A radial rim seal structure with damping holes and guide vanes

Abstract

The invention discloses a radial rim sealing structure with damping holes and flow guide blades. The radial rim sealing structure is characterized in that the radial rim sealing structure is arranged in a gas turbine rotor-stator cavity or a gas turbine rotor-rotor cavity and comprises an outer tooth and a radial inner tooth which are matched; a plurality of damping holes are evenly formed in the upper end face of an inner tooth body of the radial inner tooth in the circumferential direction, and a plurality of flow guide blades are evenly arranged on the radial end face of the inner tooth body of the radial inner tooth in the circumferential direction; furthermore, the damping holes are in a cellular shape and are evenly distributed in a sealing tooth face in the circumferential direction; the flow guide blade are arranged on the end face of the sealing radial inner tooth with equal arcs, and the blades are provided with gradually-shrunk channels. The rim sealing structure can effectively lower the high-temperature gas invading degree and improve the sealing performance of rim sealing, and therefore the overheat failure of a turbine disc is avoided, the use amount of low-temperature cooling air flow introduced from the position of an air compressor can also be reduced, and the efficiency of a unit can be improved.

Description

[0001] Technical field: [0002] The invention relates to a rim sealing structure, in particular to a rim sealing structure used in the gap between the rotary-static disc cavity or the rotary-rotary disc cavity of gas turbines and high-temperature steam turbines, and has the function of blocking the intrusion of high-temperature mainstream gas. [0003] Background technique: [0004] In impeller machinery such as aero-engines, heavy-duty gas turbines, supercritical and ultra-supercritical steam turbines, after the high-temperature gas in the main channel flows through the stator blade nozzle, due to the joint action of the dynamic and static wake and the potential flow field of the rotor blade, it will - The middle area of ​​the static part alternately forms high-pressure flow areas and low-pressure flow areas along the circumferential direction. In the high-pressure flow area, because the pressure of the main flow channel is higher than the internal pressure of the turbine dis...

AI Technical Summary

Problems solved by technology

Although the radial sealing structure can reduce the degree of gas intrusion to a certain extent, the effect is limited. Therefore, the new radial rim seal that can more effectively reduce the degree of gas intrusion can improve the heat transfer stability of the turbine disk and improve the overall Machine economy has important engineering application value

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