A high-pressure turbine rotor centering device for an aero-engine and its application method

Abstract

The invention relates to the technical field of aero-engines and provides a centering device for a high pressure turbine rotor of an aero-engine. The centering device comprises a frame, a bearing pedestal and a through connection base. The frame comprises an inner ring of the frame, an outer ring of the frame, a bearing beam, a mounting edge of the frame, a hosting bolt hole and a hanging ring screw. The inner ring of the frame is fixedly connected to the bearing pedestal through the through connection base. A centering bearing inner ring is mounted on the bearing pedestal in a sleeving manner. The invention also provides an application method of the device. The application method comprises the following steps: first, assembling a low pressure turbine rotor assembly; then putting sample paste to a to-be-measured part; then mounting the hanging bolt hole on a D type bolt of an outer cartridge receiver in a sleeving manner; then sleeving the hanging ring screw into a crane and hoisting the device and the low pressure turbine assembly; then locking the centering bearing inner ring to a centering bearing outer ring in a rotor back shaft in a fit manner; and finally, plastifying the sample paste and measuring the thickness of an indentation of the sample paste. According to the high pressure turbine rotor provided by the invention, centering of the high pressure turbine rotor and hoisting of the low pressure turbine assembly can be achieved synchronously in a clamping measuring process, so that the accuracy and effectiveness of axial clearance measurement of the rotor and the stator are improved.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to an aero-engine high-pressure turbine rotor centering device and an application method thereof. Background technique [0002] The aero-engine is composed of rotor parts and stator parts, and the thrust is generated by the air flow in the flow channel, so it is necessary to reduce the air flow loss in the flow channel as much as possible. In aero-engines, the grate teeth between the rotor and the stator are generally used to seal with the honeycomb structure to ensure the airtightness of the structure. [0003] Existing aero-engines include a high-pressure turbine rotor and a low-pressure turbine assembly, wherein the low-pressure turbine assembly is the stator assembly; the low-pressure turbine assembly includes a low-pressure turbine primary guide, a low-pressure turbine secondary guide, and an external casing. After the high-pressure turbine rotor passes through The bearin...

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Problems solved by technology

However, in the above process, there is no corresponding centering device to center the rear shaft of the high-pressure turbine rotor, so that the high-pressure turbine rotor deflects, so that it is impossible to ensure that the high-pressure turbine rotor and the low-pressure turbine assembly are in a concentric state under the false state, resulting in relatively high pressure. large measurement error

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