Double-layer wick imperforated high-efficiency cooling turbine guide vane device

Abstract

A double-layer liquid-absorbing core without openings for efficient cooling of turbine guide vanes, including a partition outer ring, turbine blades, stationary blade holding rings, ribs, and a double-layer liquid-absorbing core heat plate; the turbine blades are arranged on the partition outer ring and the static Between the blade holding rings, the upper surface of the stationary blade holding ring communicates with the interior of the turbine blade, and the lower surface communicates with the ribs. The turbine blade includes a thermal barrier coating and a metal blade wall, the thermal barrier coating is coated on the outer surface of the metal blade wall, and the double-layer liquid-absorbing core is attached to the inner surface of the metal blade wall. The turbine blade is the evaporating section, and the stationary blade holding ring is the condensing section. The invention keeps the temperature distribution of the cooling blade uniform, reduces the thermal stress caused by the temperature difference, and prolongs the service life of the blade; avoids the mixing of cooling air and high-temperature gas, and the aerodynamic loss caused by the mixing, and improves the reliability of the engine; double-layer suction The liquid core structure increases the carrying limit and capillary limit of the hot plate structure; the blade has no openings, which ensures the integrity of the blade and improves the mechanical strength of the blade; improves cooling efficiency, reduces fuel consumption, and improves engine efficiency.

Description

technical field [0001] The invention belongs to the field of cooling turbine blades of aero-engines, and relates to a high-efficiency cooling turbine guide vane device without openings of a double-layer liquid-absorbing core. 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 front inlet temperature is about 20K / year, and the temperature resistance of high-temperature component materials is about 8K / year. Therefore, efficient cooling technology is the key to achieving a 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 1970s. The application of the film cooling technolo...

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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