A turbine rotor device with a cooling and compacting structure

Abstract

The invention relates to a turbine rotor device with a cooling compression structure. The device comprises a blade and a wheel disc which are cooperatively connected with each other through a fir-shaped tenon and a mortise, and further comprises the cooling compression device installed in the gap between the end face of the tenon and the bottom of the mortise in an in interference fit mode. The cooling compression device is internally provided with a main cold air channel with the cross sectional area gradually changed, and multiple secondary cold air channels which communicate with the main cold air channel and are symmetrically formed in the two sides, so that the space of the cold air channels and the effective convection area are increased, the temperature of the connecting parts of awheel rim part, the tenon of the blade and the mortise of the wheel disc is reduced, the thermal stress of the tenon of the blade is reduced, and the creep life of the tenon of the blade, the mortisestructure of the wheel disc and the rim of the wheel disc is prolonged.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a turbine rotor device with a cooling compression structure. Background technique [0002] Aeroengine turbine rotors usually use fir-tree tenon and tongue-and-groove connection structures to realize the assembly of turbine disks and blades. This structure is an important part of the aeroengine structure, and the rationality of its structural design is directly related to the strength, life and reliability of the rotor components. properties, and greatly affect the thrust-to-mass ratio of the engine. At present, the aero-engine turbine rotor adopts a fir tree-shaped tenon and tenon-groove connection structure. It reaches or even exceeds 900K, and produces high thermal stress. At the same time, the fretting friction between the tenon of the blade and the tenon and groove of the wheel will greatly reduce the service life of the turbine rotor. With the continuous improvement of...

AI Technical Summary

Problems solved by technology

[0002] Aeroengine turbine rotors usually use fir-tree tenon and tongue-and-groove connection structures to realize the assembly of turbine disks and blades. This structure is an important part of the aeroengine structure, and the rationality of its structural design is directly related to the strength, life and reliability of the rotor components. properties, and greatly affect the thrust-to-mass ratio of the engine. At present, the aero-engine turbine rotor adopts a fir tree-shaped tenon and tenon-groove connection structure. It can reach or even exceed 900K, and generate high thermal stress. At the same time, the fretting friction between the tenon of the blade and the tenon and groove of the wheel will greatly reduce the service life of the turbine rotor

With the continuous improvement of the performance requirements of aero-engines, the working environment of turbine components is becoming more and more harsh. The shortcomings of the traditional fir-tree-shaped tenon-tenon connection structure are more and more obvious, which can no longer meet the high-quality requirements.

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