CN220956033U - Lubricating circulation oil way structure for aviation electric pump - Google Patents
Lubricating circulation oil way structure for aviation electric pump Download PDFInfo
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- CN220956033U CN220956033U CN202322758735.8U CN202322758735U CN220956033U CN 220956033 U CN220956033 U CN 220956033U CN 202322758735 U CN202322758735 U CN 202322758735U CN 220956033 U CN220956033 U CN 220956033U
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- shell
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- 230000001050 lubricating effect Effects 0.000 title claims abstract description 19
- 239000003921 oil Substances 0.000 claims abstract description 90
- 239000010687 lubricating oil Substances 0.000 claims abstract description 34
- 239000003129 oil well Substances 0.000 claims abstract description 17
- 238000005192 partition Methods 0.000 claims abstract description 16
- 239000007788 liquid Substances 0.000 claims abstract description 15
- 238000005461 lubrication Methods 0.000 claims abstract description 13
- 238000007789 sealing Methods 0.000 claims abstract description 9
- 238000001816 cooling Methods 0.000 claims description 6
- 230000009471 action Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000010724 circulating oil Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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- Details Of Reciprocating Pumps (AREA)
Abstract
The utility model belongs to the technical field of aviation lubricating oil pumps, and discloses a lubricating circulation oil way structure for an aviation electric pump, which comprises a pump assembly and a motor assembly, wherein a pump shaft of the pump assembly is connected with a motor shaft of the motor assembly through a spline; wherein, an oil well hole is arranged in a pump shell of the pump assembly, a first baffle plate of the pump assembly is arranged at the left side of the oil well hole of the pump shell, a second diaphragm of the pump assembly is mounted to the right side of the pump housing wellbore; the pump shaft passes through the central holes of the first partition plate and the second partition plate and rotates along the central axis of the central holes; the motor shell of the motor component is inserted into the oil hole of the pump shell through the left step surface; a sealing ring is arranged between the left step surface of the motor shell and the pump shell; the motor shaft is provided with a lubrication oil hole at the inner side of the motor shell and communicated with the inside of the motor shell, and an oil through hole communicated with the low-pressure oil liquid area is arranged in the motor shell.
Description
Technical Field
The utility model belongs to the technical field of aviation lubricating oil pumps, relates to a self-radiating structure of an aviation electric lubricating oil pump, and particularly relates to a lubricating circulation oil path structure for the aviation electric pump.
Background
In general, an aviation lubricating oil system comprises a plurality of oil pumps for conveying lubricating oil, and the oil pumps realize the functions of oil absorption and oil discharge by driving gears to mesh. At present, the power input of an oil pump is gradually transited from gear transmission to motor transmission, but the motor lubrication often needs to be provided with a lubricating oil way alone, so that the occupied space is large, the complexity of a lubricating oil system pipeline is increased, and the weight reduction and the improvement of the power-weight ratio of an engine are not facilitated.
Disclosure of utility model
The purpose of the utility model is that: the utility model provides a aviation is lubricated circulating oil way structure for electric pump carries out self-lubricating to self motor through the lubricating oil of electric pump self pump, has solved the technical problem that current aviation electric pump lubrication oil way is complicated and lightens lubricating oil system weight.
The technical scheme of the utility model is as follows:
A lubricating circulation oil way structure for an aviation electric pump comprises a pump assembly and a motor assembly, wherein a pump shaft of the pump assembly is connected with a motor shaft of the motor assembly through a spline; wherein, an oil well hole is arranged in a pump shell of the pump assembly, a first baffle plate of the pump assembly is arranged at the left side of the oil well hole of the pump shell, a second diaphragm of the pump assembly is mounted to the right side of the pump housing wellbore; the pump shaft passes through the central holes of the first partition plate and the second partition plate and rotates along the central axis of the central holes; the motor shell of the motor component is inserted into the oil hole of the pump shell through the left step surface; a sealing ring is arranged between the left step surface of the motor shell and the pump shell; the motor shaft is provided with a lubrication oil hole at the inner side of the motor shell and communicated with the inside of the motor shell, and an oil through hole communicated with the low-pressure oil liquid area is arranged in the motor shell.
Further, the lubricating oil holes are radial holes, and the oil through holes are connected with other parts needing lubrication and cooling in the motor.
Further, a groove for storing oil is formed in the left side inside the motor shell.
Further, one end of the oil hole is connected with the end part of the groove, and the other end of the oil hole is connected with the oil storage area on the right side of the oil well hole of the pump housing.
Further, an oil return hole is arranged on the second partition plate and is communicated with the oil storage area and the upper low-pressure oil liquid area of the pump housing.
Further, a high-pressure oil liquid area is arranged below the pump housing, a transverse hole is formed in the first partition plate and is communicated with the high-pressure oil liquid area and a shaft end cavity, and the shaft end cavity is a cavity between the pump housing and the left end of the pump shaft.
The utility model has the technical effects that:
According to the utility model, by adopting the lubricating circulation oil way structure for the aviation electric pump, the functions of lubrication and heat exchange of components working in the aviation electric pump motor of the aviation lubricating oil system can be realized, lubrication and cooling in the working process of the motor are ensured, the simplification of the oil way structure of the lubricating oil system is realized, and the reliability of the lubricating oil system is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following description will briefly explain the drawings required to be used in the embodiments of the present utility model, and it is obvious that the drawings described below are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic cross-sectional view of a lubrication circuit structure for an aviation electric pump of the present invention;
FIG. 2 is a schematic diagram of the flow of oil in the circulation of the lubricating oil of the present invention;
Wherein, 1-pump shell, 2-pump shaft, 3-first baffle, 4-second baffle, 5-motor shaft, 6-seal ring and 7-motor shell;
The arrows in fig. 2 indicate the direction of the oil flow.
Detailed Description
This section is an embodiment of the present utility model for explaining and explaining the technical solution of the present utility model. Embodiments of the utility model and features of the embodiments may be combined with each other without conflict.
In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. refer to directions or positional relationships given to the drawings for convenience of description and simplicity of description, and do not indicate or imply that the apparatus or case in question must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the utility model. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or number of technical features indicated. Thus, a feature defining "first," "second," etc. may explicitly or implicitly include more such feature. In the description of the present utility model, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present utility model, unless explicitly stated or limited otherwise, the terms "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; the mechanical connection can be realized, and the point connection can be realized; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art in a specific case.
Example 1:
The lubricating circulation oil way structure for the aviation electric pump comprises a pump assembly and a motor assembly, wherein a pump shaft 2 of the pump assembly is connected with a motor shaft 5 of the motor assembly through a spline; wherein, the pump shell 1 of the pump assembly is internally provided with an oil well hole, the first baffle plate 3 of the pump assembly is arranged at the left side of the oil well hole of the pump shell 1, and the second baffle plate 4 of the pump assembly is arranged at the right side of the oil well hole of the pump shell 1; the pump shaft 2 passes through the central holes of the first partition plate 3 and the second partition plate 4 and rotates along the central axis of the central holes; the motor shell 7 of the motor assembly is inserted into the oil well hole of the pump shell 1 through the left step surface; a sealing ring 6 is arranged between the left step surface of the motor shell 7 and the pump shell 1; the pump shaft 2 and the motor shaft 5 are hollow shafts and are communicated, the left side of the pump shaft 2 is communicated with a high-pressure oil liquid area, the motor shaft 5 is provided with a lubricating oil hole at the inner side of the motor housing 7 and communicated with the inside of the motor housing 7, and an oil communicating small hole is arranged in the motor housing 7 and communicated with a low-pressure oil liquid area.
The lubricating oil hole is a radial hole, and the oil through hole is connected with other parts needing lubrication and cooling inside the motor.
The left side inside the motor shell 7 is provided with a groove for storing oil.
One end of the oil hole is connected with the end part of the groove, and the other end of the oil hole is connected with the oil storage area on the right side of the oil well hole of the pump housing 1.
The second baffle plate 4 is provided with an oil return hole which is communicated with the oil storage area and the upper low-pressure oil liquid area of the pump housing 1.
The pump casing 1 below is high-pressure oil liquid district, is equipped with cross bore intercommunication high-pressure oil liquid district and axle head chamber on the first baffle 3, and the axle head chamber is the cavity between pump casing 1 and the left end of pump shaft 2.
Example 2:
The cross-sectional schematic diagram of the multifunctional valve structure of the invention is shown in fig. 1: comprises a pump housing 1, a pump shaft 2, a first partition plate 3, a second partition plate 4, a motor shaft 5, a sealing ring 6 and a motor housing 7.
Wherein the first baffle 3 is arranged at the left side of the oil well hole of the pump housing 1; the second baffle plate 4 is arranged on the right side of the oil well hole of the pump housing 1; the pump shaft 2 passes through the central holes of the first partition plate 3 and the second partition plate 4 and can perform rotary motion along the central axis of the central holes; the motor shell 7 is inserted into the oil well hole of the pump shell 1 through the left step surface; the sealing ring 6 is arranged on a sealing ring groove on the left step surface of the motor shell 7, and the motor shaft 5 is connected with the right internal spline of the pump shaft 2 through the left external spline and can drive the pump shaft 2 to do rotary motion along the central axis of the pump shaft 2.
The working principle of the multifunctional valve structure is as follows
As shown in fig. 1, the lubricating circulation oil path structure for the aviation electric pump is arranged in an electric pump product, the lower part of a pump housing 1 is connected with a lubricating part of a lubricating oil system to output pressure lubricating oil, and the upper part of the pump housing 1 is connected with a lubricating oil tank of the lubricating oil system to provide low-pressure lubricating oil for the electric pump.
As shown in fig. 2, when the electric pump works, the pressure lubricating oil below the pump housing 1 flows into the left side groove of the oil hole of the pump housing 1 under the pressure action of the lubricating oil on the first baffle plate 3, lubricates the contact part of the first baffle plate 3 and the pump shaft 2, and then flows to the central oil hole of the motor shaft 5 through the oil through hole inside the pump shaft 2, the oil through hole is arranged on the motor shaft 5 so that the oil through hole is connected with other parts needing to be lubricated and cooled inside the motor, when the motor shaft 5 rotates at a high speed, the lubricating oil in the oil through hole passes through the lubricating oil hole under the action of centrifugal force, after lubricating and cooling the parts inside the motor, the lubricating oil flows to the right side oil storage area of the oil hole of the pump housing 1 through the oil through hole arranged at the end part of the left side groove of the motor housing 7, the sealing ring 6 is an elastic part tightly attached to the sealing ring groove on the left side step surface of the pump housing 1 and the pump housing 7, at the moment, the lubricating oil lubricates the contact part of the second baffle plate 4 and the pump shaft 2 and the two parts of the pump shaft 2, the upper low pressure oil above the second baffle plate 4 is connected with the upper side oil return hole of the pump housing 1, the lubricating oil flows to the right side oil storage area of the oil hole of the pump housing 1, and the lower pressure oil flows to the right side oil storage area of the pump housing 1 is down the oil hole of the right side of the oil hole is left side of the oil storage area 1, and the oil is left side of the oil storage area is left side of the oil side of the pump housing 1.
Compared with other common lubricating structures, the lubricating circulation oil way structure for the aviation electric pump is characterized in that the structure and the function integration of a motor pump driving motor lubricating circulation oil way are realized, the lubricating circulation oil way structure for the aviation electric pump can realize the effects of lubrication and heat exchange of components working in an aviation electric pump motor of an aviation lubricating oil system, the lubrication and the cooling in the working process of the motor are ensured, the simplification of the lubricating oil way structure of the lubricating oil system is realized, and the reliability of the lubricating oil system is improved.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art can easily think about various equivalent modifications or substitutions within the technical scope of the present utility model, and these modifications or substitutions should be covered in the scope of the present utility model.
Claims (6)
1. The lubricating circulation oil way structure for the aviation electric pump is characterized by comprising a pump assembly and a motor assembly, wherein a pump shaft (2) of the pump assembly is connected with a motor shaft (5) of the motor assembly through a spline; the oil well hole is arranged in a pump shell (1) of the pump assembly, a first baffle plate (3) of the pump assembly is arranged on the left side of the oil well hole of the pump shell (1), and a second baffle plate (4) of the pump assembly is arranged on the right side of the oil well hole of the pump shell (1); the pump shaft (2) passes through the central holes of the first partition plate (3) and the second partition plate (4) and rotates along the central axis of the central holes; the motor shell (7) of the motor assembly is inserted into the oil hole of the pump shell (1) through the left step surface; a sealing ring (6) is arranged between the left step surface of the motor shell (7) and the pump shell (1); the pump shaft (2) and the motor shaft (5) are hollow shafts and are communicated, the left side of the pump shaft (2) is communicated with a high-pressure oil liquid area, the motor shaft (5) is provided with a lubricating oil hole at the inner side of a motor shell (7) and communicated with the inside of the motor shell (7), and an oil communicating small hole is arranged in the motor shell (7) and communicated with a low-pressure oil liquid area.
2. The lubricating circulation oil path structure for an aviation electric pump according to claim 1, wherein the lubricating oil hole is a radial hole, and the oil through hole is connected with other parts requiring lubrication and cooling inside the motor.
3. The lubricating circulation oil path structure for an aviation electric pump according to claim 1, characterized in that a groove for storing oil is provided on the left side inside the motor housing (7).
4. A lubrication circuit structure for an aviation electric pump according to claim 3, characterized in that one end of the oil passage small hole is connected to the end of the groove, and the other end of the oil passage small hole is connected to the oil storage area on the right side of the oil well hole of the pump housing (1).
5. The lubricating circulation oil path structure for the aviation electric pump according to claim 4, wherein the second partition plate (4) is provided with an oil return hole communicated with the oil storage area and the upper low-pressure oil liquid area of the pump housing (1).
6. The lubricating circulation oil way structure for the aviation electric pump according to claim 1 is characterized in that a high-pressure oil liquid area is arranged below the pump housing (1), a transverse hole is formed in the first partition plate (3) and is communicated with the high-pressure oil liquid area and a shaft end cavity, and the shaft end cavity is a cavity between the pump housing (1) and the left end of the pump shaft (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322758735.8U CN220956033U (en) | 2023-10-13 | 2023-10-13 | Lubricating circulation oil way structure for aviation electric pump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322758735.8U CN220956033U (en) | 2023-10-13 | 2023-10-13 | Lubricating circulation oil way structure for aviation electric pump |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220956033U true CN220956033U (en) | 2024-05-14 |
Family
ID=91004927
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322758735.8U Active CN220956033U (en) | 2023-10-13 | 2023-10-13 | Lubricating circulation oil way structure for aviation electric pump |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220956033U (en) |
-
2023
- 2023-10-13 CN CN202322758735.8U patent/CN220956033U/en active Active
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