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Manufacturing method for titanium alloy clad edge of composite fan blade of aircraft engine

A technology of aero-engine and composite materials, which is applied in the field of cladding edge manufacturing of fan blades, can solve the problems of low efficiency and difficulty, and achieve the effect of solving difficulty and improving impact resistance

Active Publication Date: 2016-12-07
NORTHWESTERN POLYTECHNICAL UNIV
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AI Technical Summary

Problems solved by technology

[0006] In order to overcome the low efficiency of the existing fan blade cladding manufacturing method, the present invention provides a titanium alloy cladding manufacturing method for aero-engine composite fan blades
This solves the technical problem of high difficulty and low efficiency when the titanium alloy cladding edge of the fan blade is completely dependent on CNC milling.

Method used

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  • Manufacturing method for titanium alloy clad edge of composite fan blade of aircraft engine
  • Manufacturing method for titanium alloy clad edge of composite fan blade of aircraft engine
  • Manufacturing method for titanium alloy clad edge of composite fan blade of aircraft engine

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Embodiment Construction

[0024] refer to Figure 1-5 . The specific steps of the method for manufacturing the titanium alloy clad edge of the aero-engine composite material fan blade of the present invention are as follows:

[0025] Step 1, CNC machining the cladding edge 1 into a rectangular blank with a protrusion in the middle;

[0026] Step 2, using an acid solution to remove the oxide skin on the surface of the coating edge 1 and then blowing it dry;

[0027] Step 3: Put the wrapping edge 1 into the outer mold 4 which is the same as the shape of the outer edge after forming, and the size is 1 to 5 mm larger, and apply downward pressure to the pressure head 3 to preform, so that the wrapping edge 1 forms a V shape structure;

[0028] Step 4: Put the inner mold 5 having the same inner cavity profile as that of the cladding edge 1 into the inner cavity of the cladding edge 1, wrap the sealing layer 6 outside the cladding edge 1, and vacuum the inside of the sealing layer 6 After sealing.

[002...

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Abstract

The invention discloses a manufacturing method for a titanium alloy clad edge of a composite fan blade of an aircraft engine. By the adoption of the manufacturing method, the technical problem that an existing manufacturing method for a clad edge of a fan blade is low in efficiency is solved. According to the technical scheme, the manufacturing method comprises the steps that firstly, an open plate provided with a boss is formed preliminarily; secondly, a clad edge blank is made to be of a V-shaped structure by conducting superplastic forming twice; and thirdly, the interior and exterior, not meeting the cladding requirement for the edge of the fan blade, of the clad edge are fine machined with assistance of a numerical-control machining method. The edge of the blade is completely covered with metal, and thus the impact resistance and layering resistance of the blade are improved. Accordingly, the technical problems that when machining of the titanium alloy clad edge of the fan blade completely depends on numerical-control milling, the difficulty is high, and the efficiency is low are solved.

Description

technical field [0001] The invention relates to a manufacturing method of a cladding edge of a fan blade, in particular to a manufacturing method of a titanium alloy cladding edge of an aero-engine composite material fan blade. Background technique [0002] The aero engine is the core part of the aircraft. The performance of the engine directly affects the performance of the entire aircraft. The weight reduction of the engine can improve the thrust-to-weight ratio. The fan blade is one of the most important parts of the engine. According to statistics, the mass of the fan section accounts for about 30% to 35% of the total mass of the engine. Reducing the mass of the fan section is a key means to reduce the mass of the engine and improve the efficiency of the engine. Light fan blades have become the development trend of engines. Composite materials have low density, high specific strength and high specific stiffness that are incomparable to metal materials. Compared with tit...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00B23P15/006
Inventor 张定华杜随更任军学汪文虎王松林
Owner NORTHWESTERN POLYTECHNICAL UNIV