Method of cooling gas turbine blades

Abstract

The invention relates to a method for cooling a combustion gas turbine blade. According to the method, molten salts are used as cooling working media, the bran-new blade internal passage cooling is designed, and the air film cooling is not utilized. The front edge of the blade is cooled by utilizing jet impingement holes and a turbulence reinforcing device arranged in a cooling passage, and other positions of the blade are cooled by a blade internal passage. After entering a blade cavity, the molten salts flow through the blade cavity along a cooling passage, the pressure surface and the suction surface of the blade and the tail edge of the blade are cooled in one step, partial molten salts form jet flows at the front edge of the blade for realizing the impingement cooling, then, the molten salts are discharged from a cooling passage outlet formed at the root part of the blade, a sealed U-shaped cooling loop is formed, and the cooling of the whole blade is completed. The cooling method has the advantages the temperature of the turbine blade can be maintained to be within 600 DEG C, in addition, compressed air is not consumed, the internal structure of the blade is greatly simplified, the processing process and the material requirements of the blade are reduced, the intensity of the blade is enhanced, the service life of the blade is prolonged, the manufacturing cost of a combustion gas turbine is obviously reduced, and the shaft work power of the combustion gas turbine is improved.

Description

technical field

[0001] The invention relates to a cooling medium, a cooling method and a cooling structure of a gas turbine blade. Background technique

[0002] Gas turbines are the core components in the field of energy equipment, and play an important role in military and industrial fields such as aviation, ships, and land. With the continuous increase of the inlet gas temperature of advanced gas turbine turbines, more stringent challenges have been imposed on the manufacturing process and cooling requirements of high-temperature turbine components. At present, the inlet gas temperature of advanced gas turbine turbines has exceeded 1500 °C, and is further moving towards 1900 °C and even Higher temperature, while the current working temperature of advanced nickel-based alloys is below 1100°C, in order to ensure the life of high-temperature turbine blades, it is necessary to use strong cooling methods to keep the overall temperature field and stress distribution of the blade...

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