CN103542095A - Helicopter main speed reducer oil leak troubleshooting method - Google Patents
Helicopter main speed reducer oil leak troubleshooting method Download PDFInfo
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- CN103542095A CN103542095A CN201310492802.4A CN201310492802A CN103542095A CN 103542095 A CN103542095 A CN 103542095A CN 201310492802 A CN201310492802 A CN 201310492802A CN 103542095 A CN103542095 A CN 103542095A
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Abstract
The invention relates to a helicopter main speed reducer oil leak troubleshooting method. The method includes that an oil leak position is determined, state of a sealing member is examined, an oil leak mode of a main speed reducer is determined, and then oil leak reasons can be quickly and conveniently found. The helicopter main speed reducer oil leak troubleshooting method has the advantages of simplicity and high efficiency, oil leak fault reasons of the main speed reducer of a helicopter can be quickly and effectively found, and troubleshooting period and cost are reduced.
Description
Technical field
The present invention relates to a kind of Helicopter Main Reducer leakage of oil troubleshooting method.
Background technique
China's helicopter development, through the development of decades, has obtained certain achievement.Along with increasing of helicopter quantity and application, Helicopter Main Reducer oil leakage fault in bench test drive and line using process is and increases trend.The sealing means of Helicopter Main Reducer has two kinds of static seal and motive sealings.Wherein, motive sealing comprises leather cup, graphite seal bowl and spiral seal, and static seal comprises O-ring seals and thread seal.According to statistics, from January, 2004 so far, certain Helicopter Main subtracts 138 of common generation oil leakage faults, at present, because main reducing gear leakage of oil troubleshooting does not have concrete step and method, can only dependence experience carry out troubleshooting.Generally, be all to get rid of oil leakage fault by changing the mode of Sealing.This has not only increased troubleshooting duration and cost, and has seriously affected company reputation.Therefore, study a kind of Helicopter Main Reducer leakage of oil troubleshooting method extremely urgent.
Summary of the invention
The object of the invention is to formulate the method for Helicopter Main Reducer leakage of oil troubleshooting, realize fast effect and effectively get rid of oil leakage fault, reduce the troubleshooting cycle, reduce troubleshooting expense.
Technological scheme of the present invention is: main reducing gear leakage of oil troubleshooting method comprises the following steps:
(1) for the Helicopter Main Reducer that oil leakage fault occurs, first leakage of oil position lubricating oil is cleaned, the time installation that then increases at least 30 minutes is observed its leakage of oil situation, if continuation leakage of oil, is undertaken by step (2), if oil-proof, do not need to fix a breakdown, can continue to use;
(2) according to the main leakage of oil position that subtracts, determine it is motive sealing leakage of oil or static seal leakage of oil, if motive sealing leakage of oil by step (3), undertaken, if static seal leakage of oil is undertaken by step (7);
(3) observe the movable sealing structure of leakage of oil position, determine it is cup packing or the sealing of graphite seal bowl, if the sealing of graphite seal bowl is carried out troubleshooting by step (4), if cup packing is undertaken by step (5);
(4) check that whether the elastic force of graphite block at the position of obturaging is good, if resilience is bad, change graphite seal ring, if resilience is good, check graphite seal bowl outward appearance, if there is crackle, slag-off phenomenon in graphite seal bowl, should change in time graphite seal bowl, then by step (8), undertaken; If do not deposit the problems referred to above, by step (6), carry out troubleshooting;
(5) after leakage of oil position is decomposed, carefully check leather cup state, if leather cup exists fine crack, slag-off phenomenon, should change in time leather cup, then by step (8), undertaken, if leather cup is intact, should check the surface state of phase accessory, if part surface is jagged, point limit is rounding not, on leather cup assembling circuit, the surface roughness of part does not meet design requirement, and should change phase accessory, then by step (8), is undertaken;
(6) decompose leakage of oil position, the obturage surperficial polishing scratch situation of flange plate and spacer sleeve at bowl position of inspection, if have slight, without the polishing scratch degree of depth, even circumferential, illustrate that phase accessory is working properly, if polishing scratch has unbalance loading phenomenon or phase accessory dimension overproof deeply and on circumference, should change phase accessory, then former reassembles, and by step (8), carries out test run;
(7) check " O " shape seal ring situation, if seal ring damages and should change in time, if seal ring is intact, sealing position is decomposed, then check the dimensional fits situation of " O " shape seal ring and phase accessory, and calculate its decrement and whether meet design requirement, if decrement is inadequate, can overcome oil leakage fault by changing the mode of phase accessory or apolegamy " O " shape seal ring, then by step (8), be undertaken;
(8) installation, test run, if oil leakage fault is got rid of, main reducing gear can be paid, use; If main, subtract continuation leakage of oil, repeat above-mentioned steps until oil leakage fault is got rid of.
In (4) described step, can if observe graphite block, can restore to the original state by making with graphite block under have gentle hands flicking after its distortion, represent that graphite block resilience is good.
The present invention, by determining leakage of oil position, checks Sealing state, determines that master subtracts leakage of oil mode, then can search Oil Leakage fast and easily.The method has been applied in real work at present, can find out fast and effectively Helicopter Main Reducer oil leakage fault reason, has reduced the troubleshooting cycle, has reduced troubleshooting expense.
Embodiment
Main reducing gear leakage of oil troubleshooting method comprises the following steps:
(1) for the Helicopter Main Reducer that oil leakage fault occurs, first leakage of oil position lubricating oil is cleaned, the time installation that then increases at least 30 minutes is observed its leakage of oil situation, if continuation leakage of oil, is undertaken by step (2), if oil-proof, do not need to fix a breakdown, can continue to use;
(2) according to the main leakage of oil position that subtracts, determine it is motive sealing leakage of oil or static seal leakage of oil, if motive sealing leakage of oil by step (3), undertaken, if static seal leakage of oil is undertaken by step (7);
(3) observe the movable sealing structure of leakage of oil position, determine it is cup packing or the sealing of graphite seal bowl, if the sealing of graphite seal bowl is carried out troubleshooting by step (4), if cup packing is undertaken by step (5);
(4) check that whether the elastic force of graphite block at the position of obturaging is good, if resilience is bad, change graphite seal ring, if resilience is good, check graphite seal bowl outward appearance, if there is crackle, slag-off phenomenon in graphite seal bowl, should change in time graphite seal bowl, then by step (8), undertaken; If do not deposit the problems referred to above, by step (6), carry out troubleshooting;
(5) after leakage of oil position is decomposed, carefully check leather cup state, if leather cup exists fine crack, slag-off phenomenon, should change in time leather cup, then by step (8), undertaken, if leather cup is intact, should check the surface state of phase accessory, if part surface is jagged, point limit is rounding not, on leather cup assembling circuit, the surface roughness of part does not meet design requirement, and should change phase accessory, then by step (8), is undertaken;
(6) decompose leakage of oil position, the obturage surperficial polishing scratch situation of flange plate and spacer sleeve at bowl position of inspection, if have slight, without the polishing scratch degree of depth, even circumferential, illustrate that phase accessory is working properly, if polishing scratch has unbalance loading phenomenon or phase accessory dimension overproof deeply and on circumference, should change phase accessory, then former reassembles, and by step (8), carries out test run;
(7) check " O " shape seal ring situation, if seal ring damages and should change in time, if seal ring is intact, sealing position is decomposed, then check the dimensional fits situation of " O " shape seal ring and phase accessory, and calculate its decrement and whether meet design requirement, if decrement is inadequate, can overcome oil leakage fault by changing the mode of phase accessory or apolegamy " O " shape seal ring, then by step (8), be undertaken;
(8) installation, test run, if oil leakage fault is got rid of, main reducing gear can be paid, use; If main, subtract continuation leakage of oil, repeat above-mentioned steps until oil leakage fault is got rid of.
In (4) described step, can if observe graphite block, can restore to the original state by making with graphite block under have gentle hands flicking after its distortion, represent that graphite block resilience is good.
Embodiment
During certain type Helicopter Main Reducer ground run, a right input end leakage of oil, its leakage of oil troubleshooting step is:
(1) leakage of oil position lubricating oil is cleaned, increased time installation 30 minutes, find that leakage of oil situation continued exists, and starts to carry out troubleshooting;
(2) according to the main leakage of oil position that subtracts, determine it is motive sealing leakage of oil;
(3) observe the movable sealing structure of leakage of oil position, determine it is the sealing of graphite seal bowl;
(4) check that whether the elastic force of graphite block at the position of obturaging is good, find that the elastic force of graphite block is bad, with under have gentle hands flicking, it can not arrive previous condition by spring return afterwards, change graphite seal ring;
(5) installation, test run, oil leakage fault is got rid of, and main reducing gear can be paid, use.
Claims (2)
1. a method for Helicopter Main Reducer leakage of oil troubleshooting, is characterized in that, described method comprises the following steps:
(1) for the Helicopter Main that oil leakage fault occurs, subtract device, first leakage of oil position lubricating oil is cleaned, the time installation that then increases at least 30 minutes is observed its leakage of oil situation, if continuation leakage of oil, is undertaken by step (2), if oil-proof, do not need to fix a breakdown, can continue to use;
(2) according to the main leakage of oil position that subtracts, determine it is motive sealing leakage of oil or static seal leakage of oil, if motive sealing leakage of oil by step (3), undertaken, if static seal leakage of oil is undertaken by step (7);
(3) observe the movable sealing structure of leakage of oil position, determine it is cup packing or the sealing of graphite seal bowl, if the sealing of graphite seal bowl is carried out troubleshooting by step (4), if cup packing is undertaken by step (5);
(4) check that whether the elastic force of graphite block at the position of obturaging is good, if resilience is bad, change graphite seal ring, if resilience is good, check graphite seal bowl outward appearance, if there is crackle, slag-off phenomenon in graphite seal bowl, should change in time graphite seal bowl, then by step (8), undertaken; If do not deposit the problems referred to above, by step (6), carry out troubleshooting;
(5) after leakage of oil position is decomposed, carefully check leather cup state, if leather cup exists fine crack, slag-off phenomenon, should change in time leather cup, then by step (8), undertaken, if leather cup is intact, should check the surface state of phase accessory, if part surface is jagged, point limit is rounding not, on leather cup assembling circuit, the surface roughness of part does not meet design requirement, and should change phase accessory, then by step (8), is undertaken;
(6) decompose leakage of oil position, the obturage surperficial polishing scratch situation of flange plate and spacer sleeve at bowl position of inspection, if have slight, without the polishing scratch degree of depth, even circumferential, illustrate that phase accessory is working properly, if polishing scratch has unbalance loading phenomenon or phase accessory dimension overproof deeply and on circumference, should change phase accessory, then former reassembles, and by step (8), carries out test run;
(7) check " O " shape seal ring situation, if seal ring damages and should change in time, if seal ring is intact, sealing position is decomposed, then check the dimensional fits situation of " O " shape seal ring and phase accessory, and calculate its decrement and whether meet design requirement, if decrement is inadequate, can overcome oil leakage fault by changing the mode of phase accessory or apolegamy " O " shape seal ring, then by step (8), be undertaken;
(8) installation, test run, if oil leakage fault is got rid of, main reducing gear can be paid, use; If main, subtract continuation leakage of oil, repeat above-mentioned steps until oil leakage fault is got rid of.
2. the method for Helicopter Main Reducer leakage of oil troubleshooting as claimed in claim 1, it is characterized in that, in (4) described step, can be by making with graphite block under have gentle hands flicking after its distortion, if observe graphite block, can restore to the original state, represent that graphite block resilience is good.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105650449A (en) * | 2016-03-21 | 2016-06-08 | 哈尔滨东安发动机（集团）有限公司 | Positioning method for low pressure fault cause of main oil cavity of helicopter main reducing gear |
| CN105840978A (en) * | 2016-03-21 | 2016-08-10 | 哈尔滨东安发动机（集团）有限公司 | Positioning method for main oil cavity high-pressure failure cause of helicopter main reducing gear |
| CN109210182A (en) * | 2018-08-27 | 2019-01-15 | 贺煜 | A kind of oil leak of reducer processing method |
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| CN1755170A (en) * | 2004-09-30 | 2006-04-05 | 索奈克斯工业有限公司 | Method and tools for repairing leakage of gear box hydraulic pressure leakage and piston protection ring assembly |
| CN1865734A (en) * | 2006-06-23 | 2006-11-22 | 崔国跃 | Method and device for processing oil leakage of decelerator or gear box |
| JP2009198322A (en) * | 2008-02-21 | 2009-09-03 | Yazaki Corp | Method, apparatus and system for seal inspection |
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| CN202453163U (en) * | 2012-03-12 | 2012-09-26 | 浙江东海减速机有限公司 | Reducer oil leakage detector |
| CN102817999A (en) * | 2012-07-18 | 2012-12-12 | 上海叠泉信息科技有限公司 | Oil change system of wind driven generator gearbox and leak-proof security protection method for oil chang |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1755170A (en) * | 2004-09-30 | 2006-04-05 | 索奈克斯工业有限公司 | Method and tools for repairing leakage of gear box hydraulic pressure leakage and piston protection ring assembly |
| CN1865734A (en) * | 2006-06-23 | 2006-11-22 | 崔国跃 | Method and device for processing oil leakage of decelerator or gear box |
| JP2009198322A (en) * | 2008-02-21 | 2009-09-03 | Yazaki Corp | Method, apparatus and system for seal inspection |
| US20100077612A1 (en) * | 2008-09-30 | 2010-04-01 | Courtney James Tudor | Method of manufacturing a fairing with an integrated seal |
| CN202453163U (en) * | 2012-03-12 | 2012-09-26 | 浙江东海减速机有限公司 | Reducer oil leakage detector |
| CN102817999A (en) * | 2012-07-18 | 2012-12-12 | 上海叠泉信息科技有限公司 | Oil change system of wind driven generator gearbox and leak-proof security protection method for oil chang |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105650449A (en) * | 2016-03-21 | 2016-06-08 | 哈尔滨东安发动机（集团）有限公司 | Positioning method for low pressure fault cause of main oil cavity of helicopter main reducing gear |
| CN105840978A (en) * | 2016-03-21 | 2016-08-10 | 哈尔滨东安发动机（集团）有限公司 | Positioning method for main oil cavity high-pressure failure cause of helicopter main reducing gear |
| CN109210182A (en) * | 2018-08-27 | 2019-01-15 | 贺煜 | A kind of oil leak of reducer processing method |
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| CN103542095B (en) | 2015-12-02 |
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