CN217029957U - Aircraft engine oil pump slide valve assembly - Google Patents
Aircraft engine oil pump slide valve assembly Download PDFInfo
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- CN217029957U CN217029957U CN202220438258.XU CN202220438258U CN217029957U CN 217029957 U CN217029957 U CN 217029957U CN 202220438258 U CN202220438258 U CN 202220438258U CN 217029957 U CN217029957 U CN 217029957U
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Abstract
The utility model relates to the technical field of aviation parts, in particular to an aircraft engine oil pump slide valve assembly, which comprises a switch electromagnet, a valve core and a valve sleeve, wherein the valve core is arranged inside the valve sleeve, one end of the valve sleeve is provided with an installation cavity, the valve core is sleeved with a spring sleeve, the spring sleeve is accommodated in the installation cavity, the valve core is provided with a limiting step at the position close to the outer end of the spring sleeve, the spring sleeve is provided with a return spring, two ends of the return spring respectively act on the spring sleeve and the valve sleeve, the valve sleeve further comprises an auxiliary electromagnet in the direction of the outer end of the spring sleeve, the output end of the auxiliary electromagnet acts on the spring sleeve, and the output end of the switch electromagnet acts on the valve core; the auxiliary electromagnet is arranged, so that the response speed of the sliding valve assembly is increased.
Description
Technical Field
The utility model relates to the technical field of aviation parts, in particular to a sliding valve assembly of an aero-engine oil pump.
Background
The fuel pump in an aviation power device is a special fuel pump, which is an energy conversion device for converting mechanical energy of a prime mover into hydraulic energy and is a fuel pump for providing certain pressure (pressure intensity) and flow rate for the power device. The plunger type fuel pump has the advantages of high output pressure, high volumetric efficiency, simple fuel supply regulation, easy manufacture of a variable pump, convenient realization of fuel supply control and the like.
The plunger fuel pump is characterized by that when the plunger is reciprocated in its cylinder body, the volume of sealed working cavity can be changed to implement oil suction and oil discharge. In the traditional slide valve assembly, in order to overcome the reverse forces of the elastic force, the fluid resistance and the like of a reset spring during the action of the electromagnet, the coil turns or the current is increased to obtain larger thrust, but when the electromagnet is reset by the spring, the coil current reduction time is longer, the closing time of the valve is increased on the contrary, and the performance of the slide valve assembly is influenced.
SUMMERY OF THE UTILITY MODEL
In view of this, the present invention provides a slide valve assembly for an aircraft engine oil pump, which overcomes the drawbacks of the prior art and increases the response speed of the slide valve assembly by providing an auxiliary electromagnet.
The utility model discloses a sliding valve assembly of an aircraft engine oil pump, which comprises a switch electromagnet, a valve core and a valve sleeve, wherein the valve core is arranged in the valve sleeve, one end of the valve sleeve is provided with an installation cavity, the valve core is sleeved with a spring sleeve, the spring sleeve is accommodated in the installation cavity, the valve core is provided with a limiting step at the position close to the outer end of the spring sleeve, a return spring is arranged on the spring sleeve, two ends of the return spring respectively act on the spring sleeve and the valve sleeve, the valve sleeve also comprises an auxiliary electromagnet in the outer end direction of the spring sleeve, the output end of the auxiliary electromagnet acts on the spring sleeve, and the output end of the switch electromagnet acts on the valve core.
Furthermore, the auxiliary electromagnet comprises an auxiliary electromagnetic coil, an auxiliary armature and a pushing sleeve, the pushing sleeve is fixedly connected with the auxiliary armature, and the pushing sleeve is coaxially arranged with the valve core and is abutted against the spring sleeve.
Furthermore, the switch electromagnet is arranged on the same side of the auxiliary electromagnet and comprises a switch electromagnetic coil, a switch armature and a push rod, the switch armature is movably arranged at the center of the switch electromagnetic coil, the push rod is fixedly connected with the armature, and a magnetism isolating ring and a magnetism isolating sheet are respectively arranged on one side of the switch electromagnetic coil and one side of the switch armature facing the auxiliary electromagnet.
Furthermore, the valve core forms an oil path control side at one end far away from the return spring, and a sealing ring is arranged on the valve core and used for completely isolating the return spring from the oil path control side.
Furthermore, the switch electromagnet and the auxiliary electromagnet both comprise shells, and the shells of the switch electromagnet and the auxiliary electromagnet, and the shells of the auxiliary electromagnet and the valve sleeve are connected by flanges and sealed by sealing rings.
The beneficial effects of the utility model are: the utility model discloses a sliding valve assembly of an aircraft engine oil pump, which is characterized in that an auxiliary electromagnet acting on a return spring is additionally arranged on the basis of a traditional switch electromagnet, so that the return spring counteracts the elastic force of the spring, the switch electromagnet is subjected to less reverse force, the number of required coil turns is less, the response is faster, a valve core is promoted to move faster, and the response speed of the sliding valve is improved.
Drawings
The utility model is further described below with reference to the following figures and examples:
FIG. 1 is a schematic view of the present invention.
Description of reference numerals: the electromagnetic valve comprises a switch electromagnet 1, a switch electromagnetic coil 11, a switch armature 12, a push rod 13, a magnetism isolating ring 14, a magnetism isolating sheet 15, an auxiliary electromagnet 2, an auxiliary electromagnetic coil 21, an auxiliary armature 22, a push sleeve 23, a valve core 31, a valve sleeve 32, a spring sleeve 33, a limit step 34, a return spring 35 and a sealing ring 36.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, in the embodiment, the aircraft engine oil pump sliding valve assembly includes a switch electromagnet 1, a valve core 31, and a valve sleeve 32, the valve core 31 is disposed inside the valve sleeve 32, the switch electromagnet 1 acts on the valve core 31, when the switch electromagnet 1 is energized, the switch electromagnet drives the valve core 31 to move, one end of the valve sleeve 32 is provided with an installation cavity, the valve core 31 is sleeved with a spring sleeve 33, the spring sleeve 33 is accommodated in the installation cavity, the valve core 31 is provided with a limit step 34 at a position close to an outer end of the spring sleeve 33, the spring sleeve 33 is provided with a return spring 35, two ends of the return spring 35 respectively act on the spring sleeve 33 and the valve sleeve 32, when the switch electromagnet 1 is de-energized, the return spring 35 drives the valve core 31 to retract, the valve sleeve 32 further includes an auxiliary electromagnet 2 at an outer end of the spring sleeve 33, the output end of the auxiliary electromagnet 2 acts on the spring sleeve 33, and the output end of the switch electromagnet 1 acts on the valve core 31.
In the actual action process, the switch electromagnet 1 and the auxiliary electromagnet 2 are controlled to be synchronously electrified through the controller, or the auxiliary electromagnet 2 is electrified before the switch electromagnet 1, the auxiliary electromagnet 2 is utilized to share the elastic force of the reset spring 35, the switch electromagnet 1 drives the valve core 31 to rapidly move, when the valve core moves to a dead point on one side, the limit step 34 on the valve core 31 is abutted to the spring sleeve 33, the auxiliary electromagnet 2 can be powered off, the valve core 31 is kept fixed through the force application of the switch electromagnet 1, the number of turns of a coil of the switch electromagnet 1 is small, and the generated thrust only needs to overcome the elastic force of the spring; when the switch electromagnet 1 needs to retract, the switch electromagnet 1 is powered off, the switch electromagnet 1 with fewer turns can respond quickly, and the valve core 31 can retract quickly under the action of the return spring 35.
As shown in fig. 1, the auxiliary electromagnet 2 includes an auxiliary electromagnetic coil 21, an auxiliary armature 22, and a push sleeve 23, where the push sleeve 23 is fixedly connected to the auxiliary armature 22, and the push sleeve 23 is coaxially disposed with the valve core 31 and abuts against the spring sleeve 33.
In this embodiment, the switch electromagnet 1 is disposed on the same side of the auxiliary electromagnet 2, and includes a switch electromagnetic coil 11, a switch armature 12 and a push rod 13, the switch armature 12 is movably disposed at the center of the switch electromagnetic coil 11, the push rod 13 is fixedly connected to the armature, and a magnetic isolation ring 14 and a magnetic isolation sheet 15 are respectively disposed on one side of the switch electromagnetic coil 11 and one side of the switch armature 12 facing the auxiliary electromagnet 2, so as to reduce mutual interference of magnetic forces.
The valve core 31 is provided with an oil path control side at one end far away from the return spring 35, and the valve core 31 is provided with a sealing ring 36 for completely isolating the return spring 35 from the oil path control side, so that the failure of the switching electromagnet 1 and the auxiliary electromagnet 2 caused by the oil leakage of the valve core 31 is avoided.
In this embodiment, the switching electromagnet 1 and the auxiliary electromagnet both include a casing, and the casing of the switching electromagnet and the casing of the auxiliary electromagnet, and the casing of the auxiliary electromagnet and the valve sleeve 32 are connected by flanges, and are sealed by a sealing ring 36, so that the switching electromagnet and the auxiliary electromagnet are isolated from the outside and are convenient to disassemble and repair.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, 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 modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (5)
1. The utility model provides an aeroengine oil pump sliding valve subassembly, includes switch electro-magnet, case and valve barrel, its characterized in that: the valve sleeve comprises a valve sleeve and a valve core, wherein the valve core is arranged in the valve sleeve, one end of the valve sleeve is provided with an installation cavity, the valve core is sleeved with a spring sleeve, the spring sleeve is accommodated in the installation cavity, the outer end of the valve core, which is close to the spring sleeve, is provided with a limiting step, the spring sleeve is provided with a return spring, two ends of the return spring respectively act on the spring sleeve and the valve sleeve, the valve sleeve further comprises an auxiliary electromagnet in the outer end direction of the spring sleeve, the output end of the auxiliary electromagnet acts on the spring sleeve, and the output end of the switch electromagnet acts on the valve core.
2. An aircraft engine oil pump slide valve assembly according to claim 1, wherein: the auxiliary electromagnet comprises an auxiliary electromagnetic coil, an auxiliary armature and a pushing sleeve, the pushing sleeve is fixedly connected with the auxiliary armature, and the pushing sleeve is coaxially arranged with the valve core and is abutted against the spring sleeve.
3. An aircraft engine oil pump slide valve assembly according to claim 1, wherein: the switch electromagnet is arranged on the same side of the auxiliary electromagnet and comprises a switch electromagnetic coil, a switch armature and a push rod, wherein the switch armature is movably arranged at the center of the switch electromagnetic coil, the push rod is fixedly connected with the armature, and the switch electromagnetic coil and the switch armature are respectively provided with a magnetism isolating ring and a magnetism isolating sheet towards one side of the auxiliary electromagnet.
4. An aircraft engine oil pump slide valve assembly according to claim 1, wherein: the valve core is provided with a sealing ring for completely isolating the return spring from the oil path control side.
5. An aircraft engine oil pump slide valve assembly according to claim 3, wherein: the switch electromagnet and the auxiliary electromagnet both comprise shells, and the shells of the switch electromagnet and the auxiliary electromagnet, and the shells of the auxiliary electromagnet and the valve sleeve are connected through flanges and sealed through sealing rings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220438258.XU CN217029957U (en) | 2022-03-02 | 2022-03-02 | Aircraft engine oil pump slide valve assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220438258.XU CN217029957U (en) | 2022-03-02 | 2022-03-02 | Aircraft engine oil pump slide valve assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217029957U true CN217029957U (en) | 2022-07-22 |
Family
ID=82454329
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220438258.XU Active CN217029957U (en) | 2022-03-02 | 2022-03-02 | Aircraft engine oil pump slide valve assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217029957U (en) |
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2022
- 2022-03-02 CN CN202220438258.XU patent/CN217029957U/en active Active
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