Disc center air inlet structure of double-radial-plate turbine disc with centrifugal pressurization effect and sealing effect

Abstract

The invention discloses a disc center air inlet structure of a double-radial-plate turbine disc with a centrifugal pressurization effect and a sealing effect. The disc center air inlet structure is composed of an air inlet channel (1), centrifugal blades (4) and a rotary lip-shaped sealing structure (3). The air inlet channel (1) is located in a cavity in the rotary lip-shaped sealing structure (3). The centrifugal blades (4) are located in the air inlet channel (1) and used for carrying out centrifugal pressurization and temperature rising on cooling gas. The rotary lip-shaped sealing structure (3) is located at the disc center of the double-radial-plate turbine disc (9) and used for axially sealing the cooling gas. According to the disc center air inlet structure of the double-radial-plate turbine disc with the centrifugal pressurization effect and the sealing effect, on the premise of reducing the mass of the turbine disc, the cooling gas can be fully utilized for achieving the efficient disc cavity flowing heat exchange effect, turbine disc active heat stress control and cooling gas sealing. According to the structure, the utilization level on the cooling gas can be effectively improved, the structural design and machining are simple, and the structure can be easily achieved in actual machine types.

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 double-spoke turbine disk center air intake structure with centrifugal supercharging and sealing effects. Background technique [0002] With the continuous development of engine technology, the thrust-to-weight ratio continues to increase. Today, the temperature of the disk edge of the high-pressure turbine disk has reached 700°C, and the temperature of the disk center far away from the high-temperature gas is usually around 400°C, and the working speed is as high as 16000r / min, which leads to the increasingly harsh working environment of the high-pressure turbine disk. The traditional single-spoke turbine disk has been difficult to meet the design requirements of advanced high thrust-to-weight ratio engines, which seriously limits the further development of aero-engines. [0003] The double-spoke turbine disk is a new turbine...

AI Technical Summary

Problems solved by technology

The cooling air flow comes from the high-pressure compressor axial air intake, and the radial air intake method of the disk center needs to deflect the cold air, which will inevitably lead to the loss of cold air flow and pressure, and the loss of cold air flow will reduce the heat transfer effect of the turbine disk. Increasing the amount of bleed air will reduce the efficiency of the engine, and the loss of cold air pressure will reduce the heat exchange effect of the disc and blades. In the case of a serious shortage of cold air pressure, the mainstream gas may be sucked back and burn the blades and discs

In addition, the edge of the turbine disk is close to the gas and the temperature is high. The radial air intake from the center of the disk flows in from the center of the disk with a lower temperature and then passes through the disk cavity to cool the disk and the disk edge. The cooling effect of the disc edge will likely cause a large radial temperature difference of the disc

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