CN108045559A - A kind of composite material blade blade root fastenings structure - Google Patents
A kind of composite material blade blade root fastenings structure Download PDFInfo
- Publication number
- CN108045559A CN108045559A CN201711359909.6A CN201711359909A CN108045559A CN 108045559 A CN108045559 A CN 108045559A CN 201711359909 A CN201711359909 A CN 201711359909A CN 108045559 A CN108045559 A CN 108045559A
- Authority
- CN
- China
- Prior art keywords
- blade root
- carbon
- crossbeam
- composite material
- metal
- 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.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 20
- 239000002184 metal Substances 0.000 claims abstract description 40
- 229910052751 metal Inorganic materials 0.000 claims abstract description 40
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 27
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 26
- 239000000835 fiber Substances 0.000 claims abstract description 13
- 238000004804 winding Methods 0.000 claims abstract description 10
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 7
- 239000004917 carbon fiber Substances 0.000 claims abstract description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000006260 foam Substances 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 239000004744 fabric Substances 0.000 abstract description 2
- 239000000463 material Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011203 carbon fibre reinforced carbon Substances 0.000 description 1
- 238000005119 centrifugation Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
Classifications
-
- 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
-
- 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
- B64C11/02—Hub construction
- B64C11/04—Blade mountings
- B64C11/06—Blade mountings for variable-pitch blades
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Abstract
The invention belongs to Design of Mechanical Structure, are related to a kind of composite material blade blade root fastenings structure.Carbon crossbeam is first laid on metal blade root, carbon crossbeam is made of multilayer carbon fiber unidirectional cloth and satin by the present invention to realize being reliably connected for multiple material main load-bearing part carbon crossbeam and metal blade root；Carbon fiber is wound in metal blade root curved surfaces again, carbon crossbeam and metal blade root are fixed together.When the propeller rotates, rotation brings centrifugal load and aerodynamic loading to be transferred at blade root, the winding of the radian shape and fiber of metal blade root can anti-blocking crossbeam abjection, and then avoid the damage of composite material blade.Blade root fastenings structure is reduced by original part to a part, the configuration of the present invention is simple, light-weight, good manufacturability, and then greatlys save manufacture cost, hence it is evident that is increased economic efficiency.
Description
Technical field
The invention belongs to Design of Mechanical Structure, are related to a kind of composite material blade blade root fastenings structure.
Background technology
Propeller is mainly made of metal propeller hub and composite material blade, sees Fig. 1.For ensure take off, climb, cruise,
Under all flight conditions such as landing, properller can keep maximal efficiency, and propeller generally can all be designed as automatic adjustable-pitch
Propeller, i.e.,：When state of flight changes, there is the movement rotated around own axes in blade.And propeller hub and there is no this side
To rotary motion, it is therefore desirable between blade and propeller hub centration axis increase bearing connection.Since composite material can not meet
The high-precision size of bearing fit is, it is necessary in composite material blade root built-in metal blade root.
Composite material blade will not be thrown away when therefore, to ensure propeller works, and then serious shadow is caused to flight safety
It rings, it is necessary to rationally design the connection structure between metal blade root and composite material blade.Existing blade root fastenings structure is shown in Fig. 2,
12 parts are included altogether.The major defect of this structure is complicated, weight is big, shaping and assembly process process are poor.
The content of the invention
The object of the invention：
Technical solution of the present invention：A kind of composite material blade blade root fastenings structure, which is characterized in that including metal blade root 1,
Carbon crossbeam 2, blade root winding fiber 3, covering 4 and foam 5；Carbon crossbeam 2 is laid on 1 surface of metal blade root, and foam 5 is mounted on upper and lower two
Among a carbon crossbeam 2, blade root winding fiber 3 is wrapped in 2 outside of carbon crossbeam, and all parts are rolled into an entirety by covering 4, gold
Belonging to blade root includes radian shape 6 and airfoil section 7.
The metal blade root 1 is column structure, and center is equipped with the stepped hole with propeller hub cooperation, and end face surrounding has been evenly distributed with loss of weight
Hole.
1 top of metal blade root is equipped with boss.
The carbon crossbeam 2 is thin-wall case, and cavity shape is consistent with metal blade root 1, and one is synthetic by 2 carbon crossbeams 2
A hood-like structure of entirety is fitted in the outer surface of metal blade root 1.
Blade root winding fiber 3 is a kind of carbon fiber, trade mark T700SC-12000-50C.
Beneficial effects of the present invention：The present invention is to realize reliable the connecting of multiple material main load-bearing part carbon crossbeam and metal centering axle sleeve
It connects, first carbon crossbeam is laid on metal blade root, carbon crossbeam is made of multilayer carbon fiber unidirectional cloth and satin；Again in metal leaf
Root arcuate surfaces wind carbon fiber, and carbon crossbeam and metal blade root are fixed together.When the propeller rotates, rotation brings centrifugation
Load and aerodynamic loading are transferred at blade root, the winding of the radian shape and fiber of metal blade root can anti-blocking beam abjection, and then
Avoid the damage of composite material blade.Blade root fastenings structure is reduced by original 12 parts to 5 parts, structure letter of the present invention
Single, light-weight, good manufacturability, and then greatly save manufacture cost, hence it is evident that it increases economic efficiency.
Description of the drawings
Fig. 1 --- prior art propeller arrangement schematic diagram
Fig. 2 --- prior art blade root fastenings structure diagram
Fig. 3 --- blade root fastenings structure diagram of the present invention
Wherein, 1- metals blade root, 2- carbon crossbeams, 3- blade roots winding fiber, 4- coverings, 5- foams
Fig. 4 --- metal leaf and root structure schematic diagram
Wherein, 6- is radian shape, and 7- is airfoil section
Specific embodiment
The present invention is further described below in conjunction with the accompanying drawings：
A kind of composite material and the connection structure of metal blade root, are shown in Fig. 3.The connection structure by metal blade root 1, carbon crossbeam 2,
Blade root winding fiber 3, covering 4 and foam 5 form.Metal blade root 1 plays the role of connecting metal propeller hub and composite material blade,
Carbon crossbeam 2 is laid on 1 surface of metal blade root for bearing the load generated during propeller works, and foam 5 is as the structure
Sandwich bears shear-type load, and carbon crossbeam 2 is fixed on metal blade root by blade root winding fiber 3, and all parts are rolled by covering 4
One entirety.The radian shape 6 of metal blade root 1 winds 7 collective effect of fiber with blade root, plays the role of fixed carbon crossbeam 2；For
Prevent from assembling, dismantle and use during composite material blade opposing metallic blade root rotate, added on metal blade root
Airfoil section 7, is shown in Fig. 4；Metal blade root 1 is column structure, and center is equipped with the stepped hole with propeller hub cooperation, and end face surrounding, which has been evenly distributed with, to be subtracted
Repeated hole；1 top of metal blade root is equipped with boss, reduces stiffness variation, increases load carrying capacity.Carbon crossbeam 2 is thin-wall case, interior
Chamber shape is consistent with metal blade root 1, is synthetic into a hood-like structure of entirety by 2 carbon crossbeams 2, is fitted in metal blade root 1
Outer surface.Blade root winding fiber 3 is a kind of carbon fiber, trade mark T700SC-12000-50C.
The blade root fastenings structure of the present invention is reduced by original 12 parts to 5 parts, the configuration of the present invention is simple, weight
Gently, good manufacturability, and then greatly save manufacture cost, hence it is evident that it increases economic efficiency.
Claims (5)
1. a kind of composite material blade blade root fastenings structure, which is characterized in that including metal blade root (1), carbon crossbeam (2), blade root
Wind fiber (3), covering (4) and foam (5)；Carbon crossbeam (2) is laid on metal blade root (1) surface, and foam (5) is mounted on upper and lower two
Among a carbon crossbeam (2), blade root winding fiber (3) is wrapped on the outside of carbon crossbeam (2), and all parts are rolled into one by covering (4)
A entirety, metal blade root include radian shape (6) and airfoil section (7).
2. composite material blade blade root fastenings structure as described in claim 1, which is characterized in that the metal blade root (1) is
Column structure, center are equipped with the stepped hole with propeller hub cooperation, and end face surrounding has been evenly distributed with lightening hole.
3. composite material blade blade root fastenings structure as claimed in claim 1 or 2, which is characterized in that the metal blade root (1)
There is top to be equipped with boss.
4. composite material blade blade root fastenings structure as claimed in claim 3, which is characterized in that the carbon crossbeam (2) is thin
Wall housing, cavity shape unanimously, a hood-like structure of entirety are synthetic by 2 carbon crossbeams (2) with metal blade root (1), are bonded
In the outer surface of metal blade root (1).
5. composite material blade blade root fastenings structure as claimed in claim 4, which is characterized in that the blade root winds fiber
(3) it is a kind of carbon fiber, trade mark T700SC-12000-50C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711359909.6A CN108045559A (en) | 2017-12-15 | 2017-12-15 | A kind of composite material blade blade root fastenings structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711359909.6A CN108045559A (en) | 2017-12-15 | 2017-12-15 | A kind of composite material blade blade root fastenings structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108045559A true CN108045559A (en) | 2018-05-18 |
Family
ID=62133465
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711359909.6A Pending CN108045559A (en) | 2017-12-15 | 2017-12-15 | A kind of composite material blade blade root fastenings structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108045559A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108673914A (en) * | 2018-07-25 | 2018-10-19 | 天津中车风电叶片工程有限公司 | A kind of metal blade root and nonmetallic blade connection structure and connection method |
| CN108757270A (en) * | 2018-07-10 | 2018-11-06 | 江苏新扬新材料股份有限公司 | Integrated molding composite material blade structure |
| CN109110124A (en) * | 2018-09-03 | 2019-01-01 | 南京航空航天大学 | A kind of new Main Rotor Blade |
| 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 |
| CN112550691A (en) * | 2021-01-06 | 2021-03-26 | 惠阳航空螺旋桨有限责任公司 | Helicopter rotor blade |
| 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 |
| CN114030637A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Method for cutting girder and girder belt of helicopter |
| EP4349708A1 (en) * | 2022-10-03 | 2024-04-10 | Ratier-Figeac SAS | Propeller blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4407635A (en) * | 1979-01-08 | 1983-10-04 | Trw Inc. | Aircraft propeller assembly with composite blades |
| US6443701B1 (en) * | 1999-01-29 | 2002-09-03 | MüHLBAUER LUFTFAHRTTECHNIK GMBH | Blade root for propeller and rotor blades |
| WO2012111518A1 (en) * | 2011-02-18 | 2012-08-23 | 三菱重工業株式会社 | Blade-root-forming piece for wind turbine blade, blade root structure for wind turbine blade using same, wind turbine blade, wind turbine and method for producing wind turbine blade |
| CN207875977U (en) * | 2017-12-15 | 2018-09-18 | 惠阳航空螺旋桨有限责任公司 | A kind of composite material blade blade root fastenings structure |
-
2017
- 2017-12-15 CN CN201711359909.6A patent/CN108045559A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4407635A (en) * | 1979-01-08 | 1983-10-04 | Trw Inc. | Aircraft propeller assembly with composite blades |
| US6443701B1 (en) * | 1999-01-29 | 2002-09-03 | MüHLBAUER LUFTFAHRTTECHNIK GMBH | Blade root for propeller and rotor blades |
| WO2012111518A1 (en) * | 2011-02-18 | 2012-08-23 | 三菱重工業株式会社 | Blade-root-forming piece for wind turbine blade, blade root structure for wind turbine blade using same, wind turbine blade, wind turbine and method for producing wind turbine blade |
| CN207875977U (en) * | 2017-12-15 | 2018-09-18 | 惠阳航空螺旋桨有限责任公司 | A kind of composite material blade blade root fastenings structure |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108757270A (en) * | 2018-07-10 | 2018-11-06 | 江苏新扬新材料股份有限公司 | Integrated molding composite material blade structure |
| CN108757270B (en) * | 2018-07-10 | 2024-01-09 | 江苏新扬新材料股份有限公司 | Integrated composite material blade structure |
| CN108673914A (en) * | 2018-07-25 | 2018-10-19 | 天津中车风电叶片工程有限公司 | A kind of metal blade root and nonmetallic blade connection structure and connection method |
| CN109110124A (en) * | 2018-09-03 | 2019-01-01 | 南京航空航天大学 | A kind of new Main Rotor Blade |
| 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 |
| CN112550691A (en) * | 2021-01-06 | 2021-03-26 | 惠阳航空螺旋桨有限责任公司 | Helicopter rotor blade |
| CN114030637A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Method for cutting girder and girder belt of helicopter |
| CN114030637B (en) * | 2021-11-19 | 2023-04-25 | 中国直升机设计研究所 | Helicopter girder and girder belt cutting method |
| EP4349708A1 (en) * | 2022-10-03 | 2024-04-10 | Ratier-Figeac SAS | Propeller blade |
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