CN115324931A - Fan blade, fan rotor subassembly and aeroengine - Google Patents
Fan blade, fan rotor subassembly and aeroengine Download PDFInfo
- Publication number
- CN115324931A CN115324931A CN202110511851.2A CN202110511851A CN115324931A CN 115324931 A CN115324931 A CN 115324931A CN 202110511851 A CN202110511851 A CN 202110511851A CN 115324931 A CN115324931 A CN 115324931A
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- CN
- China
- Prior art keywords
- rubber
- fan blade
- fan
- front edge
- 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.)
- Granted
Links
- 229920001971 elastomer Polymers 0.000 claims abstract description 53
- 239000000956 alloy Substances 0.000 claims abstract description 22
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 20
- 229910000838 Al alloy Inorganic materials 0.000 claims description 6
- 239000011247 coating layer Substances 0.000 claims description 3
- 229920002635 polyurethane Polymers 0.000 claims description 3
- 239000004814 polyurethane Substances 0.000 claims description 3
- 238000010276 construction Methods 0.000 abstract description 10
- 239000000463 material Substances 0.000 abstract description 10
- 238000010521 absorption reaction Methods 0.000 abstract description 3
- 230000007547 defect Effects 0.000 abstract description 3
- 239000007769 metal material Substances 0.000 abstract description 3
- 229910001234 light alloy Inorganic materials 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000004088 simulation Methods 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000004026 adhesive bonding Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 239000012792 core layer Substances 0.000 description 2
- 238000009958 sewing Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present disclosure relates to a fan blade, fan rotor subassembly and aeroengine, wherein, fan blade includes: a blade body configured to be composed of a lightweight alloy; and a rubber structure disposed at a leading edge of the blade body; wherein, the front edge is formed with a plurality of connecting bolts, and rubber construction sets up in the front edge through pouring parcel connecting bolt. The front edge of the fan blade main body is provided with the rubber structure, so that the rubber material can deform greatly after being stressed, and the defect that the local damage and the shedding are easily caused due to insufficient deformation and energy absorption of the metal material is overcome; and form a plurality of connecting bolts at the front edge, rubber construction sets up in the front edge through pouring parcel connecting bolt for connect light-duty alloy main part and rubber construction, on the fashioned basis of light-duty alloy main part, pour rubber materials, thereby guarantee light-duty alloy main part structure and rubber construction's reliability of being connected, guarantee that pneumatic appearance is continuous.
Description
Technical Field
The present disclosure relates to a fan blade, a fan rotor assembly and an aircraft engine.
Background
The statements herein merely provide background information related to the present disclosure and may not necessarily constitute prior art.
Large bypass ratio fan blades are key components of large passenger aircraft engines. The traditional solid fan blade has heavy weight, large centrifugal force and prominent flutter and vibration problems, and can not meet the requirements of design and low oil consumption of a large-passenger engine, and the titanium alloy wide-chord hollow fan blade and the carbon fiber composite fan blade are typical structures of the international large-bypass-ratio turbofan engine at present, but are protected by patents of main manufacturers of foreign aeroengines.
Lightweight alloys are ultra-strong lightweight structural metals with very high specific strength and specific modulus, or hardness ratios, such as high strength aluminum alloys, that are increasingly used in aircraft engine components, including fan blades.
However, although the performance of the aluminum alloy material can be greatly improved by a manufacturing process, the aluminum alloy material is still difficult to meet the design requirements when applied to the fan blade under bird impact load, so that the bird impact resistance of the fan blade needs to be optimized by structural design, and generally adopted optimization strategies include modes of strengthening, absorbing energy, setting weak link active control failure areas and the like.
The traditional scheme of the alloy edge-covered composite material blade needs to adopt a sewing or gluing scheme, so that the connection is unreliable, the structure deviation is easy to occur, and the continuity of the pneumatic appearance cannot be ensured.
Disclosure of Invention
One technical problem to be solved by the present disclosure is: provided are a fan blade, a fan rotor assembly and an aircraft engine, which can improve bird strike resistance and ensure continuity of aerodynamic configuration.
A fan blade is provided according to some embodiments of the present disclosure, including: a blade body configured to be composed of a lightweight alloy; and a rubber structure disposed at a leading edge of the blade body; wherein, the front edge is formed with a plurality of connecting bolts, and rubber construction sets up in the front edge through pouring parcel connecting bolt.
In some embodiments, the leading edge is formed with an internal cavity, the connecting bolt is located in the internal cavity, and the rubber structure is filled in the internal cavity.
In some embodiments, a rubber structure is cast around the leading edge, and the connecting peg is configured as a protrusion disposed on an outer wall surface of the leading edge.
In some embodiments, the lightweight alloy comprises an aluminum alloy.
In some embodiments, the rubber structure is disposed at a 10% to 90% area of the tip to the dovetail of the leading edge.
In some embodiments, the outer surface of the blade body is coated with a coating layer made of polyurethane.
According to some embodiments of the present disclosure, a fan rotor assembly is provided, comprising the aforementioned fan blade.
According to some embodiments of the present disclosure, an aircraft engine is provided, including the aforementioned fan rotor assembly.
According to the technical scheme, the rubber structure is arranged on the front edge of the fan blade main body, and the rubber material can deform greatly after being stressed, so that the defect that local damage and falling are easily caused due to insufficient deformation and energy absorption of the metal material is overcome; and form a plurality of connecting bolts at the front edge, rubber construction sets up in the front edge through pouring the parcel connecting bolt for connect light-duty alloy main part and rubber construction, on the fashioned basis of light-duty alloy main part, pour rubber materials, thereby guarantee light-duty alloy main part structure and rubber construction's connection reliability, guarantee that pneumatic appearance is continuous.
Drawings
In order to more clearly illustrate the embodiments of the present disclosure or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic view of the structure of an air intake end of some embodiments of an aircraft engine of the present disclosure;
FIG. 2 is a schematic structural view of some embodiments of the fan blade of the present disclosure;
FIG. 3 is a schematic structural view of a blade body in some embodiments of the fan blade of the present disclosure;
FIG. 4 is a schematic structural view of a rubber structure in some embodiments of fan blades of the present disclosure;
FIG. 5 is a schematic overall structural view of some embodiments of the fan blade of the present disclosure;
FIG. 6 is a schematic structural view of a blade body in other embodiments of fan blades of the present disclosure;
FIG. 7 is a schematic view of a rubber structure in further embodiments of fan blades of the present disclosure;
FIG. 8 is a schematic overall view of other embodiments of the fan blade of the present disclosure;
FIG. 9 is a schematic view of bird strike simulation results for a prior art fan blade;
FIG. 10 is a schematic view of bird strike simulation results for some embodiments of the fan blade of the present disclosure;
FIG. 11 is a schematic view of bird strike simulation results for further embodiments of the fan blade of the present disclosure.
Description of the reference numerals
1. A blade main body; 2. a leading edge; 11. a light alloy; 12. an outer wall surface; 13. a connecting bolt; 14. a rubber structure; 15. and connecting the holes.
Detailed Description
Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. The description of the exemplary embodiments is merely illustrative and is in no way intended to limit the disclosure, its application, or uses. The present disclosure may be embodied in many different forms and is not limited to the embodiments herein. These embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that: the relative arrangement of parts and steps, the composition of materials, numerical expressions and numerical values set forth in these embodiments are to be construed as merely illustrative, and not as limitative, unless specifically stated otherwise.
The use of "first," "second," and similar terms in this disclosure is not intended to indicate any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element preceding the word covers the element listed after the word, and does not exclude the possibility that other elements are also covered. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.
In the present disclosure, when a specific device is described as being located between a first device and a second device, there may or may not be intervening devices between the specific device and the first device or the second device. When a particular device is described as being coupled to other devices, the particular device may be directly coupled to the other devices without intervening devices or may be directly coupled to the other devices with intervening devices.
All terms used in the present disclosure have the same meaning as understood by one of ordinary skill in the art to which the present disclosure belongs, unless otherwise specifically defined. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate.
Referring to fig. 1-8, a fan blade according to some embodiments of the present disclosure includes: the blade comprises a blade body 1 and a rubber structure 14, wherein the blade body 1 is configured to be made of light alloy 11 and mainly bear aerodynamic force and centrifugal force under normal working conditions; the rubber structure 14 is arranged at the front edge 2 of the blade body 1; the front edge 2 is formed with a plurality of connecting bolts 13, and a rubber structure 14 is provided to the front edge 2 by casting the connecting bolts 13.
In the exemplary embodiment, the rubber structure 14 is arranged on the front edge 2 of the fan blade main body 1, so that the rubber material can deform greatly after being stressed, and the defect that the local damage and the shedding are easily caused due to insufficient deformation and energy absorption of the metal material is overcome; and form a plurality of connecting bolt 13 at leading edge 2, rubber construction 14 sets up in the leading edge through pouring parcel connecting bolt 13 for connect light-duty alloy main part, on the fashioned basis of light-duty alloy main part, pours the rubber material, reaches the connection purpose between two kinds of different material structures, thereby guarantees light-duty alloy main part structure and rubber construction 14's connection reliability, guarantees that aerodynamic configuration is continuous.
As shown in fig. 3 to 8, the contact surface between the blade body 1 and the rubber structure 14 is provided with a connecting bolt 13, and after the rubber material is poured, the rubber material and the light alloy naturally form a connection without additional sewing or gluing.
The combination of the rubber structure 14 and the lightweight alloy 11 forms a complete leading edge structure, which may be cast-wrapped or cast-wrapped, as shown in fig. 3-5, in some embodiments, the leading edge 2 is formed with an inner cavity, the connecting bolt 13 is located in the inner cavity, the rubber structure 14 is cast and filled in the inner cavity, that is, the lightweight alloy 11 covers the core layer of the rubber structure 14, and the rubber structure 14 is formed with a connecting hole 15 for the connecting bolt 13 to pass through.
As shown in fig. 6 to 8, in some embodiments, the rubber structure 14 is cast to wrap the front edge 2, the connection bolts 13 are configured as protrusions arranged on the outer wall surface 12 of the front edge 2, that is, the rubber structure 14 covers the core layer of the lightweight alloy 11, and the rubber structure 14 is formed with connection holes 15 for the connection bolts 13 to pass through.
The blade body 1 is made of light alloy forged pieces/is formed by extrusion, the rubber structure 14 is poured in a pouring mode in the middle hollow area or the surface area of the blade body 1, and the metal body is provided with the connecting bolt 13 for fixing the light alloy 11 and the rubber structure 14, so that the process complexity can be greatly reduced, the cost can be reduced, and the process stability can be improved.
In some embodiments, the lightweight alloy 11 comprises an aluminum alloy, ensuring structural strength.
As shown in fig. 2, in some embodiments, the rubber structure 14 is disposed at a 10% -90% region from the blade tip of the leading edge 2 to the tenon, and the size of the failure region after bird strike can be controlled by adjusting the size of the rubber structure, so as to meet the bird strike resistance test requirements of fan blades of different sizes.
In some embodiments, the outer surface of the blade body 1 is coated with a coating layer made of polyurethane, improving the surface finish, increasing the wear and corrosion resistance.
As shown in fig. 9 to 11, through simulation analysis, when the bird hitting energy is high to a certain degree, the rubber structure falls off and is removed from the fan along with the bird body, and even if the rubber structure collides with other structures such as a fan casing in the removing process, the rubber structure is soft, the problem that the rubber structure is the same as or non-contained in a pure metal structure cannot be caused.
According to some embodiments of the present disclosure, a fan rotor assembly is provided, which includes the fan blade, and accordingly, the fan rotor assembly also has the above-mentioned beneficial effects.
According to some embodiments of the present disclosure, an aircraft engine is provided, which includes the fan rotor assembly, and accordingly, the aircraft engine also has the beneficial technical effects.
Thus, various embodiments of the present disclosure have been described in detail. Some details that are well known in the art have not been described in order to avoid obscuring the concepts of the present disclosure. It will be fully apparent to those skilled in the art from the foregoing description how to practice the presently disclosed embodiments.
Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the foregoing examples are for purposes of illustration only and are not intended to limit the scope of the present disclosure. It will be understood by those skilled in the art that various changes may be made in the above embodiments or equivalents may be substituted for elements thereof without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.
Claims (8)
1. A fan blade, comprising:
a blade body (1) configured to be composed of a lightweight alloy (11); and
a rubber structure (14) provided to the leading edge (2) of the blade body (1);
wherein a plurality of connecting bolts (13) are formed on the front edge (2), and the rubber structure (14) is arranged on the front edge (2) by pouring and wrapping the connecting bolts (13).
2. A fan blade as claimed in claim 1, characterised in that the leading edge (2) is formed with an internal cavity in which the connection peg (13) is located, the rubber structure (14) being filled.
3. The fan blade of claim 1, characterized in that the rubber structure (14) is cast around the leading edge (2), the connecting peg (13) being configured as a protrusion provided on an outer wall surface (12) of the leading edge (2).
4. A fan blade as set forth in claim 1, characterized in that said lightweight alloy (11) comprises an aluminum alloy.
5. The fan blade of claim 1, characterized in that the rubber structure (14) is provided at the tip-to-tenon 10-90% of the area of the leading edge (2).
6. A fan blade according to claim 1, characterized in that the outer surface of the blade body (1) is coated with a coating layer made of polyurethane.
7. A fan rotor assembly comprising a fan blade as claimed in any one of claims 1 to 6.
8. An aircraft engine comprising the fan rotor assembly of claim 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110511851.2A CN115324931B (en) | 2021-05-11 | 2021-05-11 | Fan blade, fan rotor assembly and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110511851.2A CN115324931B (en) | 2021-05-11 | 2021-05-11 | Fan blade, fan rotor assembly and aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115324931A true CN115324931A (en) | 2022-11-11 |
| CN115324931B CN115324931B (en) | 2024-01-30 |
Family
ID=83912480
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110511851.2A Active CN115324931B (en) | 2021-05-11 | 2021-05-11 | Fan blade, fan rotor assembly and aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115324931B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4251189A (en) * | 1978-05-13 | 1981-02-17 | Heidolph & Zinsser Gmbh | Fan |
| GB2154286A (en) * | 1984-02-13 | 1985-09-04 | Gen Electric | Hollow laminated airfoil |
| US4895491A (en) * | 1988-06-17 | 1990-01-23 | Environmental Elements Corp. | Fan blade protection system |
| US5210946A (en) * | 1992-06-26 | 1993-05-18 | Hudson Products Corporation | Leading edge protection for fan blade |
| CN201679746U (en) * | 2010-04-10 | 2010-12-22 | 佛山市顺德区泛仕达机电有限公司 | Low-noise axial flow fan |
| GB2484697A (en) * | 2010-10-20 | 2012-04-25 | Greenwood Air Man Ltd | Fan Impeller |
| CN109026837A (en) * | 2018-10-16 | 2018-12-18 | 王永挺 | A kind of exhaust fan and its fan leaf |
| CN209100311U (en) * | 2018-10-22 | 2019-07-12 | 江苏精彩风机制造有限公司 | A kind of chemical plant dustproof and anti-explosion blower |
-
2021
- 2021-05-11 CN CN202110511851.2A patent/CN115324931B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4251189A (en) * | 1978-05-13 | 1981-02-17 | Heidolph & Zinsser Gmbh | Fan |
| GB2154286A (en) * | 1984-02-13 | 1985-09-04 | Gen Electric | Hollow laminated airfoil |
| US4895491A (en) * | 1988-06-17 | 1990-01-23 | Environmental Elements Corp. | Fan blade protection system |
| US5210946A (en) * | 1992-06-26 | 1993-05-18 | Hudson Products Corporation | Leading edge protection for fan blade |
| CN201679746U (en) * | 2010-04-10 | 2010-12-22 | 佛山市顺德区泛仕达机电有限公司 | Low-noise axial flow fan |
| GB2484697A (en) * | 2010-10-20 | 2012-04-25 | Greenwood Air Man Ltd | Fan Impeller |
| CN109026837A (en) * | 2018-10-16 | 2018-12-18 | 王永挺 | A kind of exhaust fan and its fan leaf |
| CN209100311U (en) * | 2018-10-22 | 2019-07-12 | 江苏精彩风机制造有限公司 | A kind of chemical plant dustproof and anti-explosion blower |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115324931B (en) | 2024-01-30 |
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