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Machining method of fiber reinforced type high-temperature composite used for aircraft engines

An aero-engine and fiber-reinforced technology, applied in combustion engines, internal combustion piston engines, metal processing equipment, etc., can solve problems such as tool wear, low machining accuracy, and high hardness, and achieve reduced tearing, good lubricity, and high strength. Effect

Active Publication Date: 2016-05-04
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Fiber-reinforced high-temperature composite materials for aero-engines are also widely used in the aerospace field, but due to their high hardness, high strength, anisotropy, poor thermal conductivity, and the inability to perform liquid cooling, they are typical difficult-to-machine materials
The matrix and reinforcing fibers are the main elements in the cutting process. At the same time, the cutting is also affected by factors such as fiber orientation distribution. The anisotropy of the material leads to defects such as tearing, splitting, delamination, and fluffing in the processing of composite products. These The appearance of defects leads to the reduction of mechanical properties and surface roughness of composite materials, and many large components of this material require high-precision machining, while ordinary turning has disadvantages such as low machining accuracy, low efficiency, serious tool wear, and high cost. Difficult to meet processing needs

Method used

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  • Machining method of fiber reinforced type high-temperature composite used for aircraft engines
  • Machining method of fiber reinforced type high-temperature composite used for aircraft engines
  • Machining method of fiber reinforced type high-temperature composite used for aircraft engines

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0039] Embodiment 1: Processing of aircraft brake disc

[0040] Before the processing of aircraft brake discs, 1. Make a special tool in advance: choose hard alloy steel as the tool handle material, the tool handle is thickened, and the diameter is 9mm, which is about 1.5 times thicker than the ordinary tool handle of the same specification; melting The knife handle, the knife body is immersed in the knife handle, the shape of the part where the knife body is immersed in the knife handle is an inverted trapezoid, and the knife body is made of artificial diamond material. 2. Mix water, glycerin and lard according to the volume ratio of 2:1:1 to make cooling liquid for later use.

[0041] In the process of processing, fix the tool and the workpiece, set the processing parameters for processing, and set the two steps of rough and finish processing, all of which use special tools to process along the plane at 45° to the fiber direction. The specific parameters are feed rate f=0.0...

Embodiment 2

[0042] Embodiment two: the processing of sealing sheet

[0043] Same as Example 1, the special cutting tool and coolant are prepared in advance, and the workpiece is fixed with a fixture during processing; during processing, the hard alloy body is used for rough processing, and the processing is carried out along the direction of 45° with the fiber direction, and the processing The specific parameters are feed rate f = 0.02mm / r, cutting depth ap = 0.1mm, amplitude A = 25μm; after rough machining, the artificial diamond polycrystalline body is used for finishing machining, and the same method is used at 45° to the fiber direction. The surface is processed, and the processing parameters are still the feed rate f=0.02mm / r, the cutting depth ap=0.1mm, and the amplitude A=25μm.

Embodiment 3

[0044] Embodiment 3: Drilling of cylindrical workpiece

[0045] The preparation of cutting tool and coolant is the same as that of Embodiment 1. This piece is to be drilled on one side of the cylinder, it needs to be processed first figure 2 A metal semicircular auxiliary fitting 4 matched with the cylindrical workpiece 3 shown, and then a round hole of a given size is processed on the auxiliary fitting 4, which is equal to or slightly larger than the hole to be drilled on the workpiece 3 That is, so that the cutter can be stretched in. Note: Special tools are not required for metal fittings and drilling. Then, the semicircular auxiliary fitting 4 made of metal is fixed on the cylinder with a clamp and bonded, so that the drilling position on the auxiliary fitting 4 coincides with the drilling position on the workpiece 3 . Finally, the electroplated diamond drill bit is used for drilling, and the special cooling liquid of the present invention is poured into the drilling h...

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Abstract

The invention provides a machining method of a fiber reinforced type high-temperature composite used for aircraft engines. Cooling liquid used during machining is provided to overcome the defects that tearing, splitting, layering, fluffing and size instability frequently appear during machining, wherein the cooling liquid is mixed liquid of water glycerol and animal oil, the volume size is (8-10):(4-5):(4-5), good lubricity is achieved, dust generated during machining can be absorbed, and meanwhile the cooling liquid is green and environmentally friendly. A tool is used. The diameter of a tool handle is larger than that of an ordinary tool cuter. The tool conducts cutting in the plane forming a 45-degree angle together with the fiber direction of the fiber reinforced type high-temperature composite during cutting, and the shock resistance of the lathing tool can be effectively improved. In addition, when a machined part with the surface having large curvature is drilled, an accessory completely fitting the hook face is manufactured, a drilling tool penetrates through a hole of the accessory, and therefore it can be avoided that in the machining process, because of vibration, size deviation is caused by a small amount of displacement.

Description

technical field [0001] The invention relates to the processing technology of composite materials, in particular to a processing method of fiber-reinforced high-temperature composite materials for aero-engines, including two processing technologies of curved surface shape cutting and drilling. Background technique [0002] Fiber-reinforced high-temperature composite materials for aero-engines are composite materials with carbon and ceramics as the matrix and certain carbon fibers and ceramic fibers as reinforcements. They have high specific strength, high specific modulus, high temperature resistance, corrosion resistance, fatigue resistance, and With a series of excellent properties such as creep, electrical conductivity, heat transfer and small expansion coefficient, it can be used not only as a structural material to carry heavy loads, but also as a functional material. Fiber-reinforced high-temperature composite materials for aero-engines are also widely used in the aeros...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23Q11/10B23B51/00B23B35/00
CPCB23B35/00B23B51/00B23B2215/04B23B2215/24B23B2226/275B23Q11/1061
Inventor 罗瑞盈侯振华
Owner BEIHANG UNIV
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