Composite gas compressor fan blade with integrated metal coating

A metal cladding and composite material technology, which is applied to liquid fuel engines, components of pumping devices for elastic fluids, mechanical equipment, etc. Three-dimensional weaving is difficult and other problems, to achieve the effect of excellent erosion resistance, avoid cracks or even breakage, and excellent impact resistance

Active Publication Date: 2017-05-10
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The method (1) has many disadvantages, especially the connection strength between the blade body and the blade root is seriously insufficient and the blade body made by the molding process has serious delamination defects
The disadvantage of the (2) method is that the three-dimensional weaving of complex shapes is extremely difficult, and the dimensional accuracy is difficult to guarantee
The disadvantage of the (3) method is that there are too many internal interfaces of the blade, and the outer prepreg and metal cladding are easily peeled off, causing blade failure

Method used

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  • Composite gas compressor fan blade with integrated metal coating
  • Composite gas compressor fan blade with integrated metal coating
  • Composite gas compressor fan blade with integrated metal coating

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] The first step is to calculate the size and shape of the expanded blank of the blade model in dynaform, and then cut out two corresponding TA2 plates after appropriately increasing the margin, and put them into the stamping die with the shape of the upper and lower skin surfaces of the blade respectively , forming to the desired surface shape;

[0041] In the second step, the excess skin of the formed upper and lower titanium plates is cut off, and degreasing, pickling and sodium hydroxide anodizing (sandblasting) treatment are carried out in sequence. The composition of the anodizing electrolyte is: NaOH 300g / L, Tart 65g / L, EDTA 30g / L, Na2SiO3 6g / L, the voltage is 10V, the electrolysis time is 10min, and the electrolysis temperature is 35°C;

[0042] The third step is to calculate the number of epoxy resin prepregs with a thickness of 0.125mm required for each part and the shape and size of each layer according to the intercalation laying method, and cut them in place ...

Embodiment 2

[0050] The first step is to calculate the size and shape of the expanded blank of the blade model in dynaform, and then cut out two corresponding TA2 plates after appropriately increasing the margin, and put them into the stamping die with the shape of the upper and lower skin surfaces of the blade respectively , forming to the desired surface shape;

[0051] In the second step, the excess skin of the formed upper and lower titanium plates is cut off, and degreasing, pickling and sodium hydroxide anodizing (sandblasting) treatment are carried out in sequence. The composition of the anodizing electrolyte is: NaOH 300g / L, Tart 65g / L, EDTA 30g / L, Na2SiO3 6g / L, the voltage is 10V, the electrolysis time is 10min, and the electrolysis temperature is 35°C;

[0052] The third step is to calculate the number of polyetherether copper prepregs with a thickness of 0.125mm required for each part and the shape and size of each layer according to the intercalation laying method, and cut them...

Embodiment 3

[0060] The first step is to calculate the size and shape of the expanded blank of the blade model in dynaform, and then cut out two corresponding TA2 plates after appropriately increasing the margin, and put them into the progressive forming machine tool for positioning and fastening, according to the required surface Write the NC program and input the shape, the indenter starts to move the knife, and forms to the required surface shape;

[0061] In the second step, the excess skin of the formed upper and lower titanium plates is cut off, and degreasing, pickling and sodium hydroxide anodizing (sandblasting) treatment are carried out in sequence. The composition of the anodizing electrolyte is: NaOH 300g / L, Tart 65g / L, EDTA 30g / L, Na2SiO3 6g / L, the voltage is 10V, the electrolysis time is 10min, and the electrolysis temperature is 35°C;

[0062] The third step is to calculate the number of epoxy resin prepregs with a thickness of 0.125mm required for each part and the shape an...

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Abstract

The invention relates to a composite gas compressor fan blade with an integrated metal coating. The composite gas compressor fan blade is characterized by comprising a composite base layer and a metal coating, wherein the composite base layer and the metal coating are integrally formed by mould pressing; the metal coating coats the composite base layer, and the coated flange part is adhered by adopting an adhesive and set by mould pressing. The blade has very high specific strength and excellent impact resistance and erosion resistance, and can effectively avoid cracking and even breakage caused by de-mixing and surge; and the blade forming method integrates preparation of an intermediate composite material and formation of the whole blade, so that the manufacturing cost and time are greatly reduced, and the method has the advantages of high forming precision, high automation degree, long service life of the mold and the like.

Description

technical field [0001] The invention relates to a composite material compressor fan blade and a molding method thereof, in particular to a composite material compressor fan blade with an integral metal coating layer and a molding method thereof, belonging to the technical field of composite material compressor fan blades. Background technique [0002] The fan blade involved in the present invention is the first-stage blade of the compressor in the aero-engine, and the overall performance of the compressor and even the turbine engine is closely related to the performance of the fan blade. With the continuous improvement of aero-engine performance, its bypass ratio is also increasing. The use of fan blades with greater specific strength, higher precision curved surface structure, and better aerodynamic performance has also become the development trend of engines with large bypass ratio. Traditional metal materials and even lightweight metal materials such as titanium alloys ca...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/02F04D29/30F04D29/38B29C70/34B29C70/84
CPCB29C70/345B29C70/84F04D29/023F04D29/30F04D29/388
Inventor 马文亮潘蕾王一凡吕云飞陶杰郭训忠
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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