Aircraft engine nacelle pressure relief door assembly structure
By setting up a damping structure at the pressure relief door position of the aircraft engine nacelle, the huge collision impact problem caused by the rapid opening of the pressure relief door is solved, and the effect of reducing peak load and reducing damage risks is achieved, improving the safety of the components.
Patent Information
- Application Number
- CN202311583277.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-11-24
- Publication Date
- 2025-05-27
AI Technical Summary
When the pressure relief door of the aircraft engine nacelle is opened quickly, it will create a huge impact when it comes into contact with other components or limit features, causing the components to fail or break. The method of increasing the weight of the structure to reduce risks will also lead to unnecessary weight gain.
The damping structure is set up in the appropriate position of the pressure relief door. By participating in the buffering of the pressure relief door after the pressure relief door is opened at a certain angle, it plays a continuous buffering role, reducing the impact speed during the final limit impact, reducing the peak load, and reducing the risk of damage.
Through the design of the damping structure, the impact generated by the pressure relief door during opening is reduced, the rebound amount and vibration are also reduced, avoiding component failure and weight increase, and improving the safety of the component.
Smart Images
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Abstract
Description
Technical Field
[0001] The present invention relates to the field of aero - engines, and more particularly, to an assembly structure of a pressure - relief door for an engine nacelle of an aircraft. Background Art
[0002] An aero - engine nacelle wraps the engine body inside and provides necessary protection for the engine. When the aero - engine is operating, if the gas pipeline system inside the engine is damaged and leaks, it will cause an increase in the pressure inside the nacelle. Excessive chamber pressure may damage the nacelle structure and cause catastrophic effects. Therefore, a pressure - relief door is usually designed at a specified position in the nacelle. When the pressure inside the chamber reaches the trigger pressure, the pressure - relief door opens to release the pressure inside the chamber, so as to reduce the chamber pressure and protect the main structure.
[0003] In order to quickly reduce the pressure inside the nacelle, the pressure - relief door needs to open quickly after reaching the trigger pressure. However, after the pressure - relief door opens at high speed and touches other components or limit features, it will generate a huge impact impulse, causing the components to fail or even break, posing a risk to the continued safe operation of the engine. Although the risk of fracture can be reduced by increasing the local thickness, it will also lead to an increase in the structural weight. Therefore, on the premise of ensuring the quick opening of the pressure - relief door, it is necessary to optimize the structure to reduce the instantaneous speed when the pressure - relief door impacts other components, so as to reduce the weight of each component without being damaged. Summary of the Invention
[0004] The present disclosure is provided to introduce some concepts in a simplified form that will be further described in the following detailed implementation manners. The present disclosure is not intended to identify the key features or essential features of the claimed subject matter, nor is it intended to be used to help determine the scope of the claimed subject matter.
[0005] One of the purposes of the present disclosure is to provide an assembly structure of a pressure - relief door for an aero - engine nacelle. By arranging a damping structure at an appropriate position of the pressure - relief door, the damping structure participates in buffering the pressure - relief door after the pressure - relief door opens at a certain angle, playing a continuous buffering role. On the basis of ensuring quick opening of the door to relieve pressure, the impact speed when the pressure - relief door is finally limited is reduced, so that the load is distributed over a larger range, thereby reducing the peak load and the risk of damage, and improving the safety of the components.
[0006] According to one aspect of the present disclosure, there is provided a pressure relief door assembly structure for an engine nacelle, the pressure relief door assembly structure comprising: a pressure relief door support frame mounted on the engine nacelle, the pressure relief door support frame having support frame side plates; a pressure relief door having pressure relief door side plates; a shaft pin respectively connected to the support frame side plates and the pressure relief door side plates to enable the pressure relief door to rotate around the shaft pin; a limiting structure for limiting the angular range of rotation of the pressure relief door around the shaft pin; and a damping device for damping the rotation after the pressure relief door rotates around the shaft pin to a preset angle.
[0007] According to a further embodiment of the present invention, the preset angle is not less than 10 degrees.
[0008] According to a further embodiment of the present invention, the damping device is arranged to damp the rotation during the process from when the pressure relief door rotates around the shaft pin to the preset angle to the maximum angle within the angular range of the rotation.
[0009] According to a further embodiment of the present invention, the damping value of the damping device is determined according to one or more of the following factors: the opening speed of the pressure relief door; the stiffness of the pressure relief door; the distance of the damping action; and the strength of the limiting structure.
[0010] According to a further embodiment of the present invention, the damping device further comprises: a damping chute provided on one of the support frame side plates and the pressure relief door side plates; and a damping block provided on the other of the support frame side plates and the pressure relief door side plates, wherein when the pressure relief door rotates around the shaft pin to the preset angle, the damping block contacts the damping chute and generates a damping effect.
[0011] According to a further embodiment of the present invention, the limiting structure further comprises a limiting groove provided on one of the support frame side plates and the pressure relief door side plates and a limiting pin provided on the other of the support frame side plates and the pressure relief door side plates, and the damping device further comprises: a damping block provided in the limiting groove, wherein when the pressure relief door rotates around the shaft pin to the preset angle, the damping block contacts the limiting pin and generates a damping effect.
[0012] According to a further embodiment of the present invention, the damping device is provided on one or both of the support frame side plates and the pressure relief door side plates, or on the tail of the pressure relief door.
[0013] According to a further embodiment of the present invention, the damping device damps the rotation of the pressure relief door during the process of the pressure relief door rotating from the maximum angle within the rotation angle range around the pivot pin to the preset angle.
[0014] According to another aspect of the present invention, there is provided an engine nacelle having a pressure relief door assembly structure as described in the present invention.
[0015] According to still another aspect of the present invention, there is provided an aircraft having a pressure relief door assembly structure for an engine nacelle as described in the present invention.
[0016] These and other features and advantages will become apparent by reading the following detailed description and referring to the associated drawings. It should be understood that the foregoing general description and the following detailed description are illustrative only and do not limit the various aspects claimed. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] In order to understand in detail the manner in which the above-described features of the present disclosure are used, the above briefly summarized content may be described in more detail with reference to the various embodiments, some of which are illustrated in the drawings. It should be noted, however, that the drawings only illustrate certain typical aspects of the present disclosure and should not be considered to limit its scope, as the description may admit other equally effective aspects.
[0018] Figure 1 A schematic structural diagram showing a typical pressure relief door assembly structure in the prior art is shown.
[0019] Figure 2 A schematic structural diagram showing a pressure relief door support frame according to an embodiment of the present invention is shown.
[0020] Figure 3 A schematic structural diagram showing a pressure relief door according to an embodiment of the present invention is shown.
[0021] Figure 4A and 4B A schematic diagram showing the working states before and after the action of a pressure relief door damping device according to an embodiment of the present invention is shown.
[0022] Figure 5 A schematic structural diagram showing a pressure relief door damping device according to another embodiment of the present invention is shown.
[0023] Among them, the above-mentioned drawings include the following reference numerals:
[0024] 1, pressure relief door support frame; 2, pressure relief door; 3, pivot pin; 4, limit structure;
[0025] 5, damping device; 11, support frame side plate; 12, damping chute; 14, damping pin;
[0026] 21, 21b damping blocks; 22, pressure relief door side plates; 23, limit grooves Specific embodiments
[0027] It should be noted that, without conflict, the embodiments in this application and the features in the embodiments may be combined with each other.
[0028] Next, the technical solutions in the embodiments of this application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and in no way restricts this application or its application or use. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of this application.
[0029] It should be noted that the terms used here are only for describing specific embodiments and are not intended to limit the exemplary embodiments of this application. As used here, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.
[0030] Unless otherwise specifically stated, the relative arrangements, numerical expressions, and numerical values of the components and steps set forth in these embodiments do not limit the scope of this application. At the same time, it should be understood that, for the sake of convenience of description, the dimensions of the various parts shown in the drawings are not drawn in actual proportional relationships. Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and devices should be regarded as part of the authorized specification. In all the examples shown and discussed here, any specific value should be construed as merely exemplary and not as a limitation. Therefore, 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 drawings, and thus, once an item is defined in one drawing, it does not need to be further discussed in subsequent drawings.
[0031] In the description of this application, it should be understood that the orientation or positional relationship indicated by orientation terms such as "front, rear, upper, lower, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom", etc. is usually based on the orientation or positional relationship shown in the drawings. This is only for the convenience of describing this application and simplifying the description. Without contrary explanations, these orientation terms do not indicate or imply that the devices or elements referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation on the protection scope of this application; the orientation terms "inside, outside" refer to the inside and outside relative to the contour of each component itself.
[0032] For convenience of description, spatial relative terms such as "above...", "over...", "on the upper surface of...", "above" etc. may be used here to describe the spatial positional relationship of one device or feature to other devices or features as shown in the drawings. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the drawings for the device. For example, if the device in the drawing is inverted, the device described as "above other devices or structures" or "over other devices or structures" will then be positioned "below other devices or structures" or "under other devices or structures". Thus, the exemplary term "above" can include both the orientation of "above" and "below". The device can also be positioned or rotated in other different ways, such as 90 degrees or in other orientations, and corresponding interpretations should be made for the spatial relative descriptions used here.
[0033] In addition, it should be noted that the use of terms such as "first", "second", etc. to limit components is only for the convenience of differentiating the corresponding components. Without additional declarations, the above terms have no special meanings. Therefore, it should not be construed as a limitation on the protection scope of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some of the terms mentioned in the specification of this application may be selected by the applicant according to his or her judgment, and their detailed meanings are described in the relevant parts of this description. In addition, it is required to understand this application not only through the actual terms used, but also through the meanings implied by each term.
[0034] Figure 1 The structural schematic diagram of a typical pressure relief door assembly structure in the prior art is shown. As Figure 1As shown in the figure, the pressure relief door assembly structure generally includes a pressure relief door support frame 1 installed on the engine nacelle, a pressure relief door 2, and a pin 3 connecting the two. Both sides of the pressure relief door support frame 1 and the pressure relief door 2 are respectively provided with side plates: the support frame side plate 11 and the pressure relief door side plate 22. The pressure relief door support frame 1 and the pressure relief door 2 are connected by the pin 3 on their respective side plates, so that the pressure relief door 2 can rotate around the pin 3. The support frame side plate 11 and the pressure relief door side plate 22 are also provided with their respective limiting structures 4. As Figure 1 shown in the figure, a limiting pin 14 is provided on the support frame side plate 11, and a limiting groove 23 is provided on the pressure relief door side plate 22. After the pressure relief door support frame 1 and the pressure relief door 2 are assembled, the limiting pin 14 is inserted into the limiting groove 23, so as to limit the angular range within which the pressure relief door 2 can rotate around the pin 3. For example, when the pressure relief door is in the closed state, the angle is 0, and when the pressure relief door rotates to the maximum open position, the angle is the set maximum rotatable angle.
[0035] According to the structure and assembly relationship of the engine nacelle, the pressure relief door can be divided into the inner side and the outer side. In the working state, the pressure relief door 2 is default in the closed state. Once the pressure inside the cabin reaches the trigger pressure, the pressure relief door 2 turns outwards and opens for pressure relief under the action of the high air pressure on the inner side. At this time, the pressure relief door 2 rotates around the pin 3 until the limiting pin 14 and the limiting groove 23 collide and prevent the pressure relief door 2 from opening further.
[0036] As mentioned before, after the pressure relief door 2 that has been opened at high speed touches other components or reaches the limit position (for example, the limiting pin 14 hits the end of the limiting groove 23), a huge impact impulse will be generated, causing the components to fail or even break, posing a risk to the continued safe operation of the engine. In addition, the pressure relief door 2 may also rebound after hitting the limit position, causing a secondary impact.
[0037] To solve this problem, the present invention provides a nacelle pressure relief door assembly structure with a damping device. Figures 2 - 4B shows a schematic diagram of a nacelle pressure relief door assembly structure according to an embodiment of the present invention, where Figure 2 shows a schematic diagram of the structure of a pressure relief door support frame according to an embodiment of the present invention, Figure 3 shows a schematic diagram of the structure of a pressure relief door according to an embodiment of the present invention, Figure 4A shows a schematic diagram of the working state before the action of the pressure relief door damping device according to an embodiment of the present invention, Figure 4B shows a schematic diagram of the working state after the action of the pressure relief door damping device according to an embodiment of the present invention.
[0038] According to an embodiment of the present invention, the damping device 5 can be respectively provided with a damping chute 12 and a damping block 21 on the support frame side plate 11 and the pressure relief door side plate 12. In Figure 2and Figure 3 In the example shown, the damping chute 12 is provided on the side plate 11 of the support frame, and the damping block 21 is provided at the corresponding position on the side plate 12 of the pressure relief door. Both the damping chute 12 and the damping block 21 are arc-shaped and have matching lengths and widths, so that as the pressure relief door 2 rotates around the pivot pin 3, the damping block 21 can be inserted into the damping chute 12, and the two come into contact and friction to produce a damping effect.
[0039] Figure 4A FIG. shows a schematic diagram of the working state of the pressure relief door damping device before it takes effect according to an embodiment of the present invention. As Figure 4A shown, the pressure relief door 2 is in the default closed state, and the limit pin 14 is at one end of the limit groove 23. As Figure 4A can be seen, at this time, the damping block 21 is separated from the damping chute 12, and no damping effect is generated between the two. Figure 4B FIG. shows a schematic diagram of the working state of the pressure relief door damping device after it takes effect according to an embodiment of the present invention. As Figure 4B shown, the pressure relief door 2 is in the open state, and the limit pin 14 is at the other end of the limit groove 23, that is, the pressure relief door 2 has rotated and opened to the maximum angle within the rotatable angle range defined by the limit pin 14 and the limit groove 23. As Figure 4B can be seen, at this time, the damping block 21 has been completely inserted into the damping chute 12 as the pressure relief door 2 rotates around the pivot pin 3, and a damping effect is generated between the two. It can be seen that the damping device 5 of the present invention only generates a damping effect on the rotation after the pressure relief door 2 rotates around the pivot pin 3 and opens to a preset angle. The specific value of the preset angle can be selected according to the requirements of the structure strength and the change of the damping distance. As a non-limiting example, the preset angle is not less than 10 degrees. The advantage of such a setting is that in the initial stage of opening the pressure relief door 2, that is, when the opening angle is small, the opening of the pressure relief door 2 is not blocked, so as to ensure that the pressure relief door 2 opens quickly in the initial stage of opening.
[0040] As Figure 4B can be seen, in Figures 2 - 4B the example shown, the length of the damping block 21 is shorter than the length of the damping chute 12, and at Figure 4B the maximum rotation angle, the damping block 21 still completely stays in the damping chute 12, which makes the damping device 5 generate a damping effect on the rotation throughout the process from the preset angle to the maximum angle within the rotation angle range when the pressure relief door 2 rotates around the pivot pin 3, and the damping effect is continuous and basically uniform in the middle and later stages. Preferably, the damping device 5 is configured to still have a damping effect at the maximum angle. It can be understood that the damping effect can be appropriately adjusted as needed. For example, different materials can be used at different positions of the damping chute to provide different frictional forces, such as gradually increasing frictional forces.
[0041] In the above example, the damping device 5 can not only relieve the impact of the pressure relief door on the limiting structure and other components of the nacelle during pressure relief, but also generate a damping effect on the rotation of the pressure relief door 2 when it rotates from the maximum angle to the preset angle around the pivot pin 3, thereby avoiding the secondary impact caused by the rebound of the pressure relief door. Through this design, the impact of the pressure relief door during the pressure relief process can be reduced, the rebound amount can be decreased, and the vibration can be reduced.
[0042] In the above example, the damping chute 12 is arranged on the side plate 11 of the support frame, and the damping block 21 is arranged at the corresponding position on the side plate 12 of the pressure relief door. It can be understood that the positions of the damping chute 12 and the damping block 21 can be interchanged. For example, the damping block 21 can be arranged on the side plate 11 of the support frame, and the damping chute 12 can be arranged on the side plate 12 of the pressure relief door. In addition, in the above example, the positions of the damping chute 12 and the damping block 21 are arranged near the pivot pin 3 on their respective side plates, and are approximately opposite to the positions of the limit pin 14 and the limit groove 23 with respect to the pivot pin 3. The advantage of such an arrangement is that the layout is compact and the structure is stable. However, the above-described installation positions of the damping device are only examples, and the damping device can also be arranged at any other suitable position that can provide a damping effect during the rotation of the pressure relief door 2 around the pivot pin 3. For example, it can be arranged near the limiting structure, or at the tail of the pressure relief door 2.
[0043] The damping device can also be implemented in other forms. Figure 5 Fig. shows a schematic structural view of a pressure relief door damping device according to another embodiment of the present invention. As Figure 5 shown in, in this embodiment, the damping device 5 is implemented as a damping block 21b arranged in the limit groove 23. In this example, the damping blocks 21b are distributed on both sides of the limit groove, in the middle and rear section near the maximum limit position, so that when the pressure relief door 2 is in the default closed state and at the initial stage of pressure relief opening, the limit pin 14 does not contact the damping blocks 21b and no damping effect is generated. As the pressure relief door 2 rotates to the preset angle during opening, the limit pin 14 contacts the damping blocks 21b on both sides, thereby generating a damping effect, continuously reducing the acceleration of the pressure relief door 2, and sharing the load during the deceleration and buffering process of the pressure relief door 2 over a larger range near the damping device 5b. Similarly, the implementation structure of this damping device can also play a role in reducing the peak impact load and the vibration after impact.
[0044] The specific form of the damping device is not limited to the damping block, and any other suitable structure capable of achieving the damping function can be adopted, such as a hydraulic damper. The specific damping value provided by the damping device can be configured according to the actual situation, for example, it can be determined according to factors such as the opening speed of the pressure relief door, the stiffness of the pressure relief door, the distance of the damping effect, the strength of the limiting structure, or any combination thereof.
[0045] The above describes the pressure relief door assembly structure of various embodiments of the present invention. Thanks to the alleviated impact during the pressure relief process of the pressure relief door, the engine nacelle and the aircraft adopting this pressure relief door assembly structure can optimize the structure of the engine nacelle on the premise that each structure of the nacelle will not be damaged due to pressure relief, minimizing the weight of each component and the whole.
[0046] The above description includes examples of aspects of the claimed subject matter. Of course, it is not possible to describe every conceivable combination of components or methods for the purpose of depicting the claimed subject matter, but one of ordinary skill in the art should recognize that many further combinations and permutations of the claimed subject matter are possible. Accordingly, the disclosed subject matter is intended to cover all such alterations, modifications, and variations that fall within the spirit and scope of the appended claims.
Claims
1. A pressure relief door assembly structure for an engine nacelle, characterized in that, the pressure relief door assembly structure includes: a pressure relief door support frame (1) installed on the engine nacelle, and the pressure relief door support frame (1) has a support frame side plate (11); a pressure relief door (2), and the pressure relief door (2) has a pressure relief door side plate (22); a shaft pin (3) that is respectively connected to the support frame side plate (11) and the pressure relief door side plate (22) so that the pressure relief door (2) can rotate around the shaft pin (3); a limit structure (4) that is used to limit the angle range of the rotation of the pressure relief door (2) around the shaft pin (3); and a damping device (5) that is used to generate a damping effect on the rotation after the pressure relief door (2) rotates around the shaft pin (3) and opens to a preset angle.
2. The pressure relief door assembly structure according to claim 1, characterized in that, the preset angle is not less than 10 degrees.
3. The pressure relief door assembly structure according to claim 1, characterized in that, the damping device (5) is arranged to generate a damping effect on the rotation during the process from the pressure relief door (2) rotating around the shaft pin (3) and opening to the preset angle to the maximum angle within the rotation angle range.
4. The pressure relief door assembly structure according to claim 1, characterized in that, the damping value of the damping device (5) is determined according to one or more of the following factors: the opening speed of the pressure relief door (2); the stiffness of the pressure relief door (2); the distance of the damping effect; and the strength of the limit structure (4).
5. The pressure relief door assembly structure according to claim 1, characterized in that, the damping device (5) further includes: a damping chute (12) provided on one of the support frame side plate (11) and the pressure relief door side plate (22); and a damping block (21) provided on the other of the support frame side plate (11) and the pressure relief door side plate (22), wherein when the pressure relief door (2) rotates around the shaft pin (3) to the preset angle, the damping block (21) contacts the damping chute (12) and generates a damping effect.
6. The pressure relief door assembly structure according to claim 1, characterized in that, the limit structure (4) further includes a limit groove (23) provided on one of the support frame side plate (11) and the pressure relief door side plate (22) and a limit pin (14) provided on the other of the support frame side plate (11) and the pressure relief door side plate (22), the damping device (5) further includes: a damping block (21b) provided in the limit groove (23), wherein when the pressure relief door (2) rotates around the shaft pin (3) to the preset angle, the damping block (21b) contacts the limit pin (14) and generates a damping effect.
7. The pressure relief door assembly structure according to claim 1, characterized in that, The damping device (5) is provided on one or both of the side plates (11) of the support frame and the side plates (22) of the pressure relief door, or is provided at the tail of the pressure relief door (2).
8. The pressure relief door assembly structure according to claim 1, characterized in that during the process that the pressure relief door (2) rotates from the maximum angle within the rotation angle range around the pivot pin (3) to the preset angle, the damping device (5) exerts a damping effect on the rotation.
9. An engine nacelle having the pressure relief door assembly structure according to any one of claims 1-8.
10. An aircraft having the pressure relief door assembly structure for an engine nacelle according to any one of claims 1-8.