Gas turbine blade cooling method

Abstract

Abstract PURPOSE:To cool a gas turbine blade efficiently, by arranging such that a compressed air is cooled through a temperature reducing apparatus and then supplied to one of end walls provided at inner and outer diameters of stationary blades, wherefrom it is further introduced into a turbine rotor through a cooling passageway in a moving blade. CONSTITUTION:In a gas turbine wherein a high pressure air from a compressor 1 has its temperature elevated through a combustor 2 under the heat of burning fuel and then is injected against stationary blades 3, 5 and moving blades 4, 6 of the turbine to rotate moving blades 4, 6 together with a wheel 10 and a shaft 9, the flow of cooling air B branching away from the final stage of compressor 1 has its temperature reduced through a thermal sensible apparatus 13 and then is introduced a cooling air inlet provided at one end of end wall 12a of first-stage stationary blade 3. The cooling air is further guided along the cooling passageway of stationary blade 3 to cool the surface of blade and then exhausted through a cooling air outlet provided at other end of the end wall 12b. The cooling air is then supplied to a next stage moving blade 4 or a subsequent moving blade 6 through a turbine rotor.

Inventors

• 👤 Shigeyoshi Kobayashi
• 👤 成嘉 小林
• 👤 Takashi Ikeguchi
• 👤 池口　隆
• 👤 Masami Noda
• 👤 雅美 野田
• 👤 Yasuhiro Kato
• 👤 泰弘 加藤

Bibliographic Details