Hot plate temperature-equalization mixing-free turbine blade cooling device and method

Abstract

The invention provides a hot plate temperature-equalization mixing-free turbine blade cooling device and method. The hot plate temperature-equalization mixing-free turbine blade cooling device comprises a temperature-equalization hot plate and a turbine blade. The temperature-equalization hot plate comprises an evaporation section, a condensation section and an end cover. The evaporation section is located in the turbine blade. A metal wire mesh of the hot plate is arranged on the outer circle of the hot plate. A steam channel is arranged in the temperature-equalization hot plate. The condensation section is closed by the end cover. Except the portion, connected with the turbine blade, of the wall face, the metal wire mesh is distributed on the rest of the wall face on the inner side of the condensation section, and fins are arranged on the outer side of the condensation section. The turbine blade is connected with the end cover. The outer surface of the turbine blade is covered with a thermal barrier coating. The temperature-equalization mixing-free turbine blade cooling device and method have the beneficial effects that the temperature distribution of the turbine blade is uniform; gas film cooling is replaced with the hot plate temperature-equalization mixing-free technology, mixing of cooling air and high-temperature gas is completely avoided, and reliability of engines is improved; and the cooling efficiency is substantially improved, the fuel consumption is lowered, and efficiency of the engines is improved.

Description

technical field [0001] The invention belongs to the field of cooling turbine blades of aero-engines, and relates to a cooling device and method for a turbine blade with a hot plate uniform temperature without mixing. Background technique [0002] Gas turbine engine is the main power plant of aviation aircraft, increasing the temperature before the turbine can greatly increase the thrust of the engine and reduce fuel consumption. At present, the increase rate of the turbine inlet temperature is much faster than the increase rate of the temperature resistance of high-temperature component materials, so efficient cooling technology is the key technology to achieve high thrust-to-weight ratio. [0003] Existing turbine blades often use convective cooling, impingement cooling, air film cooling and composite cooling combined with thermal barrier coatings. Among them, the film cooling technology was proposed in the 1870s. The application of the film cooling technology of the turbi...

AI Technical Summary

Problems solved by technology

At present, the main problems of film cooling are: film cooling will make the temperature of turbine blades uneven, resulting in greater thermal stress; the increasing amount of cooling gas makes the flow and flow field structure in the cascade flow channel more complicated; the injection holes and The presence of seams makes it difficult to maintain the integrity of the blade and is prone to mechanical problems

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