Bearing cavity sealing system for aero-engine high pressure ratio fan test piece

An aero-engine and supercharging ratio technology, applied in the field of aero-engines, can solve the problems of lengthening the test period, increasing the economic cost or time cost, and achieve the effect of reliable and good operation

Active Publication Date: 2017-09-01
AECC SHENYANG ENGINE RES INST
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  • Application Information

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Problems solved by technology

This will greatly lengthen the test cycle, both econo

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  • Bearing cavity sealing system for aero-engine high pressure ratio fan test piece
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  • Bearing cavity sealing system for aero-engine high pressure ratio fan test piece

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Embodiment Construction

[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0027] The bearing cavity sealing system of the aero-engine high boos...

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Abstract

The invention provides a bearing cavity sealing system for an aero-engine high pressure ratio fan test piece, which comprises an intermediate case, a bearing case and a rotation shaft, wherein the intermediate case and the rotation shaft are in matched mounting through the bearing case; a front sealing ring and a rear sealing ring are connected between the intermediate case and the rotation shaft; one end of each sealing ring is fixedly connected with the intermediate case; the other ends of the two sealing rings are in matched mounting with the rotation shaft; gaps between the rotation shaft and the two sealing rings are sealed through a labyrinth structure; the front sealing ring is used for separating a high pressure disc cavity and a front sealing cavity; the rear sealing ring is used for separating a blind cavity and a rear sealing cavity; the front sealing cavity and the rear sealing cavity are communicated through an air supply passage to form an integrated sealing cavity; an exhaust passage and a throttling device for controlling the size of the opening of the exhaust passage are also arranged on the intermediate case; and a sealing device is arranged on the rotation shaft and between the front sealing ring and the bearing case. Due to the sealing system provided by the invention, the test piece can be ensured not to leak oil in a high pressure ratio condition.

Description

technical field [0001] The invention belongs to the field of aero-engines, in particular to the field of aero-engine high boost ratio fan test pieces, in particular to a bearing cavity sealing system for aero-engine high boost ratio fan test pieces. Background technique [0002] Aeroengine is a complex and precise mechanical product, which has the characteristics of high thrust, high temperature and high reliability. Bearings of aero-engines need to be continuously sprayed with lubricating oil for lubrication and cooling, and the lubricating oil must be confined in a relatively closed cavity to prevent its overflow from affecting the safe operation of the entire engine. This usually requires a well-designed bearing cavity sealing system to achieve. However, the thrust-to-weight ratio of modern aero-engines is getting higher and higher, which puts forward higher requirements on performance parameters such as the supercharging ratio of the fan. However, the increasing pressu...

Claims

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Application Information

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IPC IPC(8): G01M15/02F16J15/16
CPCF16J15/16G01M15/02
Inventor 李宗超王海陈江华麻丽春赵义祯
Owner AECC SHENYANG ENGINE RES INST
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