SERPENTINE COOLING OF NOZZLE END WALL

摘要

PROBLEM TO BE SOLVED: To cool a leading edge of a nozzle of a gas turbine.SOLUTION: A gas turbine nozzle section 110 of a gas turbine includes an inner end wall 114 with a leading edge 115. A serpentine passage 116 is configured substantially within the leading edge 115. The serpentine passage 116 has an inlet 118 and an outlet 119. Air is received at the inlet 118 and exhausted at the outlet 119, thereby cooling the leading edge 115.