Anti-erosion and friction-resistant film for fan blades of aeto-turbofan engine and preparation method of anti-erosion and friction-resistant film

A turbofan engine and fan blade technology, applied in the direction of engine function, machine/engine, liquid fuel engine, etc., to achieve the effect of improving anti-erosion performance, high hardness, and high surface hardness

Inactive Publication Date: 2017-01-11
ZHENGZHOU UNIVERSITY OF AERONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, there is a lack of an anti-erosion and anti-friction film for aviation turbofan engin

Method used

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  • Anti-erosion and friction-resistant film for fan blades of aeto-turbofan engine and preparation method of anti-erosion and friction-resistant film

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] An anti-erosion and friction-resistant film for fan blades of aviation turbofan engines according to the present invention, the anti-erosion and friction-resistant films for fan blades of aviation turbofan engines are blade base 0 and transition layer 1 from inside to outside , anti-friction film layer and anti-erosion film layer; the anti-erosion and anti-friction film used for fan blades of aviation turbofan engines is deposited sequentially from the inside to the outside of the blade base.

[0031] The blade base 0 is a titanium alloy; the transition layer 1 is a metal titanium or metal chromium layer; The etch film layers are successively a chromium aluminum titanium nitride layer 31 and a chromium titanium nitride layer 32 from the inside to the outside.

[0032] The thickness of the metallic titanium or metallic chromium layer of described transition layer is 15nm, improves film adhesion,

[0033] The thickness of the titanium nitride layer 21 is 0.8 μm, and the ...

Embodiment 2

[0044] The difference between embodiment 2 and embodiment 1 is:

[0045] A kind of anti-erosion and anti-friction film for the fan blade of aviation turbofan engine of the present invention, the thickness of the metal titanium or metal chromium layer of described transition layer is 30nm, improves film adhesion,

[0046] The thickness of the titanium nitride layer 21 is 1.2 μm, and the thickness of the aluminum titanium nitride layer 22 is 1.0 μm.

[0047] The thickness of the chromium aluminum titanium nitride layer 31 is 1.8 μm, and the thickness of the chromium titanium nitride layer 32 is 2.0 μm.

[0048] The nitrogen content of the titanium nitride layer 21 increases gradually from the inside to the outside; the nitrogen content and titanium content of the aluminum titanium nitride layer 22 gradually decrease from the inside to the outside, and the aluminum content gradually increases; the nitrogen content of the chromium aluminum titanium nitride layer 31 increases from ...

Embodiment 3

[0058] The difference between embodiment 3 and embodiment 1 is:

[0059] A kind of anti-erosion and anti-friction film for the fan blade of aviation turbofan engine of the present invention, the thickness of the metal titanium or metal chromium layer of described transition layer is 40nm, improves film adhesion,

[0060] The thickness of the titanium nitride layer 21 is 1.5 μm, and the thickness of the aluminum titanium nitride layer 22 is 1.2 μm.

[0061] The thickness of the chromium aluminum titanium nitride layer 31 is 1.6 μm, and the thickness of the chromium titanium nitride layer 32 is 1.8 μm.

[0062] The preparation method of the anti-erosion and anti-friction film for the fan blade of aviation turbofan engine according to the present invention comprises the following steps:

[0063] (1) The multi-arc ion plating method is adopted, the coating equipment is in a clean space, the cleanliness is within 100,000 grades, the cooling water temperature is 26°C, and the humid...

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Abstract

The invention discloses an anti-erosion and friction-resistant film for fan blades of an aeto-turbofan engine and a preparation method of the anti-erosion and friction-resistant film. The anti-erosion and friction-resistant film for the fan blades of the aeto-turbofan engine comprises a blade base (0), a transition layer (1), a friction-resistant film layer and an anti-erosion film layer from inside to outside sequentially, and is deposited from inside to outside by starting from the blade base sequentially. The anti-erosion and friction-resistant film has excellent anti-erosion and friction-resistant capacity and high surface hardness, and the surface hardness is higher than 3,200 HV. A chromium nitride layer located on the outermost layer has high hardness and low friction coefficient, and the anti-erosion performance of a film surface is improved; adopted nitride layers have excellent corrosion resistance, so that the service life of each fan blade of the aeto-turbofan engine is prolonged.

Description

technical field [0001] The invention relates to the technical field of manufacturing aviation turbojet engines, in particular to an anti-erosion and friction-resistant film for fan blades of aviation turbofan engines and a preparation method thereof. Background technique [0002] Aviation turbofan engine referred to as turbofan engine is the most important engine used in modern aircraft, including fighter jets, attack aircraft, bombers and most of the regional and mainline airliners. The fan is the most front part of the turbofan engine, which is the primary booster part. For a turbofan engine, the fan part is the first part to come into contact with the nearest part. Therefore, for severe weather conditions such as sandy weather and gravel weather, the air entering the engine often carries a large amount of sand and gravel with uneven particle sizes. , directly hitting the blades of the fan, which will cause friction and scratches on the surface of the fan blades, thereby ...

Claims

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Application Information

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IPC IPC(8): F04D29/02F04D29/26C23C14/32C23C14/02C23C14/06C23C28/00
CPCF04D29/26C23C14/025C23C14/0617C23C14/0641C23C14/325C23C28/322C23C28/34F04D29/023F05D2230/90F05D2260/95
Inventor 刘战合王晓璐田秋丽
Owner ZHENGZHOU UNIVERSITY OF AERONAUTICS
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