Rapid disassembling device and method for small-aperture interference pin shaft of aero-engine

Abstract

The invention discloses a rapid disassembling device and method for a small-aperture interference pin shaft of an aero-engine, the disassembling device comprises a sleeve, a screw rod and a nut, the sleeve is a cylindrical cavity barrel with an incomplete circumferential surface and an open lower end, and a through hole is formed in the axial upper end face of the sleeve; a non-thread clamping section, a first external thread section and a second external thread section are sequentially arranged in the axial direction of the screw rod, the outer diameter of the first external thread section is larger than that of the second external thread section, the outer diameter of the first external thread section of the screw rod is smaller than the hole diameter of the through hole of the sleeve, and the outer diameter of the second external thread section is matched with the hole diameter of the internal thread hole of the pin shaft; and the nut is sleeved on the first external thread section of the screw rod and is positioned on the outer side of the cavity of the sleeve. In the disassembling process, the sleeve opening avoids the pin shaft boss and is attached to the installation base, the nut is rotated while the screw rod is stopped, so that the sleeve is extruded, the screw rod is lifted, and finally the pin shaft is disassembled. The device is easy to install and high in decomposition efficiency, and the problem of collision in the decomposition process is effectively avoided.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft engine complete machine assembly and test running, and in particular relates to a rapid disassembly device and method for a small-diameter interference pin shaft of an aircraft engine. Background Art

[0002] In order to ensure the reliability and safety of the connection, the external system of the aircraft engine, such as Figure 7 As shown, the main accessory installation structures mostly use small-diameter interference pin connections to transmit force, which can be achieved by the temperature difference method during assembly. However, when disassembling, the spatial position of the structure is usually often blocked. At the same time, because it is an interference fit, it is difficult to use conventional disassembly methods, which can easily cause quality problems such as part damage.

[0003] Based on the above problems, it is necessary to design a device that is easy to disassemble according to the structural characteristics of the part to improve the decomposition efficiency and quality. Summary of the invention

[0004] The present invention aims to provide a rapid disassembly device and method for a small-diameter interference pin shaft of an aircraft engine, which has the characteristics of rapid installation of the disassembly device, thereby achieving the purpose of rapid disassembly of the pin shaft.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A quick disassembly device for a small-diameter interference pin shaft of an aircraft engine, comprising:

[0007] The sleeve is a cylindrical hollow body with an incomplete circumferential surface and an open lower end, which is obtained by a plane parallel to the cylindrical axis being tangent to the cylinder, so that there is an opening on the circumferential cylindrical surface of the sleeve that is connected to the hollow cavity of the sleeve, and a through hole is opened on the axial upper end surface of the sleeve;

[0008] A screw rod, wherein the axial direction of the screw rod is sequentially composed of a non-threaded clamping section, a first external thread section, and a second external thread section, wherein the outer diameter of the first external thread section is greater than the outer diameter of the second external thread section, the outer diameter of the first external thread section of the screw rod is smaller than the aperture of the through hole of the sleeve, and the outer diameter of the second external thread section matches the aperture of the internal thread hole of the pin shaft;

[0009] A nut is sleeved on the first external thread section of the screw rod and is located outside the cavity of the sleeve.

[0010] Furthermore, the opening width on the sleeve is greater than the maximum outer diameter of the pin boss at the end of the internal threaded hole of the pin.

[0011] Furthermore, the non-threaded clamping section of the screw is a regular prism with four or more sides.

[0012] A method for quickly disassembling a small-diameter interference pin for an aero-engine adopts the above-mentioned quick disassembly device and comprises the following steps:

[0013] Step 1, screwing the second external thread section into the internal thread hole of the pin by screwing the non-threaded clamping section of the screw;

[0014] Step 2: Place the open end of the sleeve toward the internal threaded hole of the pin shaft, then align the through hole of the sleeve with the screw and insert the sleeve into the screw, and ensure that the pin shaft boss at the internal threaded hole end of the pin shaft just falls into the opening of the sleeve;

[0015] Step 3, screw the nut from the non-threaded clamping section of the screw rod into the first external threaded section until the end face of the nut fits the sleeve and the open end of the sleeve fits the surface of the mounting seat where the pin is located;

[0016] Step 4: Use a tool to clamp the non-threaded clamping section of the screw, and under the premise of ensuring that the non-threaded clamping section does not rotate, continue to screw the nut in the direction of screwing the nut in step 3 until the pin is disassembled from the mounting seat.

[0017] Compared with the prior art, the disassembly device provided by the present invention facilitates the disassembly of the small-diameter interference pin of the aircraft engine, is simple to install, has high disassembly efficiency, improves the disassembly quality of the engine, and effectively avoids the problem of bruises occurring during the disassembly process. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a structural diagram of the decomposition device of the small-diameter interference pin of an aircraft engine;

[0019] Figure 2 for Figure 1 A top view of

[0020] Figure 3 for Figure 2 Schematic diagram of the AA section;

[0021] Figure 4 It is a schematic diagram of a sleeve cross section (part);

[0022] Figure 5 is a schematic diagram of a screw;

[0023] Figure 6 It is a schematic diagram of the state of the disassembly device disassembling the pin shaft on the mounting seat;

[0024] Figure 7 It is a schematic diagram of the accessory pin structure, including a mounting seat and a pin;

[0025] In the figure: 1-nut, 2-sleeve, 3-screw. DETAILED DESCRIPTION

[0026] The present invention is further described below in conjunction with specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to common technical knowledge and customary means in the field are included in the scope of the present invention.

[0027] like Figure 1 to Figure 6 As shown, a small-diameter interference pin quick disassembly device provided in this embodiment comprises a nut 1, a sleeve 2 and a screw 3, wherein:

[0028] like Figure 2 and Figure 4 The sleeve 2 is designed as a semi-arc-cylindrical structure, which can withstand the pressure when the pin is disassembled on the one hand, and can effectively avoid interference with the pin boss on the other hand.

[0029] like Figure 3 and Figure 5 The screw 3 is designed with a square head and a two-stage thread structure. The square head is designed on the one hand to facilitate the small outer diameter thread of the screw 3 to be screwed into the internal thread hole of the pin shaft. On the other hand, when the nut 1 is screwed, the square head can be used to stop the screw 3 to prevent it from rotating. The large outer diameter thread interacts with the nut 1, and the end face of the sleeve 2 is squeezed by the nut 1. Under the action of force and reaction force, the screw 3 drives the pin shaft to disengage from the mounting seat, thereby realizing the rapid decomposition of the pin shaft.

[0030] The principle and method of using the above disassembly device to quickly disassemble a small-diameter interference pin is as follows:

[0031] Principle: When in use, the nut 1, the sleeve 2 and the screw rod 3 form a whole, and the pin is disengaged from the mounting seat by the interaction between the screw 1 (1 piece) and the screw rod 3 (1 piece).

[0032] Disassembly method: Use the square head on the screw rod 3 to screw the screw rod 3 into the internal threaded hole of the pin. Then insert the sleeve 2 into the screw rod 3 and pass it through. Adjust the angle of the sleeve 2 (1 piece) to ensure that the opening of the sleeve 2 avoids the step of the pin and that the lower end surface of the sleeve 2 fits the mounting seat. Finally, install the nut 1 on the screw rod 3, stop it with the help of the square head on the screw rod 3, and by screwing the nut 1, the pin is driven out of the mounting seat under the action of force and reaction force, so as to achieve rapid disassembly of the pin.

[0033] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in the field. Although the illustrative specific embodiments of the present invention are described above to facilitate the understanding of the present invention by the technical personnel in the field, it should be clear that the present invention is not limited to the scope of the specific embodiments. For ordinary technicians in the field of this technology, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

Claims

1. A quick disassembly device for a small-diameter interference pin of an aircraft engine, characterized in that: include: A sleeve (2), wherein the sleeve (2) is a cylindrical hollow body with an incomplete circumferential surface and an open lower end, and is obtained by a plane parallel to the cylindrical axis being tangent to the cylinder, so that an opening communicating with the hollow cavity of the sleeve (2) is provided on the circumferential cylindrical surface of the sleeve (2), and a through hole is provided on the axial upper end surface of the sleeve (2); A screw rod (3), which comprises a non-threaded clamping section, a first external thread section and a second external thread section in order along the axial direction of the screw rod (3), wherein the outer diameter of the first external thread section is greater than the outer diameter of the second external thread section, the outer diameter of the first external thread section of the screw rod (3) is smaller than the aperture of the through hole of the sleeve (2), and the outer diameter of the second external thread section matches the aperture of the internal thread hole of the pin shaft; A nut (1) is sleeved on a first external thread section of a screw rod (3) and is located outside a cavity of a sleeve (2).

2. A quick disassembly device for a small-diameter interference pin of an aircraft engine according to claim 1, characterized in that: The width of the opening on the sleeve (2) is greater than the maximum outer diameter of the pin boss at the end of the pin internal thread hole.

3. The rapid disassembly device for a small-diameter interference pin of an aircraft engine according to claim 1, characterized in that: The non-threaded clamping section of the screw rod (3) is a regular prism with four or more sides.

4. A method for quickly disassembling a small-diameter interference pin for an aircraft engine, characterized in that: The rapid decomposition device according to claim 1 is used, and comprises the following steps: Step 1, screwing the second external thread section into the internal thread hole of the pin shaft by screwing the non-threaded clamping section of the screw (3); Step 2: Place the open end of the sleeve (2) toward the internal threaded hole of the pin, then align the through hole of the sleeve (2) with the screw (3) and insert the sleeve (2) into the screw (3), and ensure that the pin boss at the end of the internal threaded hole of the pin fits into the opening of the sleeve (2); Step 3, screwing the nut (1) from the non-threaded clamping section of the screw (3) into the first external threaded section until the end face of the nut (1) fits the sleeve (2), and the open end of the sleeve (2) fits the surface of the mounting seat where the pin is located; Step 4: Use a tool to clamp the non-threaded clamping section of the screw rod (3), and under the premise of ensuring that the non-threaded clamping section does not rotate, continue to screw the nut (1) in the direction of screwing the nut (1) in step 3 until the pin is disassembled from the mounting seat.

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