Device and method for quickly installing connecting piece in blind cavity of aero-engine

Abstract

The invention discloses a device and a method for quickly installing a connecting piece in a blind cavity of an aero-engine, the device mainly takes a stop seat and a bow-shaped wrench as main components, and radial positioning is realized through matching of an adapter pin on the bow-shaped wrench and a positioning hole of an adapter disc on the stop seat; axial positioning is achieved through the joint of the cushion block on the bow-shaped wrench and the front end face of the adapter disc on the stop base. When the connecting piece is installed, a torque wrench or other tools are adopted to apply rotating torque to the switching pin so as to drive the bow-shaped wrench to rotate, and then the lifting pin, the pusher dog, the ratchet wheel and the sleeve at the lower end of the bow-shaped wrench drive the connecting nut to be matched with the connecting bolt, so that rapid installation is achieved. The connecting nut can be installed stably, rapidly and safely, and meanwhile the assembling quality of the gas compressor rotor is guaranteed.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft engine complete machine assembly and test running, and specifically relates to a device and method for quickly installing a connecting piece in a blind cavity of an aircraft engine. Background Art

[0002] When assembling the high-turbine rotor and high-pressure compressor rotor connector of an aircraft engine, the connecting nut at this position (such as Figure 1 The connecting nut and the connecting bolt are used in pairs to connect the high-vortex rotor and the high-pressure compressor rotor. They are located in the rotor cavity and are blocked by the turbine disk from above, so the operator cannot directly observe them. In addition, the inner hole diameter of the turbine disk is small, and the radial space between the connecting piece installation position and the turbine disk is relatively narrow. When tightening by conventional methods, the position of the connecting nut can only be judged by touch by hand. Tightening at a small angle and in a small range requires repeated installation and removal of the wrench, which is inefficient. At the same time, the connecting pieces at this position are evenly distributed along the circumference and are numerous. It is easy to miss tightening during the tightening process, which can easily lead to engine assembly quality problems, resulting in large engine vibration and affecting the safe use of the engine. Summary of the invention

[0003] The present invention aims to provide a device and method for quickly installing a connector in a blind cavity of an aero-engine, which can achieve stable, rapid and safe installation of nuts while ensuring the assembly quality of a rotor.

[0004] To achieve the above object, the present invention adopts the following technical solutions:

[0005] A device for quickly installing a connector in a blind cavity of an aero-engine, comprising:

[0006] A stop seat, wherein the stop seat is mainly composed of a support seat and an adapter plate, the support seat is a flat plate, a circular through hole is opened at the center position of the length direction of the flat plate, and a mounting foot is extended downward from the left and right ends of the flat plate in a direction perpendicular to the flat plate, and a first flange is provided at the end of the mounting foot, and a first stop is provided at the edge of the first flange; the adapter plate is a cylindrical barrel, the axial first end face of the adapter plate is located above the circular through hole and is provided with a second flange, positioning holes are opened on the second flange, and the number of positioning holes is consistent with the number of high-pressure rotor connection holes, the axial second end face of the adapter plate is located below the circular through hole and is provided with a third flange, and a second stop is provided at the edge of the third flange, a fourth flange is provided between the second flange and the third flange and on the cylindrical surface of the cylindrical barrel, and the adapter plate is installed in the circular through hole of the support seat through the fourth flange;

[0007] A bow-shaped wrench, the bow-shaped wrench comprises a cushion block, an adapter pin, a wrench body, a sleeve, a ratchet, a pin shaft, a pusher claw, a push pin and a spring, wherein a cushion block is rotatably connected to the first end of the wrench body, a notch is opened on the cushion block to avoid the transfer pin, the first end of the wrench body is fitted on the second flange edge of the transfer plate through the cushion block, the transfer pin is inserted into the through hole at the first end of the wrench body, and the end of the transfer pin extends to the positioning hole on the second flange edge of the transfer plate; a cover plate is installed at the second end of the wrench body, and a notch is formed between the second end of the wrench body and the cover plate, the ratchet, the pusher claw, the push pin and the spring are located in the notch, wherein the ratchet and the pusher claw are rotatably connected to the cover plate respectively, the transmission shaft part of the ratchet located above the cover plate is connected to the sleeve, the gear part located below the cover plate cooperates with the action claw of the pusher claw, the first end of the push pin is pressed tightly against the surface of the pusher claw so that the action claw of the pusher claw is embedded in the ratchet teeth of the ratchet, and the second end is assembled with the second end of the wrench body through the spring.

[0008] As a solution, the pad is rotatably connected to the first end of the wrench body with a pin as a rotating shaft.

[0009] As a solution, the adapter pin is provided with a square surface and a cylindrical surface, which respectively cooperate with the square through hole at the first end of the wrench body and the circular positioning hole on the second flange edge of the adapter plate.

[0010] As a solution, a square hole for driving the transfer pin to rotate is provided at one end of the transfer pin.

[0011] As a solution, the pawl includes two action claws symmetrically distributed about its rotation center, and the action claw has a sharp angle structure and an arc structure. The sharp angle structure is used to cooperate with the ratchet to stop the ratchet wheel, and the arc structure is used to cooperate with the ratchet to rotate the ratchet wheel.

[0012] As a solution, the pusher claw is in the shape of an isosceles triangle, the two action claws are distributed at two vertices of the base of the isosceles triangle, and one of the two waists of the isosceles triangle is in close contact with the first end of the ejector pin.

[0013] As a solution, one end of the cover plate is riveted to the second end of the wrench body.

[0014] As a solution, the wrench body of the bow-type wrench is C-shaped, and the axis of the through hole on the first end of the wrench body coincides with the axis of the sleeve on the second end.

[0015] A method for quickly installing a connector in a blind cavity of an aero-engine, using the above-mentioned device, and comprising the following steps:

[0016] Step 1: assemble and fix the stop seat with the high-vortex rotor and the combustion chamber casing at the same time, wherein the stop seat is installed on the rear mounting edge of the combustion chamber casing through the first flange edge and the first stopper at the end of the mounting foot of the support seat, and is installed on the high-vortex rotor through the third flange edge and the second stopper of the adapter plate;

[0017] Step 2: On the one hand, insert the outer stop bolt into the flange hole on the first flange side and the bolt hole on the rear mounting side of the combustion chamber casing, and fix the stop seat to the combustion chamber casing with the outer stop nut; on the other hand, insert the inner stop bolt into the flange hole on the third flange side and the bolt hole on the high-vortex rotor, and fix the stop seat to the high-vortex rotor with the inner stop nut;

[0018] Step three, extend the second end of the wrench body without the adapter pin into the high-vortex rotor disc cavity, rotate the pad at the first end of the wrench body to make it away from the adapter disc, adjust the position of the second end of the wrench body so that the sleeve on the second end is inserted into the high-pressure rotor connecting nut, and then rotate the pad to insert it between the first end of the dynamic wrench body and the second flange edge of the adapter disc, and insert the adapter pin to fix the relative position of the wrench body and the adapter disc;

[0019] Step 4: Apply a rotational torque to the adapter pin, drive the wrench body to rotate through the adapter pin, and then apply a rotational torque to the high-pressure rotor connecting nut through the sleeve at the second end of the wrench body.

[0020] Furthermore, in step four, before applying the rotational torque to the adapter pin, the positioning hole on the second flange side of the adapter plate is marked, and the marking content includes the corresponding numbers of the positioning hole and the high-pressure rotor connecting hole, and then the rotational torque is applied to the high-pressure rotor connecting nut one by one in sequence.

[0021] The quick installation device and installation method of the present invention have the following characteristics:

[0022] (1) The stop seat is designed with inner and outer through holes, which are respectively connected to the positioning holes on the combustion chamber casing and the high-vortex rotor. At the same time, two stoppers are designed, which are respectively matched with the outer diameter of the combustion chamber casing and the outer diameter of the high-vortex disk to respectively realize the circumferential stop and radial positioning of the high-vortex rotor, and prevent the high-vortex rotor from rotating or swinging in the direction of force during the tightening process; it is designed with a number of through holes corresponding to the high-pressure rotor connecting nuts. The through holes cooperate with the bow wrench to accurately identify the position of the high-pressure rotor connecting nuts tightened each time;

[0023] (2) The bow-type wrench is designed in a "C" shape, which can effectively avoid the small diameter of the disc cavity to prevent interference. The positioning pin on it cooperates with the through hole of the stop seat, and the axial limit of the bow-type wrench is achieved by installing a limit block. The axial movement of the bow-type wrench can be achieved by removing the limit block to ensure its normal removal;

[0024] (3) The square through hole at the first end of the wrench body on the bow-type wrench is kept on the same vertical line (coaxial) as the sleeve at the second end, which can ensure that the input tightening torque is consistent with the sleeve (used to connect the nut);

[0025] (4) The output end of the bow-type wrench is designed with a pawl-ratchet structure, which can realize the function of transmitting force when driven and disengaging when not driven. The cylindrical surface on the adapter pin is used to cooperate with the adapter plate for positioning, while the square surface on the adapter pin is used to drive the wrench body to rotate, and the square hole on the end face of the adapter pin is used to receive the rotational torque applied by the outside.

[0026] Compared with the prior art, the present invention can realize efficient tightening of the connectors of the high-pressure rotor of the aircraft engine, avoid missing assembly, improve the assembly quality of the connectors, and reduce the labor intensity of workers. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the installation of the high-pressure rotor connecting bolts;

[0028] Figure 2 This is a schematic diagram of the use of the quick installation device for the blind cavity connector;

[0029] Figure 3 This is a schematic diagram of the stop seat structure;

[0030] Figure 4 It is a schematic diagram of the bow wrench structure;

[0031] Figure 5 Schematic diagram of ratchet structure;

[0032] Figure 6 It is a schematic diagram of the claw structure;

[0033] Figure 7 is a schematic diagram of the transfer pin structure;

[0034] Figure 8 is a partial enlarged view of the second end of the wrench body;

[0035] Fig. 9 This is a schematic diagram of the combined state of the stop seat and the bow wrench;

[0036] Fig.10 The assembly diagram of the cover plate, ejector pin, pusher pawl and ratchet;

[0037] In the figure: 1. stop seat, 2. bow wrench, 11. support seat, 12. adapter plate, 13. inner stop bolt, 14. inner stop nut, 15. connecting screw, 16. outer stop nut, 17. outer stop bolt, 21. spacer, 22. adapter pin, 23. flat washer, 24. pin, 25. cotter pin, 26. wrench body, 27. sleeve, 28. ratchet, 29. pin shaft, 210. pusher claw, 211. ejector pin, 212. rivet, 213. cover plate, 214. spring, 3. high vortex rotor, 4. combustion chamber casing, 5. compressor rotor, 6. connecting bolt, 7. connecting nut. DETAILED DESCRIPTION

[0038] 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.

[0039] like Figure 2 to Figure 10 As shown in the figure, a device and method for quickly installing a connector in a blind cavity of an aircraft engine are provided in this embodiment.

[0040] In this embodiment, the connecting member of the high-pressure rotor of the aircraft engine ( Figure 1 The connecting bolt 6 and the connecting nut 7) are realized by a quick installation device of the connecting piece in the blind cavity, and the installation device is mainly composed of a stop seat 1 and a bow wrench 2.

[0041] The characteristics and functions of the quick installation device for connecting parts in the blind cavity of aircraft engines are as follows:

[0042] (1) The quick installation device is mainly composed of a stopper 1 and a bow-shaped spanner 2. The radial positioning is achieved by the matching of the adapter pin 22 on the bow-shaped spanner 2 with the positioning hole on the adapter disk 12 on the stopper 1, and the axial positioning is achieved by the connection between the pad 21 on the bow-shaped spanner 2 and the front end surface of the adapter disk 12 on the stopper 1.

[0043] (2) The stopper 1 is mainly composed of a support seat 11 (1 piece) and an adapter plate 12 (1 piece). The support seat 11 and the adapter plate 12 are rigidly fixed by connecting screws 15 (10 pieces) on the support seat 11. The stopper 1 is connected to the bolt holes on the high-vortex rotor 3 by inner stopper bolts 13 (20 pieces) and inner stopper nuts 14 (20 pieces). The stopper 1 is connected to the rear mounting edge of the combustion chamber casing 4 by outer stopper nuts 16 (12 pieces) and outer stopper bolts 17 (12 pieces). The bolt holes are connected to realize circumferential positioning; the radial positioning of the rotor and stator is realized by respectively matching the inner stop on the adapter plate 12 (1 piece) with the outer cylindrical surface of the high-vortex rotor 3, and matching the inner stop on the support seat 11 (1 piece) with the outer cylindrical surface of the rear mounting edge of the combustion chamber casing 4. There is a circular positioning hole on the adapter plate 12 (1 piece) that matches the cylindrical surface of the adapter pin 12 (1 piece) on the bow wrench 2. The positioning hole is marked according to the tightening sequence and is aligned with the high-pressure rotor ( Figure 1 The connecting holes of the intermediate compressor rotor 5) correspond one to one, ensuring that the installation position of the bow wrench 2 corresponds one to one with the connecting holes of the high-pressure rotor each time and that they are tightened in sequence.

[0044] (3) The bow-type wrench 2 is composed of a spacer 21 (1 piece), a transfer pin 22 (1 piece), a flat washer 23 (4 pieces), a pin 24 (1 piece), a cotter pin 25 (2 pieces), a wrench body 26 (1 piece), a sleeve 27 (1 piece), a ratchet 28 (1 piece), a pin shaft 29 (1 piece), a pusher claw 210 (1 piece), a push pin 211 (1 piece), a rivet 212 (4 pieces), a cover plate 213 (1 piece), and a spring 214 (1 piece). The spacer 21 (1 piece) is limited and fixed by a flat washer 23 (1 piece), a pin 24 (1 piece) and a cotter pin 25 (1 piece), and at the same time, the spacer 21 (1 piece) can be ensured to rotate around the pin 24 (1 piece). A semicircular slot is provided on the spacer 21 (1 piece) to avoid interference with the transfer pin 22 (1 piece) when realizing the axial stopping function; the transfer pin 22 (1 piece) is respectively matched with the precise square through hole of the wrench body 26 (1 piece) on the bow wrench 2 and the precise circular positioning hole of the transfer plate 12 (1 piece) on the stop seat 1 through a square surface and a precise cylindrical surface thereon, so as to realize precise transmission and precise positioning of torque. A square hole is also designed at the upper end of the transfer pin 22 (1 piece) for inputting torque (for example, a torque wrench is inserted into the square hole to apply torque); the sleeve 27 (1 piece) is connected to the ratchet 2 8 (1 piece) realizes torque transmission through the square hole and square axis thereon, and uses rivet 212 (4 pieces) and cover plate 213 (1 piece) to axially limit the ratchet 28 (1 piece) to prevent it from slipping out; the pusher claw 210 (1 piece) is limited and fixed by the pin shaft 29 (1 piece), flat washer 23 (3 pieces) and cotter pin 25 (1 piece) to ensure that the pusher claw 210 (1 piece) can rotate around the pin shaft 29 (1 piece), and the action claw of the pusher claw 210 (1 piece) is designed as two claws with symmetrical structures, one end of the claw is a sharp angle structure, and the other end is a circular arc structure, so that the sharp angle end of the claw is in contact with the groove on the ratchet 28 (1 piece) to achieve stopping, and the circular arc end of the claw is in contact with the groove on the ratchet 28 (1 piece) to not stop; with the help of the elastic force of the spring 214 (1 piece), the conical end of the ejector pin 211 (1 piece) (such as Fig.10 The end of the ejector pin 211 that contacts the pusher claw 210 is designed as a conical surface) and contacts the bevel of the pusher claw 210 (1 piece). By adjusting the symmetrical bevel contact between the conical end and the pusher claw 210 (1 piece), the reversing function of the output torque is realized.

[0045] The method for quickly installing the connector in the blind cavity of an aircraft engine using the above-mentioned quick installation device is as follows:

[0046] ① First, install the stop seat 1 on the rear mounting edge of the combustion chamber casing 4, connect it with the bolt holes on the rear mounting edge of the combustion chamber casing 4 through the outer stop nut 16 (12 pieces) and the outer stop bolt 17 (12 pieces) on the stop seat 1 (specifically, the flange hole on the first flange edge of the support seat 11 and the flange hole on the third flange edge of the adapter plate 12), and connect it with the bolt holes on the high-vortex rotor 3 through the inner stop bolt 13 (20 pieces) and the inner stop nut 14 (20 pieces);

[0047] ② Then insert the bow wrench 2 without the transfer pin 22 (1 piece) into the disc cavity of the high-vortex rotor 3, and press the cushion block 21 (1 piece) Figure 2 The middle position is rotated 180° to the right to ensure that it is out of the limit position, and then the bow wrench 2 is axially moved to make the sleeve 27 (1 piece) at the lower end be inserted into the high-pressure rotor connecting nut 7, and then the spacer 21 (1 piece) is reversely rotated 180° to return to the Figure 2 The semicircular slot of the pad 21 is just stuck in the middle position (at this time, the semicircular slot of the pad 21 is just stuck in the middle position of the pad 21). Figure 2 The transfer pin 22 is inserted into the position), axial limiting is achieved by the gasket 21 (1 piece), and the transfer pin 22 (1 piece) is inserted to ensure that the bow-shaped wrench 2 is installed on the stop seat 1 to prevent it from being disengaged, and a torque is applied just above the square hole of the transfer pin 22 of the bow-shaped wrench 2 (that is, the torque wrench is inserted into the square hole of the transfer pin 22, and the transfer pin 22 is driven by the torque wrench, and then the square surface section of the transfer pin 22 drives the wrench body 26 to rotate through the square through hole at the first end of the wrench body 26, and finally drives the sleeve 27 at the second end of the wrench body 26 to rotate to achieve the installation of the connecting nut 7), so as to tighten or loosen the high-pressure rotor connecting nut 7, and at the same time, tighten the bolts according to the tightening sequence marked on the transfer disk 22 (1 piece) on the stop seat 1 to ensure the consistency of tightening and avoid missing tightening.

[0048] 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 device for quickly installing a connector in a blind cavity of an aircraft engine, characterized in that: include: A stop seat (1), wherein the stop seat (1) is mainly composed of a support seat (11) and an adapter plate (12), wherein the support seat (11) is a flat plate, a circular through hole is provided at the center position of the length direction of the flat plate, and a mounting foot is extended downward from the left and right ends of the flat plate in a direction perpendicular to the flat plate, and a first flange is provided at the end of the mounting foot, and a first stop is provided at the edge of the first flange; the adapter plate (12) is a cylindrical body, the axial first end face of the adapter plate (12) is located above the circular through hole and is provided with a second flange, the second flange is provided with positioning holes, and the number of positioning holes is consistent with the number of high-pressure rotor connection holes, the axial second end face of the adapter plate (12) is located below the circular through hole and is provided with a third flange, the edge of the third flange is provided with a second stop, a fourth flange is provided between the second flange and the third flange and on the cylindrical surface of the cylindrical body, and the adapter plate (12) is installed in the circular through hole of the support seat (11) through the fourth flange; A bow-shaped spanner (2), the bow-shaped spanner (2) comprising a cushion block (21), an adapter pin (22), a spanner body (26), a sleeve (27), a ratchet (28), a pin shaft (29), a pusher claw (210), a push pin (211) and a spring (214), wherein a cushion block (21) is rotatably connected to the first end of the spanner body (26), a notch for avoiding the adapter pin (22) is provided on the cushion block (21), the first end of the spanner body (26) is fitted on the second flange edge of the adapter plate (12) through the cushion block (21), the adapter pin (22) is inserted into the through hole at the first end of the spanner body (26), and the end of the adapter pin (22) extends to the positioning hole on the second flange edge of the adapter plate (12); the second end of the spanner body (26) is installed A cover plate (213) is provided, and a notch is formed between the second end of the wrench body (26) and the cover plate (213), wherein the ratchet (28), the pusher pawl (210), the push pin (211) and the spring (214) are located in the notch, wherein the ratchet (28) and the pusher pawl (210) are rotatably connected to the cover plate (213), the transmission shaft part of the ratchet (28) located above the cover plate (213) is connected to the sleeve (27), the gear part located below the cover plate (213) cooperates with the action claw of the pusher pawl (210), the first end of the push pin (211) is pressed tightly against the surface of the pusher pawl (210) so that the action claw of the pusher pawl (210) is embedded in the ratchet teeth of the ratchet (28), and the second end is assembled with the second end of the wrench body (26) via the spring (214).

2. A device for rapid installation of connectors in blind cavities of aircraft engines according to claim 1, characterized in that: The cushion block (21) is rotatably connected to the first end of the wrench body (26) with the pin (24) as a rotating shaft.

3. The device for rapid installation of connectors in blind cavities of aircraft engines according to claim 1, characterized in that: The adapter pin (22) is provided with a square surface and a cylindrical surface, which respectively cooperate with the square through hole at the first end of the wrench body (26) and the circular positioning hole on the second flange edge of the adapter plate (12).

4. The device for rapid installation of connectors in blind cavities of aircraft engines according to claim 1, characterized in that: One end of the transfer pin (22) is provided with a square hole for driving the transfer pin (22) to rotate.

5. The device for rapid installation of connectors in blind cavities of aircraft engines according to claim 1, characterized in that: The pusher claw (210) comprises two action claws symmetrically distributed about its rotation center, and the action claw has a sharp angle structure and an arc structure, wherein the sharp angle structure is used to cooperate with the ratchet teeth to achieve the stopping of the ratchet wheel (28), and the arc structure is used to cooperate with the ratchet teeth to achieve the rotation of the ratchet wheel (28).

6. The device for rapid installation of connectors in blind cavities of aircraft engines according to claim 5, characterized in that: The pusher claw (210) is in the form of an isosceles triangle, with two action claws distributed at two vertices of the base of the isosceles triangle, and one of the two waists of the isosceles triangle is in close contact with the first end of the ejector pin (211).

7. The device for rapid installation of connectors in blind cavities of aircraft engines according to claim 1, characterized in that: One end of the cover plate (213) is riveted to the second end of the wrench body (26).

8. The device for rapid installation of connectors in blind cavities of aircraft engines according to claim 1, characterized in that: The wrench body (26) of the bow-shaped wrench (2) is C-shaped, and the axis of the through hole on the first end of the wrench body (26) coincides with the axis of the sleeve (27) on the second end.

9. A method for quickly installing a connector in a blind cavity of an aircraft engine, characterized in that: The device according to claim 1 is used, and comprises the following steps: Step 1: assemble and fix the stop seat (1) with the high-vortex rotor (3) and the combustion chamber casing (4) at the same time, wherein the stop seat (1) is installed on the rear installation edge of the combustion chamber casing (4) through the first flange edge and the first stopper at the end of the installation leg of the support seat (11), and is installed on the high-vortex rotor (3) through the third flange edge and the second stopper of the adapter plate (12); Step 2: On the one hand, an outer stop bolt (17) is inserted into the flange hole on the first flange side and the bolt hole on the rear mounting side of the combustion chamber casing (4), and the outer stop nut (16) is installed to fix the stop seat (1) to the combustion chamber casing (4); on the other hand, an inner stop bolt (13) is inserted into the flange hole on the third flange side and the bolt hole on the high-vortex rotor (3), and the inner stop nut (14) is installed to fix the stop seat (1) to the high-vortex rotor (3); Step three, extend the second end of the wrench body (26) without the transfer pin (22) into the disc cavity of the high-vortex rotor (3), rotate the pad (21) at the first end of the wrench body (26) to make it away from the transfer disc (12), adjust the position of the second end of the wrench body (26) so that the sleeve (27) on the second end is inserted into the high-pressure rotor connecting nut (7), then rotate the pad (21) to insert it between the first end of the dynamic wrench body (26) and the second flange edge of the transfer disc (12), and insert the transfer pin (22) to fix the relative position of the wrench body (26) and the transfer disc (12); Step 4: Apply a rotational torque to the adapter pin (22), drive the wrench body (26) to rotate through the adapter pin (22), and then apply a rotational torque to the high-pressure rotor connecting nut (7) through the sleeve (27) at the second end of the wrench body (26).

10. A method for rapid installation of a connector in a blind cavity of an aircraft engine according to claim 9, characterized in that: In the fourth step, before applying the rotational torque to the adapter pin (22), the positioning hole on the second flange side of the adapter plate (12) is marked, the marking content includes the corresponding numbers of the positioning hole and the high-pressure rotor connection hole, and then the rotational torque is applied to the high-pressure rotor connection nuts (7) one by one in sequence.

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