Reverse thrust choke valve mechanism of aero-engine

Abstract

The invention provides an aero-engine reverse thrust choke door mechanism which has a forward thrust state and a reverse thrust state and comprises a sliding cover, a choke door and a choke door follow-up assembly, and the choke door follow-up assembly is configured to enable the choke door to rotate along with translation of the sliding cover in the translation direction; the flow blocking door follow-up assembly comprises a telescopic assembly and a sliding cover, wherein the telescopic assembly is provided with a front hinge part and is constructed to keep the front hinge part to move along the translation direction along with the sliding cover; the sliding block rotating assembly is installed on the sliding cover and moves along with the sliding cover, the sliding block rotating assembly is provided with an upper hinge part connected with the flow blocking door in a pivoted mode, and the upper hinge part can move between a first position and a second position; in the forward pushing state, the upper hinge portion is located at the first position, and the inner surface of the flow blocking door limits a part of the outer wall face of the outer duct; and in the reverse pushing state, the upper hinge part is located at the second position, and the flow blocking door rotates relative to the sliding cover and enters the outer duct. By the adoption of the aero-engine reverse-pushing flow blocking door mechanism, parts are prevented from being exposed in forward-pushing airflow of an outer duct, and the aero-engine reverse-pushing flow blocking door mechanism is simple in movement mechanism, high in movement reliability and more convenient to install.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and more particularly to an aircraft engine reverse thrust blocker door mechanism. Background Art

[0002] In the field of aviation technology, the safe and efficient landing of an aircraft has always been a crucial link. When an aircraft lands, it needs to rely on specific devices to provide reverse thrust to effectively shorten the landing distance, ensure that the aircraft can stop smoothly within a limited runway length, and safeguard the lives of passengers and crew as well as the integrity of the aircraft. The existing aircraft reverse thrust device is an important component that undertakes this key mission. Its main function is that when the aircraft enters the landing phase, the reverse thrust sliding cover will be deployed, and at the same time, the reverse thrust mechanism will quickly come into play, blocking the airflow in the engine bypass duct and cleverly forcing it to blow forward, thereby generating reverse thrust to assist the aircraft in achieving efficient braking.

[0003] However, the traditional aircraft reverse thrust device has exposed many drawbacks in practical applications. One of the most prominent problems is that the resistance rod is exposed in the engine duct. During the high-speed flight of the aircraft, this exposed resistance rod is like an additional obstacle, which not only increases the friction between the air and the aircraft, brings additional resistance, reduces the flight efficiency of the aircraft, but also generates additional noise, which not only affects the passenger experience but also may have potential adverse effects on the overall structure and flight stability of the aircraft.

[0004] Since the resistance rod of the reverse thrust blocker door mechanism is arranged inside the bypass duct, this layout directly causes the engine to overcome greater resistance during operation, thereby increasing the fuel consumption of the engine. More seriously, the resistance rod and its mounting joint are also located in the bypass duct. During the long flight of the aircraft, affected by various factors such as the complex and changeable flight environment, strong airflow impact, and mechanical vibration, there have been many incidents of damage to the resistance rod mounting joint on the flight route, which has directly led to the detachment of reverse thrust components and posed a great threat to flight safety.

[0005] At present, in response to the problems existing in the above-mentioned traditional thrust reversers, two different technical routes are presented in the design of thrust reversers. Some aircraft still use a thrust reverse motion mechanism with a resistance rod arranged in the outer duct. Although this traditional design method continues the original technical architecture to a certain extent, it does not fundamentally solve the many problems caused by the resistance rod. Some other aircraft adopt a hidden design in which the resistance rod is arranged in the sliding cover. This innovative design concept effectively hides the resistance rod and avoids the additional resistance it generates in the engine duct. However, the existing hidden design usually requires a complex mechanism to be set between the inner cover and the outer cover of the sliding cover. Therefore, the structure itself is relatively complex and the difficulty of installation is also increased. Summary of the invention

[0006] In order to overcome the deficiencies in the prior art, the present invention provides an aircraft engine reverse thrust baffle mechanism, which has a forward thrust state and a reverse thrust state, and comprises: a sliding cover, which can move relative to a fixed structure of the aircraft engine reverse thrust baffle mechanism; a baffle door, which is arranged at the front side of an inner cover of the sliding cover and can rotate between a forward thrust position and a reverse thrust position; and a baffle door follower assembly, which is configured to make the baffle door rotate as the sliding cover translates in a translation direction; wherein the baffle door follower assembly comprises: a telescopic assembly, which has a hinge A front hinge portion connected to the baffle door and configured to keep the front hinge portion moving along the translation direction with the sliding cover; a slider rotation assembly, the slider rotation assembly is installed on the sliding cover and moves with the sliding cover, the slider rotation assembly has an upper hinge portion pivotally connected to the baffle door, and the upper hinge portion can move between a first position and a second position; and in the forward thrust state, the upper hinge portion is located at the first position, and the inner surface of the baffle door defines a part of the outer wall surface of the outer duct; in the reverse thrust state, the upper hinge portion is located at the second position, and the baffle door rotates relative to the sliding cover to enter the outer duct.

[0007] According to one aspect of the present invention, the slider rotation assembly includes: a slider, which is fixed to the sliding cover and has a slide rail thereon, and the slide rail defines the first position and the second position of the upper hinge part; a connecting rod, the first end of the connecting rod is connected to the blocker door, and the second end of the connecting rod is arranged to be pivotally engaged with the upper hinge part of the strip groove.

[0008] According to another aspect of the present invention, the slide rail includes a strip groove, the strip groove includes an inclined section and a horizontal section, the inclined section extends backward and outward from the front end to the rear end, and the horizontal section extends backward from the rear end of the inclined section.

[0009] According to another aspect of the present invention, the fixing structure includes a front bulkhead, the telescopic assembly includes a fixed mounting cylinder and a support gas spring that can extend relative to the fixed mounting cylinder, the fixed mounting cylinder is mounted on the front bulkhead, and the support gas spring can provide a thrust force towards the rear of the sliding cover.

[0010] According to another aspect of the present invention, the telescopic assembly includes: a fixed mounting cylinder; a fixed sleeve installed in the fixed mounting cylinder, a baffle is provided in the fixed sleeve; a connecting rod that can be telescopic relative to the fixed sleeve; a spring that provides a thrust force in the rearward direction; and a limit nut, the limit nut is fixed on the connecting rod, and when the limit nut abuts against the baffle, the extension movement of the connecting rod stops.

[0011] According to another aspect of the present invention, the sliding cover includes an inner sliding cover and an outer sliding cover, a sliding cover cavity is formed between the inner sliding cover and the outer sliding cover, and the inner surface of the inner sliding cover and the inner surface of the choke door are continuous to define the outer wall surface of the bypass duct.

[0012] According to another aspect of the present invention, the aeroengine reverse thrust choke door mechanism further includes an actuating cylinder that provides a driving force to the sliding cover, one end of the actuating cylinder is connected to the fixing structure of the reverse thrust choke door mechanism, the other end of the actuating cylinder is connected to the sliding cover, and the actuating cylinder is at least partially arranged in the sliding cover cavity between the inner sliding cover and the outer sliding cover.

[0013] Preferably, the choke door includes a front edge and a rear edge, the front hinge portion of the telescopic assembly is pivotally connected to the front edge of the choke door, in the forward thrust state, the rear edge of the choke door is adjacent to or partially overlaps with the front edge of the inner sliding cover, and the aeroengine reverse thrust choke door mechanism further includes a seal provided between the rear edge of the choke door and the front edge of the inner sliding cover.

[0014] Preferably, in the forward thrust state, the choke door follower assembly is located on the front side of the inner sliding cover and is arranged adjacent to the front edge of the choke door.

[0015] By adopting the aeroengine reverse thrust choke door mechanism according to the present invention, not only is it possible to avoid components being exposed to the forward thrust airflow in the bypass duct, but also the movement mechanism is simple, the movement reliability is high, and the installation is more convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The specific embodiments of the present invention will be described in conjunction with the accompanying drawings, and the accompanying drawings are respectively:

[0017] Figure 1 A schematic diagram showing the aeroengine reverse thrust choke door mechanism according to the first preferred embodiment of the present invention in the forward thrust state.

[0018] Figure 2 Shows a schematic diagram of a part of the reverse thrust blocker door mechanism of an aeroengine in the forward thrust state according to the first preferred embodiment of the present invention.

[0019] Figure 3 Shows a three-dimensional schematic diagram of a part of the reverse thrust blocker door mechanism of an aeroengine in the forward thrust state according to the first preferred embodiment of the present invention.

[0020] Figure 4 Shows a schematic diagram of the reverse thrust blocker door mechanism of an aeroengine in the intermediate state according to the first preferred embodiment of the present invention.

[0021] Figure 5 Is a schematic diagram of a part of the reverse thrust blocker door mechanism of an aeroengine in the intermediate state according to the first preferred embodiment of the present invention.

[0022] Figure 6 Shows a three-dimensional schematic diagram of a part of the reverse thrust blocker door mechanism of an aeroengine in the intermediate state according to the first preferred embodiment of the present invention.

[0023] Figure 7 Shows a schematic diagram of the reverse thrust blocker door mechanism of an aeroengine in the reverse thrust state according to the first preferred embodiment of the present invention.

[0024] Figure 8 Is a schematic diagram of a part of the reverse thrust blocker door mechanism of an aeroengine in the reverse thrust state according to the first preferred embodiment of the present invention.

[0025] Figure 9 Shows a three-dimensional schematic diagram of a part of the reverse thrust blocker door mechanism of an aeroengine in the reverse thrust state according to the first preferred embodiment of the present invention.

[0026] Figure 10 Shows a three-dimensional view of the assembled state of the support sliding part (9) in the reverse thrust blocker door mechanism of an aeroengine according to the second preferred embodiment of the present invention.

[0027] Figure 11 Shows a three-dimensional view of the disassembled state of the support sliding part (9) in the reverse thrust blocker door mechanism of an aeroengine according to the second preferred embodiment of the present invention.

[0028] List of reference numerals

[0029] 1 Sliding cover outer cover

[0030] 2 Slide block

[0031] 21 Slide rail

[0032] 211 First position

[0033] Second position of 212

[0034] Outer wall of the bypass duct

[0035] Inner cover of the sliding cover

[0036] Actuating cylinder

[0037] Choke door

[0038] Link rod of 20

[0039] Front hinge part of 61

[0040] Upper hinge part of 62

[0041] Mounting bracket

[0042] Fixed mounting cylinder

[0043] Support gas spring

[0044] Connecting bolt

[0045] Grille

[0046] Equivalent mechanism

[0047] Spring of 121

[0048] Link rod of 122

[0049] Limit nut of 123

[0050] Fixed sleeve of 124 Specific implementation

[0051] The present invention will be further described below in conjunction with specific embodiments and the accompanying drawings. More details are set forth in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from this description. Those skilled in the art can make similar generalizations and deductions according to the actual application situation without departing from the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0052] In the following description, "front / front side / front direction" generally refers to the side or direction close to or facing the engine air intake of the engine bypass duct, and "rear / rear side / rear direction" generally refers to the side or direction close to or facing the engine exhaust port of the engine bypass duct.

[0053] Figure 1 A schematic diagram showing the thrust reverser choke door mechanism of an aeroengine according to the first preferred embodiment of the present invention in the forward thrust state. Figure 4 A schematic diagram showing the thrust reverser choke door mechanism of an aeroengine according to the first preferred embodiment of the present invention in the intermediate state.Figure 7 Fig. 1 shows a schematic view of an aeroengine thrust reverser blocker door mechanism according to a first preferred embodiment of the present invention in a thrust reverse state.

[0054] The aeroengine thrust reverser blocker door mechanism mainly includes a sliding cover, a blocker door 6 and a blocker door follower assembly. As the sliding cover moves, the blocker door follower assembly causes the blocker door 6 to switch between a forward position and a reverse position.

[0055] The sliding cover is a component that can slide relative to the fixed structure in the aeroengine thrust reverser blocker door mechanism. The sliding action of the sliding cover is intended to open and close the thrust reverse function. The sliding cover mainly includes an inner sliding cover 4 and an outer sliding cover 1. A sliding cover cavity is formed between the inner sliding cover 4 and the outer sliding cover 1. The inner sliding cover 4 defines a part of the outer wall of the engine bypass duct. In other words, the inner surface of the inner sliding cover 4 provides a part of the aerodynamic profile of the outer wall of the bypass duct. The inner sliding cover 4 and the outer sliding cover 1 are fixedly connected at their rear ends or near the rear ends, so that the inner sliding cover 4 and the outer sliding cover 1 can translate together in the translation direction A.

[0056] As Figure 1 shown, a grille 11 is also provided on the inner side of the outer sliding cover 1. When the thrust reverser blocker door mechanism is in the thrust reverse state, the airflow will flow out through the grille 11.

[0057] Figure 2 and Figure 3 Fig. 2 schematically shows an actuating cylinder 5 for driving the translation of the sliding cover. One end of the actuating cylinder 5 is connected to the fixed structure of the thrust reverser blocker door mechanism, for example, fixedly connected to the front bulkhead, while the other end of the actuating cylinder 5 is connected to the sliding cover. A part of the actuating cylinder 5 can be arranged in the sliding cover cavity between the inner sliding cover 4 and the outer sliding cover 1, and when the blocker door 6 is in the forward position, the actuating cylinder 5 is located between the blocker door 6 and the outer sliding cover 1. It should be understood that the number and installation position of the actuating cylinder 5 can be selected according to the shape and size of the sliding cover.

[0058] As Figure 1 shown, the blocker door 6 is arranged on the front side of the inner sliding cover 4. Preferably, the blocker door 6 has a front edge, a rear edge and two opposite side edges. In the forward state of the aeroengine thrust reverser blocker door mechanism, the rear edge of the blocker door 6 is adjacent to or partially overlaps with the front edge of the inner sliding cover 4. Thus, in the forward state, the inner surface of the blocker door 6 and the inner surface of the inner sliding cover 4 constitute the aerodynamic profile of the outer wall of the bypass duct. Preferably, a seal is provided between the rear edge of the blocker door 6 and the front edge of the inner sliding cover 4 to ensure the airtightness of the outer wall 3 of the bypass duct.

[0059] The thrust reverser blocker door mechanism of an aeroengine generally includes a plurality of blocker doors 6. The specific number of the blocker doors 6 depends on the aircraft model and is usually 8 - 16. The side edges of adjacent blocker doors 6 are adjacent to each other. Preferably, a seal is provided between the side edges to ensure the continuous airtightness of the outer bypass duct aerodynamic profile in the forward thrust state.

[0060] The blocker door follower assembly mainly includes a slider rotation assembly and a telescopic assembly. The telescopic assembly is installed on the fixed structure of the thrust reverser blocker door mechanism of the aeroengine, provides a connection to the front hinge portion 61 of the blocker door 6, and keeps the front hinge portion 61 capable of moving along the translation direction. The slider rotation assembly is installed on the sliding cover to move along with the translation of the sliding cover. The slider rotation assembly defines a pivot connection to the upper hinge portion 62 of the blocker door 6, and the upper hinge portion 62 can move between a first position 211 and a second position 212. The movement of the upper hinge portion 62 between the first position 211 and the second position 212 enables the blocker door 6 to rotate around the front hinge portion 61. In other words, the slider rotation assembly and the telescopic assembly respectively provide hinge portions in different motion dimensions, and the blocker door 6 realizes its reciprocating motion between the forward thrust position and the reverse thrust position through these two hinge portions 61 and 62.

[0061] In a first preferred embodiment, the slider rotation assembly includes a slider 2 and a connecting rod 20. The slider 2 is fixed to the sliding cover. When the sliding cover translates, the sliding cover drives the slider 2 to translate together. The slider 2 is provided with a slide rail 21. In this embodiment, the slide rail 21 is in the form of a strip-shaped groove. The slide rail 21 is configured to receive the upper hinge portion 62 and defines the movement track of the upper hinge portion 62 relative to the sliding cover, and this movement track includes the first position 211 and the second position 212. The connecting rod 20 has a first end and a second end. The first end of the connecting rod 20 is connected to the blocker door 6, specifically to the outer side of the blocker door 6 facing away from the bypass duct and near the front edge of the blocker door 6, while the second end of the connecting rod 20 is provided with the upper hinge portion 62, and the upper hinge portion 62 is received in the slide rail 21. Specifically, the hinge portion 62 is composed of a hole formed at the second end of the connecting rod 20 and a bolt 10, and the bolt 10 is received in the hole and the slide rail 21, so that the second end of the connecting rod 20 moves along the track defined by the slide rail 21.

[0062] Preferably, the slider 2 is fixed to the outer cover 1 of the sliding cover. However, in some alternative embodiments, the slider 2 can also be fixed to the inner cover 4 of the sliding cover. At this time, the front end of the inner cover 4 of the sliding cover includes an installation cavity for providing the installation space for the front hinge portion 61 and the upper hinge portion 62 of the blocker door 6.

[0063] Such as Figure 4As shown, the slide rail 21 on the slider 2 is in the form of a strip-shaped groove, which includes an inclined section and a horizontal section. The inclined section of the strip-shaped groove extends from the front end to the rear end and outward (i.e., away from the duct), that is, the front end is farther from the flow blocking door 6 than the rear end, and the horizontal section extends backward from the rear end of the inclined section substantially along the translation direction. The rear end of the horizontal section of the strip-shaped groove defines a first position 211. When the upper hinge portion 62 is located at the first position 211, the inner surface of the flow blocking door 6 is in the positive thrust position that can define the aerodynamic profile of the outer wall of the outer duct. The front end of the inclined section of the strip-shaped groove defines a second position 212. When the upper hinge portion 62 is located at the second position 212, the flow blocking door 6 deflects into the outer duct. In this embodiment, the first position 211 is closer to the rear and farther from the outer duct than the second position 212.

[0064] When the reverse thrust flow blocking door mechanism of the aeroengine is in the forward thrust state, the upper hinge portion 62 is located at the horizontal section of the strip-shaped groove and abuts against the rear end of the horizontal section (the first position 211). The setting of the horizontal section can restrain the flow blocking door 6 on the aerodynamic profile of the outer wall 3 of the outer duct, and the horizontal section can prevent the flow blocking door 6 from deflecting into the outer duct due to gravity.

[0065] Figure 3 Shown is a telescopic assembly for providing the front hinge portion 61 according to the first embodiment of the present invention. The telescopic assembly includes a fixed mounting cylinder 8 and a support gas spring that is extendable relative to the fixed mounting cylinder 8. The fixed mounting cylinder 8 is mounted on the fixed structure of the reverse thrust flow blocking door mechanism of the aeroengine through a mounting bracket 7 or other fastening means. Preferably, the fixed mounting cylinder 8 is mounted on the front bulkhead of the reverse thrust flow blocking door mechanism of the aeroengine. The fixed mounting cylinder 8 can be fixed together with the outer fixed part of the support gas spring 9 through a support or other fixing means. The front hinge portion 61 is provided at the free end of the telescopic rod of the support gas spring, and the free end of the telescopic rod is pivotally connected to the front edge of the flow blocking door. For example, the front hinge portion 61 can be pivotally mounted by providing a support on the flow blocking door. The support gas spring is configured to provide a supporting force using gas pressure to hold the flow blocking door 6 through the front hinge portion 61. When the reverse thrust flow blocking door mechanism of the aeroengine is in the forward thrust state, the telescopic rod of the support gas spring is in the contracted position. When the reverse thrust flow blocking door mechanism of the aeroengine is in the reverse thrust state, the telescopic rod of the support gas spring is in the extended position. In this extended position, the support gas spring can provide a backward thrust to the flow blocking door 6. It should be understood that the extension and contraction in the support gas spring are driven by the translational movement of the sliding cover, and the extension distance of the telescopic rod of the support gas spring is less than the translational distance of the sliding cover.

[0066] Hereinafter, in combination with Figures 1 - 10 Describe the operation process of the reverse thrust flow blocking door mechanism of the aeroengine according to the first embodiment of the present invention.

[0067] Figure 1The figure shows that the thrust reverser blocker door mechanism of the aeroengine is in the forward thrust state. At this time, the inner surfaces of both the blocker door 6 and the inner cover 4 of the sliding cover continuously form a part of the aerodynamic profile of the bypass duct wall. At this time, the front hinge portion 61 on the telescopic assembly is in the retracted position, and the upper hinge portion 62 on the translation pivot assembly is in the first position.

[0068] Through the action of the actuating cylinder 5, the sliding cover translates backward towards the rear of the bypass duct, driving the slider 2 to move backward. The support gas spring 9 extends backward from the fixed mounting cylinder 8, and the blocker door 6 moves towards the rear side of the bypass duct while maintaining its forward thrust position. When the support gas spring 9 reaches its maximum extension, it stops extending, and the front hinge portion 61 remains fixed at the maximum extension position. At this time, the actuating cylinder 5 continues to act, and the sliding cover and the slider 2 continue to move backward towards the rear of the bypass duct. Since the front edge of the blocker door is restricted by the front hinge portion 61, at this time, the upper hinge portion 62 moves downward and forward in the strip-shaped groove of the slider 2 until it reaches the second position. The blocker door 6 is pushed by the connecting rod 20 to deflect into the bypass duct around the front hinge portion 61, entering the reverse thrust position where the bypass duct of the aeroengine is blocked. As Figure 7 shown, at this time, the bypass duct air flow is discharged from the grille 11, providing reverse thrust for the aircraft, thereby enabling the shortening of the aircraft's landing roll distance.

[0069] The switching of the thrust reverser blocker door mechanism of the aeroengine from the reverse thrust state to the forward thrust state is also driven by the actuating cylinder 5. As the actuating cylinder 5 contracts and drives the sliding cover to move forward towards the front of the bypass duct, initially, the support gas spring 9 is at its maximum extension and continuously provides a thrust towards the rear of the bypass duct, keeping the position of the front hinge portion 61 of the blocker door unchanged. The upper hinge portion 62 moves backward along the strip-shaped groove on the slider 2 to the horizontal section, thereby driving the blocker door 6 to deflect outward around the front hinge portion 61 to reach the forward thrust position where it is continuous with the inner cover of the slider. The actuating cylinder 5 continues to contract, and the sliding cover drives the slider 2 to continue moving forward towards the front of the bypass duct 3. The acting force of the actuating cylinder 5 is greater than the backward thrust of the support gas spring 9. At this time, the support gas spring 9 retracts into the fixed mounting cylinder 8. Finally, the thrust reverser blocker door mechanism of the aeroengine reaches the forward thrust state as Figure 1 shown.

[0070] Figure 10 and Figure 11 The figure shows the equivalent mechanism 12 of the telescopic assembly according to the second embodiment of the present invention. As Figure 11 shown, the equivalent mechanism 12 of the telescopic assembly includes a fixed mounting cylinder 8, a fixed sleeve 124 installed in the fixed mounting cylinder 8, a connecting rod 122 that is telescopable relative to the fixed sleeve 124, a spring that provides a thrust in the rearward direction, and a limit nut 123. The limit nut 123 is fixed to the connecting rod 122, and a baffle is provided in the fixed sleeve 124 to stop the movement of the limit nut, thereby limiting the extension length of the connecting rod 122.

[0071] During the process of the reverse thrust blocker door mechanism of the aero-engine switching from the forward thrust state to the reverse thrust state and from the reverse thrust state to the forward thrust state, the action mode of the telescopic assembly is similar to that of the support gas spring in the first embodiment.

[0072] Specifically, through the action of the actuator 5, the sliding cover translates backward toward the rear of the outer duct, driving the slider 2 to move backward. The support gas spring 9 extends backward from the fixed mounting cylinder 8, and the blocker door 6 moves toward the rear side of the outer duct while maintaining its forward thrust position. When the connecting rod 122 in the telescopic assembly reaches the maximum extension amount, it stops extending. At this time, the nut 123 abuts against the baffle in the fixed sleeve 124, making the front hinge portion 61 immovable. The actuator 5 continues to act, and the sliding cover and the slider 2 continue to move backward toward the rear of the outer duct. Since the front edge of the blocker door is restricted by the front hinge portion 61, at this time, the upper hinge portion 62 moves inward and forward in the slide rail 21 of the slider 2 until it reaches the second position, and the blocker door 6 deflects into the outer duct around the front hinge portion 61, entering the reverse thrust position where the outer duct of the aero-engine is blocked.

[0073] When the reverse thrust blocker door mechanism of the aero-engine switches from the reverse thrust state to the forward thrust state, as the actuator 5 contracts and drives the sliding cover to move forward toward the front of the outer duct, at the beginning, the connecting rod 122 in the telescopic assembly remains at the maximum extension amount, and the spring 121 applies a thrust force toward the rear of the outer duct to keep the position of the front hinge portion 61 of the blocker door unchanged. The upper hinge portion 62 moves backward along the strip-shaped groove on the slider 2 to the horizontal section, thereby driving the blocker door 6 to deflect outward around the front hinge portion 61 to reach the forward thrust position that is continuous with the inner cover of the sliding cover. The actuator 5 continues to contract, and the sliding cover drives the slider 2 to continue to move forward toward the front of the outer duct 3. The acting force of the actuator 5 is greater than the thrust force applied by the spring 121 toward the rear of the outer duct. At this time, the connecting rod 122 retracts into the fixed mounting cylinder 8 and finally returns to the forward thrust state.

[0074] As Figure 1 shown, the blocker door of the reverse thrust blocker door mechanism of the aero-engine according to the present invention provides a part of the outer wall surface of the outer duct. In the forward thrust state, the entire follower assembly of the blocker door is located on the front side of the inner cover of the sliding cover and is arranged adjacent to the front edge of the blocker door 6. Therefore, there is no need to reserve too much space between the inner cover 4 and the outer cover 1 of the sliding cover, making the overall sliding cover more compactly designed.

[0075] Preferably, the extension amount of the telescopic assembly is adjustable. For example, the extension amount of the telescopic assembly can be adjusted by adjusting the maximum extension length of the support gas spring 9 or by adjusting the position of the nut 123 on the connecting rod 122. In this way, the position of the front hinge portion 61 can be adjusted, and accordingly, the tilt angle of the blocker door 6 in the outer duct of the engine can be adjusted when controlling the reverse thrust state.

[0076] In addition, the tilt angle of the flow blocking door in the engine bypass duct can also be adjusted by adjusting the length of the connecting rod and the shape of the strip-shaped groove in the slider rotating assembly.

[0077] The reverse thrust flow blocking door mechanism of the aeroengine according to the present invention not only avoids the components from being exposed to the forward thrust airflow in the bypass duct, but also has a relatively simple movement mechanism, high movement reliability and more convenient installation.

[0078] Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can 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 based on the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. An aircraft engine reverse thrust baffle mechanism, the aircraft engine reverse thrust baffle mechanism has a forward thrust state and a reverse thrust state, and comprises: A sliding cover, wherein the sliding cover is movable relative to a fixed structure of a reverse thrust block mechanism of an aircraft engine; a blocker door, the blocker door being arranged at the front side of the inner cover of the sliding cover and being rotatable between a forward thrust position and a reverse thrust position; and a blocker door follower assembly, wherein the blocker door follower assembly is configured to cause the blocker door to rotate as the sliding cover translates along a translation direction; Characterized in that the baffle follower assembly comprises: A telescopic assembly (9, 12), the telescopic assembly having a front hinged portion (61) for hingedly connecting the spoiler door and configured to keep the front hinged portion moving along the translation direction with the sliding cover; A slider rotating assembly, the slider rotating assembly is mounted on the sliding cover and moves with the sliding cover, the slider rotating assembly has an upper hinge portion (62) pivotally connected to the blocking door, and the upper hinge portion (62) can move between a first position and a second position; as well as In the forward thrust state, the upper hinge portion (62) is located at a first position, and the inner surface of the baffle door defines a portion of the outer wall surface of the outer duct; In the reverse thrust state, the upper hinged portion (62) is located at the second position, and the baffle door rotates relative to the sliding cover and enters the outer duct.

2. The aircraft engine reverse thrust baffle mechanism according to claim 1, characterized in that: The slider rotating assembly comprises: a sliding block (2), the sliding block being fixed to the sliding cover and having a sliding rail (22) thereon, the sliding rail defining the first position and the second position of the upper hinge portion (62); A connecting rod, a first end of which is connected to the blocking door, and a second end of which is arranged to be pivotally engaged with the upper hinge portion (62) of the bar-shaped slot.

3. The aircraft engine reverse thrust baffle mechanism according to claim 2, characterized in that: The slide rail comprises a strip-shaped groove, and the strip-shaped groove comprises an inclined section and a horizontal section. The inclined section extends backward and outward from the front end to the rear end, and the horizontal section extends backward from the rear end of the inclined section.

4. The aircraft engine reverse thrust baffle mechanism according to claim 1, characterized in that: The fixed structure includes a front bulkhead, the telescopic assembly includes a fixed mounting tube and a supporting gas spring that can be extended relative to the fixed mounting tube, the fixed mounting tube is installed on the front bulkhead, and the supporting gas spring can provide a thrust toward the rear of the sliding cover.

5. The aircraft engine reverse thrust baffle mechanism according to claim 1, characterized in that: The telescopic assembly comprises: Fixed installation cylinder; A fixed sleeve installed in the fixed installation cylinder, wherein a baffle is provided in the fixed sleeve; a connecting rod that is retractable relative to the fixed sleeve; A spring providing a urging force in a rearward direction; and A limiting nut is fixed on the connecting rod. When the limiting nut abuts against the baffle, the extending movement of the connecting rod stops.

6. The aircraft engine reverse thrust baffle mechanism according to claim 1, characterized in that: The sliding cover comprises a sliding cover inner cover and a sliding cover outer cover, wherein a sliding cover cavity is formed between the sliding cover inner cover and the sliding cover outer cover. The inner surface of the sliding cover inner cover and the inner surface of the blocker door are continuous to define an outer wall surface of the outer duct.

7. The aircraft engine reverse thrust baffle mechanism according to claim 6, characterized in that: The aircraft engine reverse thrust blocker mechanism also includes an actuator (5) for providing driving force to the sliding cover. One end of the actuating cylinder (5) is connected to the fixed structure of the reverse thrust blocking valve mechanism, and the other end of the actuating cylinder (5) is connected to the sliding cover. The actuator (5) is at least partially arranged in the sliding cover cavity between the sliding cover inner cover and the sliding cover outer cover.

8. The aircraft engine reverse thrust baffle mechanism according to claim 6, characterized in that: The baffle door comprises a front edge and a rear edge, the front hinge portion (61) of the telescopic assembly is pivotally connected to the front edge of the baffle door, In the forward thrust state, the rear edge of the blocker door and the front edge of the inner cover of the sliding cover are adjacent to or partially overlapped with each other. The aircraft engine reverse thrust blocker mechanism further comprises a sealing member arranged between the rear edge of the blocker and the front edge of the sliding cover inner cover.

9. The aircraft engine thrust reverse blocker mechanism according to claim 6, characterized in that: In the forward thrust state, the blocker follower assembly is located at the front side of the inner cover of the sliding cover and is arranged adjacent to the front edge of the blocker.

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