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CN-118003681-B - Aviation propeller blade forming method

CN118003681BCN 118003681 BCN118003681 BCN 118003681BCN-118003681-B

Abstract

The invention discloses a method for forming an aviation propeller blade in the technical field, which comprises the following steps of 1) blanking, 2) carbon beam forming, 3) blade root inverted wedge forming, 4) carbon tube forming, 5) foam core component forming, 5-1) cleaning a mould, 5-2) foam treatment, 5-3) carbon beam treatment, 5-4) preparation of components, 5-5) preparation of sealant and adhesive, 5-6) foam core combination, 5-7) carbon Liang Baobu laying, 5-8) carbon beam mounting, 5-9) gluing, 5-10) foam mounting, 5-11) die attaching, 5-12) die assembling, 5-13) detecting, 6) metal blade root outer sleeve mounting, 7) braiding forming, 8) rear edge strip forming, 9) blade pre-shaping and 10) RTM forming.

Inventors

  • LI JUN
  • AI GUOQIANG
  • CHEN YING
  • XIAO WEIHUA
  • Zhai Wangyi
  • LI SHUN
  • YANG HENG
  • DING HUI

Assignees

  • 江苏新扬新材料股份有限公司

Dates

Publication Date
20260505
Application Date
20240322

Claims (10)

  1. 1. The molding method of the aviation propeller blade is characterized in that the blade structure comprises a carbon beam, a blade root inverted wedge, a carbon tube, a foam core, a blade root inner sleeve, a blade root outer sleeve and a weaving outer sleeve, wherein a groove of carbon Liang Tianru is processed in the middle of a working surface and a non-working surface of the foam core, so that a continuous surface is formed between the surface of a carbon Liang Shepian part and a part of a foam core component blade part during molding, and the molding method comprises the following steps: step 1), blanking, namely cutting each piece of prepreg by using an automatic blanking machine according to a program, wherein the cut prepreg is cut; Step 2) forming a carbon beam, sequentially paving, solidifying, machining, detecting and warehousing for later use after a die is cleaned, wherein the carbon beam is of a palm-closed structure and comprises a working face carbon beam and a non-working face carbon beam, and the periphery of the root of the carbon beam is processed to form a V-shaped annular groove; step 3) forming the blade root by reverse wedge, cleaning a die, and sequentially paving, curing, repairing, detecting and warehousing for later use; step 4) forming the carbon tube, cleaning a die, and then sequentially winding, curing, machining, detecting and warehousing for later use; Step 5) forming the foam core assembly; Step 5-1) cleaning a die; step 5-2), treating foam, wrapping a foam core by using a clean porous isolating film and an air felt, sending the foam core into an oven for dehumidification treatment, and uniformly wrapping a layer of adhesive film on the surface of the dehumidified foam; Step 5-3), treating the carbon beam, performing sand blasting treatment on the surface of the carbon beam, wiping the surface of the carbon beam by using absorbent cotton dipped with a proper amount of acetone until the absorbent cotton is free from heterochrosis, and airing at room temperature; Step 5-4), preparing a part, dipping proper amount of acetone into absorbent gauze to wipe the surfaces of the counterweight support, the carbon tube, the oar root inner sleeve and the sealing tool clean until the absorbent gauze is free from color difference, and placing the absorbent gauze for standby; Preparing a sealant and an adhesive, wherein the sealant consists of base paste, epoxy resin and a vulcanizing agent, firstly, putting the base paste and the epoxy resin on a clean polytetrafluoroethylene or clean nonmetallic vessel, repeatedly mixing the base paste and the epoxy resin by using a scraping plate, fully mixing the base paste and the epoxy resin, then, adding the vulcanizing agent, repeatedly mixing the base paste, the epoxy resin, the vulcanizing agent and the vulcanizing agent, fully mixing the three components for later use; Step 5-6) foam core combination, uniformly coating sealant on the end surfaces of the counterweight support, the carbon tube, the inner sleeve of the oar root and the foam core, firstly, mounting the carbon tube on the counterweight support, then pushing the counterweight support into the foam core aiming at the hole on the foam core, then inserting a sealing tool into the hole of the counterweight support, and finally, mounting one end of the inner sleeve of the oar root coated with sealant inwards on the sealing tool to be butted with the carbon tube; Step 5-7) laying carbon Liang Baobu, and respectively laying working face prepreg cut pieces and non-working face prepreg cut pieces of the carbon Liang Baobu into an upper die and a lower die cavity of a foam core assembly forming die according to the laying requirements of the foam core assembly; step 5-8), mounting a carbon beam, firstly, attaching a layer of adhesive film on the outer surface of the carbon beam with a non-working surface, and then placing the carbon beam with the non-working surface into a lower die according to the requirement of a datum line and a positioning template, and compacting and attaching; Step 5-9), gluing, namely uniformly coating the prepared adhesive on the inner surface of the root part of the carbon beam, the outer surface of the carbon tube and the outer surface of the inner sleeve of the oar root; Step 5-10), installing foam, installing the assembled foam core into a lower die according to the position requirement of a datum line, and compacting; Step 5-11), sticking a layer of adhesive film on the outer surface of the working face carbon beam, laying the working face carbon beam into an upper die according to the datum line requirement and the positioning template, and compacting and sticking; step 5-12), closing the upper die and the lower die, and then sending the dies into a hot press for solidification; step 5-13) detection; step 6) installing a metal blade root sleeve, and installing a blade root inverted wedge and the blade root sleeve to the periphery of the carbon beam; step 7), knitting and forming, namely knitting and forming by a knitting machine; Step 8), forming a rear edge strip, namely forming a high-strength glass fiber part by adopting a manual blanking die; Step 9) blade presetting, namely presetting the braided and molded blade and the rear edge strip by using a preset tool; and 10) RTM molding, namely mounting the paddle after the pre-shaping into an RTM molding die, and forming an organic whole through RTM injection.
  2. 2. The method for forming the aviation propeller blade according to claim 1, wherein the winding in the step 4) specifically comprises the steps of mounting a core mold on a winding machine, mounting a carbon fiber prepreg winding spindle on a creel, guiding carbon fiber strips out to pass through rollers, fixing a carbon fiber prepreg head at a core mold starting position, starting the winding machine, winding according to winding and layering sequence requirements, closing a power supply of the winding machine after the winding diameter of a carbon tube reaches a set diameter, cutting carbon fibers by scissors, and packaging the rest material rolls for storage.
  3. 3. The method for forming the aviation propeller blade according to claim 1 or 2, wherein the step 6) comprises the steps of cleaning the surfaces of a propeller root inverted wedge and a foam core component, preparing an adhesive, coating the adhesive on the V-shaped annular groove area on the periphery of a carbon beam and the inner surface of the propeller root inverted wedge, sleeving a propeller root jacket from the root of the foam core component, installing the propeller root inverted wedge at a corresponding position, compacting, carrying out drawing operation on the propeller root jacket by using a drawing positioning tool, and finally sending the propeller root jacket into an oven for curing.
  4. 4. A method of shaping an aircraft propeller blade according to claim 3, wherein step 6) comprises: step 6-1) surface treatment, namely taking a paddle root inverted wedge and a foam core component, respectively carrying out sand blowing treatment on the outer surface of the foam core component, then wiping the surface of a carbon beam by using absorbent cotton dipped with a proper amount of acetone until the absorbent cotton has no heterochromatic, and airing at room temperature; preparing an adhesive according to the weight ratio of a matrix, namely a curing agent, namely white carbon black=100:30:0.3, wherein the glue coating amount of each blade is 50-60 g, weighing a proper amount of the matrix, putting the matrix on a clean polyethylene film, weighing the matrix according to the proportion, adding the curing agent, mixing and stirring uniformly, weighing the white carbon black according to the proportion, and continuously stirring uniformly to obtain the adhesive; step 6-3) gluing, namely fully coating the prepared adhesive on the V-shaped annular groove area on the periphery of the carbon beam and the inner surface of the reversed wedge of the paddle root; Step 6-4), sleeving the outer sleeve of the paddle root into the root of the foam core assembly, outwards arranging the wedge-shaped flaring, reversely wedging the paddle root to a corresponding position, and compacting; step 6-5), drawing, namely drawing the outer sleeve of the paddle root by using a drawing positioning tool; step 6-6) curing, and finally sending the mixture into an oven for curing.
  5. 5. The method for forming an aviation propeller blade according to claim 4, wherein the drawing in step 6-5) is specifically: Step 6-5-1), placing the working face of the foam core assembly upwards on a fixture bracket, attaching the end face of the paddle root to the limited surface of a drawing positioning fixture, fastening a positioning pressing plate, screwing a locking nut of the fixture, and fixing the foam core assembly on the fixture; Step 6-5-2), adjusting the first anchor ear to a horizontal position by using a sliding cushion block, placing the first anchor ear under the paddle root sleeve, aligning the end face scribing of the paddle root sleeve with the end face scribing of the anchor ear, respectively placing 3 lining plates into the anchor ear, and finally fastening the first anchor ear and the second anchor ear by using four bolts; step 6-5-3), sleeving 4 limiting sleeves on a pull rod, enabling the pull rod to pass through a support plate and a hoop, fastening by nuts, respectively inserting 1 bolt at two sides of the hoop, fixing the bolts on the hoop by bolts, and pulling the paddle root sleeve to axially pull out by a rotary handle, wherein the pulling-out position is based on the condition that the four limiting sleeves are contacted with the end face of the sleeve; And then the locking flange is connected with the locking pressing plate by bolts for fastening.
  6. 6. The method for forming an aviation propeller blade according to claim 1 or 2, wherein step 2) specifically comprises: step 2-1) preparing a mould, namely cleaning the mould, and wiping the mould by using a release agent; Step 2-2), paving, namely paving the cut pieces into a die cavity in sequence at the paving initial position by taking the die blade root as a reference, and vacuumizing and pre-compacting once after paving 3-6 layers each time, wherein the vacuum degree is less than-0.095 MPa, and the vacuumizing time is 10-15 min; Step 2-3) curing, namely heating up at a heating rate of not more than 1.5 ℃ per minute, heating up the die to 90 ℃ plus or minus 5 ℃, preserving heat at the temperature for 1h plus or minus 10min, continuously heating up to 130 ℃ plus or minus 5 ℃ at the same heating rate, preserving heat at the temperature for 3h plus or minus 10min, cooling down at a cooling rate of not more than 2 ℃ per minute under the curing pressure of 1.0MPa plus or minus 0.05MPa, and releasing pressure and opening the die when the temperature is reduced to below 45 ℃; Machining the working face carbon beam and the non-working face carbon beam by using carbon Liang Shumo, checking the appearance condition after machining, and arranging 6 machining thickness detection positions within the range of 0-300mm of the root of the carbon beam, wherein the accuracy is controlled to +/-0.2 mm; And 2-5) warehousing, namely storing qualified working face carbon beams and non-working face carbon beams into a transfer warehouse.
  7. 7. The method for forming an aviation propeller blade according to claim 1 or 2, wherein the steps 5-5) are specifically: preparing a sealant, namely preparing the sealant according to the weight ratio of base paste to epoxy resin to vulcanizing agent=30:0.9:3, firstly placing the base paste and the epoxy resin on a clean polytetrafluoroethylene or clean nonmetallic vessel, repeatedly mixing for more than 20 times by using a scraping plate to fully mix the base paste and the epoxy resin, then adding the vulcanizing agent, repeatedly mixing by using the scraping plate to fully mix the three components to obtain the sealant for standby; Preparing an adhesive, namely preparing the adhesive according to the weight ratio of a matrix to a curing agent=100:30, wherein the adhesive coating amount of each blade is 50-60 g, weighing a proper amount of the matrix, putting the matrix on a clean polyethylene film, weighing the matrix according to the proportion, adding the curing agent, and uniformly mixing and stirring the mixture by using a clean glass rod until no abnormal color exists.
  8. 8. The method for forming an aircraft propeller blade according to claim 1 or 2, wherein step 7) specifically comprises: step 7-1), braiding is started from the position of the blade root, wherein the braiding angle forms 45 degrees plus or minus 5 degrees with the axis of the blade, namely, the fiber braiding angle is 90 degrees plus or minus 10 degrees, the braiding is stopped after the blade tip continues to be braided for 15 mm-20 mm, the local braiding angle of the blade is measured, and the measurement result is recorded; step 7-2), after each layer is knitted, brushing the preshaped glue solution on the knitting layer uniformly, and airing for 3-5 min; Step 7-3) cutting off fibers at the position away from the blade tip according to the closing-in position, and adhering the surface woven layer on the blade injection molding assembly at three parts of the width of the closing-in position by using an adhesive film; Step 7-4) detaching the extension rod of the blade injection molding assembly from the three-jaw chuck, enabling the working surface to pass through the braiding ring from the back of the braiding machine upwards, clamping the extension rod on the three-jaw chuck, and fixing the fiber on the extension rod by using a yellow adhesive tape; Step 7-5), repeating the steps 7-2) to 7-5) until the N layers of braiding layers are completed, and alternately upwards connecting the non-working surface and the working surface of the blade during braiding; Step 7-6), binding the blade root by a bundle of carbon fibers at the position, close to the blade root, of the blade part of the blade after the N layers are compiled, then wrapping a layer of vacuum bag film, and finally wrapping the vacuum bag film.
  9. 9. The method for forming an aircraft propeller blade according to claim 1 or 2, wherein step 9) specifically comprises: Step 9-1) installing a glue injection tool, namely fixing the blade preform from which the stop tool is removed to an assembly tool; step 9-2), placing the working surface in a mould to brush and shape glue solution; Step 9-3), folding the back edge strip wrapping cloth in half, aligning the folding line with the back edge of the die, enabling one half of the back edge strip wrapping cloth to be positioned in the die cavity, and enabling the other half of the back edge strip wrapping cloth to be positioned outside the die, and brushing the sizing glue solution; Step 9-4), placing the non-working surface of the blade preform upwards in a mould by taking the front edge of the mould as a reference, placing a triangular area of the rear edge in the mould by taking the rear edge of the braiding body as a reference, pressing the triangular area, shaking the rear edge strip up and down to an interlayer fluffy state, shaking the rear edge strip from the inflection point of the rear edge strip to the direction of the tip of the oar, gradually and backwardly shaking, gradually pressing the shaking fluffy part into a mould cavity, attaching the rear edge and the edge of the braiding body to the mould, shearing off braided fibers which are more than the tip of the oar according to the size of the mould cavity of the mould, and ensuring that the braiding body is matched with the mould cavity of the mould; step 9-5), after the rear edge strip is installed, trimming redundant skin of the working surface along the molded surface of the die by using scissors, and cutting the skin at the joint of each sliding block without cutting in the range from the paddle root to the tangent plane; Step 9-6), bonding two prepreg tapes on a gap between the rear edge strip and the braiding body; Step 9-7), turning up the trailing edge strip wrapping cloth and the covering cloth at each sliding block, and dipping the shaping glue solution by using a hairbrush to flatten the trailing edge Bao Bushua; Step 9-8), placing the non-working surface on the surface of the blade preform to brush the sizing glue solution; step 9-9), cleaning the fiber cut off around the die by using a dust collector, and wiping the edge of the die by using acetone; step 9-10), closing the mould, feeding the mould into a baking oven, and opening the mould after baking.
  10. 10. The method for forming an aviation propeller blade according to claim 1 or 2, wherein the step 10) is specifically: Step 10-1) after the step 6) is completed, taking out the blade preform, then installing the blade preform into an RTM forming mold, and forming an organic whole through RTM injection; Step 10-2), cleaning the mold, namely checking whether a glue injection port and a glue outlet port of the mold are smooth, dipping acetone into absorbent gauze to wipe the surface of the mold for several times until no different colors exist, and uniformly coating a release agent; Step 10-3) installing a sealing strip in a sealing groove of a non-working surface die, wherein the joint of the sealing strip is required to be cut at an oblique angle and is well sewn, and the joint of the sealing strip cannot be positioned on the same side of the die so as to prevent vacuum leakage due to poor sealing; step 10-4) putting the non-working surface of the preset shape body downwards into a mould, and trimming the preset shape body appropriately according to the mould surface; step 10-5) die assembly; Step 10-6), vacuumizing and preheating the die, namely heating the RTM die, vacuumizing the die, and keeping the temperature of the die at a set temperature all the time in the whole glue injection process until the glue injection beam is formed; step 10-7) configuring RTM resin; Step 10-8) resin deaeration, namely opening a vacuum valve of the glue injection tank to deaerate the resin; Step 10-9) RTM injection, namely opening a resin flow rate control valve, properly adjusting injection pressure within a set range according to the condition of resin flow until the glue is discharged from a glue outlet, properly adjusting injection pressure within the set range according to the condition of resin flow and air bubbles after the glue is discharged from a glue outlet, automatically stopping vacuumizing after the glue discharge amount in a glue discharge tank reaches limit, closing the glue discharge valve to start holding glue, and if the glue discharge amount in the glue discharge tank reaches limit, exceeding the set amount by the resin injection amount, and no air bubble exists at the glue outlet of a die, ending glue injection; Step 10-10), solidifying, and opening a die after solidifying; Step 10-11) detection.

Description

Aviation propeller blade forming method Technical Field The invention relates to the technical field of composite products, in particular to a propeller blade. Background The resin matrix composite blade can effectively reduce weight and noise. The blade is made of the resin matrix composite material, so that the weight of the blade can be greatly reduced, the weight of an engine can be practically reduced, and the thrust-weight ratio and the efficiency are improved. Therefore, the quality of the composite material blade is improved, the efficiency of the engine can be improved, and the hidden danger of aviation and flight can be reduced. At present, the domestic composite propeller blade is formed by adopting a fabric and RTM forming technology, and the technology has poor quality stability and is easy to have the defects of surface dry spots, root delamination, gum enrichment at the front edge and the like. The blade forming scheme adopts a mixed forming method of autoclave forming, compression molding and RTM forming, fully plays the advantages of each forming method, and can effectively avoid the problems. The composite material blade mainly comprises a carbon beam, a polyurethane foam core, a carbon fiber and glass fiber braided sleeve, and a blade root polyurethane foam filling layer. The main force piece is a carbon beam formed by alternately laying unidirectional carbon cloth prepreg and satin carbon cloth prepreg, the carbon beam is respectively unfolded in the axial direction and the thickness direction of a blade on a working face and a non-working face of the blade, enters a metal blade root sleeve in a circular ring mode in a palm closing mode, is unfolded at the root flaring of the blade root sleeve to form wedges with two openings, so that the carbon fiber composite material bearing beam and the metal sleeve are completely and reliably connected, the carbon beam core is a PMI foam core, the outside is a shell woven by glass fibers and carbon fibers in a mixed mode, and the organic whole is formed through RTM injection. When the blade preform is installed on the blade root sleeve, the blade preform is fixed on the drawing tool, a pulling force is applied to the blade root sleeve, and after the blade root is drawn in place, the stopping tool is used for fixing the blade root sleeve. However, when the blade preform is subjected to pre-shaping, the retaining tool needs to be detached, and at the moment, the blade root sleeve is subjected to a reaction force (tensile reaction force) so that the blade root sleeve slides towards the blade tip direction, and therefore, the blade preform and the mold are different in matching performance, the glue-rich phenomenon occurs at the front edge of the blade RTM glue injection, and the blade appearance precision is reduced. Disclosure of Invention Aiming at the defects existing in the prior art, the invention provides a molding method of the aviation propeller blade, which optimizes the process operability, greatly improves the nondestructive quality of a product, solves the problem of glue enrichment at the front edge of the blade caused by the movement of a blade root sleeve, and improves the appearance precision of the blade. The invention aims to realize the forming method of the aviation propeller blade, wherein the blade structure comprises a carbon beam, a blade root inverted wedge, a carbon tube, a foam core, a blade root inner sleeve, a blade root outer sleeve and a weaving outer sleeve, a groove of carbon Liang Tianru is processed in the middle of a working surface and a non-working surface of the foam core, so that a continuous surface is formed between the surface of the carbon Liang Shepian part and a part of the foam core component blade part during forming, and the forming method comprises the following steps of: step 1), blanking, namely cutting each piece of prepreg by using an automatic blanking machine according to a program, wherein the cut prepreg is cut; Step 2) forming a carbon beam, sequentially paving, solidifying, machining, detecting and warehousing for later use after a die is cleaned, wherein the carbon beam is of a palm-closed structure and comprises a working face carbon beam and a non-working face carbon beam, and the periphery of the root of the carbon beam is processed to form a V-shaped annular groove; step 3) forming the blade root by reverse wedge, cleaning a die, and sequentially paving, curing, repairing, detecting and warehousing for later use; step 4) forming the carbon tube, cleaning a die, and then sequentially winding, curing, machining, detecting and warehousing for later use; step 5) the foam core assembly is formed, Step 5-1) cleaning a die; step 5-2), treating foam, wrapping a foam core by using a clean porous isolating film and an air felt, sending the foam core into an oven for dehumidification treatment, and uniformly wrapping a layer of adhesive film on the surface of the dehumidified foam; Step 5-3), treati