CN108757270B - Integrated composite material blade structure - Google Patents
Integrated composite material blade structure Download PDFInfo
- Publication number
- CN108757270B CN108757270B CN201810749204.3A CN201810749204A CN108757270B CN 108757270 B CN108757270 B CN 108757270B CN 201810749204 A CN201810749204 A CN 201810749204A CN 108757270 B CN108757270 B CN 108757270B
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- China
- Prior art keywords
- composite material
- integrally formed
- blade structure
- formed composite
- blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000002131 composite material Substances 0.000 title claims abstract description 55
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 31
- 239000004917 carbon fiber Substances 0.000 claims abstract description 31
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 31
- 239000006260 foam Substances 0.000 claims abstract description 20
- 239000002184 metal Substances 0.000 claims abstract description 20
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 19
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 19
- 238000004804 winding Methods 0.000 claims abstract description 19
- 230000007704 transition Effects 0.000 claims abstract description 17
- 230000008602 contraction Effects 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 5
- 238000007493 shaping process Methods 0.000 abstract description 10
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 5
- 238000005265 energy consumption Methods 0.000 abstract description 4
- 239000010410 layer Substances 0.000 description 29
- 238000009434 installation Methods 0.000 description 11
- 230000006872 improvement Effects 0.000 description 8
- 239000011247 coating layer Substances 0.000 description 4
- 230000000670 limiting effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000005253 cladding Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
- F03B3/12—Blades; Blade-carrying rotors
- F03B3/121—Blades, their form or construction
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H1/00—Propulsive elements directly acting on water
- B63H1/02—Propulsive elements directly acting on water of rotary type
- B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
- B63H1/14—Propellers
- B63H1/26—Blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ocean & Marine Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses an integrally formed composite material blade structure in the technical field of composite material blades, which mainly comprises a carbon beam, wherein the carbon beam comprises a forked part, a transition part and an enclasping part, the forked part comprises two flat forked parts, a blade body foam layer is clamped between the forked parts, the transition part and the two forked parts are enclasped gradually until reaching the enclasping part and are enclasped into a circular tube shape, a blade handle foam layer is arranged in the transition part and the enclasping part, a cylindrical carbon fiber shaping cushion block is sleeved outside the transition part, a carbon fiber covering is arranged outside the blade body foam layer and the forked part, a carbon fiber winding layer is arranged outside the shaping cushion block and the enclasping part, and a metal liner tube is arranged on the inner surface of the rear end of the enclasping part. The blade structure of the integrally formed composite material has the characteristics of reliable structure, high safety and light overall weight, and can obviously reduce the energy consumption in the running process of the blade.
Description
Technical Field
The invention relates to a composite material blade, in particular to an integrated composite material blade structure of the composite material blade.
Background
The more advanced blades of the prior art are mostly made of composite materials, and the most important composite materials used at present are carbon fiber composite materials. The carbon fiber composite material has the excellent performances of low density, high strength, high temperature resistance, corrosion resistance, low thermal expansion coefficient, good biocompatibility and the like, so that the carbon fiber composite material becomes an important raw material for preparing composite materials with various structures and functions.
However, unlike metal pieces, composite materials have many limitations in structural use, such as threaded locking structures. Because the composite material has low strength of the threaded hole and is easy to wear in use, the threaded hole can not be opened on the composite material in use, especially under the working condition of bearing larger tensile stress. Therefore, as shown in fig. 1, in the prior art, a blade body 1 made of a composite material and a blade shank 2 made of metal are connected through a bolt 3, and the blade body is driven to rotate together by fixing the blade shank 2 on a rotating hub through threads 4 at the rear end of the blade shank 2. Because the material of the petiole is metal, the petiole has heavy weight and high energy consumption in operation.
Disclosure of Invention
The invention aims to provide a blade structure made of integrally formed composite materials, which reduces the weight of the blade, thereby reducing the operation energy consumption.
The purpose of the invention is realized in the following way: the utility model provides an integrated into one piece combined material paddle structure, main load-carrying member is the carbon beam, the carbon beam includes bifurcation portion, transition portion and surmounting portion, bifurcation portion includes two flat bifurcations, it is equipped with leaf body foam layer to press from both sides between the bifurcation, at transition portion, two bifurcation gradually surmount, until reaching the surmounting portion, surmount into the tubulose, be equipped with the petiole foam layer in transition portion and the surmounting portion, the transition portion overcoat is equipped with cylindric plastic cushion, leaf body foam layer and bifurcation portion are equipped with the carbon fiber covering outward, plastic cushion and surmounting portion are equipped with the carbon fiber winding layer outward, surmounting portion rear end internal surface is provided with metal liner.
The integrally formed composite material blade structure disclosed by the invention has the characteristics of reliable structure, high safety and light overall weight, and the blade handle and the blade body are integrally formed by adopting the carbon fiber composite material, so that the energy consumption of the composite material blade in the running process can be obviously reduced.
As a further improvement of the invention, the carbon fiber winding layer outside the embracing part comprises a connecting part, a contracting part and an expanding part, wherein the outer diameter of the connecting part is matched with the inner diameter of the bearing middle ring of the hub, and the expanding part is outwards diffused and forms an included angle of 25-35 degrees with the central axis of the integrally formed composite material blade structure. The connecting part is used for fixing the blade on the hub, and the contraction part and the expansion part are used for being matched with the locking piece to realize locking. The included angle is preferably 30 deg. to better withstand centrifugal forces during operation of the blade.
As a further improvement of the invention, the rear end of the embracing part and the rear end of the metal liner tube are both outwards diffused and form an included angle of 30 degrees with the central axis of the integrally formed composite material blade structure, so that the whole layers (carbon beam, carbon fiber winding layer and metal liner tube) of the blade handle bear the centrifugal force when the blade works, and the bearing capacity is improved.
As a further improvement of the invention, the front end of the connecting part is provided with a step matched with the blade handle installation angle fixing disc, so that the blade handle installation angle fixing disc is convenient to set, the installation angle adjusting screw penetrates through the hub to prop against the blade handle installation angle fixing disc, and the installation rotation angle of the blade can be adjusted by adjusting the installation angle adjusting screw.
As a further improvement of the invention, the shoulder is arranged at the front end of the step, and the limiting effect can be achieved in the blade assembly process.
As a further improvement of the invention, the front end of the carbon fiber winding layer is provided with a straight section of the blade stem, and the outer diameter of the straight section of the blade stem is matched with the inner diameter of the outer ring of the hub, so that the blade stem of the blade is conveniently inserted and fixed from the outer ring of the hub.
As a further improvement of the invention, the carbon fiber winding layer is formed by winding carbon wires at an angle of 89 degrees with the central axis of the integrally formed composite material blade structure, so as to increase the integrity of the blade handle and the blade body and improve the connection strength.
As a further improvement of the invention, the outer surfaces of the contraction part and the outer expansion part are sleeved with locking open rings matched with the contraction part and the outer expansion part, the tail parts of the locking open rings are propped against the bearing middle ring of the hub, the outer surfaces of the locking open rings are sleeved with locking whole rings, and the rear end surfaces of the locking whole rings, the locking open rings and the metal lining tube are respectively provided with a connecting hole for a locking screw to pass through. Thereby the problem that the threaded hole can not be opened to the combined material structure, carries out screw locking is solved.
As a further improvement of the invention, the outer surface of the front end of the metal liner tube is outwards diffused and forms an included angle of 1 degree with the central axis of the integrally formed composite material blade structure. The metal backing tube is not pulled out by the locking screw during the tightening of the locking screw.
Drawings
FIG. 1 is a schematic illustration of a prior art integrally formed composite blade structure.
FIG. 2 is a schematic view of an integrally formed composite blade structure of the present invention.
FIG. 3 is a schematic view of the internal structure of the rear end of the shank of the integrally formed composite blade structure of the present invention.
Fig. 4 is a schematic view of a carbon beam structure of an integrally formed composite blade structure of the present invention.
Fig. 5 is a schematic view of the internal structure of the blade body of the integrally formed composite blade structure of the present invention.
FIG. 6 is a schematic view of a shaping pad of an integrally formed composite blade structure of the present invention.
Fig. 7 is a schematic view of a carbon fiber wrapping layer of an integrally formed composite blade structure of the present invention.
The novel high-strength steel sheet comprises a 1 blade body, a 2 blade handle, a 3 bolt, 4 threads, a 5 carbon beam, a 5A bifurcation part, a 5B transition part, a 5C enclasping part, a 6 blade body foam layer, a 7 carbon fiber skin, an 8 blade handle foam layer, a 9 shaping cushion block, a 10 carbon fiber winding layer, a 10A connecting part, a 10B contraction part, a 10C expanding part, a 10D step, a 10E shoulder, an 11 metal liner tube, a 12 hub bearing middle ring, a 13 blade handle mounting angle fixing disc, a 14 hub, a 15 locking open ring, a 16 locking full ring, a 17 connecting hole, a 18 blade handle straight section, a 19 hub outer ring and a 20 mounting angle adjusting screw.
Detailed Description
The blade structure of the integrally formed composite material shown in fig. 2 and 3 comprises a blade body 1 and a blade handle 2. The blade structure sequentially comprises a foam layer, a carbon beam 5, a shaping cushion block and a coating layer from inside to outside, wherein the foam layer is divided into a blade body foam layer 6 and a blade handle foam layer 8, and the coating layer is divided into a blade body coating layer (namely a carbon fiber skin 7) and a blade handle coating layer (namely a carbon fiber winding layer 10). The foam layer plays a role of supporting the blade internally and applying back pressure by using elasticity of the foam layer when the blade is manufactured by mould pressing, so that the carbon fiber prepreg layer is paved and compacted everywhere of the blade. For convenience of description, the blade body direction close to the blade is defined as "front", the blade body direction far away from the blade is defined as "rear", and the direction far away from the central axis of the blade shank is defined as "outside".
As shown in fig. 4 and 5, the carbon beam 5 includes a crotch portion 5A, a transition portion 5B, and an encircling portion 5C. The bifurcation part 5A comprises two flat bifurcations, a blade body foam layer 6 is clamped between the bifurcations, and carbon fiber skins 7 are arranged outside the blade body foam layer 6 and the bifurcation part 5A, so that the blade body of the integrated composite material blade structure is formed.
As shown in fig. 3 and 4, at the transition portion 5B of the carbon beam 5, the two branches are gradually held together until reaching the holding portion 5C, and held together in a circular tube shape. The transition part 5B and the cohesion part 5C are internally provided with a petiole foam layer 8, the transition part 5C is externally sleeved with a cylindrical shaping cushion block 9, the structure of the shaping cushion block is shown in figure 6, and the petiole can be rounded by arranging the shaping cushion block 9 due to the square structure of the carbon Liang Congshe body when the carbon Liang Congshe body is led out, so that the petiole cladding layer is convenient to form. The shaping cushion block 9 and the enclasping part 5C are externally provided with the carbon fiber winding layer 10, and the carbon fiber winding layer 10 is formed by winding carbon wires at an angle of 89 degrees with the central axis of the integrated composite material blade structure, so that the enclasping part 5C of the carbon beam and the shaping cushion block 9 are integrated, the strength of the petiole is increased, the integrity is improved, and the split petiole carbon beam is ensured not to open when bearing pneumatic bending moment. The rear end surface of the embracing portion 5C is provided with a metal liner 11 which mainly functions to withstand the inward pressure of the rear end of the shank at centrifugal force and to receive the action of the set locking screw.
As shown in fig. 2, 3, and 7, the carbon fiber wound layer 10 outside the clasping portion 5C includes a connecting portion 10A, a contracting portion 10B, and an expanding portion 10C. The connecting part 10A passes through the hub bearing middle ring 12, the front end of the connecting part 10A is provided with a step 10D matched with the blade handle installation angle fixing disk 13, the installation angle adjusting screw 20 passes through the upper edge of the hub 14 and abuts against the blade handle installation angle fixing disk 13, and the installation angle of the blade can be adjusted by adjusting the installation angle adjusting screw 20. The shoulder 10E is arranged at the front end of the step 10D, and the limiting effect can be achieved in the blade assembly process. The rear ends of the outward expansion part 10C, the encircling part 5C and the rear end of the metal liner tube 11 are outward diffused and form an included angle of 30 degrees with the central axis of the integrally formed composite material blade structure so as to better bear the centrifugal force of the blade during operation. The outer surfaces of the contraction part 10B and the outer expansion part 10C are sleeved with locking open rings 15 matched with the contraction part and the outer expansion part, the tail parts of the locking open rings 15 are propped against the hub bearing middle rings 12, the outer surfaces of the locking open rings 15 are sleeved with locking whole rings 16, and the end surfaces of the locking whole rings 16, the locking open rings 15 and the metal liner tube 11 are respectively provided with connecting holes 17 for locking screws to pass through. Thereby the problem that the threaded hole can not be opened to the combined material structure, carries out screw locking is solved. The outer surface of the front end of the metal lining tube 11 is outwards diffused and forms an included angle of 1 DEG with the central axis of the integrally formed composite material blade structure, so that the metal lining tube 11 cannot be pulled out by the locking screw in the screwing process of the locking screw.
As shown in fig. 3 and 7, the front end of the carbon fiber winding layer 10 is provided with a straight section 18 of the blade stem, and the outer diameter of the straight section 18 of the blade stem is matched with the inner diameter of the hub outer ring 19, so that the blade stem of the blade is conveniently inserted and fixed from the hub outer ring 19.
The blade body and the blade handle of the integrally formed composite material blade structure of the embodiment are made of carbon fiber composite materials. Since the density of the carbon fiber composite material is only 1650kg/m3, the weight of the blade is greatly reduced. The design has the characteristics of reliable structure, high safety and light overall weight.
The invention is not limited to the above embodiments, and based on the technical solution disclosed in the invention, a person skilled in the art may make some substitutions and modifications to some technical features thereof without creative effort according to the technical content disclosed, and all the substitutions and modifications are within the protection scope of the invention.
Claims (10)
1. An integrated into one piece combined material paddle structure, its characterized in that: the main bearing part is the carbon beam, the carbon beam includes bifurcation portion, transition portion and cohesion portion, bifurcation portion includes two flat bifurcations, it is equipped with leaf body foam layer to press from both sides between the bifurcation transition portion, two the bifurcation is gradually cohesion until reaching the cohesion portion, the cohesion becomes the tubulose, be equipped with the petiole foam layer in transition portion and the cohesion portion, the transition portion overcoat is equipped with cylindric plastic cushion, leaf body foam layer and bifurcation portion are equipped with the carbon fiber covering outward, plastic cushion and cohesion portion are equipped with the carbon fiber winding layer outward, cohesion portion rear end internal surface is provided with metal liner.
2. The integrally formed composite material blade structure of claim 1, wherein: the carbon fiber winding layer outside the encircling part comprises a connecting part, a contracting part and an expanding part, wherein the outer diameter of the connecting part is matched with the inner diameter of a bearing middle ring of the hub, and the expanding part is outwards diffused and forms an included angle of 25-35 degrees with the central axis of the integrally formed composite material blade structure.
3. The integrally formed composite material blade structure of claim 2, wherein: the outer expansion part and the central axis of the integrally formed composite material blade structure form an included angle of 30 degrees.
4. An integrally formed composite material blade structure as claimed in claim 3, wherein: the rear end of the embracing part and the rear end of the metal liner tube are outwards diffused and form an included angle of 30 degrees with the central axis of the integrally formed composite material blade structure.
5. The integrally formed composite material blade structure of claim 2, wherein: the front end of the connecting part is provided with a step matched with the fixing disc of the mounting angle of the blade handle.
6. The integrally formed composite material blade structure as claimed in claim 5, wherein: the front end of the step is provided with a shoulder.
7. The integrally formed composite material blade structure of claim 2, wherein: the front end of the carbon fiber winding layer is provided with a straight section of the blade handle, and the outer diameter of the straight section of the blade handle is matched with the inner diameter of the outer ring of the hub.
8. The integrally formed composite material blade structure according to any one of claims 1-7, wherein: the carbon fiber winding layer is formed by winding carbon wires at a winding angle of 80-89 degrees with the central axis of the integrally formed composite material blade structure.
9. The integrally formed composite material blade structure according to any one of claims 2-7, wherein: the outer surface of the contraction part and the outer surface of the outer expansion part are sleeved with locking open rings matched with the contraction part and the outer expansion part, the tail parts of the locking open rings are propped against the bearing middle ring of the hub, the outer surface of the locking open rings is sleeved with locking whole rings, and the rear end surfaces of the locking whole rings, the locking open rings and the metal lining tube are all provided with connecting holes for locking screws to pass through.
10. The integrally formed composite material blade structure of claim 9, wherein: the outer surface of the front end of the metal liner tube is outwards diffused and forms an included angle of 1 degree with the central axis of the integrally formed composite material blade structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810749204.3A CN108757270B (en) | 2018-07-10 | 2018-07-10 | Integrated composite material blade structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810749204.3A CN108757270B (en) | 2018-07-10 | 2018-07-10 | Integrated composite material blade structure |
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| Publication Number | Publication Date |
|---|---|
| CN108757270A CN108757270A (en) | 2018-11-06 |
| CN108757270B true CN108757270B (en) | 2024-01-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810749204.3A Active CN108757270B (en) | 2018-07-10 | 2018-07-10 | Integrated composite material blade structure |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110470452A (en) * | 2019-08-05 | 2019-11-19 | 中国航空工业集团公司哈尔滨空气动力研究所 | Wind tunnel test high speed ducted tail rotor model composite blade assembling structure |
| CN113002759A (en) * | 2019-12-20 | 2021-06-22 | 海鹰航空通用装备有限责任公司 | Propeller root connecting structure of propeller |
| CN113530886A (en) * | 2020-04-22 | 2021-10-22 | 中国电建集团透平科技有限公司 | Large wind tunnel fan impeller |
| CN115163555B (en) * | 2022-07-18 | 2024-02-13 | 江苏航宇航空装备制造有限公司 | Carbon fiber blade used at low temperature |
| CN115163552B (en) * | 2022-07-20 | 2023-10-17 | 江苏航宇航空装备制造有限公司 | Carbon fiber blade root connection structure |
Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN88103525A (en) * | 1987-06-09 | 1988-12-28 | 国家工业宇航学会 | Composite material blade and manufacturing process thereof |
| US5346367A (en) * | 1984-12-21 | 1994-09-13 | United Technologies Corporation | Advanced composite rotor blade |
| RU2058249C1 (en) * | 1992-05-21 | 1996-04-20 | Акционерное общество Научно-производственное предприятие "Аэросила" | Propeller composite blade and method of its manufacture |
| US6305905B1 (en) * | 1999-05-05 | 2001-10-23 | United Technologies Corporation | Bolted-on propeller blade |
| JP2002357176A (en) * | 2001-03-27 | 2002-12-13 | Mitsubishi Heavy Ind Ltd | Composite material blade for wind power generating device |
| EP1914383A2 (en) * | 2006-10-18 | 2008-04-23 | Rolls-Royce Deutschland Ltd & Co KG | Fan blade of composite textile material |
| KR20110116288A (en) * | 2010-04-19 | 2011-10-26 | 김종민 | Lightweight blade with wingbox for wind power generating device, wingbox manufacturing tool and method |
| CN102490899A (en) * | 2011-12-14 | 2012-06-13 | 中国人民解放军总参谋部第六十研究所 | Composite rotor blade for unmanned helicopter and manufacturing method thereof |
| CN203532319U (en) * | 2013-09-29 | 2014-04-09 | 尹天舒 | Counter-rotating fan blade of mine fan |
| KR20140058176A (en) * | 2012-11-06 | 2014-05-14 | 한국항공우주산업 주식회사 | Blade of propeller for turboprop aircraft |
| CN103982463A (en) * | 2014-05-28 | 2014-08-13 | 航天材料及工艺研究所 | Composite material blade for wind tunnel |
| CN104358708A (en) * | 2014-08-19 | 2015-02-18 | 航天材料及工艺研究所 | Carbon fiber composite foam core sandwich structure wind tunnel fan blade and molding method |
| CN104895834A (en) * | 2015-06-01 | 2015-09-09 | 郑伟 | Propeller with metal propeller handle and manufacture technology of same |
| CN107939619A (en) * | 2017-12-04 | 2018-04-20 | 惠阳航空螺旋桨有限责任公司 | A kind of connection structure of composite material blade and metal petiole |
| CN108045559A (en) * | 2017-12-15 | 2018-05-18 | 惠阳航空螺旋桨有限责任公司 | A kind of composite material blade blade root fastenings structure |
| CN208669496U (en) * | 2018-07-10 | 2019-03-29 | 江苏新扬新材料股份有限公司 | Integrated molding composite material blade structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6676080B2 (en) * | 2000-07-19 | 2004-01-13 | Aero Composites, Inc. | Composite airfoil assembly |
| US8801386B2 (en) * | 2008-04-14 | 2014-08-12 | Atlantis Resources Corporation Pte Limited | Blade for a water turbine |
| US7963747B2 (en) * | 2009-04-02 | 2011-06-21 | General Electric Company | Braided wind turbine blades and method of making same |
| JP2011032988A (en) * | 2009-08-05 | 2011-02-17 | Nitto Denko Corp | Foam filler for wind turbine generator blade, foam filling part for wind turbine generator blade, wind turbine generator blade, wind turbine generator, and method of manufacturing wind turbine generator blade |
| GB201307176D0 (en) * | 2013-04-22 | 2013-05-29 | Rolls Royce Plc | Propeller blade retention |
-
2018
- 2018-07-10 CN CN201810749204.3A patent/CN108757270B/en active Active
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5346367A (en) * | 1984-12-21 | 1994-09-13 | United Technologies Corporation | Advanced composite rotor blade |
| CN88103525A (en) * | 1987-06-09 | 1988-12-28 | 国家工业宇航学会 | Composite material blade and manufacturing process thereof |
| RU2058249C1 (en) * | 1992-05-21 | 1996-04-20 | Акционерное общество Научно-производственное предприятие "Аэросила" | Propeller composite blade and method of its manufacture |
| US6305905B1 (en) * | 1999-05-05 | 2001-10-23 | United Technologies Corporation | Bolted-on propeller blade |
| JP2002357176A (en) * | 2001-03-27 | 2002-12-13 | Mitsubishi Heavy Ind Ltd | Composite material blade for wind power generating device |
| EP1914383A2 (en) * | 2006-10-18 | 2008-04-23 | Rolls-Royce Deutschland Ltd & Co KG | Fan blade of composite textile material |
| KR20110116288A (en) * | 2010-04-19 | 2011-10-26 | 김종민 | Lightweight blade with wingbox for wind power generating device, wingbox manufacturing tool and method |
| CN102490899A (en) * | 2011-12-14 | 2012-06-13 | 中国人民解放军总参谋部第六十研究所 | Composite rotor blade for unmanned helicopter and manufacturing method thereof |
| KR20140058176A (en) * | 2012-11-06 | 2014-05-14 | 한국항공우주산업 주식회사 | Blade of propeller for turboprop aircraft |
| CN203532319U (en) * | 2013-09-29 | 2014-04-09 | 尹天舒 | Counter-rotating fan blade of mine fan |
| CN103982463A (en) * | 2014-05-28 | 2014-08-13 | 航天材料及工艺研究所 | Composite material blade for wind tunnel |
| CN104358708A (en) * | 2014-08-19 | 2015-02-18 | 航天材料及工艺研究所 | Carbon fiber composite foam core sandwich structure wind tunnel fan blade and molding method |
| CN104895834A (en) * | 2015-06-01 | 2015-09-09 | 郑伟 | Propeller with metal propeller handle and manufacture technology of same |
| CN107939619A (en) * | 2017-12-04 | 2018-04-20 | 惠阳航空螺旋桨有限责任公司 | A kind of connection structure of composite material blade and metal petiole |
| CN108045559A (en) * | 2017-12-15 | 2018-05-18 | 惠阳航空螺旋桨有限责任公司 | A kind of composite material blade blade root fastenings structure |
| CN208669496U (en) * | 2018-07-10 | 2019-03-29 | 江苏新扬新材料股份有限公司 | Integrated molding composite material blade structure |
Non-Patent Citations (1)
| Title |
|---|
| 基于参数化组件描述的复合材料桨叶结构设计;杨建灵;张丽艳;方永红;黄文俊;周少华;;南京航空航天大学学报(第05期);全文 * |
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