Aero-engine high-pressure turbine rotor stop tool

Abstract

The invention discloses an aero-engine high-pressure turbine rotor stopping tool which is characterized in that an adapter and supporting frames are arranged at the bottom of a high-vortex stopping mounting plate, a plug pin is arranged on the adapter, and the supporting frames are arranged at the two ends of the high-vortex stopping mounting plate. The shape of the adapter is matched with that of the high-pressure turbine rotor of the aero-engine, so that the plug pin can be conveniently inserted into a corresponding hole in a high-turbine shaft neck of the high-pressure turbine rotor of the aero-engine; the locking plug pin is arranged on the connecting plate, rapid positioning of installation is achieved, the tool and the high-pressure turbine rotor of the aero-engine are stably connected through the arrangement of the screw, the high-pressure turbine rotor is stopped through the cooperation of the plug pin and the high-pressure turbine rotor, an operation space is reserved for tightening work of a high-vortex bolt, and the working efficiency is improved. And an operator can conveniently and quickly tighten the high-vortex bolt. The device is convenient to use, the high-vortex bolt tightening time can be shortened, and the production efficiency is effectively improved.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine assembly and testing technology, and particularly relates to a high-pressure turbine rotor stop tooling for aero-engines. Background Technology

[0002] Currently, high-pressure turbine rotor stop fixtures are used in engine assembly, primarily to prevent high-pressure turbine rotor wobbling during the tightening of high-pressure turbine rotor bolts and heat shields. Applications include... Figure 2 The existing tooling shown uses a high-vortex bolt tightening sleeve attached to it to tighten the high-vortex bolts, thereby fixing the high-pressure turbine rotor onto the high-pressure compressor rotor. This process requires repeated disassembly and reassembly of the high-vortex bolt tightening sleeve until all the high-vortex bolts are tightened. This operation is laborious and time-consuming, which can easily slow down the production progress and affect production efficiency. Summary of the Invention

[0003] To solve the above-mentioned technical problems, the present invention provides a stop tooling for a high-pressure turbine rotor of an aero-engine.

[0004] The present invention is achieved through the following technical solutions.

[0005] The present invention provides a high-pressure turbine rotor stop tooling for aero-engines, including a high-pressure turbine stop mounting plate, wherein an adapter and a support frame are provided at the bottom of the high-pressure turbine stop mounting plate, a pin is provided on the adapter, and the support frame is provided at both ends of the high-pressure turbine stop mounting plate.

[0006] Preferably, a connecting plate is provided at the bottom of the support frame, and a locking pin and screws are provided on the connecting plate.

[0007] Preferably, the locking pin is a ball-head locking pin.

[0008] Preferably, the screw is a screw with a threaded handle.

[0009] Preferably, the high-vortex stop mounting plate is provided with slots, grooves and through holes, and the slots and through holes are provided on both sides of the grooves.

[0010] Preferably, the high-vortex stop mounting plate and the adapter are fastened together by screws.

[0011] Preferably, one side of the adapter is provided with an inclined surface.

[0012] Preferably, the pin is inclined to the high-vortex stop mounting plate.

[0013] The beneficial effects of this invention are as follows: This invention, by designing an adapter that matches the shape of the high-pressure turbine rotor of an aero-engine, facilitates the insertion of a pin into the corresponding hole on the high-pressure turbine journal of the rotor. Existing technology uses a high-pressure turbine bolt tightening sleeve whose outer wall engages with the inner wall of a circular hole on a high-pressure turbine stop plate to achieve a stop when tightening the high-pressure turbine bolt. The pin design of this invention eliminates the need for a high-pressure turbine bolt tightening sleeve, reducing the repetitive disassembly and assembly steps required when tightening high-pressure turbine bolts. Workers can use other tools to quickly tighten the high-pressure turbine bolts, reducing the size of the tooling. A locking pin on the connecting plate enables rapid positioning during installation. The screw design ensures a stable connection between the tooling and the rear mounting edge of the low-pressure turbine guide of the aero-engine. The pin's engagement with the high-pressure turbine rotor provides a stop function for the high-pressure turbine rotor, providing operating space for tightening the high-pressure turbine bolts and allowing operators to quickly tighten them. This invention is easy to use, shortens the high-pressure turbine bolt tightening time, and effectively improves production efficiency. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a physical image of an existing high-pressure turbine rotor stop tooling; In the diagram: 1-High vortex stop mounting plate, 11-Slotted, 12-Groove, 13-Through hole, 2-Adapter, 3-Support bracket, 31-Connecting plate, 4-Pin, 5-Locking pin, 6-Screw, 7-High vortex stop plate, 8-High vortex bolt tightening sleeve. Detailed Implementation

[0015] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0016] Example 1: like Figure 1 As shown, a high-pressure turbine rotor stop fixture for an aero-engine includes a high-pressure turbine rotor stop mounting plate 1. An adapter 2 and a support frame 3 are provided at the bottom of the high-pressure turbine rotor stop mounting plate 1. The high-pressure turbine rotor stop mounting plate 1 is the main structure of the fixture. A pin 4 is provided on the adapter 2, which serves as the mounting support for the pin 4. The support frame 3 is located at both ends of the high-pressure turbine rotor stop mounting plate 1. The shape of the adapter 2 also matches the shape of the high-pressure turbine rotor of the aero-engine. The hole for the pin 4 to pass through precisely matches two holes on the high-pressure turbine rotor's high-pressure turbine journal, allowing the pin 3 to freely enter and exit the two holes on the high-pressure turbine journal.

[0017] The bottom of the support frame 3 is provided with a connecting plate 31, and the connecting plate 31 is provided with a locking pin 5 and a screw 6.

[0018] The locking pin 5 is a ball-head locking pin, which serves as a positioning pin when the tooling is installed on the high-pressure turbine rotor of the aero-engine, so that the tooling can accurately find the centering position on the high-pressure turbine rotor of the aero-engine.

[0019] The screw 6 is a threaded handle screw, which serves to fix the tooling to the mounting edge of the low-pressure turbine guide of the aero-engine.

[0020] The high-vortex stop mounting plate 1 is provided with a slot 11, a groove 12 and a through hole 13, and the slot 11 and the through hole 13 are provided on both sides of the groove 12.

[0021] The high-vortex stop mounting plate 1 and the adapter 2 are fastened together by screws.

[0022] An inclined surface 21 is provided on one side of the adapter 2.

[0023] The pin 4 is inclined to the high-pressure turbine rotor journal 1, which facilitates insertion into the corresponding hole on the high-pressure turbine rotor journal of the aero-engine. The pin 4 prevents the high-pressure turbine rotor from rotating when it is placed on the engine.

[0024] Comparative Example 1: like Figure 2 As shown, a stop fixture for a high-pressure turbine rotor of an aero-engine is an existing fixture. The high-pressure turbine bolts are tightened using the attached high-pressure turbine bolt tightening sleeve 8. The high-pressure turbine stop plate 7 has 12 fixture holes corresponding to the 12 bolts on the high-pressure turbine rotor. The high-pressure turbine bolt tightening sleeve 8 is placed into one of the fixture holes on the high-pressure turbine stop plate 7, and the high-pressure turbine rotor bolt is fitted onto it. The high-pressure turbine bolt is then tightened using the high-pressure turbine bolt tightening sleeve 8. This operation is repeated 12 times. At this point, the outer wall of the high-pressure turbine bolt tightening sleeve 8 and the inner wall of the high-pressure turbine bolt hole on the high-pressure turbine stop plate 7 cooperate, achieving the stop effect on the high-pressure turbine rotor.

[0025] As can be seen from the comparison between Example 1 and Comparative Example 1, the stop tooling of the present invention can achieve the high vortex stop function without repeatedly disassembling and assembling the high vortex bolt tightening sleeve 8. At the same time, it is convenient for operators to use other tools to quickly tighten the high vortex bolt. In addition, the high vortex stop mounting plate 1 has no annular structure in the middle, which leaves more operating space while ensuring the stop function, making it more convenient and faster to perform data measurement on the high pressure turbine rotor in the future.

Claims

1. A stop tooling for a high-pressure turbine rotor of an aero-engine, characterized in that: It includes a high vortex stop mounting plate (1), with an adapter (2) and a support frame (3) at the bottom of the high vortex stop mounting plate (1), a pin (4) on the adapter (2), and the support frame (3) at both ends of the high vortex stop mounting plate (1).

2. The aero-engine high-pressure turbine rotor stop tooling as described in claim 1, characterized in that: The support frame (3) has a connecting plate (31) at its bottom, and the connecting plate (31) is provided with a locking pin (5) and a screw (6).

3. The high-pressure turbine rotor stop tooling for an aero-engine as described in claim 2, characterized in that: The locking pin (5) is a ball-head locking pin.

4. The aero-engine high-pressure turbine rotor stop tooling as described in claim 2, characterized in that: The screw (6) is a threaded handle screw.

5. The aero-engine high-pressure turbine rotor stop tooling as described in claim 1, characterized in that: The high-vortex stop mounting plate (1) is provided with a slot (11), a groove (12) and a through hole (13), and the slot (11) and the through hole (13) are provided on both sides of the groove (12).

6. The aero-engine high-pressure turbine rotor stop tooling as described in claim 1, characterized in that: The high-vortex stop mounting plate (1) and the adapter (2) are fastened together by screws.

7. The aero-engine high-pressure turbine rotor stop tooling as described in claim 1, characterized in that: An inclined surface (21) is provided on one side of the adapter (2).

8. The aero-engine high-pressure turbine rotor stop tooling as described in claim 1, characterized in that: The pin (4) is inclined to the high-vortex stop mounting plate (1).

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