CN113895412B - Heat dissipation assembly and airplane wheel - Google Patents
Heat dissipation assembly and airplane wheel Download PDFInfo
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- CN113895412B CN113895412B CN202111352774.7A CN202111352774A CN113895412B CN 113895412 B CN113895412 B CN 113895412B CN 202111352774 A CN202111352774 A CN 202111352774A CN 113895412 B CN113895412 B CN 113895412B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T5/00—Vehicle modifications to facilitate cooling of brakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Braking Arrangements (AREA)
Abstract
The application provides a heat dissipation assembly and an aircraft wheel. The heat dissipation assembly comprises two annular pieces and a plurality of blades; the two annular parts are respectively a first annular part and a second annular part; circular openings are formed at two ends of each annular piece, the first annular piece is sleeved outside the second annular piece, and the central lines of the two annular pieces are positioned on the same straight line; a plurality of vanes spaced between the first end of the first annular member and the first end of the second annular member; when the heat dissipation assembly is rotated, air outside the heat dissipation assembly is driven by the blades to flow in a direction perpendicular to the surfaces of the blades, and airflow flowing from the first end to the second end of the second annular member is generated inside the second annular member. The structure increases the contact area between the heat shield and the air, and accelerates the convection heat dissipation efficiency. Under aircraft quiescent condition, first loop element outside is the curved surface structure of horn mouth formula, does benefit to steam and outwards emits to the air from brake equipment.
Description
Technical Field
The application relates to the technical field of airplane wheel braking, in particular to a heat dissipation assembly and an airplane wheel.
Background
After the airplane lands and brakes, the friction of a brake disc generates a large amount of heat, the temperature is rapidly increased and is transferred to the airplane wheel and the axle, and when the temperature is too high, the tire explosion, the axle overheating or the failure of equipment in the axle can be caused. And when the aircraft is dispatched again when passing a station, the aircraft can take off only after the braking temperature is cooled to a certain value for safety requirement, and the heat dissipation of the aircraft wheel braking device is slow, so that the operation efficiency is influenced.
Some aviation enterprises in foreign countries have studied on the heat dissipation performance of heat shields, for example, the patent document US20170106973a1 of Goodrich, which enhances the heat dissipation effect by perforating holes on the heat shield to increase air convection. In EP2503176a1, the openings in the heat shield end extension ring are connected to allow the air to flow in and absorb heat and then to be discharged, however, the air flow introduced through the openings in the heat shield end extension ring has no axial velocity, the air flow mainly occurs in the vicinity of the extension ring, when the brake disc is worn more, the heat reservoir is far away from this region, the air convection near the brake disc is small, and the heat dissipation effect is limited.
Disclosure of Invention
The application provides a radiator unit and aircraft wheel for improve the radiating efficiency of the hot storehouse of aircraft brake, thereby effectively prevent bad phenomena such as tire burst, shaft overheat and in-wheel equipment inefficacy, and shorten the time that the brake part cools off to the temperature that can take off, improve aircraft continuous operation's efficiency.
The application provides a heat dissipation assembly, which comprises two annular pieces and a plurality of blades; the two annular pieces are respectively a first annular piece and a second annular piece; circular openings are formed at two ends of each annular part, and the inner diameter of the first end of each annular part is larger than that of the second end of each annular part; the first annular piece is sleeved outside the second annular piece, and the central lines of the two annular pieces are positioned on the same straight line; a plurality of vanes spaced between the first end of the first annular member and the first end of the second annular member; when the heat dissipation assembly is rotated, air outside the heat dissipation assembly is driven by the blades to flow in a direction perpendicular to the surfaces of the blades, and airflow flowing from the first end to the second end of the second annular member is generated inside the second annular member.
Optionally, in some embodiments of the present application, each blade includes two arc-shaped edges, two side surfaces of each blade are arc-shaped curved surfaces, and an adsorption through hole is formed between any two adjacent blades; the blades have the same shape and size, and the suction through holes have the same shape and size.
Optionally, in some embodiments of the present application, the axial direction is the central line direction of two annular members, and the axial length of the first annular member is greater than the axial length of the second annular member; the second end of the first ring member is located on the same plane as the second end of the second ring member.
Optionally, in some embodiments of the present application, the outer side wall of the first ring member includes a mounting surface and a flow guiding surface that are engaged with each other; the mounting surface is an annular surface and is close to the second end of the first annular piece; the flow guide surface is an annular curved surface and extends from the first end of the first annular piece to the mounting surface; the diameter of the flow guide surface is gradually reduced from the first end of the first annular piece to the mounting surface.
Optionally, in some embodiments of the present application, at a joint of the flow guiding surface and the mounting surface, an included angle between the flow guiding surface and the mounting surface is 120 degrees to 175 degrees.
Optionally, in some embodiments of the present application, a surface of the vane is recessed from the first end of the first annular member and smoothly transitions to the first end of the second annular member.
Optionally, in some embodiments of the present application, the angle between the blade and the plane of the first end of the second ring member is 5 to 35 degrees.
Optionally, in some embodiments of the present application, the vane includes a first joint end and a second joint end; a first link end connected to the first ring member; a second link end connected to the second ring segment; the first joint end is inclined relative to the second joint end, and the inclination direction of the first joint end is opposite to the rotation direction of the heat dissipation assembly.
Optionally, in some embodiments of the present application, the width of the junction between the blade and the second ring member is the same as the width of the junction between the suction through hole and the second ring member.
Optionally, in some embodiments of the present application, the heat dissipation assembly further includes an annular retaining wall formed at the second end of the first annular member and detachably connected to an outer sidewall of a half hub.
Optionally, in some embodiments of the present application, the heat dissipation assembly further includes two or more mounting holes, which penetrate through the inside and outside of the annular retaining wall and are arranged at equal intervals;
a fastener passing through the mounting hole to secure the first ring member to the half hub.
Correspondingly, the application also provides an airplane wheel, which comprises the heat dissipation assembly.
Optionally, in some embodiments of the present application, the aircraft wheel further comprises a half hub connected to the first annulus.
Optionally, in some embodiments of the present application, a heat shield is disposed in the half hub, and is disposed corresponding to the second end of the first annular member.
Optionally, in some embodiments of the present application, the half hub is provided with a hub body, a heat shield, and a driving key in sequence from outside to inside; the first ring member is fixed between the drive key and the hub body, and is disposed opposite to the heat shield.
The invention has the following effects: (1) the invention adds the heat radiation component on the airplane wheel of the airplane, considers the use of the blade structure, and the blades rotate along with the airplane wheel to generate airflow blowing to the inner side of the airplane wheel in the states of ground running, sliding and the like of the airplane, thereby increasing the ventilation quantity and the turbulence degree of the outer surface of the brake device, accelerating the heat radiation rate of the whole brake device, reducing the temperature rise value of the brake device and further reducing the brake temperature. Meanwhile, the structure increases the contact area between the heat shield and the air, and accelerates the convection heat dissipation efficiency. (2) The flow guide surface of the first annular piece can guide the generated airflow into the outer surface of the brake device and the cavity of the airplane wheel under the states of ground running, sliding and the like of the airplane to reduce flow resistance; under aircraft quiescent condition, the first loop forming element outside is the curved surface structure of horn mouth formula, does benefit to steam from brake equipment outwards effluvium in the air.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic elevation view of an aircraft wheel provided herein;
FIG. 2 is a schematic side view of an aircraft wheel provided herein;
FIG. 3 is a cross-sectional view of a portion of the structure of an aircraft wheel as provided herein;
FIG. 4 is a schematic structural diagram of a heat dissipation assembly provided herein;
fig. 5 is a schematic front view of a heat dissipation assembly provided in the present application.
The designations in the drawings are as follows:
a first annular member 1, a second annular member 2, blades 3, adsorption through holes 4,
the heat dissipating module 10, the half hub 20, the brake apparatus 30,
a mounting surface 11, a flow guide surface 12, a hub body 21, a heat shield 22,
the driving key 23, the brake hot box inner shell 24, the front edge 31, the rear edge 32,
the fastening member 40, the airplane wheel 100, the mounting hole 111, the fixing hole 211,
and a threaded hole 231.
Detailed Description
The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only some embodiments of the present application, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Furthermore, it should be understood that the detailed description and specific examples, while indicating exemplary embodiments of the invention, are given by way of illustration and explanation only, and are not intended to limit the scope of the invention. In the present application, unless otherwise specified, the use of directional terms such as "upper", "lower", "left" and "right" generally refer to upper, lower, left and right in the actual use or operation of the device, and specifically to the orientation of the drawing figures.
The present application provides a heat sink assembly and an aircraft wheel, each of which is described in detail below. It should be noted that the following description of the embodiments is not intended to limit the preferred order of the embodiments of the present application. In the following embodiments, the descriptions of the respective embodiments have respective emphasis, and reference may be made to related descriptions of other embodiments for parts that are not described in detail in a certain embodiment.
The present application focuses on the application of the heat dissipation assembly to the wheels of an aircraft, but the application of the heat dissipation assembly to wheels of vehicles other than aircraft also belongs to the protection scope of the present application.
Referring to fig. 1, 2 and 3, the present application provides an aircraft wheel 100 (hereinafter referred to as a wheel) including a heat sink assembly 10 with fan blades, a half hub 20 and a brake device 30; the half hub 20 is provided with a hub body 21, a heat shield 22, a driving key 23 and a brake heat reservoir inner shell 24 in sequence from outside to inside, the heat dissipation assembly 10 is fixed at the outer end of the heat shield 22, and the brake device 30 is arranged corresponding to the brake heat reservoir inner shell 24 and is mounted on a wheel shaft of the hub body 21. The inner shell 24 of the brake hot reservoir encloses a wheel cavity, the brake hot reservoir can be arranged in the wheel cavity, and the brake device 30 is preferably a brake disc and is arranged adjacent to the brake hot reservoir.
Referring to fig. 4 and 5, the heat dissipation assembly 10 includes a first ring-shaped member 1, a second ring-shaped member 2, and a plurality of blades 3. The first annular part 1 and the second annular part 2 form two annular parts; circular openings are formed at two ends of each annular piece, and the inner diameter of the first end of each annular piece 1 is larger than that of the second end of each annular piece; the first annular piece 1 is sleeved outside the second annular piece 2, the central lines of the two annular pieces are positioned on the same straight line, and an outer horn-shaped structure which is coaxially arranged is formed, so that the blades can conveniently form air flow when being rotated and a large heat dissipation surface can be conveniently formed. The central line directions of the two annular pieces are taken as axial directions, and the axial length of the first annular piece 1 is greater than that of the second annular piece 2; the second end of the first annular member 1 and the second end of the second annular member 2 are located on the same plane.
The second end of the first ring-shaped element 1 is connected with the outer end fixed on the half hub 20 and is arranged corresponding to the heat shield 22 arranged in the half hub 20; the first ring-shaped member 1 is fixed between the driving key 23 and the hub body 21 and is arranged opposite to the heat shield 22, so that the installation is stable, the spacing distance between the first ring-shaped member 1 and the heat shield 22 is reduced, heat transmission is facilitated, and the braking temperature is rapidly reduced. The second annular piece 2 is correspondingly arranged in the first annular piece 1 and is arranged at equal intervals with the first annular piece 1; the blades 3 are arranged on one side surfaces, away from the half hub 20, of the first annular member 1 and the second annular member 2 at intervals, and adsorption through holes 4 are formed between the adjacent blades 3; that is, a plurality of blades 3 are arranged between the first end of the first annular member 1 and the first end of the second annular member 2 at intervals, each blade 3 includes two arc-shaped edges, the two side surfaces of each blade 3 are arc-shaped curved surfaces, and an adsorption through hole 4 is formed between any two adjacent blades 3. The plurality of blades 3 have the same shape and size, and the plurality of suction through holes 4 have the same shape and size.
When the heat dissipation assembly 10 is rotated with the half hub 20, the blades 3 rotate to press the outside air to move in a direction perpendicular to the surface of the blades 3 in a beveling manner, that is, the air outside the heat dissipation assembly 10 is driven by the blades 3 to flow in a direction perpendicular to the surface of the blades 3, the adsorption through holes 4 suck the air, and the second annular member 2 generates an air flow flowing from the first end to the second end thereof, and the air flow is blown from the outside of the half hub 20 to the inside of the half hub 20.
Referring to fig. 4 and 5, in the embodiment of the present application, a mounting surface 11 is disposed on a side of the first ring member 1 facing the half hub 20, and the mounting surface 11 is fixed on the half hub 20 and detachably connected to an outer side wall of the half hub 20.
Referring to fig. 2 and fig. 3, in the embodiment of the present application, the mounting surface 11 forms an annular retaining wall at the second end of the first ring member 1, and the annular retaining wall is detachably connected to the outer sidewall of the half hub 2. The mounting surface 11 is provided with more than two mounting holes 111 penetrating through the first annular member 1, that is, the more than two mounting holes 111 penetrate through the inside and outside of the annular retaining wall and are arranged at equal intervals; the outer end of the half hub 20 is provided with a fixing hole 211 corresponding to the mounting hole 111, and a fastener 40 passes through the mounting hole 111 and the fixing hole 211 to fix the first ring member 1 to the half hub 20. It will be appreciated that the driving key 23 is disposed in the threaded hole 231 at a position corresponding to the fastening member 40, and the first ring member 1 can be fixed between the driving key 23 and the hub body 21 by simultaneously penetrating the fastening member 40 into the threaded hole 231, the mounting hole 111 and the fixing hole 211.
Referring to fig. 4 and 5, in the embodiment of the present application, the first ring member 1 is further provided with a flow guide surface 12, an outer side wall of the first ring member 1 includes a mounting surface 11 and a flow guide surface 12, the mounting surface 11 is located on a circle with a radius smaller than a radius of a circle on which an inner side surface of the half hub 20 is located, and the flow guide surface 12 is located on a circle with a radius larger than a radius of a circle on which the mounting surface 11 is located. The mounting surface 11 is an annular surface and is close to the second end of the first annular part 1; the flow guide surface 12 is an annular curved surface and extends from the first end of the first annular part 1 to the mounting surface 11; the diameter of the flow guiding surface 12 decreases gradually from the first end of the first annular member 1 to the mounting surface 11. In other words, the radius of the circle where the flow guide surface 12 is located gradually increases from the side connected to the mounting surface 11 to the side away from the mounting surface 11, so that the first annular member 1 has a bell-mouth-shaped curved surface structure. The flow guide surface 12 of the first annular member 1 can guide the generated airflow into the outer surface of the brake device and the cavity of the airplane wheel under the states of ground running, sliding and the like of the airplane to reduce the flow resistance; under aircraft quiescent condition, first loop forming element 1 is the curved surface structure of horn mouth formula, does benefit to and adsorbs through-hole 4 and first loop forming element 1 outwards effluvium steam to the air from brake equipment.
In the embodiment of the present application, the radius of the circle on which the flow guiding surface 12 is located is smaller than the radius of the circle on which the half hub 20 is located. This prevents the edge of the deflector surface 12 from protruding beyond the half hub 20, which may result in the edge of the deflector surface 12 rubbing against the ground when the tire pressure mounted on the half hub 20 is low.
In the embodiment of the present application, at a joint of the flow guide surface 12 and the mounting surface 11, an included angle between the flow guide surface 12 and the mounting surface 11 is 120 degrees to 175 degrees. This facilitates the air flow from the deflector surface 12 side to the mounting surface 11 side. And the water conservancy diversion face 12 of first loop forming element 1 is the curved surface structure of horn mouth formula, can increase the area of contact with the outside air, and accessible heat conduction mode is outwards dispelled the heat.
In the embodiment of the present application, the second ring member 2 is disposed corresponding to the flow guide surface 12. Preferably, the flow guiding surface 12 and the mounting surface 11 of the first annular member 1 are connected together to form a unitary structure, and the second annular member 2 mainly serves to connect with the blades 3, so that no special requirement is imposed on the axial length of the second annular member 2.
In the embodiment of the present application, the axial length of the first annular member 1 is greater than the axial length of the second annular member 2. This reduces the overall weight and facilitates the flow of air through the suction through-holes 4.
In the embodiment of the application, on the side facing the heat shield 22, the end faces of the first ring-shaped member 1 and the second ring-shaped member 2 are flush or the distance between the end face of the second ring-shaped member 2 and the heat shield 22 is larger than the distance between the end face of the first ring-shaped member 1 and the heat shield 22; on the side facing away from the heat shield 22, the end of the first annular part 1 protrudes beyond the end of the second annular part 2, and the blades 3 are connected between the end of the first annular part 1 and the end of the second annular part 2.
In the present embodiment, the vane 3 is arc-shaped, and a surface of the vane 3 is concave from the first end of the first annular member 1 and smoothly transits to the first end of the second annular member 2.
In the embodiment of the present application, the angle between the vane 3 and the plane of the first end of the second annular member 2 is 5 to 35 degrees. The blades 3 are arranged in an inclined manner, so that when the blades 3 rotate along with the half hub 20, the blades are used for pressing outside air to move in a direction perpendicular to the surface of the blades 3 in a beveling manner, and air flow blowing towards the inner side of the wheel half hub 20 is generated.
In the present embodiment, the blade 3 includes a leading edge 31 and a trailing edge 32, the leading edge 31 is at the front end in the rotation direction, and the trailing edge 32 is at the rear end in the rotation direction. The blade 3 further comprises a first joint end 33 and a second joint end 34; a first engagement end 33 is connected to the first ring member 1; the second engagement end 34 is connected to the second ring 2; the first connection end 33 is inclined with respect to the second connection end 34 in a direction opposite to the rotation direction of the heat dissipation assembly 10. Therefore, a plurality of blades 3 with certain inclination angles and arc shapes are arranged between the second ring part 2 and the first ring part 1, the size of the blades 3 is set according to the size of the first ring part 1, the blades 3 have two rotating directions towards the left and the right, and the blades 3 extrude outside air to move towards the direction vertical to the surface of the blades 3 in a beveling mode when rotating, and airflow blowing towards the inner side of the wheel half hub 20 is generated. The arrows in fig. 3 and 4 indicate the flow direction of the air flow.
The heat dissipating module 10 may be fixed to both left and right sides of the half hub 20, and the first coupling end 33 of the blade 3 is inclined with respect to the second coupling end 34 in a direction opposite to the rotation direction of the half hub, and specifically, when the half hub rotates forward, the first coupling end 33 of the blade 3 is inclined backward with respect to the second coupling end 34; conversely, when the half-hub rotates backwards, the first joint end 33 of the blade 3 is inclined forwards with respect to the second joint end 34. The inclined blades 3 form a parallelogram-like structure.
In the present embodiment, when the heat dissipating module 10 is fixed to the left side of the half hub 20, the half hub rotates counterclockwise when viewed from the left side and the blade 3 is inclined clockwise from the first connection end 33 to the second connection end 34.
In the embodiment, when the heat dissipating module 10 is fixed to the right side of the half hub 20, the half hub rotates clockwise when viewed from the right side, and the blade 3 is inclined in the counterclockwise direction from the first connection end 33 to the second connection end 34.
In the present embodiment, the width of the junction of the blade 3 with the second annular element 2 is the same as the width of the junction of the suction through hole 4 with the second annular element 2. That is, the blades 3 are arranged at equal intervals, and the width of the suction through holes 4 is the same. The blades 3 may of course be arranged at non-equidistant intervals in order to increase the intensity of the air flow generated towards the inside of the wheel half hub 20.
In the embodiment of the present application, the width of the suction through-hole 4 is the same as the width of the blade 3 at the circumferential surface where the second ring member 2 is attached. It is of course also possible to arrange the width of the suction through-hole 4 to be different from the width of the blade 3.
The invention has the following effects: (1) according to the invention, the radiating component is additionally arranged on the radiating component of the airplane wheel, the blade structure is considered, and the blades rotate along with the airplane wheel to generate airflow blowing towards the inner side of the airplane wheel in the states of ground running, sliding and the like of the airplane, so that the ventilation quantity and the turbulence degree of the outer surface of the brake device are increased, the radiating rate of the whole brake device is accelerated, the temperature rise value of the brake device is reduced, and the brake temperature is reduced. Meanwhile, the structure increases the contact area between the heat shield and the air, and accelerates the convection heat dissipation efficiency. (2) The flow guide surface of the first annular piece can guide the generated airflow into the outer surface of the brake device and the cavity of the airplane wheel under the states of ground running, sliding and the like of the airplane to reduce flow resistance; under aircraft quiescent condition, first loop element outside is the curved surface structure of horn mouth formula, does benefit to steam and outwards emits to the air from brake equipment.
The heat dissipation assembly and the airplane wheel provided by the present application are described in detail above, and specific examples are applied herein to explain the principles and embodiments of the present application, and the description of the above embodiments is only used to help understand the method and core ideas of the present application; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.
Claims (14)
1. An aircraft wheel, comprising a heat sink assembly;
the heat dissipation assembly includes:
the two annular pieces are respectively a first annular piece and a second annular piece; circular openings are formed at two ends of each annular part, and the inner diameter of the first end of each annular part is larger than that of the second end of each annular part; the first annular piece is sleeved outside the second annular piece, and the central lines of the two annular pieces are positioned on the same straight line; and
a plurality of blades spaced between the first end of the first annular member and the first end of the second annular member;
when the heat dissipation assembly is rotated, air outside the heat dissipation assembly is driven by the blades to flow in a direction perpendicular to the surfaces of the blades, and airflow flowing from the first end to the second end of the second annular member is generated inside the second annular member.
2. An aircraft wheel according to claim 1 wherein each vane includes two arcuate edges, the two side surfaces of each vane being arcuate in shape, an attachment through-hole being formed between any two adjacent vanes; the blades have the same shape and size, and the suction through holes have the same shape and size.
3. An aircraft wheel according to claim 1 characterised in that the axial length of the first annulus is greater than the axial length of the second annulus, with the centreline direction of both annuli being axial; the second end of the first ring member is located on the same plane as the second end of the second ring member.
4. An aircraft wheel according to claim 1 characterised in that the outer side wall of the first ring member includes interengaging formations
A mounting surface that is an annular surface proximate the second end of the first annular member; and
the flow guide surface is an annular curved surface and extends from the first end of the first annular piece to the mounting surface;
the diameter of the flow guide surface is gradually reduced from the first end of the first annular piece to the mounting surface.
5. An aircraft wheel according to claim 4 wherein the angle between the deflector surface and the mounting surface at the junction thereof is from 120 to 175 degrees.
6. An aircraft wheel according to claim 1 wherein a surface of the vane is concave from the first end of the first annular member and transitions smoothly to the first end of the second annular member.
7. An aircraft wheel according to claim 6 wherein the vane is angled from 5 to 35 degrees to the plane of the first end of the second annular member.
8. An aircraft wheel according to claim 6 characterised in that the vanes include
A first link end connected to the first ring member; and
a second link end connected to the second ring segment;
the first joint end is inclined relative to the second joint end, and the inclination direction of the first joint end is opposite to the rotation direction of the heat dissipation assembly.
9. An aircraft wheel according to claim 2 characterised in that,
the width of the joint of the blade and the second annular piece is the same as that of the joint of the suction through hole and the second annular piece.
10. An aircraft wheel according to claim 1 further comprising
And the annular retaining wall is formed at the second end of the first annular piece and is detachably connected to the outer side wall of a half hub.
11. An aircraft wheel according to claim 10 further comprising
The mounting holes penetrate through the annular retaining wall and are arranged at equal intervals; and
a fastener passing through the mounting hole to secure the first ring member to the half hub.
12. An aircraft wheel according to claim 1 further including
A half hub connected to the first ring member.
13. An aircraft wheel according to claim 12 wherein a heat shield is provided within the half-hub in correspondence with the second end of the first annular member.
14. An aircraft wheel according to claim 12 characterised in that,
the half hub is sequentially provided with a hub body, a heat shield and a driving key from outside to inside;
the first ring member is fixed between the drive key and the hub body, and is disposed opposite to the heat shield.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111352774.7A CN113895412B (en) | 2021-11-16 | 2021-11-16 | Heat dissipation assembly and airplane wheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111352774.7A CN113895412B (en) | 2021-11-16 | 2021-11-16 | Heat dissipation assembly and airplane wheel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113895412A CN113895412A (en) | 2022-01-07 |
| CN113895412B true CN113895412B (en) | 2022-08-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111352774.7A Active CN113895412B (en) | 2021-11-16 | 2021-11-16 | Heat dissipation assembly and airplane wheel |
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Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITGE920081A1 (en) * | 1992-07-24 | 1994-01-24 | Giorgio Rebolini | RECYCLED ENERGY ROTARY ENGINE. |
| US6457955B1 (en) * | 2001-01-10 | 2002-10-01 | Yen Sun Technology Corp. | Composite heat dissipation fan |
| US7481616B2 (en) * | 2003-08-21 | 2009-01-27 | Nidec Corporation | Centrifugal fan, cooling mechanism, and apparatus furnished with the cooling mechanism |
| TW201132855A (en) * | 2010-03-30 | 2011-10-01 | Foxconn Tech Co Ltd | Heat dissipation fan and impeller thereof |
| US8668276B2 (en) * | 2011-07-14 | 2014-03-11 | Meggitt Aircraft Braking Systems | Wheel assembly heat shield |
| CN208698342U (en) * | 2018-08-16 | 2019-04-05 | 北京长城华冠汽车技术开发有限公司 | A kind of rim structure, wheel and automobile |
| CN114688080A (en) * | 2020-12-30 | 2022-07-01 | 亚浩电子五金塑胶（惠州）有限公司 | Fan blade structure with multiple elevation angles and heat dissipation device |
| CN112849103B (en) * | 2021-01-25 | 2022-08-16 | 中国商用飞机有限责任公司 | Cooling mechanism for airplane wheel and brake device |
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2021
- 2021-11-16 CN CN202111352774.7A patent/CN113895412B/en active Active
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| Publication number | Publication date |
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| CN113895412A (en) | 2022-01-07 |
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