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A sealing structure of aero-engine grate tooth with curved windward sharp-angle tooth

An aero-engine and grate technology, which is applied in the direction of engine components, machines/engines, mechanical equipment, etc., to achieve the effects of enhanced throttling, enhanced mixing, and reduced fluid leakage

Active Publication Date: 2018-11-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the traditional trapezoidal grate, the research on the influence of its geometric parameters is relatively in-depth, and the effect of reducing leakage through the change of geometric dimensions is small

Method used

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  • A sealing structure of aero-engine grate tooth with curved windward sharp-angle tooth
  • A sealing structure of aero-engine grate tooth with curved windward sharp-angle tooth
  • A sealing structure of aero-engine grate tooth with curved windward sharp-angle tooth

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Embodiment Construction

[0031] Embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0032] An aero-engine grate tooth sealing structure adopting curved windward acute-angle teeth, including a rotating shaft 8, a sealing bush 7 is provided on the outer coaxial sleeve of the rotating shaft 8, and three sealing grate teeth are arranged on the rotating shaft 8, respectively It is the first grate tooth 1, the second grate tooth 3 and the third grate tooth 5, a first sealing cavity 2 is formed between the first grate tooth 1 and the second grate tooth 3, the second grate tooth 3 and the third grate tooth A second sealed cavity 4 is formed between the grate teeth 5 , and the space on the leeward side of the third grate tooth 5 is a third sealed cavity 6 . The sealing grate teeth are equidistantly arranged axially on the rotating shaft 8, and the sealing grate teeth are in non-contact sealing cooperation with the sealing bushing 7, wh...

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Abstract

The invention relates to an aircraft engine labyrinth sealing structure provided with curved windward acute-angle labyrinths. The aircraft engine labyrinth sealing structure comprises a rotary shaft. A sealing bush is coaxially arranged outside the rotary shaft in a sleeving mode. A plurality of sealing labyrinths are arranged on the rotary shaft and are in non-contact sealing fit with the sealing bush. The outlines of the sealing labyrinths are in arc shapes, the windward sides of the sealing labyrinths are concave surfaces, and the leeward sides of the sealing labyrinths are convex surfaces. The labyrinth points of the sealing labyrinths are sharp and face the windward sides. By the adoption of the labyrinths of the structure, breakage of big-vortex structures on the labyrinth points of the sealing labyrinths can be enhanced, kinetic energy dissipation of labyrinth cavities of the labyrinths is effectively enhanced, flowing of airflow is reduced, and the leakage flow of fluid is decreased. The aircraft engine labyrinth sealing structure provided with the curved windward acute-angle labyrinths is simple in structure and easy to achieve and has extremely high engineering application value.

Description

technical field [0001] The invention belongs to the technical field of engine sealing structures, in particular to an aeroengine grate tooth sealing structure with curved windward acute-angle 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 ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D11/08F02C7/28
CPCF01D11/08F02C7/28
Inventor 张勃李经警吉洪湖
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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