Device for assembling turbojet engine rotor

Abstract

The utility model discloses a device for assembling a turbojet engine rotor, which relates to the technical field of aero-engine rotor assembly and comprises a main body support, a main support plate is arranged on the main body support, and a U-shaped through hole is formed in the middle of the main support plate. U-shaped through holes are formed in the main supporting plate, two main fixing clamping blocks with symmetrical structures are fixedly arranged at the positions, located in the U-shaped through holes, of the main supporting plate through bolts, a frame body is arranged on the main supporting plate, a hydraulic puller is installed on the frame body, and an auxiliary supporting mechanism used for clamping rotors of different sizes is arranged on the frame body. By arranging the main fixed clamping block and the auxiliary supporting clamping ring, the main fixed clamping block and the auxiliary supporting clamping ring can be rapidly detached and replaced, the left-right position of the auxiliary supporting clamping ring can be adjusted, the positioning supporting and clamping requirements of turbojet engine spindles and rotors of different sizes can be met, the production cost is reduced, and the production efficiency is improved. And the universality and flexibility of the device are improved, so that the assembly quality and efficiency of the device are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engine rotor assembly, in particular to a device for assembling a turbojet engine rotor. Background Art

[0002] Small turbojet engines are small in size, compact in structure, and have high requirements for working conditions, which in turn places high demands on assembly quality.

[0003] Assembly is a crucial step in engine manufacturing, and its quality directly impacts engine stability and reliability. Rotor assembly is a crucial step, and rotors are a crucial component in engine operation, often operating at high temperatures, high pressures, and high speeds. However, most existing rotor assembly devices are fixed in size and cannot position, support, or clamp turbojet engine main shafts and rotors of varying sizes. This reduces the device's versatility and flexibility, and can easily lead to poor rotor assembly quality, resulting in vibration, scratches, and even safety issues during operation, directly impacting engine reliability and lifespan. Utility Model Content

[0004] The purpose of the utility model is to provide a device for assembling turbojet engine rotors, so as to solve the problem that the existing rotor assembly device cannot play a positioning, supporting and clamping role on turbojet engine main shafts and rotors of different sizes, thereby reducing the versatility and flexibility of the device.

[0005] A device for assembling a turbojet engine rotor comprises a main support, the main support is provided with a main support plate, a U-shaped through hole is opened in the middle of the main support plate, two main fixed clamping blocks with symmetrical structure are fixed by bolts at the position of the U-shaped through hole on the main support plate, a frame is provided on the main support plate, a hydraulic puller is installed on the frame, and an auxiliary support mechanism for clamping rotors of different sizes is provided on the frame.

[0006] Preferably, the auxiliary support mechanism includes two auxiliary support frame vertical beams installed between the frame body and the main support plate, the auxiliary support frame vertical beams are connected to the auxiliary support frame cross beams by right-angle fixings, and two auxiliary support clamping rings are bolted to the auxiliary support frame cross beams.

[0007] Preferably, a pressure sensor is threadedly connected to the hydraulic puller, and an external digital display is provided on the vertical beam of the auxiliary support frame. The external digital display is electrically connected to the pressure sensor through a cable.

[0008] Preferably, the bottom of the main frame is provided with universal self-locking casters distributed in a rectangular shape, and the four corners of the bottom of the main frame are provided with rubber suction cups corresponding to the universal self-locking casters one by one.

[0009] Preferably, a tray is provided on the crossbeam in the middle of the bottom of the main support.

[0010] The advantages of the present invention are: a device for assembling a turbojet engine rotor in the present invention can be quickly disassembled and replaced by arranging a main fixed clamping block and an auxiliary support clamping ring, and the left and right positions of the auxiliary support clamping ring are adjustable, which can meet the positioning, support and holding requirements of the main shaft and rotor of turbojet engines of different sizes, reduce production costs, improve the versatility and flexibility of the device, and arrange a hydraulic puller, which is convenient and labor-saving to operate, reduces the labor intensity of the operator, improves the assembly quality and efficiency of the device, and thus improves the stability and reliability of the engine operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 、 2 It is a structural schematic diagram of the utility model from different perspectives.

[0012] Figure 3 This is a structural diagram of the auxiliary support clamping ring in the utility model.

[0013] Among them, 100, main bracket; 101, main support plate; 102, pallet; 103, main fixed clamping block; 104, frame; 105, U-shaped through hole; 106, universal self-locking caster; 107, rubber suction cup; 200, auxiliary support frame vertical beam; 201, right-angle fixing piece; 202, auxiliary support frame horizontal beam; 203, auxiliary support clamping ring; 300, hydraulic puller; 301, pressure sensor; 302, cable; 303, external digital display. DETAILED DESCRIPTION

[0014] In order to make the technical means, creative features, objectives and effects achieved by the present invention easier to understand, the present invention is further described below in conjunction with specific implementation methods.

[0015] like Figures 1 to 3 As shown, a device for assembling a turbojet engine rotor includes a main support 100, a main support plate 101 is provided on the main support 100, a U-shaped through hole 105 is opened in the middle of the main support plate 101, and the width of the U-shaped through hole 105 accounts for approximately three-fifths of the width of the rectangular main support plate 101, two symmetrical main fixed clamping blocks 103 are fixed by bolts at the position of the U-shaped through hole 105 on the main support plate 101, a frame 104 is provided on the main support plate 101, a hydraulic puller 300 is installed on the frame 104, and an auxiliary support mechanism for clamping rotors of different sizes is provided on the frame 104.

[0016] The main support 100 adopts a frame structure welded with square steel and is the main load-bearing component of the device. The main fixed clamping block 103 is connected to the main support plate 101 by bolts, so that the main fixed clamping block 103 can be replaced according to the size of the main shaft to meet the positioning, support and clamping requirements of the main shaft and rotor of turbojet engines of different sizes, thereby improving the practicality of the device.

[0017] In this embodiment, the auxiliary support mechanism includes two auxiliary support frame vertical beams 200 installed between the frame body 104 and the main support plate 101. The auxiliary support frame vertical beams 200 are connected to the auxiliary support frame cross beams 202 by right-angle fixing members 201, and two auxiliary support clamping rings 203 are bolted to the auxiliary support frame cross beams 202.

[0018] The auxiliary support frame vertical beam 200 and the auxiliary support frame cross beam 202 are both made of aluminum alloy profiles, which are light in weight and high in strength. The auxiliary support clamping ring 203 is bolted to the auxiliary support frame cross beam 202, which is convenient for quick disassembly and assembly on the auxiliary support frame cross beam 202, and adjustment of the left and right positions of the auxiliary support clamping ring 203. At the same time, the auxiliary support frame cross beam 202 can be adjusted on the auxiliary support frame vertical beam 200 through T-bolts and right-angle fixings 201, so that the auxiliary support clamping ring 203 installed on the auxiliary support frame cross beam 202 can achieve up and down position adjustment, ensuring that the auxiliary support clamping ring 203 can be replaced according to the sizes of different engine main shafts and rotors, thereby improving the versatility and flexibility of the device, and effectively ensuring the concentricity of the impeller and the main shaft, thereby improving the assembly quality of the device and reducing production costs.

[0019] In this embodiment, a pressure sensor 301 is threadedly connected to the hydraulic puller 300 , and an external digital display 303 is provided on the auxiliary support frame vertical beam 200 . The external digital display 303 is electrically connected to the pressure sensor 301 via a cable 302 .

[0020] The hydraulic puller 300 provides vertical pressing force for the rotor, and the pressing speed is controllable to ensure that the engine rotor is assembled in place. The hydraulic puller 300 is easy to operate and saves effort, which can reduce the labor intensity of the operator and improve assembly efficiency. The pressure sensor 301 is provided to facilitate the control of the pressure and reduce damage to the rotor components and unsafe operation.

[0021] In this embodiment, universal self-locking casters 106 arranged in a rectangular shape are provided at the bottom of the main frame 100 , and rubber suction cups 107 corresponding to the universal self-locking casters 106 are provided at the four corners of the bottom of the main frame 100 .

[0022] By providing the universal self-locking casters 106, the position of the device can be flexibly moved. The rubber suction cup 107 is fixed to the bottom plate of the main frame 100 with bolts, which is convenient for adjusting the height to ensure the stability of the device.

[0023] In this embodiment, a tray 102 is provided on the crossbeam in the middle of the bottom of the main frame 100 .

[0024] A silicone shock-absorbing pad with good elasticity and toughness is installed on the surface of the tray 102, which plays a role in shock absorption, buffering and collision prevention when the rotor components are assembled.

[0025] Working process and principle: When using this device, according to the different sizes of the engine main shaft and rotor, the appropriate main fixed clamping block 103 and auxiliary support clamping ring 203 can be selected for installation. The position of the auxiliary support clamping ring 203 can be adjusted up and down and left and right through bolts and right-angle fixings 201, thereby improving the versatility and flexibility of the device, and effectively ensuring the concentricity of the impeller and the main shaft, thereby improving the assembly quality of the device and reducing production costs. At the same time, the hydraulic puller 300 is used to provide a vertical clamping force for the rotor, and the clamping speed is controllable to ensure that the engine rotor can be accurately assembled in place. The hydraulic puller 300 is easy and labor-saving to operate, can reduce the labor intensity of the operator, and improve assembly efficiency. By setting a pressure sensor 301, it is convenient to control the pressure, reduce damage to the rotor components, and avoid unsafe operation. When the rotor components are assembled, the tray 102 plays a role in shock absorption, buffering and collision prevention for the rotor components.

[0026] It is understood from common technical knowledge that the present invention may be implemented through other embodiments that do not depart from its spirit or essential features. Therefore, the embodiments disclosed above are, in all respects, merely illustrative and not exclusive. All modifications within the scope of the present invention or equivalent to the scope of the present invention are intended to be encompassed by the present invention.

Claims

1. A device for assembling a turbojet engine rotor, characterized in that: The invention comprises a main support (100), wherein the main support (100) is provided with a main support plate (101), a U-shaped through hole (105) is opened in the middle of the main support plate (101), two main fixed clamping blocks (103) with symmetrical structures are fixed by bolts at the positions of the U-shaped through hole (105) on the main support plate (101), a frame (104) is provided on the main support plate (101), a hydraulic puller (300) is installed on the frame (104), and an auxiliary support mechanism for clamping rotors of different sizes is provided on the frame (104).

2. The device for assembling a turbojet engine rotor according to claim 1, characterized in that: The auxiliary support mechanism comprises two auxiliary support frame vertical beams (200) installed between the frame body (104) and the main support plate (101); the auxiliary support frame vertical beams (200) are connected to auxiliary support frame cross beams (202) by means of right-angle fixing members (201); and two auxiliary support clamping rings (203) are bolted to the auxiliary support frame cross beams (202).

3. The device for assembling a turbojet engine rotor according to claim 2, characterized in that: A pressure sensor (301) is threadedly connected to the hydraulic puller (300), and an external digital display (303) is provided on the auxiliary support frame vertical beam (200). The external digital display (303) is electrically connected to the pressure sensor (301) via a cable (302).

4. The device for assembling a turbojet engine rotor according to claim 1, characterized in that: Universal self-locking casters (106) distributed in a rectangular shape are provided at the bottom of the main frame (100), and rubber suction cups (107) corresponding to the universal self-locking casters (106) are provided at the four corners of the bottom of the main frame (100).

5. The device for assembling a turbojet engine rotor according to claim 4, characterized in that: A tray (102) is provided on the crossbeam in the middle of the bottom of the main frame (100).

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