CN204327936U - A kind of small flow lubrication system of full flight envelope work - Google Patents
A kind of small flow lubrication system of full flight envelope work Download PDFInfo
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- CN204327936U CN204327936U CN201420753525.8U CN201420753525U CN204327936U CN 204327936 U CN204327936 U CN 204327936U CN 201420753525 U CN201420753525 U CN 201420753525U CN 204327936 U CN204327936 U CN 204327936U
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Abstract
The small flow lubrication system of the full flight envelope work that the utility model relates to, be a kind of system for aircraft second power system combination power device gearbox lubrication and cooling, comprise except solenoid 17, oil feed pump 4, safety valve 2, oil filter 3, radiator 15, bypass valve 16, pressure transducer 14, lubricating oil nozzle 12, lubricating oil pressure modulating valve 13, fuel level sensor 8, centrifugal blower structure 1, pressurizing valve 18, temperature transducer 5, magnetic consider last detector 7, oil level glass 9, gravity fuel filler 11, pressure filling mouth 10, oil sump 6 to be worth doing.It is characterized in that flow is little, pressure is high and can flight envelope work entirely, be mainly used in the lubrication and cooling of inner gear of the gear box axle, bearing, clutch and other spare part.Also be applicable to the lubrication and cooling of other small-power, high rotating speed, big speed ratio gear-box, there is larger actual application value.
Description
Technical field
The present invention relates to a kind of small flow lubrication system of full flight envelope work, for the lubrication and cooling of aircraft second power system combination power device inner gear of the gear box, bearing and other parts.
Background technique
The aircraft second power system kind that present generation aircraft uses is varied, due to the needs of function on some aircrafts, two kind of two power system has been installed, as most of third-generation aircraft, auxiliary power unit was both installed, emergency power unit had been installed again, along with the needs of airplane syntheticization design, need the power plant originally performing difference in functionality to carry out comprehensive integration, form combination power plant.Combination power device uses the gear-box of comprehensive original two power plant of a shared gear-box, the gear-box that said apparatus contains all has the features such as little, the high rotating speed of power, high transmission ratio, and lubrication system is one of the reliability and life-span key factor of gear-box.
The present invention, according to the demand of aircraft second power system combination power device gear-box, designs a kind of small flow lubrication system of whole envelope work, realizes the lubrication and cooling of gear-box.
Summary of the invention
Object of the present invention: the small flow lubrication system providing a kind of full flight envelope work, for the lubrication and cooling of aircraft second power system combination power device gear-box.
Technological scheme of the present invention: a kind of small flow lubrication system of full flight envelope work, it is characterized in that, comprise except solenoid 17, oil feed pump 4, safety valve 2, oil filter 3, radiator 15, bypass valve 16, pressure transducer 14, lubricating oil nozzle 12, lubricating oil pressure modulating valve 13, fuel level sensor 8, centrifugal blower structure 1, pressurizing valve 18, temperature transducer 5, magnetic considers last detector 7 to be worth doing, oil level glass 9, gravity fuel filler 10, pressure filling mouth 9, oil sump 6, oil feed pump 4 extracts lubricating oil by oil sump 6, through oil filter 3, radiator 15, after pressure transducer 14, lubricating oil pressure is regulated by lubricating oil pressure modulating valve 11, the pressure of lubricating oil nozzle 12 is made to meet lubrication and cooling requirement,
Except solenoid 17 is for opening when starting, to reduce oil feed pump 4 dynamic loads; Fuel level sensor 7, oil level glass 8 are for monitoring oil sump 6 oil level; Temperature transducer 5, pressure transducer 14 are used for monitoring the working state of lubrication system; Magnetic considers last detector 7 to be worth doing for contact component abrasion condition in measuring gear case;
When external pressure is lower than 31kPa, pressurizing valve 18 is closed, and to gear-box supercharging, improves oil feed pump 4 inlet pressure, makes lubrication system reliable operation within the scope of whole envelope.
Combination power device gear-box belongs to high rotating speed, big speed ratio, small-power transmission, and gear lubrication and cooling adopt splash mode, adopt out side spray lubrication, are convenient to the cooling of gear.
Described lubrication system, oil flow is not less than 26L/min, and lubricating oil pressure is 410 ~ 480kPa, and oil temperature is not more than 135 DEG C.The slippery oil pollution degree of lubrication and cooling is provided to be not less than 10 grades.
Beneficial effect of the present invention: lubrication system of the present invention is the small flow lubrication system of whole envelope work, within the scope of whole envelope, can be inner gear of the gear box, bearing, clutch provide lubrication and cooling, applicability is wide, has larger application prospect.
The present invention is applied to aircraft second power system combination power device gear-box, also can be used for other transmission base part, has certain versatility and good use value.
Accompanying drawing explanation
Fig. 1 is the composition schematic diagram of a kind of whole envelope of the present invention, small flow lubrication system;
Wherein: 1-centrifugal blower structure, 2-safety valve, 3-oil filter, 4-oil feed pump, 5-temperature transducer, 6-oil sump, 7-magnetic consider last detector, 8-fuel level sensor, 9-viewing window, 10-pressure filling mouth, 11-gravity fuel filler, 12-lubricating oil nozzle, 13-lubricating oil pressure modulating valve, 14-pressure transducer, 15-radiator, 16-bypass valve, 17-to be worth doing except solenoid, 18-pressurizing valve.
Embodiment
Below by embodiment, the present invention is described in further detail.
This lubrication system adopts wet type lubrication, is oil sump, takes spray lubrication, mode that oil mist lubrication combines provides lubrication and cooling to gear, bearing, clutch etc. on the downside of gear-box.
When product is started working, except solenoid 17 is opened, reduce oil feed pump 4 cold-starting load, after oil feed pump 4 stable operation, except solenoid 17 is closed, lubricating oil is extracted out by oil feed pump 4 from oil sump 6, lubricating oil enters oil filter 3, and the rear lubricating oil of filtration enters radiator 15 and cools, and radiator bypass is provided with a bypass flap 14, when blocking occurs radiator, lubricant oil is allowed to walk around radiator; Cooled lubricating oil flows through lubricating oil pressure sensor 14; After this, lubricating oil enters gear, bearing and clutch in gear-box and other needs the position of lubrication and cooling by lubricating oil nozzle 12.On lubricating oil stream, be provided with a lubricating oil pressure modulating valve 13, the lubricating oil pressure obtaining each regions of lubrication is kept within the specific limits; Finally, the lubricating oil that lubrication is crossed gets back to oil sump 6 bottom gear-box by gravity circuit.
For the chamber of balance gear roller box is pressed, in lubrication system, be provided with centrifugal blower structure 1, by air separation out, by outlet pipe, air discharged outside gear-box by axle center, gas exhaust piping is arranged inverted flight valve.
When external pressure is lower than 31kPa, pressurizing valve 18 is closed, and to gear-box supercharging, improves oil feed pump 4 inlet pressure, makes lubrication system reliable operation within the scope of whole envelope.When gear-box inside and outside differential pressure is greater than 41kPa, pressurizing valve 18 is opened, and discharges additional air.
When the lubricating oil pressure of lubrication system, oil temperature transfinite, pressure transducer 14, temperature transducer 5 send feedback trouble signal, for lubrication system Gernral Check-up.
Oil sump 6 oil level is prescribed a time limit lower than under oil level, and fuel level sensor 8 sends feedback signal, need add lubricating oil; Also oil level confirmation is carried out by oil level glass 9.
Claims (1)
1. the small flow lubrication system of a full flight envelope job, it is characterized in that, comprise except solenoid (17), oil feed pump (4), safety valve (2), oil filter (3), radiator (15), bypass valve (16), pressure transducer (14), lubricating oil nozzle (12), lubricating oil pressure modulating valve (13), fuel level sensor (8), centrifugal blower structure (1), pressurizing valve (18), temperature transducer (5), magnetic considers last detector (7) to be worth doing, oil level glass (9), gravity fuel filler (10), pressure filling mouth (9), oil sump (6), oil feed pump (4) extracts lubricating oil by oil sump (6), after oil filter (3), radiator (15), pressure transducer (14), regulate lubricating oil pressure by lubricating oil pressure modulating valve (11), make the pressure of lubricating oil nozzle (12) meet lubrication and cooling requirement,
Except solenoid (17) is for opening when starting, play dynamic load to reduce oil feed pump (4); Fuel level sensor (7), oil level glass (8) are for monitoring oil sump (6) oil level; Temperature transducer (5), pressure transducer (14) are used for monitoring the working state of lubrication system; Magnetic considers last detector (7) to be worth doing for contact component abrasion condition in measuring gear case;
When external pressure is lower than 31kPa, pressurizing valve (18) is closed, and to gear-box supercharging, improves oil feed pump (4) inlet pressure, makes lubrication system reliable operation within the scope of whole envelope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420753525.8U CN204327936U (en) | 2014-12-03 | 2014-12-03 | A kind of small flow lubrication system of full flight envelope work |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420753525.8U CN204327936U (en) | 2014-12-03 | 2014-12-03 | A kind of small flow lubrication system of full flight envelope work |
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| CN204327936U true CN204327936U (en) | 2015-05-13 |
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| CN201420753525.8U Active CN204327936U (en) | 2014-12-03 | 2014-12-03 | A kind of small flow lubrication system of full flight envelope work |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109323117A (en) * | 2018-12-16 | 2019-02-12 | 中国航发沈阳发动机研究所 | A kind of lubricating system |
| CN109441589A (en) * | 2018-12-14 | 2019-03-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of tandem oil cooler unit |
| CN109573074A (en) * | 2018-11-30 | 2019-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of oil cooling system for aircraft auxiliary power plant |
| CN109667920A (en) * | 2018-11-30 | 2019-04-23 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of oil filling and oil level monitor gear-box |
-
2014
- 2014-12-03 CN CN201420753525.8U patent/CN204327936U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573074A (en) * | 2018-11-30 | 2019-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of oil cooling system for aircraft auxiliary power plant |
| CN109667920A (en) * | 2018-11-30 | 2019-04-23 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of oil filling and oil level monitor gear-box |
| CN109441589A (en) * | 2018-12-14 | 2019-03-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of tandem oil cooler unit |
| CN109323117A (en) * | 2018-12-16 | 2019-02-12 | 中国航发沈阳发动机研究所 | A kind of lubricating system |
| CN109323117B (en) * | 2018-12-16 | 2020-09-18 | 中国航发沈阳发动机研究所 | Lubricating system |
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