CN210396820U - Turbocharger thrust structure and turbocharger thereof - Google Patents
Turbocharger thrust structure and turbocharger thereof Download PDFInfo
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- CN210396820U CN210396820U CN201921209299.6U CN201921209299U CN210396820U CN 210396820 U CN210396820 U CN 210396820U CN 201921209299 U CN201921209299 U CN 201921209299U CN 210396820 U CN210396820 U CN 210396820U
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Abstract
The utility model relates to a turbo charger technical field discloses a turbo charger thrust structure. The turbocharger thrust structure comprises a turbine rotor shaft, a floating bearing, an impeller, a turbine and a middle body, wherein the turbine rotor shaft is arranged in the floating bearing in a penetrating manner, the two ends of the turbine rotor shaft are respectively connected with the impeller and the turbine, the floating bearing is fixed in the middle body, a sealing sleeve is sleeved on an air compression end of the turbine rotor shaft, and the turbine rotor shaft comprises a turbine rotor small shaft positioned at the air compression end and a turbine rotor large shaft connected with the turbine; the turbine rotor large shaft is located one side of the air compression end and extends out of the floating bearing, the sealing sleeves are sleeved on the turbine rotor large shaft and the turbine rotor small shaft and are respectively provided with a first inner hole and a second inner hole corresponding to the turbine rotor large shaft and the turbine rotor small shaft, and an inner hole step formed by the first inner hole and the second inner hole is positioned with a turbine rotor shaft step formed by the turbine rotor large shaft and the turbine rotor small shaft.
Description
Technical Field
The utility model relates to a turbo charger technical field specifically relates to a turbo charger thrust structure.
Background
The turbocharger turbine utilizes the energy of combustion gas to drive the compressor to compress the density of the intake gas so as to improve the intake density, so that the internal combustion engine achieves higher combustion efficiency and realizes more work output. In the working process of the internal combustion engine, the combustion working condition can be adjusted and changed from time to time according to the output requirement. The engine control unit ECU automatically calculates and outputs a control command to the turbocharger control unit to control the operating speed of the turbocharger. The axial force of the gas on the impeller of the compressor end of the turbocharger and the axial force of the gas on the turbine end of the turbocharger are not equal in most of time in the working process, so that the turbocharger needs an intermediate assembly to have the thrust function to axially position the rotor system.
As shown in fig. 1-2, the turbocharger in the prior art includes a turbine rotor shaft 101, a floating bearing 102, an impeller 103, a turbine 104, and a middle body 105, the turbine rotor shaft 101 is inserted into the floating bearing 102, and two ends of the turbine rotor shaft are respectively connected with the impeller 103 and the turbine 104, the floating bearing 102 is fixed in the middle body 105, a gland bush 106 is sleeved on a compression end of the turbine rotor shaft 101, and the turbine rotor shaft 101 includes a turbine rotor small shaft 1011 located at the compression end and a turbine rotor large shaft 1012 connected with the turbine 104. The thrust action of the structure is realized by the following scheme: the right end surface 1061 of the seal cover 106 cooperates with the floating bearing 102 to restrict the movement of the turbine rotor shaft 101 in the direction of the turbine 104, and the right end surface 1012 of the turbine rotor shaft cooperates with the floating bearing 102 to restrict the movement of the turbine rotor shaft 101 in the direction of the impeller 103.
As shown in fig. 3, the axial force applied to the turbine rotor shaft system (the turbine rotor shaft and the connected impeller and turbine) mainly includes four parts: the axial pressure of gas before the impeller, the axial pressure of gas at the back of the impeller, the axial pressure of gas at the outlet of the turbine and the axial pressure of gas at the back of the turbine are complex in working condition of the supercharger, the axial pressure changes at multiple ends, the axial force direction of a rotor system changes along with the working condition of the supercharger, when the axial force borne by the rotor system enables a turbine rotor shaft to be in a stretching state, the problem of stress concentration easily occurs on the step surface of a small shaft and a large shaft of the turbine rotor, and the reliability of the rotor system is reduced.
In addition, the patent search finds that the intermediate assembly for the turbocharger disclosed in the Chinese patent CN101413425A, the turbocharger disclosed in the Chinese patent CN206299454U and the novel turbocharger disclosed in the Chinese patent CN204140200U all adopt the structure.
The above structure is a conventional means in the field, and the present application aims to provide a novel turbocharger thrust structure which solves the problem of stress concentration on the step surface of the turbine rotor shaft and improves the reliability of the rotor system, by breaking the conventional means in the field.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a turbo charger thrust structure in order to overcome the problem that turbine rotor shaft step face stress concentration that prior art exists leads to turbine rotor system reliability to reduce.
The purpose of the utility model is realized through the following scheme:
the thrust structure of the turbocharger comprises a turbine rotor shaft, a floating bearing, an impeller, a turbine and a middle body, wherein the turbine rotor shaft is arranged in the floating bearing in a penetrating mode, two ends of the turbine rotor shaft are respectively connected with the impeller and the turbine, the floating bearing is fixed in the middle body, a sealing sleeve is sleeved on an air compression end of the turbine rotor shaft, and the turbine rotor shaft comprises a small turbine rotor shaft located at the air compression end and a large turbine rotor shaft connected with the turbine;
the turbine rotor large shaft is located one side of the air compression end and extends out of the floating bearing, the sealing sleeves are sleeved on the turbine rotor large shaft and the turbine rotor small shaft and are respectively provided with a first inner hole and a second inner hole corresponding to the turbine rotor large shaft and the turbine rotor small shaft, and an inner hole step formed by the first inner hole and the second inner hole is positioned with a turbine rotor shaft step formed by the turbine rotor large shaft and the turbine rotor small shaft.
Under the condition that the mounting position and the axial length of the sealing sleeves are not changed, the extending distance of the large turbine rotor shaft cannot extend out of the sealing sleeves at the farthest, the sealing sleeves can be sleeved on the small turbine rotor shaft and the large turbine rotor shaft, and inner hole steps are formed.
The utility model discloses a principle lies in through the institutional advancement to turbine rotor axle and seal cover, and it is outside one side that is located the end of calming the anger with the turbine rotor main shaft extends to the floating bearing to extend to the outer compressor end of floating bearing with turbine rotor axle step, utilize the hole step of seal cover to turbine rotor axle step location, shift turbine rotor main shaft with the tensile stress that turbine rotor axle step received ingeniously.
Preferably, the first inner hole is matched with the turbine rotor large shaft in a mode of meeting the requirement that the axial force is greater than the axial thrust force of the turbine rotor large shaft.
Preferably, the first inner hole is in interference fit with the turbine rotor large shaft.
Preferably, the first inner hole is matched with the turbine rotor large shaft in a threaded connection mode.
Preferably, the first inner hole is matched with the turbine rotor large shaft in a key positioning mode.
Preferably, the second inner hole is matched with the small shaft of the turbine rotor in a clearance fit mode.
Another object of the utility model is to provide a turbo charger, including above-mentioned turbo charger thrust structure.
Compared with the prior art, the utility model discloses possess following advantage:
the utility model discloses on prior art's basis, improve the structure of turbine rotor axle and seal cover, extend to the floating bearing outside the turbine rotor main shaft, install the seal cover on extending to the turbine rotor main shaft outside the floating bearing, and a terminal surface through the first hole of seal cover and the step face location of turbine rotor axle, when rotor system receives axial force makes the turbine rotor axle be in tensile state, the concentrated stress that the step face of turbine rotor axle received shifts to the turbine rotor main shaft, very big improvement the intensity of turbocharger rotor system, turbocharger's product reliability has been improved.
The utility model discloses can directly use on current turbo charger, need not to change current turbo charger's other parts, only need to change the structure of turbine rotor shaft and the structure of seal cover can further improve the intensity of improving turbo charger rotor system, broken the familiar structure in this field, have simple structure, improve with low costs, use advantages such as product reliability reinforce.
The utility model discloses first hole is interference fit with the turbine rotor main shaft, and the second hole is clearance fit with the turbine rotor staff, through optimizing the cooperation relation between seal cover and the turbine rotor axle, further shifts the concentrated stress that the step face of turbine rotor axle received to the turbine rotor main shaft on.
Other features and advantages of the present invention will be described in detail in the detailed description which follows.
Drawings
FIG. 1 is a schematic view of a prior art turbocharger configuration.
FIG. 2 is a schematic view of a prior art turbine rotor shaft mated with a gland.
FIG. 3 is a turbine rotor system force profile.
FIG. 4 is a schematic view of a turbocharger thrust structure in embodiment 1.
FIG. 5 is a schematic view of the structure of the turbine rotor shaft matched with the sealing sleeve in the embodiment 1.
Description of the reference numerals
1-turbine rotor shaft, 2-floating bearing, 3-impeller, 4-turbine, 5-intermediate body, 6-seal cartridge, 11-turbine rotor small shaft, 12-turbine rotor large shaft, 13-turbine rotor shaft step, 61-first inner hole, 62-second inner hole, 62-inner hole step.
Detailed Description
The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings. It is to be understood that the description of the embodiments herein is for purposes of illustration and explanation only and is not intended to limit the invention.
As shown in fig. 4-5, the embodiment provides a turbocharger thrust structure, including turbine rotor shaft 1, floating bearing 2, impeller 3, turbine 4 and midbody 5, turbine rotor shaft 1 wears to locate in floating bearing 2 and both ends are connected with impeller 3 and turbine 4 respectively, floating bearing 2 fixes in midbody 5, the cover has seal cover 6 on the compressor end of turbine rotor shaft 1, turbine rotor shaft 1 is including being located the turbine rotor small shaft 11 of compressor end and the turbine rotor large shaft 12 of connecting turbine 4.
The turbine rotor large shaft 12 is located at one side of the compression end and extends out of the floating bearing 2, the sealing sleeve 6 is sleeved on the turbine rotor small shaft 11 and the turbine rotor large shaft 12 and is respectively provided with a first inner hole 61 and a second inner hole 62 corresponding to the turbine rotor large shaft 12 and the turbine rotor small shaft 11, and an inner hole step 63 formed by the first inner hole 61 and the second inner hole 62 is positioned with a turbine rotor shaft step 13 formed by the turbine rotor large shaft 12 and the turbine rotor small shaft 11.
Under the condition that the installation position and the axial length of the sealing sleeve 6 are not changed, the extending distance of the large turbine rotor shaft 12 is farthest and cannot extend out of the sealing sleeve 6, the sealing sleeve 6 is ensured to be sleeved on the small turbine rotor shaft 11 and the large turbine rotor shaft 12, and an inner hole step 63 is formed.
Through the scheme, the present embodiment extends the turbine rotor shaft 12 to the outside of the floating bearing 2 on the existing structure through the structural improvement of the turbine rotor shaft 1 and the sealing sleeve 6, so as to extend the turbine rotor shaft step 13 to the outside of the floating bearing 2 at the compressor end, and the inner hole step 62 of the sealing sleeve 6 is utilized to position the turbine rotor shaft step 13, so that the tensile stress applied to the turbine rotor shaft step 13 is skillfully transferred to the turbine rotor shaft 12.
In the embodiment, the left end (air compression end) of the turbine rotor large shaft 12 is limited by the inner hole step 62 of the sealing sleeve 6 and the left end of the floating bearing 2, the right end of the turbine rotor large shaft 12 is limited by the right end of the floating bearing 2, and the floating bearing 2 is fixed in the intermediate body 5. Although the structure of the turbine rotor shaft 1 and the sealing sleeve 6 is changed in the embodiment, the two ends of the turbine rotor shaft 1 can still be matched with the floating bearings 2, and the movement of the turbine rotor shaft 1 towards the impeller 2 or the turbine 8 is limited.
It should be noted here that the sealing sleeve 6 has various fitting manners with the turbine rotor shaft 1, such as interference fit, transition fit, clearance fit, and the like. In order to further transfer the tensile stress on the turbine rotor shaft step 13 to the turbine rotor large shaft 12, the first inner hole 61 and the turbine rotor large shaft 12 are matched in a manner that the axial force on the first inner hole is greater than the axial thrust of the turbine rotor large shaft 12. Specifically, in the present embodiment, the first inner hole 61 and the turbine rotor large shaft 12 are preferably in an interference fit, a threaded connection, or a key-located fit, and the second inner hole 62 and the turbine rotor small shaft 11 are preferably in a clearance fit.
It can be understood that, under the condition of not changing the structure of the turbocharger, the axial length of the turbine rotor shaft 1 is not changed, the turbine rotor small shaft 11 and the turbine rotor large shaft 12 both need to meet the condition in the sealing sleeve 6, and therefore, the extending distance of the turbine rotor large shaft 12 needs to be considered to meet the requirement in the matching mode with the first inner hole 61. For example, an interference fit manner is adopted, conditions such as the length and the interference magnitude of the interference portion where the first inner hole 61 of the sealing sleeve 6 is fitted with the large turbine rotor shaft 12 need to be satisfied, and the axial force applied to the first inner hole is greater than the axial thrust of the large turbine rotor shaft 12.
The floating bearing 2 is fixed in the intermediate body 5 through a positioning pin in the embodiment, and specifically, positioning holes matched with the positioning pin are respectively arranged in the floating bearing 2 and the intermediate body 5. The impeller 3 is fixed on the small shaft 11 of the turbine rotor and the sealing sleeve 6 through locking nuts.
The embodiment also provides a turbocharger comprising the turbocharger thrust structure.
In the embodiment, on the basis of the prior art, the structures of the turbine rotor shaft 1 and the sealing sleeve 6 are improved, and the concentrated stress on the step 13 of the turbine rotor shaft is transferred to the large turbine rotor shaft 12, so that the strength of a rotor system of the turbocharger is improved, and the product reliability of the turbocharger is improved.
The embodiment can be directly applied to the existing turbocharger, other parts of the existing dynamic turbocharger are not required to be changed, the strength of a rotor system of the turbocharger can be further improved by only changing the structure of the turbine rotor shaft 1 and the structure of the sealing sleeve 6, the familiar structure in the field is broken through, and the turbocharger rotor system has the advantages of simple structure, low improvement cost, high reliability of application products and the like.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited thereto. The technical idea of the utility model within the scope, can be right the utility model discloses a technical scheme carries out multiple simple variant, makes up with any suitable mode including each concrete technical feature. In order to avoid unnecessary repetition, the present invention does not separately describe various possible combinations. These simple variations and combinations should also be considered as disclosed in the present invention, all falling within the scope of protection of the present invention.
Claims (7)
1. A turbocharger thrust structure comprises a turbine rotor shaft, a floating bearing, an impeller, a turbine and a middle body, wherein the turbine rotor shaft is arranged in the floating bearing in a penetrating mode, the two ends of the turbine rotor shaft are respectively connected with the impeller and the turbine, the floating bearing is fixed in the middle body, a sealing sleeve is sleeved on an air compression end of the turbine rotor shaft, and the turbine rotor shaft comprises a turbine rotor small shaft located at the air compression end and a turbine rotor large shaft connected with the turbine;
the turbine rotor shaft locating device is characterized in that one side, located at the air compression end, of the turbine rotor large shaft extends out of the floating bearing, the sealing sleeves are sleeved on the turbine rotor large shaft and the turbine rotor small shaft and are respectively provided with a first inner hole and a second inner hole corresponding to the turbine rotor large shaft and the turbine rotor small shaft, and inner hole steps formed by the first inner hole and the second inner hole are located with turbine rotor shaft steps formed by the turbine rotor large shaft and the turbine rotor small shaft.
2. The turbocharger thrust structure of claim 1, wherein the first inner hole is matched with the turbine rotor large shaft in a mode that the axial force applied to the first inner hole is larger than the axial thrust force of the turbine rotor large shaft.
3. The turbocharger thrust structure of claim 2, wherein the first inner hole is in interference fit with the turbine rotor large shaft.
4. The turbocharger thrust structure of claim 2, wherein the first inner hole is matched with the turbine rotor large shaft in a threaded connection mode.
5. The turbocharger thrust structure of claim 2, wherein the first inner hole is matched with the turbine rotor large shaft in a key positioning mode.
6. The turbocharger thrust structure of claim 1, wherein the second inner hole is in clearance fit with the small turbine rotor shaft.
7. A turbocharger comprising the turbocharger thrust structure according to any one of claims 1 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921209299.6U CN210396820U (en) | 2019-07-30 | 2019-07-30 | Turbocharger thrust structure and turbocharger thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921209299.6U CN210396820U (en) | 2019-07-30 | 2019-07-30 | Turbocharger thrust structure and turbocharger thereof |
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| Publication Number | Publication Date |
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| CN210396820U true CN210396820U (en) | 2020-04-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921209299.6U Active CN210396820U (en) | 2019-07-30 | 2019-07-30 | Turbocharger thrust structure and turbocharger thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110410154A (en) * | 2019-07-30 | 2019-11-05 | 湖南天雁机械有限责任公司 | A kind of turbocharger thrust structure and its turbocharger |
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2019
- 2019-07-30 CN CN201921209299.6U patent/CN210396820U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110410154A (en) * | 2019-07-30 | 2019-11-05 | 湖南天雁机械有限责任公司 | A kind of turbocharger thrust structure and its turbocharger |
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