| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbine nozzle cooling structure capable of effectively cooling a band part without giving the part a double plate structure and thereby, attaining cost reduction and improvement of reliability, and improving engine performance by reducing weight, in a gas turbine in which turbine inlet temperature is high. SOLUTION: A turbine nozzle 10 which is positioned between a combustor 2 and a turbine moving blade 4 and introduces high temperature gas from the combustor 2 to a turbine in a downstream side and a seal plate 8 for sealing a space between a front end part of the turbine nozzle 10 and the combustor 2 are provided. A flange part 2a of the combustor 2 contacted with the seal plate 8 has a plurality of notch grooves 20 communicating the inner and outer faces. Through these notch grooves 20, cooling air flows in and along a band surface of the turbine nozzle 10, performing film cooling of the surface. COPYRIGHT: (C)2005,JPO&NCIPI
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