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Aero engine centrifugal ventilator

An aero-engine and ventilator technology, which is applied to engine components, engine lubrication, separation methods, etc., can solve problems such as large oil consumption, and achieve the effects of reasonable pressure drop, high separation efficiency and good manufacturability

Active Publication Date: 2018-05-29
CHINA AVIATION POWER MACHINE INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the problem of large lubricating oil consumption under the condition of relatively large ventilation volume of small and medium-sized aero-engines, the purpose of the present invention is to provide a ventilation device for lubricating oil systems installed in the accessory transmission case of aero-engines, which solves the problem of the current small and medium-sized aero-engines. The problem of large oil consumption under the condition of large ventilation volume

Method used

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  • Aero engine centrifugal ventilator
  • Aero engine centrifugal ventilator

Examples

Experimental program
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Effect test

Embodiment 1

[0024] See figure 1 with figure 2 An aero engine centrifugal ventilator is arranged in the aero engine accessory transmission casing, and is integrated with the gear 1 in the accessory transmission casing on the same gear transmission shaft 2; both ends of the gear transmission shaft 2 are respectively provided with gears for supporting gears The rolling bearing one 3 and the rolling bearing two 13 of the transmission shaft 2; the gear transmission shaft 2 is a hollow structure, and the center of the gear transmission shaft 2 includes three coaxial holes: the center straight hole 6, the center cone hole 14 and the transmission shaft hole 15, the center cone The hole 14 is arranged between the central straight hole 6 and the drive shaft hole 15. The central straight hole 6 communicates with the small end of the central taper hole 14; the central straight hole 6 communicates with the chamber 5 where the outlet of the gear drive shaft communicates with the atmosphere, and the cham...

Embodiment 2

[0029] The structure of the centrifugal ventilator of the aeroengine in this embodiment is basically the same as that of the embodiment 1. The difference lies in the following: the ratio of the length of the central taper hole 14 at the center of the gear drive shaft 2 to the length of the central straight hole 6 is 1:1.1, The oblique hole 11 and the oblique hole two 17 intersect and communicate with the cone surface of the central cone hole 14 at angles b and c, respectively, b is 30° and c is 50°; the angle formed by the cone surface of the central cone hole 14 and the axis is a , A is 15°; the number of oblique holes 11 is 7, and the aperture is 4 mm, the number of oblique holes 17 is 7, and the aperture is 4 mm.

Embodiment 3

[0031] The structure of the aeroengine centrifugal ventilator in this embodiment is basically the same as that of embodiment 1, but the difference lies in: the ratio of the length of the central taper hole 14 at the center of the gear drive shaft 2 to the length of the central straight hole 6 is 1:1.2. One 11 and two oblique holes 17 intersect and communicate with the cone surface of the central cone hole 14 at angles b and c, respectively, b is 50° and c is 75°; the angle formed by the cone surface of the central cone hole 14 and the axis is a, a The angle is 10°; the number of oblique holes 11 is 9 and the hole diameter is 2 mm, the number of oblique holes 17 is 9, and the hole diameter is 2 mm.

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Abstract

The invention relates to the design of an aviation gas turbine engine lubricating oil system, discloses an aero engine centrifugal ventilator, and solves the problem of large consumption of lubricating oil of medium and small sized aero engines under the condition of larger ventilation quantity. According to the aero engine centrifugal ventilator, the centrifugal ventilator is arranged in an accessory drive casing of the aero engine and is integrated with gears in the accessory drive casing on the same gear transmission shaft; the centrifugal ventilator can be suitable for the medium and smallsized aero-engines with larger ventilation quantity to separate lubricating oil from the oil gas discharged from a bearing chamber, the lubricating oil consumption of the engine is reduced, environmental pollution is reduced, the pressure drop is reasonable, and the separation efficiency is high; and at the same time, the structure is simple, the technology capability is good, and the cost is low.

Description

Technical field [0001] The invention relates to the design of an aviation gas turbine engine lubricating oil system, in particular to a centrifugal ventilator for an aviation engine. Background technique [0002] The main shaft bearing cavity of an aero engine is usually sealed with a certain pressure of air. During the working process of the engine, the sealed air will enter the bearing cavity of the lubricating oil system through the sealing device. In the bearing cavity, the air and lubricating oil are mixed to form oil and gas. If the oil and gas are directly discharged from the bearing cavity, it will cause a large amount of oil consumption and certain Environmental pollution. For this reason, ventilators are installed on the ventilation path between the bearing cavity and the outside to separate the lubricating oil in the air to reduce lubricating oil consumption and environmental pollution. When the oil and gas flow along the channel in the ventilator, there will be a ce...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/06B01D45/14
CPCB01D45/14F02C7/06
Inventor 王亮云李焱谭锋肖根升石建成单晓明江平郭晖薛筱萌周海涛
Owner CHINA AVIATION POWER MACHINE INST
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