CN115111191B - Fan blade and aeroengine - Google Patents

Fan blade and aeroengine Download PDF

Info

Publication number
CN115111191B
CN115111191B CN202110307446.9A CN202110307446A CN115111191B CN 115111191 B CN115111191 B CN 115111191B CN 202110307446 A CN202110307446 A CN 202110307446A CN 115111191 B CN115111191 B CN 115111191B
Authority
CN
China
Prior art keywords
fan blade
blade
leading edge
laminations
impact
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.)
Active
Application number
CN202110307446.9A
Other languages
Chinese (zh)
Other versions
CN115111191A (en
Inventor
柴象海
倪晓琴
刘传欣
欧阳胜超
龚煦
史同承
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Commercial Aircraft Engine Co Ltd
Original Assignee
AECC Commercial Aircraft Engine Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AECC Commercial Aircraft Engine Co Ltd filed Critical AECC Commercial Aircraft Engine Co Ltd
Priority to CN202110307446.9A priority Critical patent/CN115111191B/en
Publication of CN115111191A publication Critical patent/CN115111191A/en
Application granted granted Critical
Publication of CN115111191B publication Critical patent/CN115111191B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F04D29/382—Flexible blades
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses a fan blade and an aeroengine. The fan blade includes a leading edge. And the leading edge includes a blade body and a cushioning layer. Wherein the cushioning layer comprises a plurality of laminations arranged on the outer surface of the blade body. And adjacent laminations are at least partially stacked and arranged so that the laminations move when the leading edge is impacted. When the fan blade is impacted by foreign matters such as bird strike, at least part of the lamination of the buffer layer moves under the action of the external force, so that concentrated load generated by impact is diffused, and a larger area of the fan blade bears the impact load together, thereby reducing local stress concentration and improving the impact resistance.

Description

Fan blade and aeroengine
Technical Field
The invention relates to a fan blade and an aeroengine.
Background
The take-off and landing process of an aircraft is the stage where bird strikes are most likely to occur. Before the aircraft appears, the flying of birds in the air and the activities of human beings are not overlapped, the damage is not caused, the situation is changed due to the appearance of the aircraft, the flying speed of the aircraft is high, the aircraft is often damaged greatly after being collided with the birds, and the aircraft is crashed seriously, so that the bird strike is one of the important factors threatening the aviation safety at present. Particularly for turbofan engines, birds are often sucked into the air inlet, deform the blades of the turbine engine, or jam the engine, causing the engine to stop or even fire, so that the damage of the birds to the power system of the aircraft is often fatal, and can directly lead to the stall and crash of the aircraft.
The bird strike damage of the turbofan engine refers to the damage of the aircraft engine caused by the collision of the aircraft with the bird during the flight. The bird mass is small, but the relative speed of the aircraft and the bird is high, so that certain key parts can be damaged and the flying safety is endangered, the design and the strength of the turbofan engine are strictly required, and a bird strike test is carried out to ensure the safety. The engine should be able to withstand a certain number and quality of bird strikes while still maintaining the required performance. In recent years, according to actual demands, stricter bird strike regulations have been proposed for large-sized civil engines.
Most birds are characterized by small, lightweight, and thus the destruction of the bird strike is primarily due to the speed of the aircraft rather than the mass of the bird itself. With the development of aviation technology, the speed of an artificial aircraft is continuously improved, according to the momentum theorem, a bird with the speed of 0.45 kg collides with an aircraft with the speed of 80 km per hour to generate 1500 newton force, collides with an aircraft with the speed of 960 km per hour to generate 21.6 kilonewton force, and the high-speed movement enables the destructive power of bird striking to reach a striking degree.
The fan blade of the turbofan engine has higher rotating speed, so that the borne bird strike load is larger, the bird strike resistance of the fan blade is guaranteed by adopting a titanium alloy material or a titanium alloy metal reinforcing edge, but along with the improvement of the economic requirement of the engine, higher requirements are put forward on the reduction of the weight of the aeroengine, and in order to lighten the weight of the fan blade, the problem of design is solved how to ensure the bird strike resistance of the fan blade after the thickness of the fan blade is thinned or light alloy is adopted.
It should be noted that the statements in this background section merely provide background information related to the present disclosure and may not necessarily constitute prior art.
Disclosure of Invention
The invention provides a fan blade and an aeroengine, which are used for improving the shock resistance of the fan blade.
A first aspect of the invention provides a fan blade comprising a leading edge comprising:
A blade body; and
The buffer layer comprises a plurality of lamination sheets arranged on the outer surface of the blade body, and the adjacent lamination sheets are at least partially overlapped, so that when the front edge is impacted, the lamination sheets move.
In some embodiments, the laminate is fish scale shaped.
In some embodiments, the leading edge further comprises a coating disposed on an outer surface of the buffer layer.
In some embodiments, the coating is releasably disposed upon impact.
In some embodiments, the material of the coating is ABS plastic or VPS silicone.
In some embodiments, the outer surface of the laminate has micro-holes.
In some embodiments, the material of the laminate is a shape memory alloy.
In some embodiments, the fan blade is made by 3D printing.
In some embodiments, the fan blade further comprises a blade body comprising a blade body and a cushioning layer.
A second aspect of the invention provides an aeroengine comprising a fan blade as described above.
In accordance with aspects provided by the present invention, a fan blade includes a leading edge. And the leading edge includes a blade body and a cushioning layer. Wherein the cushioning layer comprises a plurality of laminations arranged on the outer surface of the blade body. And adjacent laminations are at least partially stacked and arranged so that the laminations move when the leading edge is impacted. When the fan blade is impacted by foreign matters such as bird strike, at least part of the lamination of the buffer layer moves under the action of the external force, so that concentrated load generated by impact is diffused, and a larger area of the fan blade bears the impact load together, thereby reducing local stress concentration and improving the impact resistance.
Other features of the present invention and its advantages will become apparent from the following detailed description of exemplary embodiments of the invention, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute a limitation on the application. In the drawings:
fig. 1 is a schematic structural view of an aeroengine according to an embodiment of the present invention.
Fig. 2 is a schematic view of the fan blade of fig. 1 without a coating.
Fig. 3 is a schematic cross-sectional view of the fan blade shown in fig. 2.
FIG. 4 is a schematic view of a partial cross-sectional structure of the fan blade of FIG. 1 when provided with a coating.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the authorization specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
Spatially relative terms, such as "above … …," "above … …," "upper surface on … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations "above … …" and "below … …". The device may also be positioned in other different ways and the spatially relative descriptions used herein are construed accordingly.
As shown in fig. 1, in some embodiments, the aircraft engine includes a nacelle 5, fan blades 1, low pressure compressor rotor blades 2, low pressure compressor stator blades 3, and outlet guide vanes 4. The air intake direction is shown by the arrows in the figure. In particular, in one embodiment, the fan blade 1 is a first stage rotor blade of a large bypass ratio turbofan engine.
Referring to fig. 2 and 3, in some embodiments, the fan blade 1 includes a leading edge 11. And the leading edge 11 includes a blade body 111 and a cushioning layer 112. Wherein the cushioning layer 112 includes a plurality of laminations 1121 arranged in an aligned manner on the outer surface of the blade body 111. And adjacent laminations 1121 are at least partially stacked, the laminations 1121 moving when the leading edge 11 is impacted.
When the fan blade 1 is impacted by a foreign object such as bird strike, at least part of the lamination 1121 of the buffer layer 112 moves under the action of the external force, so that the concentrated load generated by the impact is diffused, and the larger area of the fan blade bears the impact load together, thereby reducing the local stress concentration and improving the impact resistance.
The fan blade 1 of the above embodiment increases the impact resistance of the fan blade 1 by providing the cushioning layer 112. On this basis, the design of the fan blade can be made thinner or lighter materials can be selected so as to reduce the weight of the whole fan blade. The interior of the fan blade may be formed as a hollow space or the hollow space may be filled with a lightweight material to reduce the weight.
In some embodiments, referring to fig. 2, the shape of the laminate 1121 is a biomimetic fish scale. The fish scales are used as protective armor for fish, have the characteristics of ultra-thin, ultra-light and the like, and have good flexibility. Some embodiments design the shape of the lamination 1121 as a bionic fish scale shape, and on the basis of fully inheriting the physical characteristics of the fish scale, the lamination can serve as an impact-resistant structure and can play a role in effectively diffusing impact and concentrating loads.
In other embodiments, the lamination may be in other shapes, such as a circle, an ellipse, a square, etc., as long as a plurality of lamination sheets are arranged on the outer surface of the blade body 111 and have portions overlapping each other so that the entire buffer layer 112 is in a multi-layered laminated structure in the thickness direction, so as to spread the concentrated load generated by the impact of foreign objects such as bird strike.
In some embodiments, the outer surface of laminate 1121 has micro-holes. The micropores are concave hole structures imitating the surfaces of fish scales. By providing micro-holes in the outer surface of the lamination 1121, frictional resistance of the foreign objects to the surface of the fan blade 1 can be reduced, thereby reducing adhesion of the foreign objects and increasing the chordwise velocity component along the blade. It should be explained here that the micropores are microstructures provided on the laminate 1121.
In some embodiments, the material of lamination 1121 is a shape memory alloy. The memory alloy has a shape memory effect, and deformation (low temperature phase) occurring at a relatively low temperature can be eliminated by heating up and restored to the original shape (high temperature phase) before deformation. In other embodiments, laminate 1121 may be made of other high plastic materials.
To ensure aerodynamic performance of the fan blade 1, it is desirable to smooth the outer surface of the fan blade, and in some embodiments, with reference to FIG. 4, the leading edge 11 further includes a coating 113 disposed on the outer surface of the buffer layer 112. The coating 113 is disposed on the outer surface of the buffer layer 112, and further covers the multi-layered laminated structure of the buffer layer 112, so that the outer surface of the fan blade 1 is smooth.
The coating 113 is a solid continuous film that is applied.
In some embodiments, the material of the coating 113 is ABS plastic or VPS silicone.
To exert a drag reducing effect on the micropores of the outer surface of the laminate 1121, in some embodiments, the coating 113 is disposed so as to be removable when subjected to an impact load.
In some embodiments, the fan blade 1 is made by 3D printing. The integrated processing of the fan blade 1 is realized through a 3D printing process, so that the processing cost can be reduced and the higher structural reliability can be ensured.
Referring to fig. 2, the fan blade further includes a blade body 12. Referring to FIG. 3, in some embodiments, the blade airfoil 12 includes only a blade body. But in other embodiments the blade body may also comprise a cushioning layer. Similarly, the cushioning layer structure may be provided at the tip, the trailing edge, or the like.
The structure of the fan blade according to an embodiment will be described in detail with reference to fig. 2 to 4.
As shown in fig. 2, the fan blade 1 of the present embodiment includes a leading edge 11 and a blade body 12. As shown in fig. 4, wherein the leading edge 11 comprises a blade body 111, a buffer layer 112 and a coating 113. The cushioning layer 112 includes a plurality of fish scale shaped laminations 1121 aligned along the outer surface of the blade body 111.
To illustrate the structure of the buffer layer 112, the coating 113 is removed in the fan blade illustrated in FIG. 2. As shown in fig. 2, a plurality of laminations 1121 are sequentially arranged on the outer surface of the blade body 111 in the direction from the leading edge to the trailing edge and from the root to the tip. And in the direction from the front edge to the rear edge, two adjacent laminations are staggered to form a fish scale arrangement similar to that of a fish body. The buffer layer is of a multi-layer laminated structure, and can diffuse concentrated loads generated by impact of foreign matters such as bird strike and the like, so that larger areas of the fan blades bear impact loads jointly, local stress concentration is reduced, and impact resistance is improved.
In some embodiments, the blade body 111 of the fan blade 1 may be a light alloy fan blade such as a titanium alloy metal blade, an aluminum alloy, or a resin-based carbon fiber composite material fan blade. The blade body 111 is used to provide the fan blade 1 with overall stiffness.
For metal blades, the cushioning layer structure may be applied to the leading edge of the blade, as well as to other portions of the blade. For composite fan blades, as shown in FIG. 4, the structure is applied to the wrapping of the leading edge of the blade. That is, the entire buffer layer is wrapped around the outer surface of the blade body 111 to form a wrapping.
In other embodiments, the buffer layer may also be provided on the outer surface of only one side of the blade body 111. For example, a cushioning layer may be provided on the outer surface of the blade body 111 near the outside of the nacelle 5, thereby serving to improve the impact.
In addition, the outer surface of the lamination 1121 of the present embodiment is provided with micro holes, which are concave holes for emulating the surface of fish scales, and function to reduce friction resistance between foreign objects and the surface of the fan blade. The coating 113 is made of ABS plastic, VPS silica gel and other materials, and is used for forming a smooth surface and guaranteeing aerodynamic performance.
The fan blade 1 realizes the integrated processing of the fan blade by adopting a 3D printing process, and has higher structural reliability and lower processing cost compared with the process of respectively processing the light alloy body and the high-strength alloy bordure and bonding/welding the bordure with the body.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same; while the invention has been described in detail with reference to the preferred embodiments, those skilled in the art will appreciate that: modifications may be made to the specific embodiments of the present invention or equivalents may be substituted for part of the technical features thereof; without departing from the spirit of the invention, it is intended to cover the scope of the invention as claimed.

Claims (10)

1. A fan blade, characterized by comprising a leading edge (11), said leading edge (11) comprising:
a blade body (111); and
The buffer layer (112) comprises a plurality of laminations (1121) which are arranged on the outer surface of the blade main body (111), and the adjacent laminations (1121) are at least partially overlapped, and in the direction from the front edge to the rear edge, the adjacent two laminations are staggered to form a fish scale arrangement, and when the front edge (11) is impacted, at least part of the laminations (1121) in the buffer layer (112) moves under the action of external force.
2. The fan blade according to claim 1, wherein the laminate (1121) is fish scale-like in shape.
3. A fan blade according to claim 1, wherein the leading edge (11) further comprises a coating (113) arranged on the outer surface of the buffer layer (112).
4. A fan blade according to claim 3, characterized in that the coating (113) is arranged to be releasable upon impact.
5. A fan blade according to claim 3, characterized in that the material of the coating (113) is ABS plastic or VPS silica gel.
6. The fan blade according to claim 1, wherein the outer surface of the laminate (1121) has micro-holes.
7. The fan blade according to claim 1, wherein the material of the laminate (1121) is a shape memory alloy.
8. The fan blade of claim 1, wherein the fan blade is made by 3D printing.
9. The fan blade of claim 1, further comprising a blade body (12), the blade body (12) comprising a blade body and a cushioning layer.
10. An aeroengine comprising a fan blade as claimed in any one of claims 1 to 9.
CN202110307446.9A 2021-03-23 2021-03-23 Fan blade and aeroengine Active CN115111191B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110307446.9A CN115111191B (en) 2021-03-23 2021-03-23 Fan blade and aeroengine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110307446.9A CN115111191B (en) 2021-03-23 2021-03-23 Fan blade and aeroengine

Publications (2)

Publication Number Publication Date
CN115111191A CN115111191A (en) 2022-09-27
CN115111191B true CN115111191B (en) 2024-05-14

Family

ID=83323998

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110307446.9A Active CN115111191B (en) 2021-03-23 2021-03-23 Fan blade and aeroengine

Country Status (1)

Country Link
CN (1) CN115111191B (en)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1320539A (en) * 1970-12-10 1973-06-13 Secr Defence Aerofoil-shaped blade for a fluid flow machine
US4318672A (en) * 1978-11-06 1982-03-09 Nordisk Ventilator Co. A/S Particle erosion resistant covering for fan blade leading edge
US5591009A (en) * 1995-01-17 1997-01-07 General Electric Company Laser shock peened gas turbine engine fan blade edges
CN109026836A (en) * 2018-07-19 2018-12-18 广东美的厨房电器制造有限公司 Fan and preparation method thereof, fan component and electric appliance
CN110168197A (en) * 2017-02-08 2019-08-23 株式会社Ihi Fan blade

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7510777B2 (en) * 2005-12-16 2009-03-31 General Electric Company Composite thermal barrier coating with improved impact and erosion resistance

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1320539A (en) * 1970-12-10 1973-06-13 Secr Defence Aerofoil-shaped blade for a fluid flow machine
US4318672A (en) * 1978-11-06 1982-03-09 Nordisk Ventilator Co. A/S Particle erosion resistant covering for fan blade leading edge
US5591009A (en) * 1995-01-17 1997-01-07 General Electric Company Laser shock peened gas turbine engine fan blade edges
CN110168197A (en) * 2017-02-08 2019-08-23 株式会社Ihi Fan blade
CN109026836A (en) * 2018-07-19 2018-12-18 广东美的厨房电器制造有限公司 Fan and preparation method thereof, fan component and electric appliance

Also Published As

Publication number Publication date
CN115111191A (en) 2022-09-27

Similar Documents

Publication Publication Date Title
US8066222B2 (en) Energy absorbing impact band
CN106585948B (en) A kind of empty amphibious unmanned vehicle of water
Ghori et al. The role of advanced polymer materials in aerospace
EP2730501B1 (en) Rotational annular airscrew with integrated acoustic arrester
EP2457821B1 (en) Compliant panel for aircraft
Huda et al. Materials selection in design of structures and engines of supersonic aircrafts: A review
US8393567B2 (en) Method and apparatus for reducing aircraft noise
US8240125B2 (en) Thrust vectoring system and method
EP2971528B1 (en) Hollow fan blade with extended wing sheath
CN109386500B (en) Low noise airfoil for open rotor
JPH08210102A (en) Combined blade
EP2551197B1 (en) Reduced flow field velocity for a propulsor
EP3112650B1 (en) Inlet flow restrictor
US9708030B1 (en) Impact-energy tolerant method and structures
CN115111191B (en) Fan blade and aeroengine
CA3030269C (en) A shrouding for interacting with at least one rotor assembly
CN107407154A (en) Frangible composite airfoil
Clark et al. Aircraft system noise assessment of the NASA D8 subsonic transport concept
Handschuh et al. Materials, manufacturing and test development of a composite fan blade leading edge subcomponent for improved impact resistance
CN115111192B (en) Fan blade and aeroengine
JP3550104B2 (en) Wing reinforcement
Fraley Design, Manufacturing, and Integration of Fins for 2017-2018 OSU ESRA 30k Rocket
Lovell Military vortices
CN216618008U (en) Aircraft engine fan blade
Chao et al. A conceptual analysis of an aircraft with rear-mounted open rotor engines

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant