stage vane airfoils by dividing 360 degrees by N;
• and
• locating said first stage vane airfoils at said average angular distance within said cool zones of said circumferential temperature distribution.

A turbine engine, comprising:

• N number of fuel nozzles circumferentially spaced from one another;
• N number of first stage stationary vane airfoils downstream of said fuel nozzles;
• a plurality of first stage rotating blades downstream of said first stage stationary vane airfoils;
• wherein said first stage stationary vane airfoils are selectively spaced circumferentially to situate hot zones of hot streaks from said fuel nozzles between said first stage stationary vane airfoils;
• wherein said N number of fuel nozzles is equal to said N number of said first stage stationary vane airfoils;
• and
• wherein said hot zones avoid impingement with said first stage stationary vane airfoils.