CN216518165U - Supercharger vortex end sealing structure for high supercharging system - Google Patents
Supercharger vortex end sealing structure for high supercharging system Download PDFInfo
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- CN216518165U CN216518165U CN202123210114.3U CN202123210114U CN216518165U CN 216518165 U CN216518165 U CN 216518165U CN 202123210114 U CN202123210114 U CN 202123210114U CN 216518165 U CN216518165 U CN 216518165U
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Abstract
The utility model relates to the field of turbochargers, in particular to a supercharger vortex end sealing structure for a high supercharging system, which comprises a supporting component and a sealing component, wherein the supporting component comprises a bearing shell, a bearing seat, a radial bearing and a turbine shaft; the turbine end gas seal is arranged on the bearing shell through a positioning pin, and the turbine end gas seal and the back end face of the turbine shaft wheel form a gas cavity; a second ring groove is formed in the inner hole of the vortex end gas seal, and the second ring groove and the turbine shaft form a second labyrinth seal structure; the vortex end high-pressure fuel gas enters the first labyrinth seal, the combustion and the second labyrinth seal and undergoes throttling, pressure reduction and re-throttling processes to reduce the pressure and flow rate of the high-pressure fuel gas. The pressure airflow impact on the vortex end is reduced, so that the abrasion is reduced, and the service life of the whole device is prolonged.
Description
Technical Field
The utility model relates to the field of turbochargers, in particular to a turbocharger turbine end sealing structure for a high-supercharging system.
Background
With the development of diesel engine technology towards high supercharging, the diesel engine system has been applied to a two-stage supercharger system matching technology, and the turbocharger is used as a key matching set of the diesel engine. The ultrahigh pressure ratio brings the problem of bearing oil density to the supercharger.
The turbine end seal of the conventional supercharger is a single piston ring structure, under the condition of ultrahigh pressure working condition, a piston ring at the turbine end of the turbocharger is seriously worn, and a large amount of high-pressure gas enters a bearing oil cavity and enters lubricating oil, so that the lubricating oil burning condition of a running supercharger turbine end bearing is easily caused, the lubrication of a bearing-rotor oil film is failed, and the bearing-rotor is burnt.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a supercharger vortex end sealing structure for a high-supercharging system, which improves the sealing performance of the supercharger vortex end sealing structure and solves the problem that the sealing structure fails to work on an air-oil seal in the operation process of an ultrahigh-pressure supercharger under high working conditions.
In order to achieve the purpose, the utility model provides a supercharger vortex end sealing structure for a high supercharging system, which comprises a supporting assembly and a sealing assembly, wherein the supporting assembly comprises a bearing shell, a bearing seat, a radial bearing and a turbine shaft, the bearing seat is fixedly arranged in the bearing shell, the radial bearing is fixedly arranged in the bearing seat, the turbine shaft is provided with a back ring groove, and the turbine shaft is arranged in the radial bearing; the sealing assembly comprises a heat insulation wall and a vortex end air seal, the heat insulation wall is provided with a first ring groove, the heat insulation wall is fixed on the bearing shell, and the first ring groove and the back ring groove form a first labyrinth sealing structure; vortex end atmoseal has the second annular, vortex end atmoseal is fixed on the bearing housing, vortex end atmoseal with form the gas chamber between the bearing housing, the second annular with the turbine shaft forms second labyrinth seal structure, first labyrinth seal structure the gas chamber with second labyrinth seal structure communicates in proper order.
Wherein, the seal assembly still includes first piston ring and second piston ring, vortex end atmoseal has first spacing groove and second spacing groove, the turbine shaft has third annular and fourth annular, first piston ring sets up first spacing groove with between the third annular, the second piston ring sets up the second spacing groove with between the fourth annular.
The supporting assembly further comprises an oil baffle plate, and the oil baffle plate is fixedly connected with the bearing seat and is positioned between the bearing seat and the vortex end air seal.
The turbine shaft is provided with an oil slinger, the oil slinger is arranged in the vortex end air seal, the vortex end air seal is provided with an oil blocking ring groove and an oil return groove, and the oil blocking ring groove and the oil return groove are arranged on one side close to the oil blocking plate.
Wherein, the number of the back ring grooves is at least 3.
Wherein the number of the second ring grooves is at least 10.
According to the supercharger vortex end sealing structure for the high supercharging system, the bearing seat is fixed on the bearing shell through the fixing bolt, the radial bearing is installed on the bearing seat through the set screw, and the radial bearing supports the circumferential operation of the turbine shaft. The heat insulation wall is fixed on the bearing shell, a first annular groove is formed in the small end of the heat insulation wall, and the first annular groove and the back annular groove formed in the back of the turbine shaft wheel form a first labyrinth seal structure together; the turbine end gas seal is mounted on the bearing shell through a positioning pin, and a gas cavity is formed by the turbine end gas seal and the back end face of the turbine shaft wheel; the inner hole of the vortex end gas seal is provided with the second ring groove, and the second ring groove and the turbine shaft form a second labyrinth seal structure; the vortex end high-pressure fuel gas enters the first labyrinth seal, the fuel and the second labyrinth seal, and undergoes the processes of throttling, depressurization and re-throttling, so that the pressure and the flow of the reduced high-pressure fuel gas are greatly reduced. The pressure airflow impact on the vortex end is reduced, so that the abrasion is reduced, the service life of the whole device is prolonged, and the problem that the sealing structure of the ultrahigh-pressure supercharger fails to work on an air-oil seal in the working condition operation process of a high-speed worker is solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a structural view of a scroll end seal structure of a supercharger for a high supercharging system according to the present invention.
Fig. 2 is an enlarged view of a detail a of fig. 1.
Fig. 3 is an enlarged view of a detail B of fig. 1.
Fig. 4 is an enlarged view of a detail C of fig. 1.
FIG. 5 is a block diagram of the vortex end gas seal of the present invention.
1-supporting component, 2-sealing component, 11-bearing shell, 12-bearing seat, 13-radial bearing, 14-turbine shaft, 15-oil baffle, 21-heat insulation wall, 22-vortex end gas seal, 23-first piston ring, 24-second piston ring, 141-back ring groove, 142-third ring groove, 143-fourth ring groove, 144-oil slinger, 211-first ring groove, 212-first labyrinth seal structure, 221-second ring groove, 222-gas cavity, 223-second labyrinth seal structure, 224-first limiting groove, 225-second limiting groove, 226-oil baffle ring groove and 227-oil return groove.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the utility model and are not to be construed as limiting the utility model.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 1 to 5, the present invention provides a turbine end sealing structure of a supercharger for a high supercharging system:
the sealing device comprises a supporting assembly 1 and a sealing assembly 2, wherein the supporting assembly 1 comprises a bearing shell 11, a bearing seat 12, a radial bearing 13 and a turbine shaft 14, the bearing seat 12 is fixedly arranged inside the bearing shell 11, the radial bearing 13 is fixedly arranged inside the bearing seat 12, the turbine shaft 14 is provided with a back ring groove 141, and the turbine shaft 14 is arranged inside the radial bearing 13; the sealing assembly 2 comprises a heat insulation wall 21 and a vortex end air seal 22, wherein the heat insulation wall 21 is provided with a first ring groove 211, the heat insulation wall 21 is fixed on the bearing shell 11, and the first ring groove 211 and the back ring groove 141 form a first labyrinth sealing structure 212; the turbine end gas seal 22 is provided with a second annular groove 221, the turbine end gas seal 22 is fixed on the bearing shell 11, a gas cavity 222 is formed between the turbine end gas seal 22 and the bearing shell 11, the second annular groove 221 and the turbine shaft 14 form a second labyrinth seal structure 223, and the first labyrinth seal structure 212, the gas cavity 222 and the second labyrinth seal structure 223 are sequentially communicated.
In the present embodiment, the bearing seat 12 is fixed to the bearing housing 11 by a fixing bolt, the radial bearing 13 is mounted on the bearing seat 12 by a set screw, and the radial bearing 13 supports the turbine shaft 14 for circumferential movement. The heat insulation wall 21 is fixed on the bearing shell 11, a first ring groove 211 is formed in the small end of the heat insulation wall 21, and the first ring groove 211 and the back ring groove 141 formed in the back of the turbine shaft 14 jointly form a first labyrinth seal structure 212; the turbine end gas seal 22 is mounted on the bearing shell 11 through a positioning pin, and the turbine end gas seal 22 and the back end face of the turbine shaft 14 form a gas cavity 222; the inner hole of the turbine end gas seal 22 is provided with the second annular groove 221, and the second annular groove 221 and the turbine shaft 14 form a second labyrinth seal structure 223; the vortex end high-pressure fuel gas enters the first labyrinth seal, the fuel and the second labyrinth seal, and undergoes the processes of throttling, depressurization and re-throttling, so that the pressure and the flow of the reduced high-pressure fuel gas are greatly reduced. The pressure airflow impact on the vortex end is reduced, so that the abrasion is reduced, and the service life of the whole device is prolonged.
Further, the seal assembly 2 further includes a first piston ring 23 and a second piston ring 24, the scroll end gas seal 22 has a first limit groove 224 and a second limit groove 225, the turbine shaft 14 has a third ring groove 142 and a fourth ring groove 143, the first piston ring 23 is disposed between the first limit groove 224 and the third ring groove 142, and the second piston ring 24 is disposed between the second limit groove 225 and the fourth ring groove 143.
In the present embodiment, the contact dynamic sealing between the first piston ring 23 and the second piston ring 24 is realized by the above structure, and the turbine end gas which is depressurized and throttled is sealed again, so that the effect of zero leakage of the turbine end seal of the ultrahigh-pressure supercharger is achieved.
Further, the support assembly 1 further comprises an oil baffle 15, wherein the oil baffle 15 is fixedly connected with the bearing seat 12 and is located between the bearing seat 12 and the vortex end air seal 22.
In the present embodiment, the oil deflector 15 greatly reduces the leakage of the lubricating oil by greatly throttling the lubricating oil flowing out of the radial bearing 13.
Further, the turbine shaft 14 has an oil slinger 144, the oil slinger 144 is disposed in the combustion gas cavity 222, the vortex end gas seal 22 has an oil blocking ring groove 226 and an oil return groove 227, and the oil blocking ring groove 226 and the oil return groove 227 are disposed on a side close to the oil blocking plate 15.
In the present embodiment, the oil slinger 144 can fling the lubricating oil out, and then return the lubricating oil to the oil baffle ring groove 226, and then return the lubricating oil to the oil baffle plate 15 through the oil return groove 227, thereby achieving reverse leakage of the lubricating oil to the turbine working region.
Further, the number of the back ring grooves 141 is at least 3.
In this embodiment, a plurality of the back ring grooves 141 may increase the sealing effect.
Further, the number of the second ring grooves 221 is at least 10.
In this embodiment, the plurality of second grooves 221 may further increase the sealing effect.
While the utility model has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the utility model.
Claims (6)
1. A supercharger vortex end sealing structure for a high supercharging system is characterized in that,
the turbine shaft is provided with a back ring groove, and the turbine shaft is arranged in the radial bearing; the sealing assembly comprises a heat insulation wall and a vortex end air seal, the heat insulation wall is provided with a first ring groove, the heat insulation wall is fixed on the bearing shell, and the first ring groove and the back ring groove form a first labyrinth sealing structure; vortex end atmoseal has the second annular, vortex end atmoseal is fixed on the bearing housing, vortex end atmoseal with form the gas chamber between the bearing housing, the second annular with the turbine shaft forms second labyrinth seal structure, first labyrinth seal structure the gas chamber with second labyrinth seal structure communicates in proper order.
2. The scroll seal structure of a supercharger for a high supercharging system according to claim 1,
the seal assembly further comprises a first piston ring and a second piston ring, the vortex end gas seal is provided with a first limiting groove and a second limiting groove, the turbine shaft is provided with a third ring groove and a fourth ring groove, the first piston ring is arranged between the first limiting groove and the third ring groove, and the second piston ring is arranged between the second limiting groove and the fourth ring groove.
3. The scroll seal structure of a supercharger for a high supercharging system according to claim 1,
the supporting component further comprises an oil baffle plate, and the oil baffle plate is fixedly connected with the bearing seat and is positioned between the bearing seat and the vortex end air seal.
4. The scroll seal structure of a supercharger for a high supercharging system according to claim 3,
the turbine shaft is provided with an oil slinger which is arranged in the vortex end air seal, the vortex end air seal is provided with an oil blocking ring groove and an oil return groove, and the oil blocking ring groove and the oil return groove are arranged on one side close to the oil blocking plate.
5. The scroll seal structure of a supercharger for a high supercharging system according to claim 1,
the number of the back ring grooves is at least 3.
6. The scroll seal structure of a supercharger for a high supercharging system according to claim 1,
the number of the second ring grooves is at least 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123210114.3U CN216518165U (en) | 2021-12-20 | 2021-12-20 | Supercharger vortex end sealing structure for high supercharging system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123210114.3U CN216518165U (en) | 2021-12-20 | 2021-12-20 | Supercharger vortex end sealing structure for high supercharging system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216518165U true CN216518165U (en) | 2022-05-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123210114.3U Active CN216518165U (en) | 2021-12-20 | 2021-12-20 | Supercharger vortex end sealing structure for high supercharging system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216518165U (en) |
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2021
- 2021-12-20 CN CN202123210114.3U patent/CN216518165U/en active Active
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