CN114718760A - Fan blade made of layered composite material and reinforcing method thereof - Google Patents
Fan blade made of layered composite material and reinforcing method thereof Download PDFInfo
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- CN114718760A CN114718760A CN202110011492.4A CN202110011492A CN114718760A CN 114718760 A CN114718760 A CN 114718760A CN 202110011492 A CN202110011492 A CN 202110011492A CN 114718760 A CN114718760 A CN 114718760A
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- pin
- fan blade
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- composite material
- implantation
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- 239000002131 composite material Substances 0.000 title claims abstract description 56
- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000003014 reinforcing effect Effects 0.000 title claims abstract description 15
- 238000002513 implantation Methods 0.000 claims abstract description 36
- 239000000835 fiber Substances 0.000 claims abstract description 14
- 239000007943 implant Substances 0.000 claims description 12
- 238000010438 heat treatment Methods 0.000 claims description 10
- 239000004642 Polyimide Substances 0.000 claims description 3
- 229920001721 polyimide Polymers 0.000 claims description 3
- 239000011347 resin Substances 0.000 claims description 3
- 229920005989 resin Polymers 0.000 claims description 3
- 238000011156 evaluation Methods 0.000 claims description 2
- 239000011229 interlayer Substances 0.000 abstract description 4
- 238000005452 bending Methods 0.000 description 8
- 238000012360 testing method Methods 0.000 description 7
- 239000010410 layer Substances 0.000 description 5
- 230000032798 delamination Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 238000004873 anchoring Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
Abstract
The invention aims to provide a fan blade made of a layered composite material and a reinforcing method thereof, wherein the blade structure or the reinforcing method can be used for reinforcing the interlayer performance of the layered composite material. In order to achieve the purpose, the fan blade made of the layered composite material is implanted with Z-Pin, wherein the Z-Pin is organic fiber and is implanted in a pre-perforation implantation mode.
Description
Technical Field
The invention relates to a fan blade made of a layered composite material and a reinforcing method thereof.
Background
The fan blade made of the layered composite material is an important technical approach for reducing weight and reducing noise of an aviation turbofan engine with a large bypass ratio. Bird strike resistance and centrifugal strength are two most important performance indexes of the composite fan blade. A large amount of test and simulation data show that the bird impact and centrifugal strength of the fan blade made of the layered composite material and high-cycle vibration fatigue closely related to the centrifugal strength are in a first failure mode of layering, the overall bending rigidity of the blade after layering is reduced to be below 1/4 before layering, and further bending compression and tensile fracture occur under bird impact load. The layering of the tenon in the centrifugal strength test makes the blade have the risk of pulling out from the tongue-and-groove, and layering in the high cycle vibration fatigue makes blade body amplitude increase, has increaseed the risk of engine blade detuning.
The Z-Pin technology can effectively enhance the interlayer performance of the layered composite material, but the traditional Z-Pin technology adopts carbon fiber manufacture and ultrasonic hammer assisted implantation, has the defects that the implantation depth is difficult to exceed 5mm, and the in-plane performance damage of the layered composite material is as high as more than 15% -25%, and the carbon fiber Z-Pin is often subjected to brittle fracture under the high strain rate load of bird impact, so that the enhancement effect of the interlayer performance is greatly reduced. The thickness of the tenon is as high as more than 50-80mm, and the Z-Pin implantation depth needs more than 20mm to inhibit the delamination of the key position in the structural layer under the centrifugal load and the high-cycle vibration fatigue load.
Disclosure of Invention
The invention aims to provide a fan blade made of a layered composite material and a reinforcing method thereof, wherein the blade structure or the reinforcing method can enhance the interlayer performance of the layered composite material.
In order to achieve the purpose, the fan blade made of the layered composite material is implanted with Z-Pin, wherein the Z-Pin is organic fiber and is implanted in a pre-perforation implantation mode.
In one embodiment, the organic fibers are high tenacity S35 grade polyimide fibers.
In one embodiment, the implantation range of the Z-Pin covers the leading edge region, the tip region and the trailing edge region of the blade, but does not include the middle region between the leading edge region and the trailing edge region.
In one embodiment, the implantation range of Z-Pin also covers the tenon area.
In one embodiment, the implantation range of Z-Pin also covers the area of the flow channel line.
In one embodiment, the Z-Pin has a diameter of 0.4 to 0.5mm and an implant density of (2.5 to 3.5mm) × (2.5 to 3.5mm) square pitch.
In one embodiment, the implantation density of the Z-Pin in the leading edge region, the tip region and the tail edge region is greater than that in the flow channel line region.
To achieve the purpose, the reinforcing method of the fan blade made of the layered composite material comprises the following steps:
pricking a hole with a specified depth at a specified position of the fan blade made of the spread composite material, wherein the direction of the hole is vertical to the blade profile where the hole is located;
embedding the Z-Pin with the corresponding length into the hole, and if the Z-Pin cannot be embedded smoothly, repeatedly pricking the hole until the Z-Pin is embedded smoothly into the hole;
compacting the implanted Z-Pin, and taking the Z-Pin which cannot be seen on the surface of the blade as an evaluation standard;
after all the Z-Pin implantation work is completed, the blade is cured.
In one embodiment, before the hole is punched out, a heating sheet is adhered to a corresponding mold position below the implantation area to heat the fan blade of the ply-up composite material, and the temperature or the output power of the heating sheet is adjusted until the prepreg resin of the fan blade of the ply-up composite material is softened.
In one embodiment, the Z-Pin is an organic fiber.
Because Z-Pin is organic fiber and is implanted by adopting a pre-perforation implantation mode, the Z-Pin has high toughness and low implantation damage, the anti-layering capability of the blade is obviously improved, the large-area layering phenomenon in bird strike of the layered blade is avoided, and the key problem of insufficient bird strike resistance of the fan blade made of the layered composite material is solved.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic view of a Z-Pin implant region of a layered composite fan blade;
FIG. 2 is a curve of the bending performance of a fan blade made of a layered composite material with or without Z-Pin;
FIG. 3 is a flow chart of a method of reinforcing a ply composite fan blade.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.
As shown in FIG. 1, Z-pins with different densities are implanted in different areas around a fan blade of the layered composite material, wherein the Z-pins are used for being pinned into uncured prepreg or fiber preform, and after curing is completed, an anchoring and toughening micro-rod is formed in the thickness direction of the composite material. The Z-pin is formed from an organic fiber, such as a high tenacity S35 grade polyimide fiber, having a diameter of about 0.4 mm. The Z-pin is implanted in a pre-perforation implantation mode, and the toughness is high, implantation damage is low, so that the bending and delamination resistance of the composite material fan blade can be improved.
The implantation range of Z-Pin covers the leading edge region 1, the tip region 2, the trailing edge region 3 of the blade, but does not include the middle region 4 between the leading edge region and the trailing edge region. The leading edge region 1, the tip region 2, and the trailing edge region 3 are blade bodies in a certain range including a leading edge, a tip, and a trailing edge of the blade, respectively. The Z-Pin is implanted into the front edge region 1, the blade tip region 2 and the tail edge region 3, so that the bird strike resistance and the layering resistance of the fan blade made of the layered composite material can be enhanced.
With continued reference to fig. 1, the implantation range of Z-Pin also covers the runner line region 4, the runner line region 4 being a region that includes a range of runner lines. The high-cycle vibration fatigue resistance of the fan blade made of the Z-Pin reinforced layer composite material is implanted in the flow channel line area 4.
With continued reference to FIG. 1, the Z-Pin implantation range also covers the tenon area 5, where the tenon area 5 is an area that includes a range of tenons. The tenon area 5 is implanted with Z-Pin to enhance the low-cycle fatigue resistance and the centrifugal strength performance.
The implantation density of each implantation area may be different, for example, the implantation density is 1.47% + -0.07% by implanting 3.0mm × 3.0mm square spacing in a certain area range from the front edge, the blade tip and the tail edge. The leaf height is below 60%, the flow passage line area is implanted by adopting the interval of 6.0mm multiplied by 6.0mm, and the implantation surface density is 0.37% +/-0.07%. The tenon area is implanted by adopting the interval of 6.0mm multiplied by 6.0mm, and the implantation density can be further properly widened or increased according to the constraint of a process window period. The implantation density of the Z-Pin in the front edge area, the blade tip area and the tail edge area is larger than that in the flow channel line area. The foregoing specific data points may vary within a range of ± 0.5 mm.
The certain area is determined by the service actual working condition of the fan blade combined with the layered composite material.
According to the fan blade made of the spread-layer composite material, the problems that fibers are prone to breaking under high strain rate, the interlaminar reinforcing effect is weakened and the like are solved, and the key problem that the fan blade made of the spread-layer composite material is insufficient in bird impact resistance is solved. In one test, a ply composite fan blade according to the previous embodiment increased bird strike speed by 25% relative to a blade without Z-Pin.
In a test, compared with a blade without Z-Pin, the layering composite material fan blade according to the embodiment can effectively improve the centrifugal strength of the tenon by more than 15% and improve the high-cycle vibration fatigue life of the tenon by more than 2 times, and the service life and the use safety of the blade are improved.
As shown in FIG. 2, curve 6 is the bending performance curve of the Z-Pin-free laminated composite fan blade, curve 7 is the bending performance curve of the Z-Pin-free laminated composite fan blade, and under the same standard load, the deformation of the Z-Pin-implanted laminated composite fan blade is obviously lower than that of the Z-Pin-free laminated composite fan blade, for example, under the action of a load of 3000N, the deformation of the Z-Pin-implanted laminated composite fan blade is about 11mm, while the deformation of the Z-Pin-free laminated composite fan blade is 15mm, and the larger the load is, the larger the deformation difference between the two is.
FIG. 3 illustrates a flow chart of a method of reinforcing a ply composite fan blade.
Implant region design is performed first. A Z-Pin implantation region of the composite material fan blade is designed according to the actual working condition of the composite material fan blade in service, and in the embodiment shown in figure 1, the Z-Pin is implanted in a certain region range from the front edge, the blade tip and the tail edge so as to enhance the bird strike resistance and delamination capability. And the Z-Pin is implanted in the area of the flow line to enhance the high-cycle vibration fatigue resistance. The Z-Pin is implanted into the tenon area to enhance the low-cycle fatigue resistance and the centrifugal strength performance.
The implant density is then determined. In one embodiment, the implant is implanted in a range of 3.0mm by 3.0mm spacing from the leading edge, the apex of the blade, and the trailing edge, and the implant areal density is 1.47% ± 0.07%. Below 60% of the leaf height, the area of the flow line is implanted by adopting the space of 6.0mm multiplied by 6.0mm, and the implantation surface density is 0.37% +/-0.07%. The tenon area is implanted by adopting the interval of 6.0mm multiplied by 6.0mm, and the implantation density can be further properly widened or increased according to the constraint of a process window period.
Next, pre-implant preparation is performed. Sticking coordinate paper in the expected area for implanting the Z-Pin, completely covering the implanted area, and dividing the coordinate paper into different areas according to the requirement of the length of the implanted Pin.
Then, blade heating is performed if necessary. Before the main implantation, the blade surface is drilled by using a tool, and if the blade surface is difficult to insert, a heating sheet is adhered to a corresponding mold position below an implantation area to heat the blade. And adjusting the temperature (or output power) of the heating plate until the blade prepreg resin is softened. The temperature of the heating plate is reduced as much as possible on the premise that the holes can be punched, and the maximum temperature of the blade surface is usually not higher than 50 ℃.
The Z-Pin implantation comprises three steps, specifically as follows:
a) using a tool, such as a needle, to punch a hole with a specified depth at a specified position, wherein the direction of the hole is perpendicular to the blade profile, and the punching action can be performed manually or by a machine;
b) embedding Z-Pin with corresponding length into the hole, and if the Z-Pin cannot be embedded smoothly, repeating the step a) until the Pin is embedded smoothly into the hole;
c) implanted pins were compacted using forceps or other tools, and were evaluated as being invisible on the blade surface.
And repeating the three steps to complete the whole Z-Pin implantation work. In order to guarantee the implantation efficiency, a plurality of operation teams can be arranged to operate simultaneously.
And then curing the blades, namely curing the paved blades in an autoclave by taking a high-temperature curing material system as an example, heating to 180 +/-5 ℃ at 0.5 ℃/min-3 ℃/min, keeping the temperature for 120-180 minutes at a constant temperature, keeping the curing pressure at 0.074Mpa, vacuumizing in the heating process, and cooling to room temperature at a cooling rate of less than or equal to 3 ℃/min after the heat preservation is finished.
Finally, performance testing and analysis. In an actual test of the fan blade made of the ply composite material, Z-Pin causes the attenuation of an ultrasonic nondestructive test signal of 1/5-1/6, the influence of the Z-Pin on the vibration frequency is less than 1%, the mass gain is 0.287%, the bending stiffness attenuation is less than 2.52%, the natural vibration frequency attenuation is less than 1.26%, the bending peak load of the blade with the Z-Pin is increased by 21% compared with that of the blade without the Z-Pin, and no delamination damage occurs in the Z-Pin blade type.
The fan blade made of the layered composite material also reduces the dependency of the performance of the layered composite material blade on the process parameters and the defect control quality, and particularly when the performance of the blade is reduced due to process parameter fluctuation and defect control out-of-tolerance layers, the Z-Pin enhanced performance is more obvious, and the Z-Pin enhanced blade has the overall effects of smaller and more stable performance divergence of the Z-Pin enhanced blade in bird strike, centrifugal strength and high-cycle vibration fatigue life than the Z-Pin enhanced blade.
Although the present invention has been disclosed in terms of preferred embodiments, it is not intended to be limited thereto, and variations and modifications may be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention are within the scope of the present invention defined by the claims.
Claims (10)
1. The fan blade is characterized in that the Z-Pin is organic fiber and is implanted in a pre-perforation implantation mode.
2. The ply composite fan blade of claim 1, wherein the organic fibers are high tenacity S35 grade polyimide fibers.
3. A ply composite fan blade as claimed in claim 1 or claim 2, in which the Z-Pin implantation range covers the leading edge region, the tip region, the trailing edge region of the blade, but does not include the central region between the leading edge region and the trailing edge region.
4. The ply composite fan blade of claim 3, wherein the Z-Pin implant range also covers a tenon area.
5. The ply composite fan blade of claim 3, wherein the Z-Pin implant range also covers a runner line area.
6. A ply composite fan blade as defined in claim 1 in which the Z-Pin has a diameter of 0.4-0.5mm and a square pitch of implant density (2.5-3.5mm) x (2.5-3.5 mm).
7. A ply composite fan blade as defined in claim 5, wherein the Z-Pin has an implant density in the leading edge region, tip region, trailing edge region that is greater than the implant density in the runner line region.
8. A method for reinforcing a fan blade made of a layered composite material is characterized in that,
pricking a hole with a specified depth at a specified position of the fan blade made of the spread composite material, wherein the direction of the hole is vertical to the blade profile where the hole is located;
embedding the Z-Pin with the corresponding length into the hole, and if the Z-Pin cannot be embedded smoothly, repeatedly pricking the hole until the Z-Pin is embedded smoothly into the hole;
compacting the implanted Z-Pin, and taking the Z-Pin which cannot be seen on the surface of the blade as an evaluation standard;
after all the Z-Pin implantation work is completed, the blade is cured.
9. The method of reinforcing a ply composite fan blade of claim 8,
before the holes are punched out, heating sheets are adhered to corresponding positions of the die below the implantation area to heat the fan blades of the layered composite material, and the temperature or the output power of the heating sheets is adjusted until prepreg resin of the fan blades of the layered composite material is softened.
10. A method of reinforcing a ply composite fan blade as defined in claim 8 wherein said Z-Pin is an organic fiber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110011492.4A CN114718760A (en) | 2021-01-06 | 2021-01-06 | Fan blade made of layered composite material and reinforcing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110011492.4A CN114718760A (en) | 2021-01-06 | 2021-01-06 | Fan blade made of layered composite material and reinforcing method thereof |
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| CN114718760A true CN114718760A (en) | 2022-07-08 |
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| CN202110011492.4A Pending CN114718760A (en) | 2021-01-06 | 2021-01-06 | Fan blade made of layered composite material and reinforcing method thereof |
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