CN216768664U - Flange connection structure, air inlet channel connection structure and airplane - Google Patents
Flange connection structure, air inlet channel connection structure and airplane Download PDFInfo
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- CN216768664U CN216768664U CN202220538277.XU CN202220538277U CN216768664U CN 216768664 U CN216768664 U CN 216768664U CN 202220538277 U CN202220538277 U CN 202220538277U CN 216768664 U CN216768664 U CN 216768664U
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Abstract
The utility model provides a flange connecting structure, an air inlet connecting structure and an airplane, which can prolong the fatigue life of the flange connecting structure and improve the shock resistance of the flange connecting structure. This aircraft includes this intake duct connection structure, and this intake duct connection structure includes this flange connection structure, and this flange connection structure includes first flange, second flange, bolt and nut, first flange with the second flange includes first connecting hole and second connecting hole respectively, the bolt with the nut passes through first connecting hole with the second connecting hole is connected first flange with the second flange, flange connection structure still includes the bush piece, the bush piece sets up the radial outside of bolt, and respectively with first connecting hole and second connecting hole interference fit.
Description
Technical Field
The utility model relates to the technical field of an aircraft engine nacelle, in particular to a flange connecting structure, an air inlet connecting structure and an aircraft.
Background
The main functions of an aircraft engine nacelle are to fix the engine on the aircraft, to optimize the aerodynamic flow field of the engine and to protect the engine from external damage. The engine nacelle mainly comprises an air inlet, a fan cover, a thrust reverser, a tail nozzle, an installation system and other components, wherein the air inlet mainly has the functions of providing a stable and uniform air inlet flow field for the engine and decelerating and pressurizing the air inlet flow field so as to ensure the stable and reliable operation of the engine.
The docking ring is a main stressed part of the air inlet channel arranged on the engine, and the damage of the docking ring can cause the air inlet channel to fall off from the engine, thereby seriously threatening the safe flight of the airplane. When a fan blade of an engine falls off from an engine rotor, i.e., a Fan Blade Out (FBO) event occurs, the fan blade having a very large energy directly strikes the fan case, which generates a very large impact load. Impact load acts on the air inlet butting ring from the fan case of the engine, and in order to avoid the phenomenon that the air inlet falls off from the engine under the action of the impact load, the connection design of the butting ring and the fan case is very critical, and besides the impact load generated by FBO (film bulk oxide) needs to be borne, the air inlet butting ring also needs to have the fatigue life meeting the strength design requirement.
The main technical scheme for connecting the air inlet passage and the engine at present is that a flange mounting edge of a butt joint ring is connected with a flange mounting edge of a fan casing through a bolt. Generally, the butt ring is made of aluminum alloy material, the fan case is made of aluminum alloy or composite material, the bolts are made of high-strength alloy material, the yield strength, the failure strength and the fatigue life of the aluminum alloy and the composite material are far lower than those of the high-strength alloy, so that the risk that the flange mounting edge of the butt ring and the flange mounting edge of the fan case are damaged earlier than the connecting bolts exists, in addition, because gaps exist between the bolts and bolt holes of the flange mounting edge of the butt ring and the flange mounting edge of the fan case, stress concentration is easily generated at the bolt holes through loads transmitted by the bolts, cracks are easily generated at the stress concentration positions, and the fatigue life of the butt ring and the fan case is reduced.
SUMMERY OF THE UTILITY MODEL
An object of the present invention is to provide a flange connection structure that can improve fatigue life and impact resistance.
In order to realize the flange connection structure of purpose, including first flange, second flange, bolt and nut, first flange with the second flange includes first connecting hole and second connecting hole respectively, the bolt with the nut passes through first connecting hole with the second connecting hole is connected first flange with the second flange, flange connection structure still includes the bushing spare, the bushing spare sets up the radial outside of bolt to respectively with first connecting hole and second connecting hole interference fit.
In one or more embodiments of the flange connection structure, the bushing member is a split structure, and includes a first bushing and a second bushing, the first bushing is disposed in the first connection hole, and the second bushing is disposed in the second connection hole.
In one or more embodiments of the flanged connection, a yield strength and a failure strength of the first bushing are higher than a yield strength and a failure strength of the first flange, respectively, and a yield strength and a failure strength of the second bushing are higher than a yield strength and a failure strength of the second flange, respectively.
In one or more embodiments of the flange connection structure, the material of the bushing member is the same as the material of the bolt.
In one or more embodiments of the flange connection structure, the material of the bushing member is a high-strength alloy.
In one or more embodiments of the flange connection structure, the material of the bushing member is low-alloy high-strength steel or high-temperature alloy.
In one or more embodiments of the flange connection structure, the bushing member includes a fitting section and a positioning section, a shoulder is formed between the fitting section and the positioning section, the fitting section is configured to be in interference fit with the first connection hole or the second connection hole, and the shoulder is configured to abut against a surface of the first flange or the second flange.
In one or more embodiments of the flange connection structure, the flange connection structure further includes an energy absorbing element disposed between the head of the bolt and the first flange or the second flange, or/and between the nut and the first flange or the second flange, wherein the energy absorbing element is capable of deforming to absorb a load when the load borne by the flange connection structure is higher than a predetermined value.
This flange joint structure sets up sleeve spare through the second connecting hole at the first connecting hole of first flange and second flange, make sleeve spare respectively with first connecting hole and second connecting hole interference fit, can reduce the stress concentration of first connecting hole and second connecting hole department effectively, the crackle of slowing down first connecting hole and second connecting hole department is sprouted, the fatigue life and the shock resistance of first flange and second flange are improved, and when bush spare takes place to damage, can conveniently change it, the maintenance simple operation, the maintenance cost is lower. The flange connection structure is simple in structure, easy to manufacture and assemble and low in cost, and is not only suitable for the connection structure of the air inlet channel, but also suitable for connection of other components.
It is another object of the present invention to provide an air intake duct connection structure having high fatigue life and impact resistance.
For realizing the air inlet channel connecting structure of purpose, including aforementioned flange joint structure, the air inlet channel with aeroengine provides respectively first flange with the second flange.
It is a further object of the present invention to provide an aircraft having an air scoop connection structure with improved fatigue life and impact resistance.
The aircraft comprises the air inlet connecting structure.
This aircraft and this intake duct connection structure can improve the fatigue life and the shock resistance of butt joint ring and fan machine casket through adopting this flange connection structure, and protection butt joint ring and fan machine casket avoid FBO load to destroy, and the maintenance simple operation, and the maintenance cost is lower.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic view of an air scoop.
Fig. 2 is a schematic view of a docking ring.
Fig. 3 is a schematic view of a flange connection structure.
Fig. 4 is a schematic view of a first bushing.
Fig. 5 is a schematic view of a second bushing.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the utility model. It is to be noted that the drawings are designed solely as examples and are not to scale and should not be construed as limiting the scope of the utility model as it may be practiced. Furthermore, some of the features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
Referring to fig. 1 to 3, an aircraft (not shown) according to an embodiment of the present invention includes a nacelle (not shown) in which an aircraft engine (not shown) including an air intake duct 2 is located, and an air intake duct connection structure 1 for connecting a docking ring 4 of the air intake duct 2 to the fan case 3, thereby connecting the air intake duct 2 to the aircraft engine.
The air inlet connecting structure 1 comprises a flange connecting structure 5, wherein the flange connecting structure 5 comprises a first flange 41 positioned on the butt ring 4, a second flange 31 positioned on the fan case 3, a bolt 6, a nut 7, a bushing part 8 and an energy absorbing element 9.
A plurality of first coupling holes 42 are formed in the circumferential direction of the first flange 41, a plurality of second coupling holes 32 are formed in the circumferential direction of the second flange 31, and the bolts 6 and the nuts 7 couple the first flange 41 and the second flange 31 through the first coupling holes 42 and the second coupling holes 32.
The bush spare 8 sets up in the radial outside of bolt 6, and respectively with first connecting hole 42 and second connecting hole 32 interference fit, so that the load through the transmission of bolt 6 transmits bush spare 8 earlier, first flange 41 and second flange 31 are transmitted to rethread bush spare 8, thereby can reduce the stress concentration of first connecting hole 42 and second connecting hole 32 department effectively, the crackle of first connecting hole 42 and second connecting hole 32 department is slowed down and erupt at, improve the fatigue life and the shock resistance of butt joint ring 4 and fan machine casket 3, protection butt joint ring 4 and fan machine casket 3 avoid FBO load to destroy, and when bush spare 8 takes place to damage, can conveniently change it, the maintenance operation is convenient, the maintenance cost is lower.
Referring to fig. 3 to 5, in one embodiment, the bushing member 8 is a split structure including a first bushing 81 and a second bushing 82, the first bushing 81 being disposed in the first coupling hole 42, and the second bushing 82 being disposed in the second coupling hole 32, for ease of manufacture and assembly. In another embodiment, not shown, the bushing member 8 is a one-piece structure, and both ends of the bushing member 8 in the axial direction are interference-fitted with the first connection hole 42 and the second connection hole 32, respectively.
With continued reference to fig. 3 to 5, the yield strength and the failure strength of the first bushing 81 are respectively higher than those of the first flange 41, and the yield strength and the failure strength of the second bushing 82 are respectively higher than those of the second flange 31, so that the fatigue life and the impact resistance of the first bushing 81 and the second bushing 82 can be improved, the replacement frequency can be reduced, and the maintenance time can be saved, furthermore, only the first bushing 81 and the second bushing 82 need to be made of higher-strength materials, and the materials of the docking ring 4 and the fan case 3 do not need to be replaced, so that the fatigue life and the impact resistance of the flange connection structure 5 can be improved, the cost can be saved, and the weight can be reduced.
Optionally, the material of the first bushing 81 and the second bushing 82 is high-strength alloy, such as low-alloy high-strength steel, or high-temperature alloy such as GH4169, or other materials, so as to have high yield strength and breaking strength.
Alternatively, the first bushing 81 and the second bushing 82 are made of the same material as the bolt 6, and thus have a yield strength and a breaking strength similar to those of the bolt 6.
The first bushing 81 comprises a first matching section 811 and a first positioning section 812, a first shoulder 813 is formed between the first matching section 811 and the first positioning section 812, the first matching section 811 is used for being in interference fit with the first connecting hole 42, the first shoulder 813 is used for abutting against the first surface 43 of the first flange 41, and the first surface 43 is opposite to the nut 7, so that the first bushing 81 can be positioned through the first positioning section 812 to facilitate assembly, the first surface 43 can be protected through the first positioning section 812, and the first surface 43 is prevented from being worn by the nut 7.
Similarly, the second bushing 82 includes a second fitting segment 821 and a second positioning segment 822, a second shoulder 823 is formed between the second fitting segment 821 and the second positioning segment 822, the second fitting segment 821 is used for being in interference fit with the second connecting hole 32, the second shoulder 823 is used for abutting against the second surface 33 of the second flange 31, and the second surface 33 is opposite to the energy-absorbing element 9, so that the second bushing 82 can be positioned through the second positioning segment 822 to facilitate assembly, the second surface 33 can be protected through the second positioning segment 822, and the energy-absorbing element 9 can be prevented from rubbing against the second surface 33.
The energy-absorbing element 9 is arranged between the head of the bolt 6 and the second flange 31, for example the energy-absorbing element 9 is a sleeve which is sleeved on the radial outside of the bolt 6, and two ends of the sleeve abut against the washer 10 adjacent to the head of the bolt 6 and the second positioning section 822 of the second bush 82 respectively. Under normal operating conditions, the energy absorbing element 9 can ensure accurate positioning of the bolts 6, and when the flange connection structure 5 is subjected to a load tending to separate the first flange 41 from the second flange 31, which exceeds a predetermined value, for example, when an FBO event occurs, the energy absorbing element 9 can deform to absorb the load, so as to reduce the load transmitted to the bolts 6 and avoid the bolts 6 from being damaged, so that the connection between the first flange 41 and the second flange 31 can be maintained when the FBO event occurs or other impact loads are applied, and the air inlet duct 2 is prevented from falling off from the aircraft engine under the impact load.
The energy-absorbing element 9 can be designed as a thin-walled sleeve or can be provided with through-holes or through-slots in the wall of the sleeve, so that the sleeve is easily deformed under a predetermined load. The material of the energy-absorbing element 9 can be steel or a memory alloy or another material.
In the illustrated embodiment, the nut 7 is located on the first flange 41 side and the head of the bolt 6 is located on the second flange 31 side, and in another embodiment, the head of the bolt 6 is located on the first flange 41 side and the nut 7 is located on the second flange 31 side.
In the illustrated embodiment, the energy-absorbing element 9 is arranged between the head of the bolt 6 and the corresponding flange, in another embodiment the energy-absorbing element 9 is arranged between the nut 7 and the corresponding flange, and in yet another embodiment the energy-absorbing element 9 is arranged both between the nut 7 and the corresponding flange and between the head of the bolt 6 and the corresponding flange.
This flange connection structure 5 sets up sleeve part 8 through the second connecting hole 32 at first connecting hole 42 of first flange 41 and second flange 31, make sleeve part 8 respectively with first connecting hole 42 and second connecting hole 32 interference fit, can reduce the stress concentration of first connecting hole 42 and second connecting hole 32 department effectively, the crackle of slowing down first connecting hole 42 and second connecting hole 32 department is sprouted, improve the fatigue life and the shock resistance of first flange 41 and second flange 31, and when bushing part 8 takes place to damage, can conveniently change it, the maintenance operation is convenient, the maintenance cost is lower. The flange connection structure 5 is simple in structure, easy to manufacture and assemble and low in cost, and is suitable for the connection of other components as well as the air inlet channel connection structure 1.
This aircraft and this intake duct connection structure 1 can improve the fatigue life and the shock resistance of butt ring 4 and fan machine casket 3 through adopting this flange joint structure 5, and protection butt ring 4 and fan machine casket 3 avoid FBO load to destroy, and maintain the simple operation, and the maintenance cost is lower.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the utility model, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the utility model. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (10)
1. The flange connection structure comprises a first flange, a second flange, a bolt and a nut, wherein the first flange and the second flange respectively comprise a first connection hole and a second connection hole, and the bolt and the nut are connected with the first flange and the second flange through the first connection hole and the second connection hole.
2. The flange connection according to claim 1, wherein the bushing member is a split structure including a first bushing disposed in the first connection hole and a second bushing disposed in the second connection hole.
3. The flange connection structure according to claim 2, wherein the first bushing has a yield strength and a failure strength higher than those of the first flange, respectively, and the second bushing has a yield strength and a failure strength higher than those of the second flange, respectively.
4. A flange connection according to any one of claims 1 to 3, wherein the material of the bushing member is the same as the material of the bolt.
5. A flange connection according to any one of claims 1 to 3, wherein the material of the bush member is a high-strength alloy.
6. The flange connection structure according to claim 5, wherein the material of the bushing member is low-alloy high-strength steel or high-temperature alloy.
7. A flange connection structure according to any one of claims 1 to 3, wherein the bushing member includes a fitting section and a positioning section, a shoulder being formed between the fitting section and the positioning section, the fitting section being adapted to be interference-fitted with the first connection hole or the second connection hole, the shoulder being adapted to abut against a surface of the first flange or the second flange.
8. A flange connection according to any one of claims 1 to 3, characterized in that the flange connection further comprises an energy-absorbing element disposed between the head of the bolt and the first or second flange or/and between the nut and the first or second flange, the energy-absorbing element being capable of deforming to absorb a load when the flange connection is subjected to the load above a predetermined value.
9. Air inlet connection structure for connecting air inlet and aeroengine, characterized in that, air inlet connection structure includes the flange joint structure of any one of claims 1 to 8, the air inlet with aeroengine provides respectively first flange with the second flange.
10. An aircraft comprising the inlet connection of claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220538277.XU CN216768664U (en) | 2022-03-10 | 2022-03-10 | Flange connection structure, air inlet channel connection structure and airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220538277.XU CN216768664U (en) | 2022-03-10 | 2022-03-10 | Flange connection structure, air inlet channel connection structure and airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216768664U true CN216768664U (en) | 2022-06-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220538277.XU Active CN216768664U (en) | 2022-03-10 | 2022-03-10 | Flange connection structure, air inlet channel connection structure and airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216768664U (en) |
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2022
- 2022-03-10 CN CN202220538277.XU patent/CN216768664U/en active Active
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