A composite sealing structure of brush type and grate teeth

A comb-tooth and brush-type technology, which is applied in the field of brush-tooth and comb-tooth composite sealing structures, can solve the problems of difficult replacement, damaged seals, and easy breakage, etc.

Active Publication Date: 2019-07-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the brush seal is easy to break due to the long brush type, resulting in damage or failure of the seal, making replacement difficult and costly

Method used

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  • A composite sealing structure of brush type and grate teeth
  • A composite sealing structure of brush type and grate teeth
  • A composite sealing structure of brush type and grate teeth

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Effect test

Embodiment Construction

[0023] Embodiments of the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0024] A composite sealing structure of brush type and grate teeth according to the present invention comprises a rotating shaft 1, a sealing bush 2 is provided on the outer coaxial sleeve of the rotating shaft 1, and a plurality of axially arranged annular sealing grate teeth are arranged on the rotating shaft 1 3. It is characterized in that: the inner surface of the sealing bush 2 is provided with an annular groove 4 corresponding to the sealing grate 3, the annular groove 4 is a smooth arc groove, and the tooth root of the annular sealing grate 3 is fixed on the rotating shaft 1, a protrusion 31 is formed in the middle of the outer peripheral surface of the tooth tip, the protrusion 31 is a smooth arc-shaped protrusion, and the curvature of the protrusion 31 is greater than the curvature of the annular groove 4, and the protrusion 31 extends...

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PUM

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Abstract

The invention discloses a sealing structure combining the brush type and comb teeth. An annular groove is formed in the position, corresponding to each sealing comb tooth, of the inner surface of a sealing bushing. Each annular groove is a smooth arc-shaped groove. The tooth roots of the annular sealing comb teeth are fixed to a rotating shaft. A protruding portion is formed in the middle of the outer circumferential face of each tooth top. Each protruding portion is a smooth arc-shaped protrusion, and the curvature of each protruding portion is greater than that of the corresponding annular groove. Each protruding portion extends to the corresponding annular groove and is in clearance fit with the corresponding annular groove. The middle of each protruding portion directly faces the groove bottom of the corresponding annular groove. The middle of each protruding portion is provided with a ball bearing. Multiple elastic brush wires are arranged on the tooth top of each annular sealingcomb tooth, wherein the multiple elastic brush wires are arranged in the axial direction. Wire tips of the elastic brush wires abut against the annular grooves. The sealing structure has the beneficial effects that the friction generated between the comb teeth and the bushing can be effectively reduced; the sealing mode that the comb teeth are combined with the brush type is adopted, so that the sealing effect is effectively improved; and meanwhile, the height of each brush wire is reduced, and the service life of each brush wire is prolonged.

Description

technical field [0001] The invention belongs to the technical field of aerospace engine sealing, and in particular relates to a composite sealing structure of a brush type and grate teeth. Background technique [0002] With the development of the aviation industry, the requirements for the maneuverability, reliability and economy of the aircraft are getting higher and higher, so it is urgent to improve the various components of the aero-engine to ensure the high-performance requirements of the engine. Low fuel consumption, high thrust ratio, high reliability and durability are the development trends of modern aviation gas turbine engines, but the temperature and pressure ratio inside the engine are gradually increasing, making the leakage of the internal flow system more and more serious, and the performance of the seal is directly It affects the performance of aero-engines such as fuel consumption rate, flight cost, and thrust-to-weight ratio. In order to reduce leakage lo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D11/16
Inventor 张勃张纳如吉洪湖
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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