CN106739003B - Co-curing damping perforation type presses down the pneumatic equipment bladess and preparation method thereof for structure of quivering - Google Patents

Co-curing damping perforation type presses down the pneumatic equipment bladess and preparation method thereof for structure of quivering Download PDF

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CN106739003B
CN106739003B CN201611187229.6A CN201611187229A CN106739003B CN 106739003 B CN106739003 B CN 106739003B CN 201611187229 A CN201611187229 A CN 201611187229A CN 106739003 B CN106739003 B CN 106739003B
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layer
damping
circular perforations
pneumatic equipment
rectangle
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CN106739003A (en
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孙大刚
郭进军
李占龙
燕碧娟
张洪宁
张洋
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Taiyuan University of Science and Technology
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/36—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and impregnating by casting, e.g. vacuum casting
    • 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 present invention relates to pneumatic equipment bladess, specifically a kind of co-curing damping perforation type presses down the pneumatic equipment bladess and preparation method thereof for structure of quivering.The present invention solves the problems, such as that the existing suppression technology of quivering can not fundamentally improve itself suppression of pneumatic equipment bladess and quiver ability.Co-curing damping perforation type presses down the pneumatic equipment bladess for structure of quivering, including blade body, web；The blade body includes outer layer covering, internal layer covering；Rectangle damping layer, round resin nail are equipped with around vibration peak in the blade body under corresponding main rank mode；Wherein, rectangle damping layer is layed between outer layer covering and internal layer covering；The surface of rectangle damping layer offers several inside and outside circular perforations penetrated through；The number of round resin nail is consistent with the number of circular perforations；Each circle resin nail is embedded at the inner cavity of each circular perforations correspondingly；The both ends end face of each circle resin nail is integrated with outer layer covering and internal layer covering consolidation respectively.The present invention is suitable for wind energy conversion system.

Description

Co-curing damping perforation type presses down the pneumatic equipment bladess and preparation method thereof for structure of quivering
Technical field
The present invention relates to pneumatic equipment bladess, the damping perforation type suppression of specifically a kind of co-curing quiver structure pneumatic equipment bladess and Its production method.
Background technique
With going deep into for wind energy conversion system enlargement development trend, pneumatic equipment bladess also more and more soft and fine change.However practice have shown that, Soft and fine pneumatic equipment bladess are easy to happen flutter, are thus easy to influence the operation robustness of pneumatic equipment bladess, to influence wind-force Generating efficiency.Therefore, main at present that technology is quivered to wind energy conversion system using following suppression in order to guarantee the operation robustness of pneumatic equipment bladess The flutter of blade is inhibited: one, Chinese patent CN 105134482A discloses a kind of large-scale intelligent fan blade grey combination The method of modeling and optimization vibration control.This method is by establishing fan blade system Grey Combinatorial Model Method and setting model prediction Controller realizes blade vibration control.Though this method can change flow field around blade by intelligent controller, its structure is multiple It is miscellaneous, installation difficulty is big, and increase leaf quality.Two, Chinese patent CN 104965408A and Chinese patent CN 104898722A individually discloses a kind of fan blade vibration detection and control device.The device is by controlling magnetic current and liquid flow The frequency for entering to the quality of fan blade inner cavity to change fan blade reaches mitigation vibration purpose.The device fails fundamentally It improves blade itself and presses down ability of quivering, and control accuracy requirement is high, system robustness is poor.Three, Chinese patent CN 102348892A is public A kind of structural damping device of pneumatic equipment bladess is opened.The damper invests blade inner wall by modes such as bondings, can be wider Blade vibration is effectively controlled in working frequency, but there are dampers to be detached from, increases the disadvantages of leaf quality.Four, Chinese patent CN 103321853A discloses a kind of pneumatic equipment bladess suppression using compound damping structure and quivers method.This method passes through in blade surface It is laid with restriction damping layer, sets vector free axis method in girder outer surface, can play and improve blade construction damping, inhibit blade vibration Effect, but to sacrifice larger blade stiffness as cost, reduce blade safety in operation.The technology in conclusion existing suppression is quivered It is the effective damping of pneumatic equipment bladess to be improved by increasing additional damping element, or pass through around control pneumatic equipment bladess mostly Flow field reach vibration damping purpose.This requires the dynamic response capability of controlled damping element is fast, and work can be run to wind energy conversion system Condition, which is made, to be accurately identified and responds, and thus causes the operation robustness of pneumatic equipment bladess and the response accuracy of controlled damping element straight Correlation is connect, the ability so that itself suppression that can not fundamentally improve pneumatic equipment bladess is quivered.It is a kind of completely new it is necessary to invent thus Pneumatic equipment bladess are quivered the above problem existing for technology with solving existing suppression.
Summary of the invention
Itself suppression that the present invention can not fundamentally improve pneumatic equipment bladess in order to solve the existing suppression technology of quivering is quivered ability Problem provides a kind of damping perforation type suppression of co-curing and quivers the pneumatic equipment bladess and preparation method thereof of structure.
The present invention is achieved by the following technical scheme:
Co-curing damping perforation type presses down the pneumatic equipment bladess for structure of quivering, including blade body, web；The blade body packet Include outer layer covering, internal layer covering；Rectangle damping layer, circle are equipped with around vibration peak in the blade body under corresponding main rank mode Resin nail；Wherein, rectangle damping layer is layed between outer layer covering and internal layer covering；The surface of rectangle damping layer offers several A inside and outside circular perforations penetrated through；The diameter of each circular perforations is consistent, and each circular perforations equidistant arrangement forms perforation Array；The number of round resin nail is consistent with the number of circular perforations；Each circle resin nail is embedded at each correspondingly The inner cavity of circular perforations, and consistency of thickness of the thickness of each round resin nail with rectangle damping layer；Each circle resin nail Both ends end face respectively with outer layer covering and internal layer covering consolidation be integrated.
Co-curing damping perforation type suppression is quivered, and (this method is for making institute of the present invention for the production method of pneumatic equipment bladess of structure The co-curing damping perforation type stated presses down the pneumatic equipment bladess for structure of quivering), this method is realized using following steps:
Step A: being laid with outer layer covering layer of cloth on blade mold, is then laid in the inner surface of outer layer covering layer of cloth certain Thus the outer layer of composite material layer of number, outer layer covering layer of cloth and outer layer of composite material layer collectively form outer layer in blade body and cover The upper half of skin, while being laid with priming by vacuum system；
Step B: rectangle damping layer is chosen, is then drilled with inside and outside several using upright drill on the surface of rectangle damping layer The circular perforations of perforation；The diameter of each circular perforations is consistent, and each circular perforations equidistant arrangement forms perforation array；It will Rectangle damping layer is layed in the specific region of the inner surface of outer layer of composite material layer, which refers to corresponding in blade body Around vibration peak under main rank mode；
Step C: being laid with inner layer composite material layer in the inner surface of outer layer composite layer and the inner surface of rectangle damping layer, Then it is laid with internal layer covering layer of cloth in the inner surface of internal layer composite layer, internal layer covering layer of cloth and inner layer composite material layer are thus The upper half of internal layer covering in blade body is collectively formed, while priming by vacuum system being laid with completely；
Step D: resin, resin are injected using between priming by vacuum system outer layers composite layer and internal layer covering layer of cloth Thus enter the inner cavity of each circular perforations on rectangle damping layer；
Step E: making resin solidification under certain condition, so that the inner cavity of each circular perforations is respectively formed a circle Resin nail；At this point, in above-mentioned specific region, the both ends end face of each circle resin nail respectively with outer layer of composite material layer and interior Layer composite layer consolidation is integrated；The upper half of outer layer covering, the upper half of internal layer covering, rectangle damping layer, each circle Resin follows closely the upper half for thus collectively forming blade body；
Step F: repeating step A~E, and the lower half of blade body is made；
Step G: choosing web, then web be pasted on to the lower half of blade body, then by the upper half of blade body, Web, blade body lower half molded and solidified, thus be made pneumatic equipment bladess, finally to pneumatic equipment bladess carry out after Processing.
Quiver compared with technology with existing suppression, co-curing damping perforation type suppression of the present invention quiver structure pneumatic equipment bladess and Its production method is from the angle for the structural damping and the rigidity of structure for adjusting pneumatic equipment bladess, by opening on rectangle damping layer If perforating array, and the area accounting by the way that rectangle damping layer is rationally arranged, realize in the less premise for sacrificing blade stiffness Under preferably promote the operation robustness of blade, itself suppression for thus fundamentally improving pneumatic equipment bladess is quivered ability, thus The operation robustness of pneumatic equipment bladess has been effectively ensured, and then wind power generation efficiency has been effectively ensured.
The present invention, which efficiently solves the existing suppression technology of quivering and can not fundamentally improve itself suppression of pneumatic equipment bladess, to quiver ability The problem of, it is suitable for wind energy conversion system.
Detailed description of the invention
Fig. 1 is the overall structure signal for the pneumatic equipment bladess that co-curing damping perforation type of the present invention presses down structure of quivering Figure.
Fig. 2 is the partial structurtes signal for the pneumatic equipment bladess that co-curing damping perforation type of the present invention presses down structure of quivering Figure.
In figure: 1- blade body, 2- web, 11- outer layer covering, 12- internal layer covering, 13- rectangle damping layer, 14- are round Resin nail, 15- circular perforations.
Specific embodiment
Co-curing damping perforation type presses down the pneumatic equipment bladess for structure of quivering, including blade body 1, web 2；The blade body 1 includes outer layer covering 11, internal layer covering 12；Rectangular resistance is equipped with around vibration peak in the blade body 1 under corresponding main rank mode Buddhist nun's layer 13, round resin nail 14；Wherein, rectangle damping layer 13 is layed between outer layer covering 11 and internal layer covering 12；Rectangular resistance The surface of Buddhist nun's layer 13 offers several inside and outside circular perforations 15 penetrated through；The diameter of each circular perforations 15 is consistent, and each A 15 equidistant arrangement of circular perforations forms perforation array；The number of round resin nail 14 is consistent with the number of circular perforations 15；Respectively A circle resin nail 14 is embedded at the inner cavity of each circular perforations 15 correspondingly, and the thickness of each round resin nail 14 is equal With the consistency of thickness of rectangle damping layer 13；The both ends end face of each circle resin nail 14 is covered with outer layer covering 11 and internal layer respectively The consolidation of skin 12 is integrated.
The area accounting of the rectangle damping layer 13 meets following condition:
In above formula: the area accounting of δ (D, S) expression rectangle damping layer；L1Indicate the length of rectangle damping layer；L2Indicate square The width of shape damping layer；D indicates the diameter of each circular perforations；S indicates the pitch-row of two neighboring circular perforations.
The material of the rectangle damping layer 13 is damping viscoelastic material or damping alloy.
Co-curing damping perforation type suppression is quivered, and (this method is for making institute of the present invention for the production method of pneumatic equipment bladess of structure The co-curing damping perforation type stated presses down the pneumatic equipment bladess for structure of quivering), this method is realized using following steps:
Step A: being laid with outer layer covering layer of cloth on blade mold, is then laid in the inner surface of outer layer covering layer of cloth certain Thus the outer layer of composite material layer of number, outer layer covering layer of cloth and outer layer of composite material layer collectively form outer layer in blade body 1 The upper half of covering 11, while being laid with priming by vacuum system；
Step B: rectangle damping layer 13 is chosen, is then drilled with several on the surface of rectangle damping layer 13 using upright drill The circular perforations 15 of inside and outside perforation；The diameter of each circular perforations 15 is consistent, and 15 equidistant arrangement of each circular perforations is formed Perforation array；Rectangle damping layer 13 is layed in the specific region of the inner surface of outer layer of composite material layer, which refers to Around vibration peak in blade body 1 under corresponding main rank mode；
Step C: inner layer composite material is laid in the inner surface of outer layer composite layer and the inner surface of rectangle damping layer 13 Then layer is laid with internal layer covering layer of cloth, internal layer covering layer of cloth and inner layer composite material layer in the inner surface of internal layer composite layer Thus the upper half of internal layer covering 12 in blade body 1 is collectively formed, while priming by vacuum system being laid with completely；
Step D: resin, resin are injected using between priming by vacuum system outer layers composite layer and internal layer covering layer of cloth Thus enter the inner cavity of each circular perforations 15 on rectangle damping layer 13；
Step E: making resin solidification under certain condition, so that the inner cavity of each circular perforations 15 is respectively formed a circle Shape resin nail 14；At this point, in above-mentioned specific region, the both ends end face of each circle resin nail 14 respectively with outer layer of composite material Layer and inner layer composite material layer consolidation are integrated；The upper half of outer layer covering 11, the upper half of internal layer covering 12, rectangle damping layer 13, thus each round resin nail 14 collectively forms the upper half of blade body 1；
Step F: repeating step A~E, and the lower half of blade body 1 is made；
Step G: choosing web 2, then web 2 be pasted on to the lower half of blade body 1, then by the upper of blade body 1 Half portion, web 2, blade body 1 lower half molded and solidified, thus be made pneumatic equipment bladess, finally to wind energy conversion system leaf Piece is post-processed.
In the step A, outer layer of composite material layer is by different directions and with the single fiber layer of regular order with certain Angle lack of balance is laid with, and is aided with adhesive；Laying angle selects between 0 °, ± 45 °, 90 °, and defers to ± 45 ° again Condensation material layer pairs of principle of paving in groups；When being laid at blade root, additional enhancement layer is laid with to mention close to blade root in rear High bending resistance energy.
In the step C, inner layer composite material layer is by different directions and with the single fiber layer of regular order with certain Angle lack of balance is laid with, and is aided with adhesive；Laying angle selects between 0 °, ± 45 °, 90 °, and defers to ± 45 ° again Condensation material layer pairs of principle of paving in groups；When being laid at blade root, additional enhancement layer is laid with to mention close to blade root in rear High bending resistance energy.
In the step B, the diameter of each circular perforations 15 and the pitch-row of two neighboring circular perforations 15 are to pass through foundation Genetic Algorithm Model, and what simulation optimization determined is carried out to Genetic Algorithm Model.
In the step B, the specific region for being laid with rectangle damping layer 13 is to combine modal analysis method, is imitated by ANSYS software What the result after true optimization determined.
In the step B, upright drill is Z5150 upright drill.
In order to verify beneficial effects of the present invention, tested as follows:
Referring to certain wind field 1500kW vane design of wind turbines parameter, according to IEC standard second level wind field, main design parameters are such as Shown in table 1:
1 main design parameters of table
One, contrast model is established:
In ANSYS software, referring to 1500kW vane design of wind turbines parameter, and mass of equivalence is combined, established respectively Undamped structure pneumatic equipment bladess model (undamped structure blade), local co-curing damping structure pneumatic equipment bladess model (resistance Buddhist nun's structure blade) and local co-curing damping perforation type pneumatic equipment bladess model (perforation damping structure vane).Damping material is equal Select epoxy resin viscoelastic material, performance parameter are as follows: β=1.5, G=3.43 × 106N/m, E=1.14 × 106N/m。
Determine design parameter: thickness h=1mm of rectangle damping layer, the length L of rectangle damping layer1=10502mm, rectangle The width L of damping layer2=364mm；The diameter D=30mm of circular perforations, the pitch-row S=250mm of two neighboring circular perforations are opened If the area accounting δ (D, S)=97.7% of rectangle damping layer after circular perforations.
Two, press down performance comparison analysis of quivering:
Choosing certain wind field mean wind speed is 12m/s, and wind speed variance is 9m2/s2, and be fitted based on Two-parameter Weibull Distribution Outlet air frequency curve carries out dynamic analysis to above-mentioned three kinds of structure blades in ANSYS software to simulate practical wind regime, and provides Simulation comparison is as a result, as shown in table 2:
Table 2 imitates straight result
Note: it opens up to position i.e. aerofoil section away from the ratio between blade root distance r and blade radius R
By analysis, and table 2 is combined to emulate data it is found that damping structure and perforation damping structure vane are at four kinds of positions Compared with undamped structure blade:
1, vibration displacement standard deviation reduces 21.00% and 18.79%, 16.25% and 13.08%, 4.56% and respectively 4.41%, 4.61% and 3.17%；Vibration velocity standard deviation reduces 42.49% and 36.90%, 22.72% and respectively 15.41%, 19.47% and 13.65%, 9.94% and 6.18%.Illustrate damping structure vane and perforation damping structure vane all Blade flutter can effectively be inhibited, and damping capacity is suitable.
2, perforation damping vane first-order modal natural frequency ratio undamped structure blade first-order modal intrinsic frequency has dropped 0.067%, and the first-order modal natural frequency ratio undamped structure blade intrinsic frequency of damping structure vane has dropped 2.50%, Its range of decrease is 37.31 times of the perforation damping vane intrinsic frequency range of decrease.Illustrate that perforation damping vane can keep original leaf substantially The rigidity of structure of piece, and the Stiffness of damping structure vane is more serious.
To sum up analyze, the present invention constructed by co-curing damping perforation type suppression quiver structure pneumatic equipment bladess not only vibration damping imitate Fruit is preferable, and structural behaviour is more excellent, can effectively inhibit the vibration strong or weak of pneumatic equipment bladess in the process of running and vibration speed Degree improves it and runs robustness and safety.

Claims (6)

  1. The pneumatic equipment bladess of structure 1. a kind of co-curing damping perforation type suppression is quivered, including blade body (1), web (2)；The leaf Piece ontology (1) includes outer layer covering (11), internal layer covering (12)；It is characterized by: corresponding main rank mould on the blade body (1) Rectangle damping layer (13), round resin nail (14) are equipped with around vibration peak under state；Wherein, rectangle damping layer (13) is layed in outer layer Between covering (11) and internal layer covering (12)；The surface of rectangle damping layer (13) offers several inside and outside circular perforations penetrated through (15)；The diameter of each circular perforations (15) is consistent, and each circular perforations (15) equidistant arrangement forms perforation array；It is round The number that resin follows closely (14) is consistent with the number of circular perforations (15)；Each circle resin nail (14) is embedded at respectively correspondingly The inner cavity of a circular perforations (15), and consistency of thickness of the thickness of each round resin nail (14) with rectangle damping layer (13)； The both ends end face of each circle resin nail (14) is integrated with outer layer covering (11) and internal layer covering (12) consolidation respectively；
    The area accounting of the rectangle damping layer (13) meets following condition:
    In above formula: the area accounting of δ (D, S) expression rectangle damping layer；L1Indicate the length of rectangle damping layer；L2Indicate rectangular resistance The width of Buddhist nun's layer；D indicates the diameter of each circular perforations；S indicates the pitch-row of two neighboring circular perforations；
    The material of the rectangle damping layer (13) is damping viscoelastic material or damping alloy；
    It is specific the preparation method is as follows:
    Step A: being laid with outer layer covering layer of cloth on blade mold, is then laid with certain amount in the inner surface of outer layer covering layer of cloth Outer layer of composite material layer, thus outer layer covering layer of cloth and outer layer of composite material layer collectively form outer layer in blade body (1) and cover The upper half of skin (11), while being laid with priming by vacuum system；
    Step B: choosing rectangle damping layer (13), is then drilled with several on the surface of rectangle damping layer (13) using upright drill The circular perforations (15) of inside and outside perforation；The diameter of each circular perforations (15) is consistent, and each circular perforations (15) are equidistantly arranged Column form perforation array；Rectangle damping layer (13) is layed in the specific region of the inner surface of outer layer of composite material layer, this is specific Region refers to around the vibration peak on blade body (1) under corresponding main rank mode；
    Step C: being laid with inner layer composite material layer in the inner surface of outer layer composite layer and the inner surface of rectangle damping layer (13), Then it is laid with internal layer covering layer of cloth in the inner surface of internal layer composite layer, internal layer covering layer of cloth and inner layer composite material layer are thus The upper half of internal layer covering (12) in blade body (1) is collectively formed, while priming by vacuum system being laid with completely；
    Step D: resin is injected using between priming by vacuum system outer layers composite layer and internal layer covering layer of cloth, resin is thus Into the inner cavity of each circular perforations (15) on rectangle damping layer (13)；
    Step E: making resin solidification under certain condition, so that the inner cavity of each circular perforations (15) is respectively formed a circle Resin follows closely (14)；At this point, in above-mentioned specific region, the both ends end face of each circle resin nail (14) respectively with outer layer composite wood The bed of material and inner layer composite material layer consolidation are integrated；The upper half of outer layer covering (11), the upper half of internal layer covering (12), rectangle Damping layer (13), each round resin nail (14) thus collectively form the upper half of blade body (1)；
    Step F: repeating step A~E, and the lower half of blade body (1) is made；
    Step G: choosing web (2), web (2) be then pasted on to the lower half of blade body (1), then by blade body (1) The upper half, web (2), blade body (1) lower half molded and solidified, thus be made pneumatic equipment bladess, it is finally right Pneumatic equipment bladess are post-processed.
  2. The pneumatic equipment bladess of structure 2. co-curing damping perforation type suppression according to claim 1 is quivered, it is characterised in that: described In step A, outer layer of composite material layer is that lack of balance is spread at a certain angle by different directions and with the single fiber layer of regular order If forming, and it is aided with adhesive；Laying angle selects between 0 °, ± 45 °, 90 °, and defers to ± 45 ° of composite layers in groups Pairs of principle of paving；When being laid at blade root, additional enhancement layer is laid with to improve anti-bending strength close to blade root in rear.
  3. The pneumatic equipment bladess of structure 3. co-curing damping perforation type suppression according to claim 1 is quivered, it is characterised in that: described In step C, inner layer composite material layer is that lack of balance is spread at a certain angle by different directions and with the single fiber layer of regular order If forming, and it is aided with adhesive；Laying angle selects between 0 °, ± 45 °, 90 °, and defers to ± 45 ° of composite layers in groups Pairs of principle of paving；When being laid at blade root, additional enhancement layer is laid with to improve anti-bending strength close to blade root in rear.
  4. The pneumatic equipment bladess of structure 4. co-curing damping perforation type suppression according to claim 1 is quivered, it is characterised in that: described In step B, the diameter of each circular perforations (15) and the pitch-row of two neighboring circular perforations (15) are by establishing genetic algorithm Model, and what simulation optimization determined is carried out to Genetic Algorithm Model.
  5. The pneumatic equipment bladess of structure 5. co-curing damping perforation type suppression according to claim 1 is quivered, it is characterised in that: described In step B, the specific region for being laid with rectangle damping layer (13) is to combine modal analysis method, after the optimization of ANSYS software emulation As a result it determines.
  6. The pneumatic equipment bladess of structure 6. co-curing damping perforation type suppression according to claim 1 is quivered, it is characterised in that: described In step B, upright drill is Z5150 upright drill.
CN201611187229.6A 2016-12-20 2016-12-20 Co-curing damping perforation type presses down the pneumatic equipment bladess and preparation method thereof for structure of quivering Active CN106739003B (en)

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CN103321853A (en) * 2013-04-12 2013-09-25 太原科技大学 Method for restraining wind turbine blade adopting compound damping structure from vibrating
CN104085118A (en) * 2014-06-11 2014-10-08 青岛理工大学 Making technology of embedded co-cured perforating damping film composite material structure

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