CN216588892U - Aircraft engine oil pump case - Google Patents
Aircraft engine oil pump case Download PDFInfo
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- CN216588892U CN216588892U CN202220371017.8U CN202220371017U CN216588892U CN 216588892 U CN216588892 U CN 216588892U CN 202220371017 U CN202220371017 U CN 202220371017U CN 216588892 U CN216588892 U CN 216588892U
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Abstract
The utility model relates to an aviation spare part technical field, concretely relates to aeroengine oil pump case, including main part and reset spring, assemble in the valve barrel, the main part includes sealing part, pressure regulating part and control part, the sealing part external diameter is greater than the external diameter of pressure regulating part and control part, and the both sides of sealing part form first cavity and second cavity, and the valve barrel corresponds first cavity and second cavity respectively and is provided with low pressure oil outlet and high pressure oil inlet; the periphery of the pressure regulating part is provided with a plugging part, the control part is used for communicating or closing an oil pump oil way, an oil way channel is arranged in the main body, an oil inlet hole is formed in the front end of the pressure regulating part, a throttling piece is arranged at an opening at the rear end of the oil way channel, the oil inlet hole is used for being always communicated with a high-pressure oil inlet on the valve sleeve, and the plugging part is used for disconnecting the second cavity from the high-pressure oil inlet when the main body enters a closed state; the utility model has the advantages of close more stable.
Description
Technical Field
The utility model relates to an aviation spare part technical field, concretely relates to aeroengine oil pump case.
Background
Fuel pumps are important components of aircraft engine fuel control systems, and their operating characteristics affect the overall engine operating performance. In a fuel pipeline taking a fuel pump as a core, the fuel pump valve controls the on-off and flow of each pipeline, and a valve core of the pump valve is a core component of the fuel pipeline.
The patent CN110608100A discloses a two oil circuit aeroengine fuel oil draining device, it adopts single valve core project organization, through controlling throttling element both ends chamber pressure differential, drive the valve core action, when guaranteeing that the engine parks, the draining valve is opened fast, two fuel oil way are let out simultaneously, system architecture is simple, easy engineering realizes, drive the valve core action through controlling throttling element both ends chamber pressure differential, the dynamic characteristic is good, the valve response is fast, when can guaranteeing that the engine parks, the draining valve is opened fast, need not to wait for the pressure reduction of main, vice fuel oil circuit.
However, in the practical process of actual engineering, the throttling element positioned at the central part of the valve core has high precision requirement and large processing difficulty.
On the other hand, the fuel pressure of the aircraft engine changes along with the engine state, and due to the existence of the throttling element, the pressure change response speed of the two end cavity pressures has difference, so that the closed state of the valve core is unstable due to the fuel pressure fluctuation entering the high pressure cavity in the valve core and the high pressure cavity outside the valve core when the valve core is in the closed state.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model aims at overcoming the defect among the prior art, provide an aeroengine oil pump case, have more stable advantage.
The utility model discloses an aeroengine oil pump case, including main part and reset spring, both are with the coaxial assembly in the valve barrel of front and back order, the main part includes along axial integrated into one piece's sealing, pressure regulating part and control part, the sealing external diameter is greater than the external diameter of pressure regulating part and control part, is used for sealing cooperation with the valve barrel, forms the first cavity by the back and leans on preceding second cavity in the both sides of sealing, and the valve barrel corresponds first cavity and second cavity respectively and is provided with low pressure oil-out and high pressure oil inlet; the periphery of the pressure regulating portion is provided with a plugging portion with the outer diameter smaller than that of the sealing portion, the control portion is used for communicating or closing an oil pump oil way, the main body is provided with a rear end opening and an oil way channel extending to the sealing portion and the pressure regulating portion, the front end of the pressure regulating portion is provided with an oil inlet hole communicated with the oil way channel, the rear end opening of the oil way channel is provided with a throttling piece, the oil inlet hole is used for being communicated with a high-pressure oil inlet on the valve sleeve all the time, and the plugging portion is used for disconnecting the second cavity and the high-pressure oil inlet when the main body enters a closed state.
Furthermore, the pressure regulating part forms a necking with the diameter smaller than the inner diameter of the valve sleeve at the position corresponding to the oil inlet hole.
Further, the plugging part is of a conical structure with a small front part and a large rear part.
Further, the throttling element is a sheet structure fixed at the rear end of the sealing part, a throttling hole is formed in the center of the sheet structure, and the diameter of the throttling hole is smaller than the inner diameter of the oil passage.
Further, sealing rings are arranged on the sealing part, the control part and the plugging part.
The utility model has the advantages that: the utility model discloses an aircraft engine oil pump valve core, which reduces the processing difficulty of the main body by arranging the throttle at the rear end of the main body; the main body is provided with the plugging portion, when the main body is positioned at the foremost end and the control portion closes the oil pump oil way, the plugging portion simultaneously seals the second cavity of the main body close to the front position, so that in a closed state, the main body is mainly subjected to the elastic force of the reset spring and the oil pressure in the first cavity, and the closed state is more stable.
Drawings
The invention will be further described with reference to the following figures and examples:
FIG. 1 is a schematic view of the assembly of the present invention;
FIG. 2 is a schematic structural view of the present invention;
fig. 3 is a schematic structural diagram of another embodiment of the present invention.
Description of reference numerals: the valve comprises a main body 1, a sealing part 11, a pressure regulating part 12, a blocking part 121, a constriction 122, a control part 13, a first cavity 14, a second cavity 15, a low-pressure oil outlet 141, a high-pressure oil inlet 151, an oil channel 16, an oil inlet hole 161, a throttling element 17, a throttling hole 171, a return spring 18 and a valve sleeve 2.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely below, and it should be apparent that the described embodiments are only some embodiments of the present invention, but not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
As shown in fig. 1-2, the valve core of the aircraft engine oil pump in the present embodiment comprises a main body 1 and a return spring 18, which are coaxially assembled in a valve sleeve 2 in a front-rear sequence, the valve sleeve 2 used in the present embodiment is substantially identical to the valve sleeve 2 in the background patent, the front end of the main body 1 is provided with a plurality of inlets or outlets, the main body comprises a sealing part 11, a pressure regulating part 12 and a control part 13 which are integrally formed along the axial direction, the outer diameter of the sealing part 11 is larger than the outer diameters of the pressure regulating part 12 and the control part 13, for sealing engagement with the valve housing 2, preferably a sealing ring is provided on the sealing portion 11 for sliding sealing, a first cavity 14 at the back and a second cavity 15 at the front are formed at two sides of the sealing part 11, the valve housing 2 is provided with a low-pressure oil outlet 141 and a high-pressure oil inlet 151 corresponding to the first cavity 14 and the second cavity 15, respectively, and the position of the main body 1 is controlled by controlling the opening and closing of the low-pressure oil outlet 141; when the control part 13 is close to the front, the oil pump oil path inlet or outlet at the front end of the valve housing 2 is sealed, when the control part is close to the rear, the oil pump oil path inlet or outlet can be conducted, the control part 13 is provided with a sealing ring to prevent oil leakage, the main body 1 is provided with an oil path channel 16 with a rear end opening and extending to the sealing part 11 and the pressure regulating part 12, the periphery of the pressure regulating part 12 is provided with a blocking part 121 with an outer diameter smaller than that of the sealing part 11, the front end of the pressure regulating part 12 at the blocking part 121 is provided with an oil inlet hole 161 communicated with the oil path channel 16, the rear end opening of the oil path channel 16 is provided with a flow regulating part 17, the oil inlet hole 161 is used for being always communicated with a high-pressure oil inlet 151 on the valve housing 2, and the blocking part 121 is used for disconnecting the second cavity 15 and the high-pressure oil inlet 151 when the main body 1 enters a closed state.
As shown in fig. 1, when the main body 1 is at the rear position and the front inlet or outlet is in a conducting state, the low-pressure oil outlet 141 is closed, the pressure in the first cavity 14, the second cavity 15 and the oil passage 16 in the main body 1 is the same, but the stressed areas are different, the low-pressure oil outlet moves forward under the action of the pressure difference between the two sides and the action of the return spring 18, when the low-pressure oil outlet moves to the front dead center, the control part 13 of the low-pressure oil outlet cuts off the passage of the front inlet or outlet, the blocking part 121 simultaneously cuts off the liquid circulation between the high-pressure oil inlet 151 and the second cavity 15, the main body 1 is always fixed under the action of the first cavity 14 and the return spring 18, and even if the oil pressure fluctuates, the main body 1 cannot be retracted; under the condition that the low-pressure oil outlet 141 is opened, the pressure of the first cavity 14 is reduced, the main body 1 firstly counteracts the elastic force of the return spring 18 by means of the pressure difference between the two sides of the throttling element 17, and after the second cavity 15 is communicated with the high-pressure oil inlet 151, the pressure generated by the second cavity 15 assists the main body 1 to retreat.
In this embodiment, the pressure regulating portion 12 forms a constriction 122 having a diameter smaller than the inner diameter of the valve housing 2 at a position corresponding to the oil inlet hole 161, so as to maintain the communication between the oil inlet hole 161 and the high-pressure oil inlet 151.
In this embodiment, the blocking portion 121 is a tapered structure with a small front part and a large rear part, and preferably, the valve housing 2 is provided with a corresponding tapered sleeve structure at a position corresponding to the pressure regulating portion 12, and the tapered structure has a large adhering surface when fitting, so that the sealing performance is better, and more preferably, a corresponding sealing ring structure is provided on the blocking portion 121.
In some further embodiments, such as shown in fig. 3, an annular protrusion may be provided as the blocking portion 121.
In the prior art, the throttle 17 is arranged in the oil passage 16, and the processing is difficult, in the embodiment, the throttle 17 is a sheet structure fixed at the rear end of the sealing part 11, a throttle hole 171 is opened at the center position of the sheet structure, and the diameter of the throttle hole 171 is smaller than the inner diameter of the oil passage 16.
Further, the seal portion 11, the control portion 13, and the blocking portion 121 are provided with seal rings.
Finally, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the present invention can be modified or replaced by other means without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.
Claims (5)
1. The utility model provides an aeroengine oil pump case, includes main part and reset spring, and both are with the coaxial assembly of fore-and-aft order in the valve barrel which characterized in that: the main body comprises a sealing part, a pressure regulating part and a control part which are integrally formed along the axial direction, the outer diameter of the sealing part is larger than the outer diameters of the pressure regulating part and the control part, the sealing part is used for being in sealing fit with the valve sleeve, a first cavity close to the back and a second cavity close to the front are formed on two sides of the sealing part, and the valve sleeve is respectively provided with a low-pressure oil outlet and a high-pressure oil inlet corresponding to the first cavity and the second cavity; the periphery of the pressure regulating portion is provided with a plugging portion with the outer diameter smaller than that of the sealing portion, the control portion is used for communicating or closing an oil pump oil way, the main body is provided with a rear end opening and an oil way channel extending to the sealing portion and the pressure regulating portion, the front end of the pressure regulating portion is provided with an oil inlet hole communicated with the oil way channel, the rear end opening of the oil way channel is provided with a throttling piece, the oil inlet hole is used for being communicated with a high-pressure oil inlet on the valve sleeve all the time, and the plugging portion is used for disconnecting the second cavity and the high-pressure oil inlet when the main body enters a closed state.
2. The aircraft engine oil pump cartridge of claim 1, wherein: and the pressure regulating part forms a necking with the diameter smaller than the inner diameter of the valve sleeve at the position corresponding to the oil inlet hole.
3. The aircraft engine oil pump cartridge of claim 1, wherein: the plugging part is of a conical structure with a small front part and a large back part.
4. The aircraft engine oil pump cartridge of claim 1, wherein: the throttling element is a sheet structure fixed at the rear end of the sealing part, a throttling hole is formed in the center of the sheet structure, and the diameter of the throttling hole is smaller than the inner diameter of the oil passage.
5. The aircraft engine oil pump cartridge of claim 1, wherein: and sealing rings are arranged on the sealing part, the control part and the plugging part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220371017.8U CN216588892U (en) | 2022-02-23 | 2022-02-23 | Aircraft engine oil pump case |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220371017.8U CN216588892U (en) | 2022-02-23 | 2022-02-23 | Aircraft engine oil pump case |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216588892U true CN216588892U (en) | 2022-05-24 |
Family
ID=81635979
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220371017.8U Active CN216588892U (en) | 2022-02-23 | 2022-02-23 | Aircraft engine oil pump case |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216588892U (en) |
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2022
- 2022-02-23 CN CN202220371017.8U patent/CN216588892U/en active Active
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