CN104235012A - Multi-joint variable-flow aerial gear oil pump - Google Patents
Multi-joint variable-flow aerial gear oil pump Download PDFInfo
- Publication number
- CN104235012A CN104235012A CN201410436533.4A CN201410436533A CN104235012A CN 104235012 A CN104235012 A CN 104235012A CN 201410436533 A CN201410436533 A CN 201410436533A CN 104235012 A CN104235012 A CN 104235012A
- Authority
- CN
- China
- Prior art keywords
- gear
- pump
- oil
- gear pump
- level
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Details And Applications Of Rotary Liquid Pumps (AREA)
- Rotary Pumps (AREA)
Abstract
The invention discloses a multi-joint variable flow aerial gear oil pump which comprises a gear pump shell, a driving shaft, a driven shaft, two pairs of identical gears, a one-way valve, a piston and a cylinder, wherein the driving shaft and the driven shaft are positioned in the pump body and are arranged in parallel; a gear on the same side connected with the driving shaft is a driving gear; a gear on the other side connected with the driven shaft is a driven gear; a meshed primary gear pair and a gear cavity form a primary gear pump; a meshed secondary gear pair and a gear cavity form a secondary gear pump; the primary gear pump is communicated with an oil inlet of the secondary gear pump; the one-way valve is arranged between oil outlets and is used for controlling oil to flow from the outlet of the secondary gear pump to the outlet of the primary gear pump, and the one-way valve is controlled by the pressures at the outlets of the primary gear pump and the secondary gear pump; oil flows back into the inlet from the outlet of the secondary gear pump by virtue of an oil return port; the piston is used for opening and closing the reflux inlet; opening and closing of the reflux inlet by the piston is controlled by the pressures at the outlet of the secondary gear pump and the cylinder. The gear oil pump is simple in structure, light in weight and high in power utilization rate.
Description
Technical field
The present invention relates to aeropropulsion system technical field, specifically, relate to a kind of multi-joint variable-flow Aeronautical Gears oil pump.
Background technique
Aviation Fuel gear pump is the important accessory of aeroengine propulsion system, is widely used as fuel pump at aerospace field, usually used as master, the afterburning fuel pump of aeropropulsion system.At present, military aircraft requires to have higher flexibility and mobility, and aeropropulsion system must can provide more powerful, more lasting power, and this proposes new higher requirement to propulsion system.In existing aeropropulsion system, when engine speed is constant, for a change characteristic of fuel delivery of oil pump, adopts change motor to implement to the mode of gear pump shaft velocity ratio.
Change oil pump feed characteristic and mainly adopt the mode changing velocity ratio, use dissimilar speed changer, as mechanical transmission, hydraulic transformer, electric gear shift(ing), air pressure speed changer etc.; Plant speed changer for first three, must have special regulating system, cause the increase of the volume of motor, weight, power reduction, this is infeasible to aeropropulsion system; Air pressure speed changer changes velocity ratio by self-regulation character can be utilized, but also there is the problem that power loss is comparatively large and fuel oil utilization is lower.So, under needing design one constant based on change velocity ratio, meet the Aviation Fuel gear pump of different flight state by changing fuel flow.
Disclose a kind of gear pump with variable capacity in patent of invention CN 1069552, this gear pump with variable capacity does not relate to aero fuel pump field, and just gives the gear pump structure of a single-stage, does not consider the fuel utilization ratio of multistage pump and the feature of pressure pulsation.
For solving prior art Problems existing, the present invention proposes the variable multi-joint Aeronautical Gears oil pump of a kind of rotating speed constant situation down-off.A kind ofly determine rotating speed, become discharge capacity, the Aviation Fuel gear pump of the fuel feeding demand that can meet under different H, Ma.
Summary of the invention
In order to avoid the deficiency that prior art exists, the problem overcome, the present invention proposes a kind of multi-joint variable-flow Aeronautical Gears oil pump.
The technical solution adopted for the present invention to solve the technical problems is: comprise gear pump case, driving shaft, driven shaft, one-level gear pair, secondary gear wheel set, one-way valve, piston, oil cylinder, one-level driving gear, secondary driving gear, one-level driven gear, secondary driven gear, driving shaft and driven shaft are positioned at gear pump case and install according to axis parallel, it is driving gear with side gear that driving shaft connects two gear cavities interior, and the gear that driven shaft connects opposite side in two gear cavities is driven gear, one-level gear pair and the gear cavity of engagement form one-level gear pump, secondary gear wheel set and the gear cavity of engagement form secondary gear wheel pump, one-level gear pump is connected with secondary gear wheel pump filler opening, one-way valve pumps between hydraulic fluid port at one-level gear pump and secondary gear, one-way valve controls oil and flows to one-level gear pump outlet from secondary gear pump discharge, and one-way valve is by one-level gear pump, secondary gear pump discharge pressure controls, oil is flowed back to import from secondary gear pump discharge by return opening, piston is used for opening and closing refluxing opening, piston serves as the effect of stop valve, piston switch refluxing opening is by secondary gear pump discharge, oil cylinder working-pressure controls, gear pump case is provided with filler opening and oil outlet.
Described one-way valve is by valve body, and helical spring, support, valve seat form, and valve body is spheroidal, stent support helical spring, and coil spring urges valve body moves, and valve body opens and closes afterbody discharge passage, and valve seat is positioned at discharge chamber side.
Beneficial effect
The multi-joint variable-flow Aeronautical Gears oil pump that the present invention proposes is a kind of gear oil pump variable for rotating speed constant situation down-off.This oil pump element is few, with in prior art with compared with the oil supplying device of speed changer, all less on volume and weight, transmission efficiency and power utilization are comparatively large, bring negative effect can not to the thrust weight ratio important performance of aeroengine.This oil pump import and export and mounting type substantially identical with single-stage pump, be convenient to installation.
Multi-joint variable-flow Aeronautical Gears oil pump is compared with single gear pump, operating range is larger, under small flow state, the power of nest oil pump is less relative to single-stage pump, if front and back stages pump delivery is 1:1, under small flow state, the power of multi-joint variable-flow gear oil pump is only equivalent to the half of single-stage pump.
Multi-joint variable-flow Aeronautical Gears oil pump structure is simple, size is little, lightweight, power utilization is high, is convenient to installation and maintenance, can meet the demand and supply of aeroengine to fuel oil.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of multi-joint variable-flow Aeronautical Gears oil pump of the present invention is described in further detail.
Fig. 1 is the present invention's multi-joint variable-flow Aeronautical Gears oil pump principle assumption diagram.
Fig. 2 is the side view cutaway drawing of the present invention's multi-joint variable-flow Aeronautical Gears oil pump.
Fig. 3 is the vertical view cutaway drawing of the present invention's multi-joint variable-flow Aeronautical Gears oil pump.
Fig. 4 is the elevational cross-sectional view of the present invention's multi-joint variable-flow Aeronautical Gears oil pump.
Fig. 5 is " large discharge " working state schematic representation of the present invention's multi-joint variable-flow Aeronautical Gears oil pump.
Fig. 6 is " small flow " working state schematic representation of the present invention's multi-joint variable-flow Aeronautical Gears oil pump.
In figure:
1. gear pump case 2. driving shaft 3. driven shaft 4. one-level gear cavity 5. secondary gear chamber 6. one-level gear pair 7. secondary gear wheel set 8. one-way valve 9. piston 10. oil cylinder 11. filler opening 12. oil outlet 13. valve body 14. helical spring 15. support 16. piston cylinder 17. discharge chamber 18. valve seat 19. discharge of pipes chamber 20. bypass channel 21. oil returning tube 22. front cover 23. inipple 24. rear end cover 25. front side plate 26. side plate 27. one-level driving gear 28. secondary driving gear 29. one-level driven gear 30. secondary driven gear 31. separate cavities 32. front end discharge passage 33. afterbody discharge passage
Embodiment
The present embodiment is a kind of multi-joint variable-flow Aeronautical Gears oil pump.
Consult Fig. 1 ~ Fig. 6, the present embodiment multi-joint variable-flow Aeronautical Gears oil pump is made up of gear pump case 1, driving shaft 2, driven shaft 3, one-level gear cavity 4, secondary gear chamber 5, one-level gear pair 6, secondary gear wheel set 7, one-way valve 8, piston 9 and oil cylinder 10, front cover 22, rear end cover 24, driving shaft 2 and driven shaft 3 are fixed in gear pump case 1 and install according to axis parallel, and it is driving gear with side gear that driving shaft 2 connects two gear cavities interior, and the gear that driven shaft 3 connects opposite side in two gear cavities is driven gear, one-level gear pair 6 and the gear cavity of engagement form one-level gear pump, secondary gear wheel set 7 and the gear cavity of engagement form secondary gear wheel pump, one-level gear pump is connected with secondary gear wheel pump filler opening, one-way valve 8 is arranged on one-level gear pump and secondary gear pumps between hydraulic fluid port, one-way valve 8 controls oil and flows to one-level gear pump outlet from secondary gear pump discharge, and one-way valve 8 is by one-level gear pump, secondary gear pump discharge pressure controls, oil is flowed back to import from secondary gear pump discharge by return opening, piston 9 is used for opening and closing refluxing opening, piston 9 serves as the effect of stop valve, piston 9 switch refluxing opening is by secondary gear pump discharge, oil cylinder 10 Stress control, gear pump case 1 is provided with filler opening 11 and oil outlet 12.
One-way valve 8 is by valve body 13, helical spring 14, support 15, valve seat 18 form, valve body 13 is spheroidal, support 15 support helix spring 14, helical spring 14 promotes valve body 13 and moves, and valve body 13 opens and closes afterbody discharge passage, when the pressure in afterbody discharge passage is greater than setting value, the thrust that valve body 13 heads on helical spring 14 moves along a straight line, and afterbody passage is opened.When the pressure in afterbody passage is less than setting value, valve body 13 heads on the thrust of helical spring 14, makes afterbody pathway closure.And the pressure of front end discharge passage is different from afterbody discharge passage.Valve seat 18 is positioned at discharge chamber 17 side.Because make valve body 13 and valve seat 18 separately effectively, the Driving force of helical spring 14 can be arranged on a less valve.Piston cylinder 16 is arranged at the bottom of rear end cover 24, has slidably cylindrical piston 9, and serve as the effect of stop valve in piston cylinder 16.The space of piston cylinder 16 is communicated with the pipeline of oil cylinder by inipple 25.Meanwhile, discharge tube has a masterpiece for the space of piston cylinder 16 li.The transversal sectional area of piston cylinder 16 is greater than the upstream passageway in bypass channel 20.
The outer dia of piston 9 is applicable to the inside diameter of piston cylinder 16.Piston 9 opens and closes bypass channel 20 at the internal surface of piston cylinder 16 by sliding.Piston 9 front end is as the first cross section accepting bypass channel 20 pressure, and the other end of piston 9, as the second cross section of receiving piston cylinder 16 internal pressure, namely accepts the pressure of discharge passage 19.Due to the upstream passageway being greater than bypass channel 20 that the transversal sectional area of piston cylinder 16 is arranged.When piston 9 closes bypass channel 20, the area of the second pressure receiving surface of piston 9 is greater than the first pressure receiving surface of acceptance first pressure.When bypass channel 20 is closed by piston 9, the pressure receiving surface of the first pressure receiving surface is as the pressure accepting to discharge from secondary gear pump part P2, and area is less than the area of the second pressure receiving surface.
First pressure receiving surface of piston 9 and the difference of the second pressure receiving surface pressure cause the movement of piston 9, and the pressure that namely bypass channel 20 pairs of pistons 9 cause moves with the different piston 9 that causes of pressure that piston cylinder 16 acts on piston 9 another side.When piston 9 opens bypass channel 20, the area of the second pressure receiving surface is greater than the area of the first pressure receiving surface accepting bypass channel 20 pressure.If when bypass duct 20 is identical with piston cylinder 16 pressure, the power acting on the second pressure receiving surface is greater than the power acting on the first pressure receiving surface, and bypass channel 20 is closed by piston 9.
Gear pump case 1 two ends are connected with front cover 22 and rear end cover 24 respectively, and gear pump case 1, front cover 22, rear end cover 24 form the main body of gear pump jointly.One-level gear cavity 4 is close with front cover 22, and secondary gear chamber 5 is close with rear end cover 24.Front side plate 25 is between one-level gear cavity 4 and front cover 22 end face, and side plate 26 is between secondary gear chamber 5 and rear end cover 24 end face.
There is one-level gear pair 6 in one-level gear cavity 4, be positioned at gear pump case 1 Inner Front End, in secondary gear chamber 5, have secondary gear wheel set 7 to be positioned at gear pump case 1 rear end; One-level driving gear 27, the secondary driving gear 28 of one-level gear pair 6, secondary gear wheel set 7 are coaxially connected with driving shaft 2 respectively by flat key; One-level driven gear 29, the secondary driven gear 30 of one-level gear pair 6, secondary gear wheel set 7 are coaxially connected with driven shaft 3 respectively by flat key; Driving shaft 2 enters rear end cover 24 through front cover 22, front side plate 25, separate cavities 31, and by bearings in rear end cover, one end of driving shaft 2 is extended outside front cover 22, and is connected with the aeroengine main shaft as driving source; Driven shaft 3 only extends and front cover 22, rear end cover 24, and by bearings front cover 22, rear end cover 24, driven shaft 3 does not stretch out front cover 22.
Have two spaces formed by one-level gear cavity 4 internal surface and one-level driving gear 27, one-level driving gear in one-level gear cavity 4, i.e. oil-feed space and fuel-displaced space, secondary gear chamber 5 comprises two spaces equally.Front end discharge passage 32 is communicated with afterbody discharge passage 33 and defines a discharge passage in the pump housing 1 inside, and discharge passage has been communicated with the fuel-displaced space of main pump P1 and the fuel-displaced space of auxiliary pump P2.
According to working principle mentioned above, according to the position of one-way valve 8 and piston 9, this oil pump has large discharge and small flow two kinds of working staties, below sketches the working procedure under two states
The large discharge working state of the present embodiment: when piston 9 cuts off being communicated with between bypass channel 20 with oil returning tube 21, the fluid that auxiliary pump P2 discharges makes auxiliaryly to pump oily space pressure and increase, when pressure is higher than the pressure preset, the valve body 13 of one-way valve 8 is by upwards jack-up thus open discharge cavity: discharge chamber 17 is communicated with oil outlet 12, the fluid mixing that the fluid of therefore discharging in gear pump P2 is discharged with gear pump P1, finally discharges together from front end discharge passage 19.Two stage pump is fuel feeding all outwards, and gear pump delivery is 100%.
The small flow working state of the present embodiment: when piston 9 opens being communicated with between bypass channel 20 with oil returning tube 21, the fluid that auxiliary pump P2 discharges flows back to filler opening 11 through bypass duct 20, oil returning tube 21, pressure in discharge chamber 17 reduces, when pressure is lower than the pressure preset, the valve body 13 of one-way valve 8 moves down thus closes discharge chamber 17, the outside fuel feeding of main pump P1, the fluid of discharging in auxiliary pump P2 is just from bypass duct 20, oil returning tube 21 oil return to filler opening 11.
By single-stage external gear pump and multi-joint variable-flow Aeronautical Gears oil pump comparing calculation as follows:
1. suppose that certain single-stage pump is identical with multi-gear pump operating conditions, rotating speed is n, and inlet pressure is p
1, oil outlet pressure is p
2, mechanical efficiency is η
m, single-stage pump discharge capacity q
1with multistage pump total displacement q
2equal, i.e. q
1=q
2=2q.In addition, if multi-gear pump is two-stage parallel connection, the ratio of first order pump, second level pump delivery is 1:1, then, under large discharge state, gear pump delivery is q
2 is large=2q; Under small flow state, gear pump delivery is q
2 is little=q.
2. according to input power, theoretical delivery formula in " HBZ 134-1988 engine fuel control gear type fuel pump design guideline ":
the input power that can be calculated this single-stage pump and multi-gear pump is as shown in table 1, and in table, pump 1 is single-stage pump, and pump 2 is multistage pump.
Table 1 single-stage pump and multistage pump input power result of calculation
3., when rotating speed is constant: when fuel feeding demand is large, under multi-gear pump is operated in large discharge state, single-stage pump is identical with the theoretical input power of multi-gear pump; When fuel feeding demand hour, under multi-gear pump is operated in small flow state, the theoretical input power of multi-gear pump is only equivalent to the half of single-stage pump.Power loss significantly reduces, and power utilization increases.
Claims (2)
1. a multi-joint variable-flow Aeronautical Gears oil pump, it is characterized in that: comprise gear pump case, driving shaft, driven shaft, one-level gear pair, secondary gear wheel set, one-way valve, piston, oil cylinder, one-level driving gear, secondary driving gear, one-level driven gear, secondary driven gear, driving shaft and driven shaft are positioned at gear pump case and install according to axis parallel, it is driving gear with side gear that driving shaft connects two gear cavities interior, and the gear that driven shaft connects opposite side in two gear cavities is driven gear, one-level gear pair and the gear cavity of engagement form one-level gear pump, secondary gear wheel set and the gear cavity of engagement form secondary gear wheel pump, one-level gear pump is connected with secondary gear wheel pump filler opening, one-way valve pumps between hydraulic fluid port at one-level gear pump and secondary gear, one-way valve controls oil and flows to one-level gear pump outlet from secondary gear pump discharge, and one-way valve is by one-level gear pump, secondary gear pump discharge pressure controls, oil is flowed back to import from secondary gear pump discharge by return opening, piston is used for opening and closing refluxing opening, piston serves as the effect of stop valve, piston switch refluxing opening is by secondary gear pump discharge, oil cylinder working-pressure controls, gear pump case is provided with filler opening and oil outlet.
2. multi-joint variable-flow Aeronautical Gears oil pump according to claim 1, it is characterized in that: described one-way valve is by valve body, helical spring, support, valve seat form, valve body is spheroidal, stent support helical spring, coil spring urges valve body moves, and valve body opens and closes afterbody discharge passage, and valve seat is positioned at discharge chamber side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410436533.4A CN104235012A (en) | 2014-08-29 | 2014-08-29 | Multi-joint variable-flow aerial gear oil pump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410436533.4A CN104235012A (en) | 2014-08-29 | 2014-08-29 | Multi-joint variable-flow aerial gear oil pump |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104235012A true CN104235012A (en) | 2014-12-24 |
Family
ID=52223744
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410436533.4A Pending CN104235012A (en) | 2014-08-29 | 2014-08-29 | Multi-joint variable-flow aerial gear oil pump |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104235012A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107975474A (en) * | 2018-01-05 | 2018-05-01 | 湖南机油泵股份有限公司 | A kind of three-level lubricating oil pump |
| CN109578143A (en) * | 2018-12-10 | 2019-04-05 | 中国航发南方工业有限公司 | Gear box oil rig |
| CN112412779A (en) * | 2020-11-27 | 2021-02-26 | 上海尚实能源科技有限公司 | Compact aviation multistage gear pump |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1069552A (en) * | 1992-05-06 | 1993-03-03 | 朱寿和 | Gear pump with variable capacity |
| JP2002070757A (en) * | 2000-08-31 | 2002-03-08 | Tokico Ltd | Variable displacement gear pump |
| US20090041594A1 (en) * | 2007-08-09 | 2009-02-12 | Kabushiki Kaisha Toyota Jidoshokki | Variable displacement type gear pump |
-
2014
- 2014-08-29 CN CN201410436533.4A patent/CN104235012A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1069552A (en) * | 1992-05-06 | 1993-03-03 | 朱寿和 | Gear pump with variable capacity |
| JP2002070757A (en) * | 2000-08-31 | 2002-03-08 | Tokico Ltd | Variable displacement gear pump |
| US20090041594A1 (en) * | 2007-08-09 | 2009-02-12 | Kabushiki Kaisha Toyota Jidoshokki | Variable displacement type gear pump |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107975474A (en) * | 2018-01-05 | 2018-05-01 | 湖南机油泵股份有限公司 | A kind of three-level lubricating oil pump |
| CN109578143A (en) * | 2018-12-10 | 2019-04-05 | 中国航发南方工业有限公司 | Gear box oil rig |
| CN109578143B (en) * | 2018-12-10 | 2020-02-04 | 中国航发南方工业有限公司 | Transmission box oil pumping device |
| CN112412779A (en) * | 2020-11-27 | 2021-02-26 | 上海尚实能源科技有限公司 | Compact aviation multistage gear pump |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2521848B1 (en) | Dual-supply fluid distribution system and method of supplying fluid | |
| CN102575586B (en) | Circuit for supplying fuel to an aircraft engine and aircraft engine comprising fuel supplying circuit | |
| EP3004647B1 (en) | Variable displacement lubricant pump | |
| EP2891781B1 (en) | Engine fuel control system | |
| CN102575587A (en) | Circuit for supplying fuel to an aircraft engine | |
| CN101379296A (en) | Variable displacement variable pressure vane pump system | |
| CN104153419B (en) | Power control valve and loading machine are determined variable delivery hydraulic system | |
| CN103711897A (en) | Hydraulic pressure supply system of automatic transmission | |
| US9546728B2 (en) | Balanced binary pump for CVT transmission | |
| CN104235012A (en) | Multi-joint variable-flow aerial gear oil pump | |
| CN102678338A (en) | Oil supply pressure regulating system for aircraft engine and regulating method thereof | |
| CN106051441B (en) | A kind of output displacement can be changed duplex impeller pump and its control system | |
| CN107074374B (en) | Pump authority switching device for fluid distribution system | |
| CN111173916B (en) | Cooling priority valve for a hydraulic system of a motor vehicle transmission | |
| US3067689A (en) | Variable capacity fluid supply | |
| US6641372B2 (en) | Dual discharge hydraulic pump and system therefor | |
| CN108412831A (en) | Shunt variable voltage control commutation pile-up valve | |
| US20130098468A1 (en) | Hydraulic distribution system employing a dual pump | |
| US10077834B2 (en) | Hydraulic control system for a transmission | |
| CN208203689U (en) | Shunt variable voltage control commutation pile-up valve | |
| CN109139176B (en) | Pressure control system based on fixed displacement engine oil pump | |
| EP2426393A1 (en) | Pressure-reducing gas storage devic, gas injection system and automobile | |
| CN101865143B (en) | Device for automatically adjusting power of turbine pump | |
| US9828908B2 (en) | Device for internal cooling and pressurization of rotary engine | |
| CN103174816B (en) | A kind of pressure differential control type stepless speed variator flow active control system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20141224 |