A method for preventing aeroengine low-pressure turbine shaft front fulcrum bearing wear

Abstract

The invention relates to a wear preventing method for a bearing, and specifically relates to a wear preventing method for a front supporting point bearing of a low-pressure turbine shaft of an aero-engine. According to the technical scheme, the method comprises the steps of (1) detecting and adjusting the low-pressure turbine shaft; (2) detecting and adjusting a mounting surface of the front supporting point bearing under the state of assembling a low-pressure turbine disk and the low-pressure turbine shaft; (3) mounting an inner ring of the front supporting point bearing on the mounting surface of the front supporting point bearing under an interference state; (4) detecting and adjusting an outer ring mounting seat of the front supporting point bearing; (5) mounting an outer ring of the front supporting point bearing into the outer ring mounting seat of the front supporting point bearing under the interference state; (6) concentrically arranging a bevel gear and a rear supporting point bearing of the low-pressure turbine shaft; (7) eccentrically arranging the inner ring of the front supporting point bearing and the outer ring of the front supporting point bearing; (8) assembling. With the adoption of the method, the faults caused by sliding and scratching of the front supporting point bearing can be effectively inhibited, and meanwhile, the fault due to wearing of the front supporting point bearing can be effectively reduced.

Description

technical field [0001] The invention relates to a method for preventing bearing wear, in particular to a method for preventing wear of a front fulcrum bearing of an aeroengine low-pressure turbine shaft. Background technique [0002] The position where the low-pressure turbine shaft of an aero-engine is connected to the low-pressure compressor shaft is far away from the other end of the low-pressure turbine shaft, so some aero-engine low-pressure turbine shafts are equipped with front fulcrum bearings. [0003] The design structure of the aero-engine is as follows: the low-pressure turbine shaft is longer and its size exceeds 1m. The low-pressure turbine disk is fixed on the rear end of the low-pressure turbine shaft. On the turbine disc, the radial load of the front fulcrum bearing of the low-pressure turbine shaft under this structure is small when it works, and the roller rods inside are prone to slipping and scratching due to insufficient drag force. Due to the large di...

AI Technical Summary

Problems solved by technology

Most of the troubleshooting work of the front fulcrum bearings is to replace the new front fulcrum bearings, and additional verification is performed again. The troubleshooting is relatively passive, and there are few control measures in advance, and the phenomenon of repeated engine test runs is more serious.

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