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
CN109854307BActive Publication Date: 2020-10-16BEIHANG UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
BEIHANG UNIV
Publication Date
2020-10-16

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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.
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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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