CN212455237U - Bearing seat for aviation gear pump test - Google Patents
Bearing seat for aviation gear pump test Download PDFInfo
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- CN212455237U CN212455237U CN201921895843.7U CN201921895843U CN212455237U CN 212455237 U CN212455237 U CN 212455237U CN 201921895843 U CN201921895843 U CN 201921895843U CN 212455237 U CN212455237 U CN 212455237U
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- bearing
- cooling water
- bearing seat
- end cover
- bearing block
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Abstract
The utility model relates to a bearing frame for an aviation gear pump test, which is arranged at the output end of a transmission system and is arranged on a transmission rack, and is characterized in that a bearing frame sealing structure consists of a framework oil seal (6) arranged between an installation end cover (2) and a transmission shaft (1) and an O-shaped sealing ring (5) arranged between the installation end cover (2) and a bearing seat body (7); the lubricating oil loop consists of oil passing holes at the top and the side of the bearing seat body (7), oil passing holes on the bearing outer ring retainer ring (4) and a lubricating joint (8); the cooling water loop comprises a heat dissipation connector (9), a cooling water tank inside the mounting end cover (2) and a cooling water hole inside the bearing seat body (7), and lubricating oil and cooling water are respectively introduced into the lubricating loop and the cooling loop when the bearing seat works, so that the bearing abrasion is reduced, and heat generated by the bearing is conducted out. The oil pump is convenient to install during use, easy to realize in processing technology, good in sealing performance, sufficient in lubrication and stable in transmission.
Description
Technical Field
The utility model belongs to nonstandard equipment mechanical transmission field relates to bearing frame seal structure, lubricated and the cooling water heat dissipation of lubricating oil.
Background
The shaft end often has the residual oil to spill over when aviation gear pump work, except need satisfying installation and high-speed drive requirement during the experiment, still leak to the fluid of pump axle end and seal, prevents in the residual oil gets into the bearing frame, leads to the test medium to reveal. The traditional bearing seat adopts a deep groove ball bearing, grease lubrication or oil spray lubrication is carried out, the shaft end has no sealing structure, the output end has no installation and positioning structure, and the bearing seat is mainly characterized in that: when the shaft end can not be used in a sealing mode, oil liquid leaks, lubrication is insufficient, the heat dissipation effect is poor, heat is easy to generate, the failure rate is high, the maintainability is poor, and the requirement of an aviation gear pump test can not be met.
Disclosure of Invention
The utility model aims at: the bearing seat for the aviation gear pump test is used for positioning, mounting, driving and sealing pump shaft end residual oil during the gear pump test.
The technical scheme of the utility model is that: a bearing seat for an aviation gear pump test comprises a transmission shaft, an installation end cover, an angular contact ball bearing, a bearing outer ring retainer ring, an O-shaped sealing ring, a framework oil seal, a bearing seat body, a lubricating joint, a heat dissipation joint, a positioning taper pin, a fixing screw and the like. An angular contact ball bearing is arranged on the transmission shaft, oil lubrication is adopted, and the limit rotating speed can reach 20000 rpm; the mounting end cover is provided with an end face sealing ring groove, a cooling water channel, a framework oil seal mounting hole and a test mounting positioning boss which are respectively used for mounting a sealing ring, a framework oil seal and a gear pump test tool, so that the requirements of sealing residual oil at the shaft end of the gear pump and lubricating oil in a bearing seat and mounting the test tool are met; the heat dissipation connector provides cooling water for the bearing seat and is used for ensuring the heat dissipation of the bearing seat; the lubricating joint provides lubricating oil for the bearing seat, and is used for ensuring the lubrication of the bearing.
The specific scheme is as follows:
a bearing block for an aviation gear pump test is arranged at the output end of a transmission system, the bearing block is arranged on a transmission rack, and a bearing block sealing structure is composed of a framework oil seal 6 arranged between an installation end cover 2 and a transmission shaft 1 and an O-shaped sealing ring 5 arranged between the installation end cover 2 and a bearing seat body 7; the lubricating oil loop consists of oil passing holes at the top and the side of the bearing seat body 7, oil passing holes on the bearing outer ring retainer ring 4 and a lubricating joint 8; the cooling water circuit comprises the cooling water hole inside the cooling water tank of thermal coupling 9, installation end cover 2 inside, bearing pedestal 7, and the bearing frame during operation lets in lubricating oil and cooling water to lubricating circuit and cooling circuit respectively, reduces the bearing wearing and tearing and goes out the heat conduction that the bearing produced.
Preferably, the mounting end cover 2 is provided with 2 end face seal ring grooves and 2 framework oil seal mounting holes.
Preferably, a framework oil seal 6 arranged between the mounting end cover 2 and the transmission shaft 1 seals and isolates lubricating oil inside the bearing seat from the outside.
Preferably, the O-ring 5 installed between the installation end cap 2 and the bearing seat body 7 seals and isolates the lubricating oil, cooling water and the outside in the bearing seat.
Preferably, the bearing seat body 7 is provided with a lubricating oil hole, and the bearing outer ring retainer ring 4 is provided with a lubricating oil hole.
Preferably, a cooling water tank inside the end cap 2 and a cooling water hole inside the bearing housing 7 are installed.
The technical effects of the utility model are that: shaft end, bearing frame inner chamber and external sealed requirement when can satisfying the aviation gear pump test to bearing lubrication and cooling system mutual independence, lubricated cooling is abundant, and the commonality is good, and the location is accurate, simple to operate. The bearing seat is stable in transmission and good in reliability.
Drawings
FIG. 1 is a front view of a bearing seat for an aviation gear pump test;
FIG. 2 is a left side view of a bearing block for an aviation gear pump test;
FIG. 3 is an axial side view of a bearing block for an aviation gear pump test;
the bearing comprises a transmission shaft 1, a transmission shaft 2, an installation end cover 3, an angular contact ball bearing 4, a bearing outer ring retainer ring 5, an O-shaped sealing ring 6, a framework oil seal 7, a bearing seat body 8, a lubricating joint 9, a radiating joint 10, a positioning taper pin 11 and a fixing screw.
Detailed Description
The bearing seat for the aviation gear pump test comprises a transmission shaft 1, a mounting end cover 2, an angular contact ball bearing 3, a bearing outer ring retainer ring 4, an O-shaped sealing ring 5, a framework oil seal 6, a bearing seat body 7, a lubricating joint 8, a heat dissipation joint 9, a positioning taper pin 10 and a fixing screw 11. The transmission shaft 1 and the mounting end cover 2 are mounted in the bearing seat body 7; the angular contact ball bearing 3 and the bearing outer ring retainer ring 4 are arranged between the transmission shaft 1 and the bearing seat body 7, and the O-shaped seal ring 5 and the framework oil seal 6 are arranged in the mounting end cover 2. The bearing seat body 7 is provided with a lubricating joint 8 and a heat radiation joint 9, and the bearing seat body 7 is arranged on the transmission platform through a positioning taper pin 10 and a fixing screw 11.
A bearing inner ring positioning shaft shoulder, a bearing retainer ring groove and a framework oil seal sealing strip are arranged on the transmission shaft 1; the mounting end cover 2 is provided with an end face sealing ring groove, a cooling water channel, a framework oil seal mounting hole and a test mounting positioning boss; a bearing outer ring retainer ring 4 is provided with a lubricating oil hole for axially positioning the bearing outer ring and ensuring the circulation of lubricating oil; a cooling water hole, a lubricating oil hole, a fixed mounting hole and a positioning pin hole are formed in the bearing seat body 7 and are used for bearing lubrication, heat dissipation and positioning and mounting of the bearing seat; the lubricating joint 8 provides lubricating oil for the bearing seat to ensure the lubrication of the bearing; the heat dissipation connector 9 provides cooling water for the bearing seat to ensure the heat dissipation of the bearing seat; after the bearing seat is screwed to the transmission platform through the fixing screw 11, the positioning taper pin 10 is installed, so that the bearing seat is prevented from moving in the using process, and meanwhile, the follow-up maintenance and disassembly are facilitated.
Claims (6)
1. A bearing block for an aviation gear pump test is arranged at the output end of a transmission system, and the bearing block is arranged on a transmission rack and is characterized in that a bearing block sealing structure consists of a framework oil seal (6) arranged between an installation end cover (2) and a transmission shaft (1) and an O-shaped sealing ring (5) arranged between the installation end cover (2) and a bearing seat body (7); the lubricating oil loop consists of oil passing holes at the top and the side of the bearing seat body (7), oil passing holes on the bearing outer ring retainer ring (4) and a lubricating joint (8); the cooling water loop comprises a heat dissipation connector (9), a cooling water tank inside the mounting end cover (2) and a cooling water hole inside the bearing seat body (7), and lubricating oil and cooling water are respectively introduced into the lubricating loop and the cooling loop when the bearing seat works, so that the bearing abrasion is reduced, and heat generated by the bearing is conducted out.
2. The bearing seat for the aviation gear pump test according to claim 1, wherein the mounting end cover (2) is provided with 2 end face seal ring grooves and 2 framework oil seal mounting holes.
3. A bearing block for an aviation gear pump test according to claim 1, wherein a framework oil seal (6) arranged between the mounting end cover (2) and the transmission shaft (1) seals and isolates lubricating oil inside the bearing block from the outside.
4. A bearing block for an aviation gear pump test according to claim 1, characterized in that an O-shaped sealing ring (5) arranged between the mounting end cover (2) and the bearing block body (7) seals and isolates lubricating oil, cooling water and the outside in the bearing block.
5. The bearing block for the aviation gear pump test as recited in claim 1, wherein a lubrication hole is formed in the bearing block body (7), and a lubrication hole is formed in the bearing outer ring retainer ring (4).
6. A bearing block for an aviation gear pump test according to claim 1, wherein a cooling water tank is arranged inside the mounting end cover (2), and a cooling water hole is arranged inside the bearing block body (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921895843.7U CN212455237U (en) | 2019-11-05 | 2019-11-05 | Bearing seat for aviation gear pump test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921895843.7U CN212455237U (en) | 2019-11-05 | 2019-11-05 | Bearing seat for aviation gear pump test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212455237U true CN212455237U (en) | 2021-02-02 |
Family
ID=74480935
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921895843.7U Active CN212455237U (en) | 2019-11-05 | 2019-11-05 | Bearing seat for aviation gear pump test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212455237U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114688170A (en) * | 2022-05-17 | 2022-07-01 | 南京高精齿轮集团有限公司 | Bearing seat structure for shield machine gear box test and shield machine gear box test system |
-
2019
- 2019-11-05 CN CN201921895843.7U patent/CN212455237U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114688170A (en) * | 2022-05-17 | 2022-07-01 | 南京高精齿轮集团有限公司 | Bearing seat structure for shield machine gear box test and shield machine gear box test system |
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