Nacelle core machine and cabin pressure relief device thereof

Abstract

The nacelle core cabin pressure relief device is high in adaptability, and the position design flexibility of the pressure relief door is enhanced. Wherein the inner wall plate is provided with a front end and a rear end and comprises a plurality of pressure relief holes; the outer wall plate is stacked on the inner wall plate; the hinge device is used for connecting the front end of the outer wall plate to a core cabin cover; the locking device is used for locking the inner wall plate and the outer wall plate and can be unlocked under the action of set pressure; the limiting device is used for limiting the maximum opening angle of the outer wall plate. The nacelle core cabin comprises the pressure relief device.

Description

Technical Field

[0001] The invention relates to a nacelle core cabin pressure relief device. Background Art

[0002] The nacelle is a key connecting device between the engine and the aircraft. There is a high-pressure air pipe in the core cabin of the nacelle. When the high-pressure pipe leaks or bursts, a large amount of high-temperature and high-pressure gas will enter the cabin, which may cause excessive pressure in the nacelle and endanger the safety of the nacelle structure.

[0003] The Civil Aviation Administration of China's "Airworthiness Standards for Transport Airplanes" CCAR25.1103(d) requires that damage to the power unit bleed air duct will not cause harm. At present, nacelle companies usually use pressure relief devices in the form of pressure relief doors to relieve pressure in order to control the pressure load in the cabin, thereby ensuring the safety of the cabin structure under fault conditions such as pipe explosions. In order to avoid the impact of the leaking high-temperature airflow on the reverse thrust moving cowl and the impact on the structure inside the outer duct when the pressure relief door is opened, the pressure relief door in the core cabin is usually arranged on the outer wall of the core cabin outside the outer duct, which leads to the limitation of the position and opening area of ​​the pressure relief door. Summary of the invention

[0004] The object of the present invention is to provide a nacelle core cabin pressure relief device, which has strong structural adaptability and enhances the flexibility of the position design of the pressure relief door.

[0005] Another object of the present invention is to provide a nacelle core compartment, comprising the aforementioned pressure relief device.

[0006] According to one aspect of the present invention, a nacelle core cabin pressure relief device, wherein the inner wall panel has a front end and a rear end, and includes a plurality of pressure relief holes; the outer wall panels are stacked on the inner wall panel; a hinge device is used to connect the front end of the outer wall panel to the core cabin cover; a locking device is used to lock the inner wall panel and the outer wall panel, and can be unlocked under the action of a set pressure; a limiter is used to limit the maximum opening angle of the outer wall panel.

[0007] In one embodiment, the porosity ε of the inner wall plate is in the range of 0.7≤ε≤0.85.

[0008] In one embodiment, the locking device includes a pressure sensor, a driving device and a locking structure. The pressure sensor is used to detect the pressure in the nacelle core compartment. The driving device drives the locking structure to unlock when the signal received from the pressure sensor reaches the set pressure.

[0009] In one embodiment, the locking device includes a fusible locking structure, and the locking structure breaks under the set pressure to achieve unlocking.

[0010] In one embodiment, the limiter limits the maximum opening angle α of the outer wall panel to a range of 25°≤α≤45°.

[0011] In one embodiment, the pressure relief hole is a circular hole.

[0012] In one embodiment, the number n of the pressure relief holes of the inner wall plate is in the range of 50≤n≤70.

[0013] A nacelle core cabin according to another aspect of the present invention comprises a core cabin cover, on which any of the nacelle core cabin pressure relief devices is arranged.

[0014] In one embodiment, the nacelle core cabin pressure relief device is arranged in the outer area of ​​the core cabin cover.

[0015] In one embodiment, it further includes a pressure relief door disposed in an area downstream of the outer duct area of ​​the core nacelle cover.

[0016] The aforementioned nacelle core cabin pressure relief device slows down the airflow released from the cabin on the one hand and guides it on the other hand, which can solve the problem that the position of the traditional core cabin pressure relief door design is limited to the tail area outside the outer duct, so as to enhance the flexibility of the position design when designing the pressure relief door. The porous structure of the inner wall plate can avoid the impact damage of the airflow on the outer duct structure. When the opening area of ​​the pressure relief door is not enough, the pressure relief device is designed in the outer duct to accelerate the release of high-temperature gas in the cabin and improve the pressure relief efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0018] Figure 1 It is a schematic diagram of a commercial aircraft.

[0019] Figure 2 is a schematic diagram of a turbofan engine showing a nacelle core compartment according to an embodiment.

[0020] Figure 3 It is a front view of a nacelle core cabin pressure relief device in an open state according to one embodiment.

[0021] Figure 4 It is a front view of a nacelle core cabin pressure relief device in a closed state according to one embodiment.

[0022] Figure 5 It is a stereoscopic view of a nacelle core cabin pressure relief device in a closed state according to one embodiment.

[0023] Figure 6It is a top view of a nacelle core cabin pressure relief device in a closed state according to one embodiment.

[0024] Figure 7 is a perspective view of a first portion of a nacelle core cabin pressure relief device according to an embodiment.

[0025] Figure 8 is an exploded view of the first portion according to an embodiment.

[0026] Fig. 9 is a perspective view of a second portion of a nacelle core cabin pressure relief device according to an embodiment.

[0027] Fig.10 is an exploded view of a second portion of a nacelle core cabin pressure relief device according to an embodiment. DETAILED DESCRIPTION

[0028] Reference will now be made in detail to embodiments of the present invention, one or more examples of which are illustrated in the accompanying drawings. Each example is provided to explain the present invention, not to limit the present invention. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made in the present invention without departing from the scope or spirit of the present invention. For example, a feature illustrated or described as part of one embodiment may be used together with another embodiment to produce yet another embodiment. Therefore, the present invention is intended to cover these modifications and variations within the scope of the appended claims and their equivalents.

[0029] Figure 1 The diagram shows a configuration of a commercial aircraft 0, in which an engine is mounted on a wing via a nacelle 1 or 2 to provide power for the aircraft to fly.

[0030] exist Figure 2 In the figure, the turbofan engine body 6 is wrapped by a nacelle. The nacelle includes an air inlet compartment 3, a fan compartment 4, and a reverse thrust movable cover compartment 5. When the turbofan engine is working, the cold air flow passing through the fan will flow through the core nacelle cover 8 of the nacelle and the outer wall 7 of the outer cladding of the nacelle to form the outer cladding area. In addition, the core nacelle cover 8 and the engine casing 9 constitute the core nacelle. The outer cladding area of ​​the core nacelle is the part where the core nacelle and the outer cladding area of ​​the nacelle overlap axially. The area on the downstream side of the outer cladding area of ​​the core nacelle is roughly located at the right end of the core nacelle cover 8 in the figure, and does not overlap with the outer cladding area of ​​the nacelle in the axial direction.

[0031] There are high-temperature and high-pressure air pipelines in the core engine room, such as high-pressure pipeline 11, in which there is a burst source 12 as shown. When the high-pressure air pipe bursts, the pressure in the cabin continues to accumulate, which may cause damage to the core engine room cover and other structures, endangering safety. One way to deal with it is to use a pressure relief device in the form of a pressure relief door to relieve pressure, so as to control the pressure load in the cabin, and then ensure the safety of the cabin structure under fault conditions such as pipe explosion. In order to avoid the impact of the leaked high-temperature airflow on the reverse thrust moving cover and the impact on the structure inside the outer duct when the pressure relief door is opened, the pressure relief door of the core engine room is usually arranged in the area downstream of the outer duct area of ​​the core engine room, which leads to great restrictions on the position of the pressure relief door and the opening area. The nacelle core engine room pressure relief device described in the following embodiments can deal with such problems.

[0032] like Figures 3 to 6 As shown, the nacelle core cabin pressure relief device includes an inner wall panel 16 , an outer wall panel 13 , hinge devices 14 , 15 , a locking device 18 and a limiter 19 .

[0033] Combined with Figure 7 and Figure 8 The inner wall panel 16 includes a plurality of pressure relief holes. The outer wall panel 13 is overlapped and arranged on the inner wall panel 16. The hinge device includes two hinges 14 and 15, which are used to connect the front end of the outer wall panel 13 to the core nacelle cover 8. The locking device 19 is used to lock the inner wall panel 16 and the outer wall panel 13, and can be unlocked under the action of a set pressure. The limiter 19 is used to limit the maximum opening angle of the outer wall panel 13.

[0034] When the high-pressure air pipe bursts, the pressure in the cabin continues to accumulate. After reaching the set pressure, the locking device 19 unlocks the outer wall panel 13, causing the outer wall panel 13 to rotate to open the inner wall panel 16. The airflow passes through the inner wall panel 16 to release the pressure in the cabin. When the airflow passes through the inner wall panel 16, it is affected by the pressure relief holes on the inner wall panel 16, and the flow speed of the airflow is slowed down. On the other hand, the maximum opening angle of the outer wall panel 13 is limited, and the maximum opening angle is set according to the minimum impact on the outer duct. The outer wall panel 13 has a guiding effect on the decompression airflow. Therefore, the decompression airflow from the cabin is slowed down on the one hand, and guided on the other hand. This can avoid the impact of the leaked high-temperature airflow on the reverse thrust moving cover and the impact on the structure inside the outer duct during pressure relief. That is, the nacelle core cabin pressure relief device can be set in the outer duct area of ​​the core cabin, which can solve the problem that the position of the traditional core cabin pressure relief door design is limited to the tail area outside the outer duct. When the cabin cover area outside the outer duct of the pressure relief door is insufficient, on the basis of adopting the traditional pressure relief door, the pressure relief device according to the present invention is used at the same time. This can avoid the impact damage of the airflow on the outer duct structure. It is installed inside the duct to accelerate the release of high-temperature gas in the cabin and improve the pressure relief efficiency.

[0035] like Figure 2As shown, the nacelle core cabin pressure relief device 10 according to the aforementioned embodiment is arranged in the outer duct area of ​​the core cabin cover 8, and includes an inner wall panel 16 close to the outer duct and an outer wall panel 13 close to the core cabin. The inner and outer wall panels 16 / 13 are arranged overlappingly when no pipe explosion occurs, and the two wall panels are airtight. When a burst source 12 appears in the high-pressure gas pipe 11, the pressure in the cabin rises sharply to reach the set trigger pressure, and the outer wall panel 13 opens and rotates with the pressure difference between the inside and outside to release the gas in the cabin.

[0036] In one embodiment, the pressure relief holes of the inner wall plate 16 are circular flow holes, and the number of flow holes n is preferably in the range of 50≤n≤70, and the porosity ε of the inner wall plate 16 is preferably in the range of 0.7≤ε≤0.85.

[0037] In one embodiment, the locking device 18 includes a pressure sensor, a drive device and a locking structure. The pressure sensor is used to detect the pressure in the nacelle core cabin. The drive device drives the locking structure to unlock when receiving a signal from the pressure sensor that reaches the set pressure. The pressure sensor is preferably installed at the tail or rear end of the inner wall panel 16 to accurately monitor abnormal changes in the cabin pressure and transmit burst signals. The drive device can be a motor, and the locking device can be a mechanical structure, such as a latch or a shaft, which enters or exits the locking position under the action of the motor. In another embodiment, the drive device and the locking device are electromagnets, such as Fig. 9 and Fig.10 As shown, a part of the locking device 18 is arranged at the rear end of the outer wall plate 13, and the other part is arranged at the rear end of the inner wall plate 16. When the pressure detected by the pressure sensor reaches the set pressure, the electromagnet is actuated to release the two originally adsorbed parts.

[0038] In one embodiment, the locking device 18 includes a fusible locking structure, which breaks under the set pressure to achieve unlocking.

[0039] The outer wall panel 13 is consistent with the aerodynamic shape of the nearby core nacelle cover 8, reducing the impact of the pressure relief device on the outer duct.

[0040] like Figure 5 , 6 As shown in FIGS. 9 and 10, the front end of the outer wall panel 13 is connected to the core engine nacelle 8 through hinges 14 and 15 to allow the outer wall panel 13 to rotate according to the designed trajectory. When receiving the burst signal from the pressure sensor 17, the lock device 18 opens, and the outer wall panel 13 of the pressure relief door rotates with the internal and external pressure difference by hinges 14 and 15, and the gas in the cabin is released through the pressure relief hole of the inner wall panel 16.

[0041] An example of a limiter 19 is a cross bar, which blocks the rotation range of the hinges 14 and 15 and indirectly limits the rotation of the outer wall panel 13. The limiter is arranged at the front end of the outer wall panel 13. Preferably, the maximum opening angle α of the pressure relief outer wall panel limited by the limiter is in the range of 25°≤α≤45°, so as to prevent the pressure relief wall panel from impacting and damaging the external duct.

[0042] The above-mentioned embodiment provides a nacelle core cabin pressure relief device with strong position adaptability for rapid gas release in the event of a high-temperature pipeline burst, and uses a double-wall plate structure to guide the release of high-temperature airflow. On the one hand, it can enhance the flexibility of the position design when designing the pressure relief door, ensuring that the released high-temperature gas will not impact other structures in the outer duct; on the other hand, it can be realized to design a pressure relief door in the outer duct when the opening area of ​​the pressure relief door is not enough, accelerate the release of high-temperature gas in the cabin, and improve the pressure relief efficiency.

[0043] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. Nacelle core cabin pressure relief device, characterized in that: include: an inner wall panel including a plurality of pressure relief holes; An outer wall panel is arranged overlappingly on the inner wall panel; A hinge device for connecting the front end of the outer wall panel to the core nacelle cover; A locking device for locking the inner wall panel and the outer wall panel, which can be unlocked under a set pressure; and The limiter is used to limit the maximum opening angle of the outer wall panel.

2. The nacelle core compartment pressure relief device according to claim 1, characterized in that: The porosity ε of the inner wall plate ranges from 0.7≤ε≤0.

85.

3. The nacelle core compartment pressure relief device according to claim 1 or 2, characterized in that: The locking device includes a pressure sensor, a driving device and a locking structure. The pressure sensor is used to detect the pressure in the nacelle core compartment. The driving device drives the locking structure to unlock when the signal received from the pressure sensor reaches the set pressure.

4. The nacelle core compartment pressure relief device according to claim 1 or 2, characterized in that: The locking device comprises a fusible locking structure, which breaks under the action of the set pressure to achieve unlocking.

5. The nacelle core compartment pressure relief device according to claim 1 or 2, characterized in that: The limiter limits the maximum opening angle α of the outer wall panel to a range of 25°≤α≤45°.

6. The nacelle core compartment pressure relief device according to claim 1 or 2, characterized in that: The pressure relief hole is a circular hole.

7. The nacelle core compartment pressure relief device according to claim 1 or 2, characterized in that: The number n of the pressure relief holes of the inner wall plate is in the range of 50≤n≤70.

8. A nacelle core cabin, comprising a core cabin cover, characterized in that: A nacelle core cabin pressure relief device according to any one of claims 1 to 7 is arranged on the core cabin cover.

9. The nacelle core cabin according to claim 8, characterized in that: The nacelle core cabin pressure relief device is arranged in the outer cladding area of ​​the core cabin cover.

10. The nacelle core cabin according to claim 9, characterized in that: The invention also includes a pressure relief door arranged in an area downstream of the outer duct area of ​​the core nacelle cover.

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