Flow guide and cooling structure applied to double-wheel-disc turbine disk cavity

Abstract

The invention provides a double-wheel-disc turbine disk cavity flow guide and cooling structure with an enhanced disk edge cooling effect. The flow guide and cooling structure is composed of front wheel disc flow guide fins (4), rear wheel disc flow guide fins (5) and cooling air channels (10). The front wheel disc flow guide fins (4) and the rear wheel disc flow guide fins (5) are located on the inner wall surface of a front wheel disc (6) and the inner wall surface of a rear wheel disc (7) located on the two sides inside a double-wheel-disc turbine disk cavity (3) correspondingly, the front wheel disc flow guide fins (4) and the rear wheel disc flow guide fins (5) are inclined flow guide fins, the cooling air channels (10) are located in a disk edge (9), and the cooling air channels (10) are inclined cooling air channels. The front wheel disc flow guide fins (4) and the rear wheel disc flow guide fins (5) play a flow guide role in cooling air, and the cooling air in an Ekman layer is gradually deflected and flows to the cooling air channels (10) in the disk edge and then is guided to a turbine blade internal cooling channel by the cooling air channels (10). The fins designed according to the flowing structural features can guide the cooling air into the blade internal cooling channel under the centrifugal effect, and thus the problem that outlet cooling air is blocked is effectively avoided; and meanwhile, the fins enlarge the heat exchange area in the disk cavity, so that the heat exchange effect is facilitated.

Description

technical field [0001] The invention belongs to the technical field of aero-engine high-pressure turbine disk cooling, and in particular relates to a disk cavity guide fin and a disk edge cold air passage structure which can enhance the cooling effect of a double-spoke turbine disk edge. Background technique [0002] Turbine discs are subjected to centrifugal force loads, thermal stress loads and external loads of the discs during their work, which are typical life-limiting parts. According to statistics, about half of all non-containment accidents of aero-engines are caused by damage to the discs . Based on the current level of technological development, the gas temperature at the turbine inlet of the aero-engine with a thrust-to-weight ratio of 10 used by the fourth-generation fighter jets has reached 1850K-1950K, and the technical index of an aero-engine with a thrust-to-weight ratio of 15 under development is as high as 2100K. -2300K, far exceeding the limit of high-tem...

AI Technical Summary

Problems solved by technology

Due to the high-speed rotation of the turbine disk, the flow direction of the cooling gas is almost tangential to the disk body before entering the disk edge cooling channel. If the disk edge cooling channel still adopts the structure of radial straight holes, two There are two problems: one is that the direction of the cold air is almost perpendicular to the center line of the channel, it is difficult to enter the cold air channel, and a recirculation zone is formed on one side of the channel, which blocks a large part of the channel; From the perspective of the rotating coordinate system, the cold air is incident on the wall of the channel, and the kinetic energy is converted into internal energy, which stagnates the temperature rise, which seriously reduces the quality of the cold air and weakens the cooling effect of the rim area

[0012] The radial straight fins in the patent US3982852B2 and the patent US1999 / 005961287A can solve the problem of blockage of the cold air channel on the plate edge. During the process, as the tangential velocity of the wheel disk increases, the straight fins will do too much work on the cold air, causing the temperature of the cold air to rise rapidly, which is extremely unfavorable for the cooling of the disk edge

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