Gas turbine guide flow disk

Abstract

The invention provides a gas turbine guide flow disk. Through arranging a flexible thin plate and adjusting a sealing structure, the pressing force of a sealing structure to a turbine disk is realized, so that the sealing structure can automatically bond to the turbine disk under the function of centrifugal force, so as to further guarantee the sealing reliability; the guide flow disk is positioned without the use of a 'snap ring'; besides, the gas turbine guide flow disk can eliminate the technical shortcomings of increased burden of turbine disk, raised stress level, and reduced rotate speed brought by the 'snap ring' in the prior art. The guide flow disk has good axial symmetry, good technique, and high reliability; for the thickness of a part having big radius of the guide flow disk and consisting of a fork, a middle section and a middle wheel plate is relatively thin, the centrifugal load is reduced; therefore, the stress level is decreased, the rupture rotate speed is improved, the fatigue service life is prolonged, weight is lightened, and the burden of the turbine disk is reduced, and demand of a high-performance aero-engine can be satisfied.

Description

technical field [0001] The invention relates to the technical field of turbines, and more specifically, to a gas turbine deflector. Background technique [0002] The main function of the deflector plate is to form a cooling gas passage together with the (gas or high pressure) turbine disk, and to ensure the sealing of the passage during the working process, so as to "guide" the cold air to the mortise (connection) joints and blades. In some cases, it also prevents the turbine blade (tenon) from sliding along the tenon groove. [0003] figure 1 Shown is a gas turbine deflector of prior art design. The guide disc 2 and the turbine disc 1 are connected to each other at the bolt connection 9 to realize the positioning of the guide disc 2 . In order to ensure that the sealing part 4 is always in close contact during the working process and prevent it from opening, a snap ring 3 is provided on the deflector plate 2 . Under the action of centrifugal force, the snap ring 3 will ...

AI Technical Summary

Problems solved by technology

[0004] The snap ring structure used in the prior art interacts with the turbine disk, increasing the burden on the turbine disk; the existence of the snap ring moves the center of gravity of the structure to the right, which easily leads to the displacement of the seal; the existence of the snap ring increases its own Weight, resulting in increased stress level, reduced rupture speed, and shortened fatigue life; the snap ring is provided with ventilation grooves along the axial direction, which increases the processing procedure and processing difficulty, thereby increasing the scrap rate and processing cost; the axial ventilation of the snap ring slots, prone to defects and reduced reliability

In summary, the existing technology cannot meet the design needs of high-performance aeroengine deflectors

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