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Turbine convex sealing structure

A technology of turbines and blades, which is applied in the field of aero-engine turbine rotation and static sealing, which can solve the problems of gas intrusion, reduce engine life, fluid reduction, etc., and achieve the effect of reducing wind resistance, small wind resistance, and inhibiting gas intrusion

Active Publication Date: 2020-10-16
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If the sealing flow is small, it will cause the main flow of gas to enter the rotating chamber and reduce the life of the engine. This phenomenon is called gas intrusion; but if excessive sealing cold air is introduced, the fluid that actually does work in the main flow will decrease.

Method used

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  • Turbine convex sealing structure
  • Turbine convex sealing structure
  • Turbine convex sealing structure

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Experimental program
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Effect test

Embodiment Construction

[0025] Such as figure 1 with 2 As shown, the sealing structure of the present invention is a blade-shaped protrusion 3, and the blade-shaped protrusion 3 is uniformly installed on the moving disk 2 of the rotating-stationary disk cavity with a simple radial sealing structure.

[0026] The radius of the moving disk is b, and the clearance ratio is s; the height h of the blade-shaped protrusion 3 is 1 / 3 to 2 / 3 of the rotational and static clearance s, and the chord length d is 1 / 3 to 4 / 3 of the rotational and static clearance s, The bending angle θ of the airfoil is 10°~70°, and the radial position r of the installation is 6 / 10~9 / 10 of the radius d of the moving disk.

[0027] image 3 It is a comparison of the radial sealing efficiency of blade-shaped protrusions installed at different radial positions. It can be seen that with the same number of protrusions, the sealing efficiency increases as the installation radius increases. In addition, previous studies have shown that...

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Abstract

The invention discloses a novel turbine protrusion sealing structure used in a stator cavity of a turbine section of an aero-engine. The structure is a blade-shaped protrusion arranged on the radial position of a movable disc. The protrusion structure can act on fluid in a disc cavity, so that a high-pressure belt is formed in the cavity. Compared with a traditional cylindrical protrusion, the structure can effectively prevent mainstream fuel gas from invading, and the minimum sealing cold air flow needed by the disc cavity is reduced substantially; and the protrusion is arranged on the properradiation position, additional wind resistance caused by the protrusion can be reduced, and the sealing structure can utilize the protrusion to prevent the fuel gas from invading, and has a better practical prospect.

Description

technical field [0001] The invention relates to the technical field of aero-engine turbine rotor-status sealing, in particular to a turbine protruding sealing structure. Background technique [0002] With the rapid development of the aviation industry, the turbine inlet temperature and boost ratio of modern aero-engines continue to increase, which leads to increasingly serious leakage problems in the sealing system of the rotor-stationary disc cavity. Engine designers usually design complex seals in the sealing gap. The tight structure prevents the high-temperature gas from entering the disk cavity through the sealing gap to deteriorate the cooling of the turbine disk (that is, gas intrusion). Under normal circumstances, sealed cold air will be introduced into the rotor static system disc cavity to prevent the occurrence of gas intrusion. If the sealing flow is small, it will cause the mainstream gas to enter the rotating chamber and reduce the life of the engine. This phen...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D11/04F01D5/02
Inventor 罗翔曹楠李雪邬泽宇
Owner BEIHANG UNIV
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