Silica gel removing tool suitable for air inlet cavity of airplane auxiliary power device

Abstract

The utility model discloses a silica gel removing tool suitable for an air inlet cavity of an airplane auxiliary power device, which comprises a turntable, a plurality of supporting legs and a plurality of blades, the number of the supporting legs is in one-to-one correspondence with the number of the blades, the plurality of supporting legs extend downwards from the turntable, and the blades are fixedly connected to the lower ends of the supporting legs; the turntable is mounted on the turbine transmission shaft sequentially through a first nut, a second nut and a third nut which are arranged from inside to outside, and the first nut is fixedly connected with the turntable; the first nut, the second nut and the third nut are all in threaded connection with the turbine transmission shaft. The second nut and the third nut are tightly attached to form a positioning part capable of being matched with a wrench, and a gap is formed between the first nut and the positioning part. The first nut is rotated to drive the rotating disc, the supporting legs and the blade to rotate. The silica gel removing device is good in silica gel removing effect, can prevent the blade from being broken, and has the advantages of being convenient to operate, time-saving and labor-saving.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft auxiliary power devices, in particular to a silica gel removal tool suitable for an air intake cavity of an aircraft auxiliary power device. Background Art

[0002] The aircraft auxiliary power unit (APU) is located at the tail end of the aircraft. It is usually a small gas turbine engine. When working, it uses air as the medium. After compression, it mixes with fuel in the combustion chamber and burns to produce high-temperature and high-pressure combustion gas. Under the action of the turbine drive shaft, the turbine converts chemical energy into mechanical energy to ensure that the aircraft can operate various equipment normally on the ground or in the air. The aircraft auxiliary power unit takes in air through the air intake housing. An air intake cavity is formed in the air intake housing. To avoid gas leakage, a circle of silicone seal is required at the gap at the bottom of the air intake cavity.

[0003] When inspecting and disassembling the aircraft auxiliary power unit, it is necessary to manually remove the silicone at the bottom edge of the air intake cavity. However, since the aircraft has been flying at high altitude for a certain period of time, the silicone has hardened to a certain extent, so it is very inconvenient for workers to perform the disassembly work. The current method of removing silicone is to use a paper cutter to remove it little by little along the gap where the silicone is applied. This is not only time-consuming and laborious, but also the blade often breaks, which poses a great threat to the personal safety of workers and the status of parts. Utility Model Content

[0004] The utility model aims to provide a silicone removal tool suitable for an air intake cavity of an auxiliary power unit of an aircraft, which is easy to operate, saves time and effort, has a good silicone removal effect and can avoid blade breakage.

[0005] In order to achieve the above purpose, the technical solution adopted by the utility model is:

[0006] A silicone removal tool suitable for an aircraft auxiliary power unit air intake cavity, comprising a turntable, a plurality of legs and a plurality of blades, wherein the number of the legs corresponds to the number of the blades one by one; the legs are extended downward from the edge of the turntable, and the blades are fixedly connected to the lower ends of the legs; the turntable is installed on a turbine transmission shaft through a first nut, a second nut and a third nut arranged from the inside to the outside in sequence, and the first nut is fixedly connected to the turntable; the first nut, the second nut and the third nut are all threadedly connected to the turbine transmission shaft; the second nut and the third nut are tightly attached to each other and form a positioning portion that can cooperate with a wrench, and a gap is provided between the first nut and the positioning portion; by rotating the first nut, the turntable, the legs and the blades can be driven to perform rotational motion.

[0007] As a preferred embodiment of the present invention, the support leg is in an inverted L-shape and includes a cross bar arranged along the radial direction of the turntable and a vertical bar arranged vertically, one end of the cross bar is fixedly connected to the turntable, the other end of the cross bar is fixedly connected to the upper end of the vertical bar, and the blade is fixedly connected to the lower end of the vertical bar.

[0008] As a preferred solution of the utility model, a reinforcing rib is connected between the cross bar and the vertical bar.

[0009] As a preferred solution of the utility model, the number of the supporting legs is three, and the three supporting legs are evenly arranged along the circumferential direction.

[0010] As a preferred solution of the present utility model, the first nut is arranged at the middle position of the turntable.

[0011] The implementation of the utility model provides a silicone removal tool suitable for an air intake cavity of an aircraft auxiliary power unit. Compared with the prior art, the beneficial effects thereof are:

[0012] When the utility model is working, the turntable is first installed on the turbine transmission shaft through the first nut, the second nut and the third nut in sequence, and the blade is abutted against the silicone ring at the bottom edge of the air inlet cavity, wherein a gap is provided between the first nut and the positioning portion formed by the second nut and the third nut in close contact; subsequently, since the second nut and the third nut are in close contact, a reverse rotation force is applied to the second nut by a wrench, thereby increasing the driving torque required for relative rotation between the turbine transmission shaft and the second nut and the third nut, so that the turbine transmission shaft does not rotate; then, by screwing the first nut in the forward direction, the turntable, the legs and the blade can be driven to rotate and advance downward, thereby realizing the cutting of the silicone ring by the blade. Compared with the cutting method using a paper cutter in the prior art, the silicone removal effect is better, the operation is more convenient, time and labor are saved, work efficiency is improved, and the phenomenon of blade breakage can be avoided. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solution of the embodiment of the utility model, the drawings of the embodiment will be briefly introduced below.

[0014] Figure 1 It is an assembly diagram of a silicone removal tool and a turbine drive shaft suitable for an aircraft auxiliary power unit air intake cavity provided by an embodiment of the utility model;

[0015] Figure 2 It is Figure 1 A partial enlarged view of region A in the structure shown;

[0016] Figure 3 It is a schematic diagram of the structure of the turntable, legs and blades.

[0017] Markings in the figure:

[0018] 1. Turntable; 2. Legs; 21. Crossbar; 22. Vertical bar; 3. Blade; 4. First nut; 5. Positioning part; 51. Second nut; 52. Third nut; 6. Air intake shell; 61. Air intake cavity; 7. Silicone ring; 8. Turbine drive shaft; 9. Reinforcement ribs. DETAILED DESCRIPTION

[0019] The following is a further detailed description of the specific implementation of the present invention in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0020] In the description of the present utility model, it should be understood that the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. It should be understood that the terms "first", "second", etc. are used in the present utility model to describe various information, but such information should not be limited to these terms, which are only used to distinguish the same type of information from each other. For example, without departing from the scope of the present utility model, the "first" information may also be referred to as the "second" information, and similarly, the "second" information may also be referred to as the "first" information.

[0021] See also Figures 1 to 3 The preferred embodiment of the utility model provides a silicone removal tool suitable for an aircraft auxiliary power unit air intake cavity, which includes a turntable 1, a plurality of legs 2 and a plurality of blades 3, the number of the legs 2 corresponding to the number of the blades 3; the legs 2 extend downward from the edge of the turntable 1, and the blades 3 are fixedly connected to the lower ends of the legs 2; the turntable 1 is installed on a turbine transmission shaft 8 through a first nut 4, a second nut 51 and a third nut 52 arranged from the inside to the outside in sequence, and the first nut 4 is fixedly connected to the turntable 1; the first nut 4, the second nut 51 and the third nut 52 are all threadedly connected to the turbine transmission shaft 8; the second nut 51 and the third nut 52 are tightly attached to each other and form a positioning portion 5 that can cooperate with a wrench, and a gap is provided between the first nut 4 and the positioning portion 5; by rotating the first nut 4, the turntable 1, the legs 2 and the blades 3 can be driven to rotate.

[0022] It should be noted that in the aircraft auxiliary power unit, since the turbine drive shaft 8 is rotatably connected to the air intake housing 6, when using the tool to remove the silicone, it is necessary to ensure that the turbine drive shaft 8 does not rotate relative to the tool.

[0023] According to the silicone removal tool for the air intake cavity of an aircraft auxiliary power unit of the utility model, when working, the turntable 1 is first installed on the turbine transmission shaft 8 through the first nut 4, the second nut 51 and the third nut 52 in sequence, and the blade 3 is abutted against the silicone ring 7 at the bottom edge of the air intake cavity 61, wherein a gap is provided between the first nut 4 and the positioning portion 5 formed by the second nut 51 and the third nut 52 in close contact; then, since the second nut 51 is in close contact with the third nut 52, a wrench is used to apply a reverse rotation force to the second nut 51 , so it can increase the driving torque required for relative rotation between the turbine transmission shaft 8 and the second nut 51 and the third nut 52, so that the turbine transmission shaft 8 will not rotate; then, by screwing the first nut 4 in the positive direction, the turntable 1, the legs 2 and the blade 3 can be driven to rotate and advance downward, thereby realizing the cutting of the silicone ring 7 by the blade 3. Compared with the cutting method using a paper cutter in the prior art, the silicone removal effect is better, the operation is more convenient, time-saving and labor-saving, the work efficiency is improved, and the blade 3 can be avoided from breaking.

[0024] It should be noted that after the tooling completes the removal of the silicone ring 7, since the second nut 51 and the third nut 52 are in close contact, a positive rotational force is applied to the third nut 52 using a wrench, thereby increasing the driving torque required for relative rotation between the turbine transmission shaft 8 and the second nut 51 and the third nut 52, so that the turbine transmission shaft 8 does not rotate; then, by unscrewing the first nut 4 in the opposite direction, the turntable 1, the leg 2 and the blade 3 can be driven to rotate upward and exit.

[0025] Exemplarily, the leg 2 is in an inverted L-shape and includes a cross bar 21 arranged along the radial direction of the turntable 1 and a vertical bar 22 arranged vertically, one end of the cross bar 21 is fixedly connected to the turntable 1, the other end of the cross bar 21 is fixedly connected to the upper end of the vertical bar 22, and the blade 3 is fixedly connected to the lower end of the vertical bar 22; a reinforcing rib 9 is connected between the cross bar 21 and the vertical bar 22. In such a design, since the reinforcing rib 9 is connected between the cross bar 21 and the vertical bar 22 of the leg 2, the reinforcing rib 9, the cross bar 21 and the vertical bar 22 together form a triangular structure, according to the principle that the triangle has stability, the structural strength of the leg 2 can be improved, so that the stability of the tooling is higher during operation.

[0026] Exemplarily, in order to make the force on the tool more uniform during operation and prevent the blade 3 from being broken, the number of the legs 2 is preferably three, and the three legs 2 are evenly arranged along the circumferential direction; the first nut 4 is arranged in the middle position of the turntable 1.

[0027] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0028] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principle of the present invention. These improvements and substitutions should also be regarded as the protection scope of the present invention.

Claims

1. A silicone removal tool suitable for an aircraft auxiliary power unit air intake cavity, characterized in that: It includes a turntable, a plurality of legs and a plurality of blades, the number of the legs corresponds to the number of the blades; the legs are extended downward from the edge of the turntable, and the blades are fixedly connected to the lower ends of the legs; the turntable is installed on the turbine transmission shaft through a first nut, a second nut and a third nut arranged from the inside to the outside in sequence, and the first nut is fixedly connected to the turntable; the first nut, the second nut and the third nut are all threadedly connected to the turbine transmission shaft; the second nut and the third nut are tightly attached to each other and form a positioning portion that can cooperate with a wrench, and a gap is provided between the first nut and the positioning portion; by rotating the first nut, the turntable, the legs and the blades can be driven to rotate.

2. The silicone removal tool for an aircraft auxiliary power unit air intake cavity according to claim 1, characterized in that: The support leg is in an inverted L shape and includes a cross bar arranged along the radial direction of the turntable and a vertical bar arranged vertically, one end of the cross bar is fixedly connected to the turntable, the other end of the cross bar is fixedly connected to the upper end of the vertical bar, and the blade is fixedly connected to the lower end of the vertical bar.

3. The silicone removal tool for an aircraft auxiliary power unit air intake cavity according to claim 2, characterized in that: A reinforcing rib is connected between the cross bar and the vertical bar.

4. The silicone removal tool for an air intake cavity of an aircraft auxiliary power unit according to claim 1, characterized in that: The number of the supporting legs is three, and the three supporting legs are evenly arranged along the circumferential direction.

5. The silicone removal tool for an aircraft auxiliary power unit air intake cavity according to claim 1, characterized in that: The first nut is arranged at the middle position of the turntable.

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