Reverse thrust cover opening retainer of aero-engine

Abstract

The utility model discloses a retaining frame for opening a reverse thrust cover of an aero-engine. The retaining frame comprises a connecting piece and two main body pieces, a large number of air entraining pipelines and fuel oil pipelines exist between an aircraft hanger and a core engine of an engine, and most of the air entraining pipelines and the fuel oil pipelines are hard metal pipes. Therefore, the space for mounting the retainer and the operation space of personnel are very limited. And due to the split mounting type design, the size of a single part is effectively reduced, and the mounting difficulty is greatly reduced. According to the installation process, the two main body pieces can be rapidly and respectively connected between the two reverse thrust covers and the aircraft hanger, and then the connecting piece is installed between the two main body pieces, so that the two reverse thrust covers are kept open. The thrust reverser has the beneficial effects that an actuating cylinder is replaced to maintain the opening state of the thrust reverser for a long time; the situations of hydraulic oil return, insufficient pressure and reverse thrust cover shrinkage of the actuator cylinder are avoided; and the actuating cylinder can also be detached to be overhauled and maintained.

Description

Technical Field

[0001] The utility model relates to the opening of an aircraft engine reverse thrust cover, in particular to an aircraft engine reverse thrust cover opening retaining frame. Background Art

[0002] For airlines, routine inspection, maintenance, servicing, and replacement of aircraft engines are essential tasks, many of which require opening the engine's thrust reverser cowlings. Each engine's thrust reverser system consists of two left and right thrust reverser cowlings (hereinafter referred to as "reverse cowlings"), each weighing approximately 350 kg. During normal aircraft operation, the thrust reversers are opened by two actuators controlled by electric valves. However, during maintenance, the cowlings must first be opened by manually depressurizing the opening actuators. Since maintenance work can take anywhere from two hours to over ten days, leaving the depressurization equipment connected to the actuators for extended periods of time can cause hydraulic oil backflow, insufficient pressure, and collapse of the cowlings. This can cause damage to maintenance personnel, the depressurization equipment, and even the engine's hydraulic components, posing a safety hazard. Utility Model Content

[0003] The utility model aims to design an aircraft engine reverse thrust cover opening retaining frame, which can be installed and fixed after the reverse thrust cover is opened, and can maintain the reverse thrust cover in the open state for a long time.

[0004] In the present application, an aircraft engine thrust reverser cowl opening retainer is provided, comprising:

[0005] The main part has installation positions on both the left and right sides;

[0006] Two connecting parts are respectively detachably fixedly connected to the two installation positions of the main body; the top surface of the connecting part is inclined and has a raised outer connection point and an inner connection point; among the outer connection point and the inner connection point of the connecting part, the outer connection point is used for connection to the reverse thrust cover and has a lower height; the inner connection point is used for suspension connection and has a higher height.

[0007] In some embodiments, the two installation positions of the main body are both installation slots, and the front and rear side portions of the installation slot each have two first holes; the connecting member has two matching second holes.

[0008] In some embodiments, the angle between the top surfaces of the two connecting members is 115° to 125°.

[0009] In some embodiments, an inclined boss is further provided at a middle position on the rear side of the main body.

[0010] In some embodiments, a quick-release pin for achieving detachability is provided between the connecting member and the main body.

[0011] In some embodiments, both the front and rear side surfaces of the connecting member have cutting grooves between the two second hole positions, and the two cutting grooves are not connected.

[0012] In some embodiments, a gap is left between the bottom surface of the connecting member and the inner bottom wall of the mounting groove.

[0013] In summary, in the present application, an aircraft engine reverse thrust cowl opening retainer includes a connecting piece and two main parts. There are many air bleed pipes and fuel pipes between the aircraft pylon and the engine core, and most of them are hard metal pipes. Therefore, the space for installing the retainer and the operating space for personnel are very limited. The assembled design effectively reduces the volume of individual parts, greatly reducing the difficulty of installation. Installation process: The two main parts can be quickly connected between the two reverse thrust cowls and the aircraft pylon, and then the connecting piece is installed between the two main parts, so that the two reverse thrust cowls remain open. Beneficial effects: replacing the actuator to maintain the open state of the reverse thrust cowl for a long time; avoiding the possible hydraulic oil return, insufficient pressure, and retraction of the reverse thrust cowl in the actuator; and allowing the actuator to be removed for inspection and maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the background technology, the drawings required for use in the embodiments of the present application or the background technology will be described below.

[0015] Figure 1 A schematic diagram of this application;

[0016] Figure 2 is a schematic diagram of the main part;

[0017] Figure 3 is a schematic diagram of the connecting parts;

[0018] Figure 4 It is a rear side view of the present application after the connecting piece is cut open.

[0019] In the figure,

[0020] 1. Connector; 1a. Installation position; 1a1. First hole; 1a2. Inner bottom wall; 1b. Inclined boss;

[0021] 2. Main body; 2a. Outer connection point; 2b. Inner connection point; 2c. Second hole; 2d. Cutting groove;

[0022] 3. Fasteners. DETAILED DESCRIPTION

[0023] The following is further explained with reference to the accompanying drawings, which are provided for illustrative purposes only and are not drawn to scale. Unless otherwise defined, technical or scientific terms used in this disclosure should have the same ordinary meaning as those understood by persons of ordinary skill in the art to which this disclosure pertains. The terms "first," "second," and similar expressions used in this disclosure do not denote any order, quantity, or importance, but are used only to distinguish between different components. Terms such as "include" or "comprising" mean that the element or object preceding the term includes the elements or objects listed after the term, and their equivalents, without excluding other elements or objects. Terms such as "connected" or "connected" are not limited to physical or mechanical connections but may include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; if the absolute position of the described object changes, the relative positional relationship may also change accordingly. The embodiments of this application are combinable unless there is a conflict.

[0024] See also Figure 1 and Figure 4 , an aircraft engine reverse thrust cover opening retainer, including a connecting part 1 and two main parts 2.

[0025] See also Figure 1 and Figure 3 , there are installation positions 1a on the left and right sides of the connecting member 1.

[0026] See also Figure 1 and Figure 2 The two main parts 2 are respectively detachably fixed to the two mounting positions 1a of the connector 1. The top surface of the main part 2 is inclined, and there are also raised outer connection points 2a and inner connection points on the top surface.

[0027] Of the outer and inner connection points 2a, 2b of the main body 2, the outer connection point 2a is used for connection to the thrust reverser shield and is at a lower height, while the inner connection point 2b is used for connection to the aircraft sling and is at a higher height. In other words, the top surface of the main body 2 is tilted so that the outer side is lower and the inner side is higher.

[0028] The connection between the outer connection point 2a and the reverse thrust cover, and the connection between the inner connection point 2b and the aircraft suspension can both be completed using quick-release pins, which facilitates the release and establishment of connections.

[0029] There are many air bleed pipes and fuel pipes between the aircraft pylon and the engine core, and most of them are hard metal pipes. Therefore, the space for installing the retaining bracket and the operating space for personnel are very limited. If an integrated design is used, it is very difficult to pass the retaining bracket through the various pipes, and it is also very difficult to install the left and right quick-release pins. The assembled design effectively reduces the volume of individual parts, greatly reducing the difficulty of installation. Installation process: The two main parts 2 can be quickly connected to the two reverse thrust cowls and the aircraft pylon respectively, and then the connecting part 1 is installed between the two main parts 2, so that the two reverse thrust cowls remain open.

[0030] The bottom surface of the main body 2 may be horizontal in some embodiments, or inclined in some embodiments.

[0031] See also Figure 2 Preferably, the bottom surface of the main body 2 is designed as the latter, and the inclination is the same as that of the top surface, that is, the bottom surface and the top surface of the main body 2 are parallel. In this way, the main body 2 has a uniform width and is generally rectangular, which makes it easier to design the fixed connection between the main body 2 and the main body and is more conducive to ensuring the strength of the main body 2 and the main body at the connection point.

[0032] Regarding the fixed connection method between the main body 2 and the main body, in some embodiments, the two installation positions 1a of the connector 1 can both be installation planes, and there is a third hole position on the installation plane. The bottom surface of the main body 2 has a matching fourth hole position, which fits the installation plane, that is, the fastener 3 is used to match the third hole position and the fourth hole position to complete the fixed connection; in some embodiments, the two installation positions 1a of the connector 1 can both be installation grooves, and the front and rear side parts of the installation groove have two first hole positions 1a1, and the main body 2 has two matching second hole positions 2c, that is, the fastener 3 is used to match the first hole position 1a1 and the second hole position 2c to complete the fixed connection.

[0033] See also Figure 2 and Figure 3 Preferably, the fixed connection between the main body 2 and the connector 1 is designed to be the latter. Thus, after the retainer is connected to the two reverse thrust cowls and the aircraft pylon, the retainer primarily bears the weight of the reverse thrust cowls when closed under gravity. This load is carried by the fasteners 3, converting it into shear force within the fasteners 3. This not only reduces the stress on the main body 2 and connector 1, but also utilizes the lighter 7075 aviation aluminum alloy, reducing maintenance costs by requiring only regular inspection and replacement of the fasteners 3.

[0034] See also Figure 1 In some embodiments, a quick-release pin is provided between the main body 2 and the connecting member 1 for achieving detachability, that is, the above-mentioned fastener 3 is a quick-release pin.

[0035] Compared with bolts, nuts, etc., the quick-release pin makes the installation and disassembly between the main part 2 and the connecting part 1 more convenient, and the replacement of a new quick-release pin is also more convenient.

[0036] See also Figure 2 and Figure 4 In some embodiments, based on the above-mentioned embodiment of "both the two installation positions 1a of the connecting member 1 can be installation grooves", the front side and the rear side of the main body 2 have cutting grooves 2d, and the cutting grooves 2d are between the two second hole positions 2c, and the two cutting grooves 2d are not connected.

[0037] Two cutting grooves 2d are designed to reduce the weight of the middle position of the main body 2. In order to ensure the overall strength of the main body 2, the entire part is not cut, that is, a part is left between the two cutting grooves 2d to ensure strength.

[0038] See also Figure 3 and Figure 4 In some embodiments, based on the above embodiment of "both the two installation positions 1a of the connecting member 1 can be installation grooves", a distance is left between the bottom surface of the main body 2 and the inner bottom wall 1a2 of the installation groove.

[0039] For mounting positions 1a that are grooves, even if the bottom surface of the main body 2 and the inner bottom wall 1a2 of the groove do not align, it is still relatively easy to position the main body 2 and the connector 1 so that the second hole 2c aligns with the first hole 1a1. The gap left by the misalignment between the bottom surface of the main body 2 and the inner bottom wall 1a2 of the groove allows for wires to pass through when needed.

[0040] See also Figure 4 In some embodiments, the angle between the top surfaces of the two main body members 2 (i.e. Figure 4 The angle of ∠1) is 115° to 125°. In this way, after the retaining frame is connected to the two reverse thrust shields and the aircraft suspension, the angle between the two reverse thrust shields can be within a more appropriate range, showing a more appropriate opening state.

[0041] See also Figure 3 In some embodiments, an inclined boss 1b is further provided in the middle of the rear side of the connector 1. More specifically, a portion of the connector 1 is cut away at this location, thereby tilting the top surface of the inclined boss 1b. This is done to prevent interference during actual use.

Claims

1. An aircraft engine thrust reverser cowl opening retainer, characterized in that: include: The main body (2) has mounting positions (1a) on both the left and right sides; Two connecting members (1) are respectively and detachably fixedly connected to two installation positions (1a) of the main body (2); the top surface of the connecting member (1) is inclined and has a raised outer connecting point (2a) and an inner connecting point (2b); of the outer connecting point (2a) and the inner connecting point (2b) of the connecting member (1), the outer connecting point (2a) is used for connection with the reverse thrust cover and has a lower height; the inner connecting point (2b) is used for suspension connection and has a higher height.

2. The aircraft engine thrust reverser cover opening retainer according to claim 1, characterized in that: The two installation positions (1a) of the main body (2) are both installation slots, and the front and rear side portions of the installation slot each have two first hole positions (1a1); the connecting member (1) has two matching second hole positions (2c).

3. The aircraft engine thrust reverser cover opening retainer according to claim 1, characterized in that: The angle between the top surfaces of the two connecting members (1) is 115° to 125°.

4. The aircraft engine thrust reverser cover opening retainer according to claim 1, characterized in that: An inclined boss (1b) is also provided at the middle position of the rear side of the main body (2).

5. The aircraft engine thrust reverser cover opening retainer according to claim 1, characterized in that: A quick-release pin for achieving detachability is provided between the connecting member (1) and the main body member (2).

6. The aircraft engine thrust reverser cover opening retainer according to claim 2, characterized in that: The front and rear side surfaces of the connecting member (1) are both provided with cutting grooves (2d) between the two second hole positions (2c), and the two cutting grooves (2d) are not connected.

7. The aircraft engine thrust reverser cowl opening retainer according to claim 2, characterized in that: A distance is left between the bottom surface of the connecting member (1) and the inner bottom wall (1a2) of the installation groove.

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