Flow guiding and blocking sealing structure for high-pressure turbine disc rear bearing cavity

A high-pressure turbine and sealing structure technology, which is used in the lubrication of turbine/propulsion devices, gas turbine devices, and engine lubrication.

Active Publication Date: 2020-11-17
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If this air flow leaks into the bearing cavity, it will bring great risk to the normal operation of the bearing. Therefore, it is necessary to introduce lower temperature gas from the low pressure stage of the compressor to wrap the bearing cavity

Method used

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  • Flow guiding and blocking sealing structure for high-pressure turbine disc rear bearing cavity

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Embodiment Construction

[0019] The technical solutions of the present invention will be further specifically described below through the embodiments and in conjunction with the accompanying drawings. The following description of the embodiments of the present invention with reference to the accompanying drawings is intended to explain the general inventive concept of the present invention, but should not be construed as a limitation of the present invention.

[0020] Such as figure 1 As shown, the flow diversion blocking sealing structure for the bearing cavity behind the high-pressure turbine disk of the present invention includes a high-pressure turbine disk 1, a multi-layer grate rotor sealing ring 2, a sealing seat 4, a load-bearing casing 6, and a low-temperature airflow channel 5. Bearing 10 behind the high-pressure turbine disc. The load-bearing casing 6 is arranged on the downstream side of the high-pressure turbine disk 1, and the radial inner side of the load-bearing casing 6 is provided w...

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Abstract

The invention discloses a flow guiding and blocking sealing structure for a high-pressure turbine disc rear bearing cavity. A sealing seat is used for the sealing position of the high-pressure turbinedisc rear bearing cavity. The sealing seat is provided with a discrete ventilation flow channel, so that introduction and circulation of low-temperature gas are guaranteed; an annular gas guide cavity is formed, so that low-temperature gas is guided, high-temperature gas is blocked, and it is guaranteed that the low-temperature gas enters the high-pressure turbine disc rear bearing cavity; a wear-resistant coating such as graphite and silver-copper is formed, so that when a sealed rotor and a sealed stator are scraped and worn, high temperature is not generated, softening materials such as graphite or silver-copper fall from the scraped and worn rotor and stator, and a bearing cannot be damaged even if the materials enter the bearing cavity; a sunken groove structure is arranged, so thatthe sealing seat and a force bearing casing are fixed on the premise of not occupying space; and discrete bosses are arranged, so that the weight is reduced while axial positioning of a bearing outerring is ensured.

Description

technical field [0001] The invention belongs to the technical field of air systems of ground gas turbines and aero-engines, and relates to a sealing structure, in particular to a sealing structure with diversion and blocking function for the bearing cavity behind the high-pressure turbine disc, through which the high-pressure turbine disc and its rear fulcrum A sealing seat with diversion and blocking effect is set between them to guide the introduction of low-temperature gas and block the high-temperature gas, so as to ensure that the gas entering the turbine rear fulcrum bearing chamber is always low-temperature gas. Background technique [0002] Gas turbines / aeroengines have the characteristics of high temperature and high speed, and their rotor bearings bear high radial and axial loads. The bearings must be lubricated and cooled by spraying lubricating oil to ensure their normal operation. In addition to the heat generated by the bearing under high load and high speed, t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/28F02C7/06
CPCF02C7/06F02C7/28
Inventor 柳光杜强廉曾妍王沛刘军刘红蕊徐庆宗王若楠谢垒肖向涛常胜
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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