CN103542095B - Helicopter Main Reducer leakage of oil troubleshooting method - Google Patents
Helicopter Main Reducer leakage of oil troubleshooting method Download PDFInfo
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- CN103542095B CN103542095B CN201310492802.4A CN201310492802A CN103542095B CN 103542095 B CN103542095 B CN 103542095B CN 201310492802 A CN201310492802 A CN 201310492802A CN 103542095 B CN103542095 B CN 103542095B
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Abstract
The present invention relates to a kind of Helicopter Main Reducer leakage of oil troubleshooting method, by determining leakage of oil position, check Sealing state, determine that master subtracts leakage of oil mode, then Oil Leakage can be searched fast and easily, the present invention has simple feature efficiently, can find out Helicopter Main Reducer oil leakage fault reason fast and effectively, reduce troubleshooting duration and cost.
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 achieved certain achievement.Along with increasing of helicopter quantity and application, Helicopter Main Reducer in bench test drive and line process oil leakage fault in increasing trend.The sealing means of Helicopter Main Reducer has static seal and motive sealing two kinds.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 common generation oil leakage fault 138, at present, because main reducing gear leakage of oil troubleshooting does not have concrete step and method, experience can only be relied on to carry out troubleshooting.Under normal circumstances, be all get rid of oil leakage fault by the mode of replacing Sealing.This not only adds troubleshooting duration and cost, and seriously have impact on company reputation.Therefore, a kind of Helicopter Main Reducer leakage of oil troubleshooting method is studied extremely urgent.
Summary of the invention
The object of the invention is to the method formulating 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 cleaned by leakage of oil position lubricating oil, the time installation then increasing at least 30 minutes observes its leakage of oil situation, if continuation leakage of oil, then undertaken, if oil-proof by step (2), then do not need to fix a breakdown, can continue to use;
(2) subtract leakage of oil position according to main, determine motive sealing leakage of oil or static seal leakage of oil, if motive sealing leakage of oil, then undertaken by step (3), if static seal leakage of oil, then undertaken by step (7);
(3) observe the movable sealing structure of leakage of oil position, determine cup packing or the sealing of graphite seal bowl, if the sealing of graphite seal bowl, carry out troubleshooting by step (4), if cup packing, undertaken by step (5);
(4) check that whether the elastic force of the graphite block at position of obturaging is good, if resilience is bad, then change graphite seal ring, if resilience is good, then check graphite seal bowl outward appearance, if graphite seal bowl exists crackle, slag-off phenomenon, then should change graphite seal bowl in time, then be undertaken by step (8); If do not deposit the problems referred to above, then carry out troubleshooting by step (6);
(5) by after leakage of oil site decomposition, careful inspection leather cup state, if leather cup exists fine crack, slag-off phenomenon, should change leather cup in time, then undertaken by step (8), if leather cup is intact, then should check the surface state of phase accessory, if part surface is jagged, the non-rounding in point limit, on leather cup assembling circuit, the surface roughness of part does not meet design requirement, then should change phase accessory, then be undertaken by step (8);
(6) leakage of oil position is decomposed, check the flange plate at bowl position and the surperficial polishing scratch situation of spacer sleeve of obturaging, if have slight, without the degree of depth, the polishing scratch of even circumferential, then illustrate that phase accessory is working properly, if polishing scratch more deeply and circumferentially have unbalance loading phenomenon or phase accessory dimension overproof, then should change phase accessory, then former reassembles, and carries out test run by step (8);
(7) " O " shape seal ring situation is checked, 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, oil leakage fault can be overcome by the mode changing phase accessory or apolegamy " O " shape seal ring, then be undertaken by step (8);
(8) installation, test run, if oil leakage fault is got rid of, then main reducing gear can be paid, use; Subtract continuation leakage of oil if main, then repeat above-mentioned steps until oil leakage fault is got rid of.
In (4) described step, by with after graphite block makes it be out of shape under have gentle hands flicking, can restore to the original state if observe graphite block, then 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.Current the method has been applied in real work, can find out Helicopter Main Reducer oil leakage fault reason fast and effectively, reduce the troubleshooting cycle, reduce 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 cleaned by leakage of oil position lubricating oil, the time installation then increasing at least 30 minutes observes its leakage of oil situation, if continuation leakage of oil, then undertaken, if oil-proof by step (2), then do not need to fix a breakdown, can continue to use;
(2) subtract leakage of oil position according to main, determine motive sealing leakage of oil or static seal leakage of oil, if motive sealing leakage of oil, then undertaken by step (3), if static seal leakage of oil, then undertaken by step (7);
(3) observe the movable sealing structure of leakage of oil position, determine cup packing or the sealing of graphite seal bowl, if the sealing of graphite seal bowl, carry out troubleshooting by step (4), if cup packing, undertaken by step (5);
(4) check that whether the elastic force of the graphite block at position of obturaging is good, if resilience is bad, then change graphite seal ring, if resilience is good, then check graphite seal bowl outward appearance, if graphite seal bowl exists crackle, slag-off phenomenon, then should change graphite seal bowl in time, then be undertaken by step (8); If do not deposit the problems referred to above, then carry out troubleshooting by step (6);
(5) by after leakage of oil site decomposition, careful inspection leather cup state, if leather cup exists fine crack, slag-off phenomenon, should change leather cup in time, then undertaken by step (8), if leather cup is intact, then should check the surface state of phase accessory, if part surface is jagged, the non-rounding in point limit, on leather cup assembling circuit, the surface roughness of part does not meet design requirement, then should change phase accessory, then be undertaken by step (8);
(6) leakage of oil position is decomposed, check the flange plate at bowl position and the surperficial polishing scratch situation of spacer sleeve of obturaging, if have slight, without the degree of depth, the polishing scratch of even circumferential, then illustrate that phase accessory is working properly, if polishing scratch more deeply and circumferentially have unbalance loading phenomenon or phase accessory dimension overproof, then should change phase accessory, then former reassembles, and carries out test run by step (8);
(7) " O " shape seal ring situation is checked, 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, oil leakage fault can be overcome by the mode changing phase accessory or apolegamy " O " shape seal ring, then be undertaken by step (8);
(8) installation, test run, if oil leakage fault is got rid of, then main reducing gear can be paid, use; Subtract continuation leakage of oil if main, then repeat above-mentioned steps until oil leakage fault is got rid of.
In (4) described step, by with after graphite block makes it be out of shape under have gentle hands flicking, can restore to the original state if observe graphite block, then 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, increase time installation 30 minutes, find that leakage of oil situation continued exists, then start to carry out troubleshooting;
(2) subtract leakage of oil position according to main, 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 the graphite block at position of obturaging is good, find that the elastic force of graphite block is bad, after under have gentle hands flicking, it can not arrive previous condition by spring return, carries out replacing 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 Reducer that oil leakage fault occurs, first leakage of oil position lubricating oil is cleaned, then the time installation increasing at least 30 minutes observes its leakage of oil situation, if continuation leakage of oil, then undertaken by step (2), if oil-proof, then do not need to fix a breakdown, can continue to use;
(2) according to main reducing gear leakage of oil position, determine motive sealing leakage of oil or static seal leakage of oil, if motive sealing leakage of oil, then undertaken by step (3), if static seal leakage of oil, then undertaken by step (7);
(3) observe the movable sealing structure of leakage of oil position, determine cup packing or the sealing of graphite seal bowl, if the sealing of graphite seal bowl, carry out troubleshooting by step (4), if cup packing, undertaken by step (5);
(4) check that whether the resilience of the graphite block at graphite seal bowl position is good, if resilience is bad, then change graphite seal bowl, if resilience is good, then check graphite seal bowl outward appearance, if graphite seal bowl exists crackle, slag-off phenomenon, then should change graphite seal bowl in time, then be undertaken by step (8); If do not deposit the problems referred to above, then carry out troubleshooting by step (6);
(5) by after leakage of oil site decomposition, careful inspection leather cup state, if leather cup exists fine crack, slag-off phenomenon, should change leather cup in time, then undertaken by step (8), if leather cup is intact, then should check the surface state of phase accessory, if phase accessory surface is jagged, the non-rounding in point limit, on leather cup assembling circuit, the surface roughness of phase accessory does not meet design requirement, then should change phase accessory, then be undertaken by step (8);
(6) leakage of oil position is decomposed, check the flange plate at graphite seal bowl position and the surperficial polishing scratch situation of spacer sleeve, if have slight, without the degree of depth, the polishing scratch of even circumferential, then illustrate that phase accessory is working properly, if polishing scratch more deeply and circumferentially have unbalance loading phenomenon or phase accessory dimension overproof, then should change phase accessory, then former reassembles, and carries out test run by step (8);
(7) " O " shape seal ring situation is checked, 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, overcome oil leakage fault by the mode changing phase accessory or apolegamy " O " shape seal ring, then undertaken by step (8);
(8) installation, test run, if oil leakage fault is got rid of, then main reducing gear can be paid, use; If main reducing gear continues leakage of oil, then 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, by with after under have gentle hands flicking, graphite block makes it be out of shape, if observe graphite block can restore to the original state, then represent that graphite block resilience is good.
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| CN201310492802.4A CN103542095B (en) | 2013-10-21 | 2013-10-21 | Helicopter Main Reducer leakage of oil troubleshooting method |
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| CN201310492802.4A CN103542095B (en) | 2013-10-21 | 2013-10-21 | Helicopter Main Reducer leakage of oil troubleshooting method |
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| CN103542095B true CN103542095B (en) | 2015-12-02 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 |
| 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 |
| 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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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20100077612A1 (en) * | 2008-09-30 | 2010-04-01 | Courtney James Tudor | Method of manufacturing a fairing with an integrated seal |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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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