CN210264827U - Turbine rotor and turbocharger - Google Patents
Turbine rotor and turbocharger Download PDFInfo
- Publication number
- CN210264827U CN210264827U CN201920639464.5U CN201920639464U CN210264827U CN 210264827 U CN210264827 U CN 210264827U CN 201920639464 U CN201920639464 U CN 201920639464U CN 210264827 U CN210264827 U CN 210264827U
- Authority
- CN
- China
- Prior art keywords
- turbine rotor
- shaft
- blades
- cavity
- intermediate housing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Supercharger (AREA)
Abstract
The utility model discloses a turbine rotor and turbo charger, including wheel hub, accept the pressure of waste gas and make a plurality of first blades of wheel hub rotation, still including accepting the pressure of waste gas and make a plurality of second blades of wheel hub rotation, first blade and second blade are arranged along wheel hub's circumference in turn, the one end of second blade is located wheel hub's same circumference with the one end of first blade, the second blade is less than first blade along the axial size of wheel hub, give way the space for the gas vent that forms between two adjacent first blades. The utility model discloses a turbine rotor has the advantage that makes the exhaust resistance obtain reducing.
Description
Technical Field
The utility model relates to a turbine rotor and turbo charger.
Background
The turbocharger can improve power, reduce fuel consumption rate and reduce the size and weight of the engine without changing the structure of the engine, and is an important means for improving the dynamic property and the economical efficiency of the modern engine. The combustion condition is improved, and simultaneously, the emission of solid suspended particles, carbon monoxide and nitrogen oxide in the waste gas can be reduced.
Oil leakage often occurs during operation of the turbocharger, which is determined by the unique structure of the turbocharger. At present, the turbocharger applied to various engines generally adopts a floating bearing structure, namely a bearing and a rotor of the turbocharger, and a small gap is reserved between the bearing and a middle shell. When the turbine rotor rotates at a high speed, the high-pressure lubricating oil fills the gaps, high-pressure oil films are formed on the inner layer and the outer layer of the floating bearing, the floating bearing rotates along with the rotor shaft in the same direction, and the rotating speed of the floating bearing can reach half of that of the rotor shaft. Because a double-layer oil film is formed, high-pressure lubricating oil enters the middle shell and flows to two ends along the rotating shaft, and once the sealing structure fails, oil leakage of the supercharger can be caused. The oil leakage phenomenon of the supercharger causes the oil consumption to increase and the power of the engine to decrease. The seal ring is a core component of the turbocharger seal structure. The exhaust temperature of the gasoline engine is higher than that of the diesel engine, and the engine oil at the turbine end is easier to carbonize due to the high temperature.
The carbon deposit at the turbine end can wear the sealing ring, and the sealing ring is worn to further cause the failure of the sealing structure at the turbine end. The supercharger leaks oil, and the floating bearing cannot form a high-pressure oil film on the inner layer and the outer layer, so that the abrasion among the bearing, the rotor and the middle shell is intensified, the supercharger is damaged, and the performance of an engine is reduced.
In addition, as shown in fig. 1 and 2, for the turbine rotor 1 in the prior art, no matter how many first blades 11 are, but the size of each first blade 11 along the axial direction of the hub 10 is the same (i.e. the length of the blade is the same), these first blades 11 extend from the bottom of the hub to the top of the hub 10, i.e. one end of all the first blades 11 is located on the first circumference of the hub 10, the other end of all the first blades 11 is located on the second circumference of the hub 10, and an exhaust port 13 is formed between the other ends of two adjacent first blades 11, however, the distance between the other ends of two adjacent first blades 11 is smaller, and the exhaust port 13 is formed to be narrower, so that the resistance of the exhaust gas is increased.
Disclosure of Invention
An object of the utility model is to provide a make the turbine rotor that exhaust resistance obtains reducing.
The technical scheme for solving the technical problems is as follows:
the turbine rotor comprises a hub, a plurality of first blades and a plurality of second blades, wherein the first blades receive the pressure of exhaust gas to enable the hub to rotate, the second blades receive the pressure of the exhaust gas to enable the hub to rotate, the first blades and the second blades are alternately arranged along the circumferential direction of the hub, one ends of the second blades and one ends of the first blades are located on the same circumference of the hub, the axial size of the second blades along the hub is smaller than that of the first blades along the axial direction of the hub, and a space is reserved for an exhaust port formed between every two adjacent first blades.
The length design of second blade is less than the length of first blade, gives out the space for the gas vent that forms between two adjacent first blades, has just so increased the width of gas vent to the hindrance when having reduced the flow to the air current, to the turbine rotor that has the same blade of quantity, the structure of this embodiment compares with prior art, can make turbine rotor's conversion efficiency obtain promoting.
Another object of the present invention is to provide a turbocharger. The specific scheme is as follows:
the turbocharger comprises a shaft, a middle shell, a pinch roller and a turbine rotor, wherein at least one part of the turbine rotor is positioned outside the middle shell, one end of the turbine rotor is fixed with one end of the shaft, one end of the shaft is supported at one end of the middle shell, the middle shell is provided with an axial through hole, the shaft passes through the through hole of the middle shell, a sealing component is arranged between one end of the shaft and the middle shell, the other end of the shaft is connected with the pinch roller, a first cavity is arranged at the end where the turbine rotor and the shaft are fixed, the shaft seals the opening of the first cavity to form a first sealing cavity after the shaft and one end of the turbine rotor are fixed, a first blocking medium for blocking the turbine rotor from directly conducting heat transfer with a part of the shaft is sealed in the first sealing cavity, the first barrier medium has a thermal conductivity less than that of the shaft and the turbine rotor to reduce heat transfer of exhaust gases through the turbine rotor and the shaft to the seal assembly.
The turbocharger comprises a turbine rotor, a shaft, a middle shell and a pressing wheel, wherein at least one part of the turbine rotor is positioned outside the middle shell, one end of the turbine rotor is fixed with one end of the shaft, one end of the shaft is supported at one end of the middle shell, an axial through hole is formed in the middle shell, the shaft penetrates through the through hole of the middle shell, a sealing assembly is arranged between one end of the shaft and the middle shell, the other end of the shaft is connected with the pressing wheel, the turbocharger also comprises a heat insulation assembly for isolating the heat of waste gas and directly conducting the heat to one end of the middle shell, the heat insulation assembly is fixed at one end of the middle shell, and the heat insulation assembly is positioned between the;
the heat insulation assembly comprises a first heat insulation part and a second heat insulation part, a second cavity is formed between the first heat insulation part and the second heat insulation part, and a second blocking medium for blocking the waste gas from directly carrying out heat transfer with a part of the intermediate shell is sealed in at least the second cavity so as to reduce the heat transfer of the waste gas to the sealing assembly through the intermediate shell;
the turbine rotor is provided with a first cavity at one end fixed with the shaft, the shaft seals the opening of the first cavity to form a first sealing cavity after the shaft is fixed with one end of the turbine rotor, a first blocking medium for blocking the turbine rotor and one part of the shaft from directly carrying out heat transfer is sealed in the first sealing cavity, so that the heat of waste gas is reduced and is transferred to the sealing assembly through the turbine rotor and the shaft, and the heat conductivity coefficient of the first blocking medium is smaller than that of the shaft and the turbine rotor.
The utility model has the advantages that: after the turbine rotor is fixed with the shaft, a first sealing cavity is formed between the turbine rotor and the shaft after the turbine rotor is fixed with the shaft. This not only reduces the contact area between the turbine rotor and the shaft, but also reduces heat transfer to the seal ring. Moreover, the first blocking medium sealed in the first cavity is in a static state, the thermal conductivity coefficient of the static first blocking medium is smaller than that of the turbine rotor and the shaft, and convection heat transfer cannot be generated, so that the structure is beneficial to further reducing heat conducted from the turbine rotor and the shaft to the sealing assembly, the temperature of the sealing assembly is reduced, and lubricating oil carbon deposition and sealing assembly failure are avoided.
Drawings
FIG. 1 is a schematic structural view of a prior art turbine rotor;
FIG. 2 is a cross-sectional structural schematic view of a prior art turbine rotor;
FIG. 3 is a cross-sectional view of a turbocharger according to the present invention;
FIG. 4 is a schematic view of the outer structure of the turbine rotor of the present invention;
FIG. 5 is a schematic cross-sectional view of a first turbine rotor according to the present invention;
FIG. 6 is a schematic view of a turbine rotor and shaft connection according to the present invention;
FIG. 7 is a schematic cross-sectional view of a second turbine rotor according to the present invention;
1 is a turbine rotor, 10 is a hub, 11 is a first blade, 12 is a second blade, 13 is an exhaust port, 14 is a space, 15 is a first cavity, and 16 is a first barrier medium;
2 is a shaft, 20 is a first ring groove, 21 is a second ring groove, 22 is a first sealing ring, and 23 is a second sealing ring;
3 is a middle shell, 30 is a channel, and 31 is an oil storage cavity;
4 is a pinch roller;
Detailed Description
The first embodiment:
as shown in fig. 3, the turbocharger of the present invention, including the turbine rotor 1, the shaft 2, the middle housing 3, and the pinch roller 4, will be described in detail below for each part and the relationship between them:
as shown in fig. 3 to 5, at least a part of the turbine rotor 1 is located outside the middle casing 3, the turbine rotor 1 includes a hub 10, a plurality of first blades 11 receiving pressure of exhaust gas to rotate the hub, and a plurality of second blades 12 receiving pressure of exhaust gas to rotate the hub, the first blades 11 and the second blades 12 are alternately arranged along a circumferential direction of the hub, one end of each of the second blades 12 and one end of each of the first blades 11 are located on the same circumference of the hub 10, a dimension of each of the second blades 12 in an axial direction of the hub 10 is smaller than a dimension of each of the first blades 11 in the axial direction of the hub 10, that is, a length of each of the second blades 12 is smaller than a length of each of the first blades 11, and a space 14 is provided for an exhaust port 13 formed between two adjacent first blades 11.
As shown in fig. 3 to 5, in the present embodiment, the length of the second blade 12 is designed to be smaller than the length of the first blade 11, and a space 14 is provided for the exhaust port 13 formed between two adjacent first blades 11, so that the width of the exhaust port 13 is increased, and the obstruction to the flow of the air current is reduced, and for the turbine rotor 1 having the same number of blades, the structure of the present embodiment can improve the conversion efficiency of the turbine rotor 1 compared with the prior art. And if the size of the gas vent of the turbine rotor among the prior art is great, namely the interval between two first blades 11 is great, to such structure, second blade 12 is set up between two first blades to this embodiment, adds second blade 12 after, neither influences the size of gas vent, has increased the pressure area that the atress accepted the waste gas again to make the conversion efficiency of turbine rotor 1 obtain promoting.
As shown in fig. 3 to 6, one end of the turbine rotor 1 is fixed to one end of the shaft 2, the turbine rotor 1 and the shaft 2 are preferably fixed by friction welding, one end of the shaft is supported at one end of the middle housing 3, an axial through hole is formed in the middle housing 3, the shaft 2 penetrates through the through hole of the middle housing 3, a sealing assembly is arranged between one end of the shaft 3 and the middle housing, and the other end of the shaft 2 is connected with the pinch roller 4. Shaft 2 is connected and is equipped with first annular 20 and second annular 21 on the global of the one end of turbine rotor 1 at least, seal assembly includes first sealing ring 22 and second sealing ring 23, and first sealing ring 22 is installed in first annular 20, and second sealing ring 23 is installed in second annular 21, and first sealing ring 22 and second sealing ring 23 cooperate with the hole wall face of the through-hole of middle casing 3 respectively to sealed shaft 2 and middle casing 3 prevents that lubricating oil from leaking.
As shown in fig. 3 to 6, the shaft 2 of the present embodiment has at least two ring grooves, and each ring groove has a sealing ring mounted therein, for the purpose of: exhaust gas temperature of internal-combustion engine is very high (the temperature of the exhaust gas of gasoline engine can be higher than the temperature of the exhaust gas of diesel engine), waste gas acts on turbine rotor 1 back, the heat transmits the one end of axle 2 through turbine rotor 1, consequently, the heat of 2 one ends of axle risees the back, let the lubricating oil of flow direction 2 one end carbonize more easily and arouse the carbon deposit on the sealing ring, the carbon deposit can wear and tear the sealing ring, lead to the seal structure inefficacy of 2 one ends of axle, lead to the booster oil leakage. Through the design have twice seal ring structure, first sealing ring 22 satisfies the demand of sealed function, and second sealing ring 23 further promotes sealing performance, prevents to lead to seal structure to become invalid because of the sealing ring wearing and tearing.
As shown in fig. 3 to 6, the sealing assembly is made of M2 molybdenum-based high-speed steel. The first seal ring 22 and the second seal ring 23 are made of M2 molybdenum-based high-speed steel. The M2 molybdenum series high-speed steel has the characteristics of good hardness and wear resistance. In the working process of the turbocharger, the whole middle shell 3 is not completely fixed when viewed from the axial direction, and small deviation continuously occurs under the action of the axial force of the pinch roller 4, the axial force of the turbine and the thrust force of the thrust bearing. The intermediate housing 3 is slightly axially displaced, and the first seal ring 22 and the second seal ring 23 instantaneously rub against the intermediate housing 3, so that the seal rings need to be made of materials with good wear resistance. The exhaust temperature of the gasoline engine is higher than that of the diesel engine, the high temperature of the exhaust gas of the engine is continuously introduced into the turbine end of the supercharger, and the engine oil is coked and deposited with carbon, so that the sealing ring is further abraded. The M2 molybdenum series high-speed steel has the advantages of small carbide nonuniformity and higher toughness, and can better cope with the working conditions. Therefore, the sealing ring is made of M2 molybdenum high-speed steel, so that the service life of the sealing ring can be effectively prolonged, and the sealing reliability of the supercharger is improved.
As shown in fig. 3 to 6, the intermediate housing 3 is provided with a passage 30 through which lubricating oil flows, an inlet of the passage 30 is located on the outer peripheral surface of the intermediate housing 3, the passage 30 communicates with an axial through hole in the intermediate housing 3, an oil reservoir chamber 31 is provided inside the intermediate housing 3, the oil reservoir chamber 31 stores a part of the lubricating oil so as to always provide lubrication to the shaft 2, and the oil reservoir chamber 31 is located near the end of the shaft 2 where a seal assembly is provided.
As shown in fig. 3 to 6, a first cavity 15 is disposed at one end of the turbine rotor 1 fixed to the shaft 2, the shaft 2 seals a mouth of the first cavity 15 after the shaft 2 is fixed to one end of the turbine rotor 1 to form a first sealed cavity, a first blocking medium 16 for blocking the turbine rotor from directly transferring heat with a part of the shaft is sealed in the first sealed cavity to reduce heat transfer of the exhaust gas to the sealing assembly through the turbine rotor and the shaft, and a thermal conductivity coefficient of the first blocking medium 16 is smaller than that of the shaft 2 and the turbine rotor 1. The first barrier medium 16 is a first gas.
As shown in fig. 3 to 6, the exhaust temperature of the gasoline engine is high, the exhaust gas is directly blown to the turbine rotor 1, heat is continuously conducted from the first blades 11 and the second blades 12 to the hub 10 having a lower temperature, and the heat is conducted to the shaft 2 through the hub 10. In the traditional machining process of the turbine rotor 1, the blank surface of the blade of the turbine rotor 1 is flat and is solid after being friction welded with the shaft 2. The heat is transferred to the sealing ring from the contact surface of the shaft 2 and the turbine rotor 1, so that lubricating oil (turbine end) flowing to one end of the shaft 2 is more easily carbonized, and the carbon deposit can abrade the sealing ring. In the present embodiment, after the first cavity 15 is disposed at the end where the turbine rotor 1 and the shaft 2 are fixed, a first sealing cavity is formed between the turbine rotor 1 and the shaft 2 after the turbine rotor 1 and the shaft 2 are friction welded. This not only reduces the contact area between the turbine rotor 1 and the shaft 2, but also reduces the heat transfer to the seal ring. Moreover, the first barrier medium 16 (gas) enclosed in the first cavity 15 is in a static state, and the static first barrier medium 16 has a smaller thermal conductivity than the turbine rotor 1 and the shaft 2, and does not generate convection heat transfer, so that the structure helps to further reduce the heat conducted from the turbine rotor 1 and the shaft 2 to the seal assembly, thereby obtaining the temperature at the seal assembly and avoiding the failure of the seal assembly.
The first blocking medium 16 is air or inert gas, and in this embodiment, the first blocking medium 16 is preferably air, and the thermal conductivity of the air at 100 ℃ is 0.031W/m · K. The inert gas may be any one of helium (He), neon (Ne), argon (Ar), krypton (Kr), and xenon (Xe), but other gas having a low thermal conductivity, such as carbon dioxide or nitrogen, may be used for the first barrier medium 16. The first barrier medium 16 may also be a solid, such as asbestos, which has a thermal conductivity of 0.15W/m.k at 100 ℃. The first barrier medium 16 may also be a liquid, such as water, which absorbs heat transferred by the turbine rotor 1 and converts the heat to steam, which has a thermal conductivity of 0.025W/m · K at 100 ℃.
As shown in fig. 3, it further includes a heat insulating assembly for insulating the exhaust gas from heat directly conducted to one end of the intermediate housing, which is fixed to one end of the intermediate housing 3, and which is located between the turbine rotor 1 and the intermediate housing 3. The heat insulation assembly comprises a first heat insulation component 5 and a second heat insulation component 6, a second cavity 7 is formed between the first heat insulation component 5 and the second heat insulation component 6, and a second blocking medium for blocking the waste gas from directly carrying out heat transfer with a part of the middle shell 3 is at least sealed in the second cavity 7 so as to reduce the heat transfer of the waste gas to the sealing assembly through the middle shell 3.
As shown in fig. 3, the first heat insulating member 5 includes a first annular member, one end of the first annular member 5 being provided with a first annular groove; the second heat insulating member 6 includes a second annular member which is fitted to the mouth of the first annular groove to form the second cavity 7. A third chamber 8 is formed between the second annular component and the intermediate housing 3, in which a third barrier medium is enclosed for blocking direct heat transfer from the exhaust gases to a part of the intermediate housing, in order to reduce the heat transfer from the exhaust gases to the sealing assembly through the intermediate housing. The second barrier medium and the third barrier medium are made of the same material as the first barrier medium 16.
As shown in fig. 3, in the present embodiment, the first heat insulating member 5 and the second heat insulating member 6 form the second cavity 7 between the first heat insulating member 5 and the second heat insulating member 6 after the first heat insulating member 5 is assembled with the intermediate case 3. The second and third insulating media are preferably air, and the heat conduction coefficient of the static air between the first and second heat-insulating members 5 and 6 is low, and convection heat transfer is not generated, so that the heat conduction of the turbine to the middle shell 3 outside the sealing ring can be effectively reduced. The seal assembly in this embodiment is composed of the first heat insulating member 5 and the second heat insulating member 6, and is combined to the second cavity 7, the third cavity 8, the second barrier medium and the third barrier medium, so that the temperature at the turbine end seal assembly is effectively reduced, and the seal assembly is prevented from being failed.
Second embodiment:
as shown in fig. 3 and 7, one end of the fixed shaft 2 of the turbine rotor 1 is provided with a first cavity 15, a first blocking medium 16 for isolating the turbine rotor 1 from the shaft 2 for direct heat transfer is enclosed in the first cavity 15, so as to reduce the heat transfer of the exhaust gas to the sealing assembly through the turbine rotor 1 and the shaft 2, and the thermal conductivity of the first blocking medium 16 is smaller than that of the shaft 2 and the turbine rotor 1. The rest of the structure is the same as the first embodiment, and is not described herein again.
The third embodiment:
as shown in fig. 3, the difference from the first embodiment is that: the heat insulation assembly is fixed at one end of the middle shell, and the heat insulation assembly is positioned between the turbine rotor 1 and the middle shell 3; the heat insulation assembly comprises a first heat insulation component 5 and a second heat insulation component 6, a second cavity 7 is formed between the first heat insulation component 5 and the second heat insulation component 6, and a second blocking medium for blocking the waste gas from directly carrying out heat transfer with a part of the middle shell is at least sealed in the second cavity 7 so as to reduce the heat transfer of the waste gas to the sealing assembly through the middle shell 3.
In the case of several embodiments of the turbocharger described above, the aim is to reduce the heat transfer of the exhaust gases to the sealing assembly, so as to avoid the failure of the sealing assembly and the leakage of lubricating oil.
Claims (10)
1. The turbine rotor comprises a hub and a plurality of first blades which receive the pressure of waste gas to enable the hub to rotate, and is characterized by further comprising a plurality of second blades which receive the pressure of the waste gas to enable the hub to rotate, wherein the first blades and the second blades are alternately arranged along the circumferential direction of the hub, one ends of the second blades and one ends of the first blades are located on the same circumference of the hub, and the axial size of the second blades along the hub is smaller than that of the first blades along the axial direction of the hub, so that a space is reserved for an exhaust port formed between every two adjacent first blades.
2. A turbocharger, comprising a shaft, an intermediate housing, a pressure roller, and the turbine rotor as claimed in claim 1, wherein at least a part of the turbine rotor is located outside the intermediate housing, one end of the turbine rotor is fixed to one end of the shaft, and one end of the shaft is supported at one end of the intermediate housing, the intermediate housing is provided with an axial through hole, the shaft passes through the through hole of the intermediate housing, a sealing assembly is provided between one end of the shaft and the intermediate housing, the other end of the shaft is connected to the pressure roller, the fixed end of the turbine rotor and the shaft is provided with a first cavity, the shaft seals an opening of the first cavity after the shaft and one end of the turbine rotor are fixed to form a first sealing cavity, a first blocking medium for blocking the turbine rotor and a part of the shaft from directly conducting heat transfer is sealed in the first sealing cavity to reduce the heat transfer of exhaust gas to the sealing assembly through the turbine rotor and the shaft, the first barrier medium has a thermal conductivity less than the thermal conductivity of the shaft and the turbine rotor.
3. The turbocharger of claim 2, wherein the seal assembly comprises a first seal ring and a second seal ring.
4. The turbocharger of claim 3, wherein the seal assembly is made of M2 molybdenum-based high speed steel.
5. The turbocharger of claim 2, wherein the first barrier medium is a first gas.
6. The turbocharger of claim 2, further comprising a thermal insulation assembly that insulates heat of exhaust gas directly conducted to one end of the intermediate housing, the thermal insulation assembly being fixed to one end of the intermediate housing, and the thermal insulation assembly being located between the turbine rotor and the intermediate housing.
7. The turbocharger of claim 6, wherein the thermal isolation assembly comprises a first thermal isolation member and a second thermal isolation member, a second cavity is formed between the first thermal isolation member and the second thermal isolation member, and a second blocking medium for blocking direct heat transfer of the exhaust gas with a portion of the intermediate housing is enclosed at least in the second cavity to reduce heat transfer of the exhaust gas through the intermediate housing to the seal assembly.
8. The turbocharger according to claim 7, wherein the first heat insulating member comprises a first annular member provided at one end with a first annular groove; the second heat insulation component comprises a second annular component which is arranged at the opening of the first annular groove to form the second cavity.
9. The turbocharger of claim 8, wherein a third cavity is formed between the second annular member and the intermediate housing, and a third blocking medium for blocking direct heat transfer from the exhaust gas to a portion of the intermediate housing is enclosed within the third cavity to reduce heat transfer from the exhaust gas through the intermediate housing to the seal assembly.
10. Turbocharger, including the turbine rotor, the axle, middle casing, the pinch roller, at least a part of turbine rotor is located middle casing outside, the one end of turbine rotor is fixed with the one end of axle, and the one end of axle supports the one end at middle casing, be equipped with axial through-hole on the middle casing, the axle passes the through-hole of middle casing, be equipped with seal assembly between the one end of axle and middle casing, the other end and the pinch roller of axle are connected, a serial communication port, the one end of turbine rotor fixed axle is equipped with first cavity, it has the first separation medium that is used for keeping apart turbine rotor and axle and directly carries out the heat transfer to seal assembly has been sealed to deposit in first cavity, in order to reduce the heat of waste gas according to transmitting seal assembly through turbine rotor and axle, the coefficient of heat conductivity of first separation medium is less than the coefficient of.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920639464.5U CN210264827U (en) | 2019-05-07 | 2019-05-07 | Turbine rotor and turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920639464.5U CN210264827U (en) | 2019-05-07 | 2019-05-07 | Turbine rotor and turbocharger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210264827U true CN210264827U (en) | 2020-04-07 |
Family
ID=70023897
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920639464.5U Active CN210264827U (en) | 2019-05-07 | 2019-05-07 | Turbine rotor and turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210264827U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412542A (en) * | 2020-11-23 | 2021-02-26 | 湖南路捷道夫涡轮增压系统有限公司 | Variable-section supercharger adopting mixed flow blades |
-
2019
- 2019-05-07 CN CN201920639464.5U patent/CN210264827U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412542A (en) * | 2020-11-23 | 2021-02-26 | 湖南路捷道夫涡轮增压系统有限公司 | Variable-section supercharger adopting mixed flow blades |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP0941431B1 (en) | Pressure balanced turbocharger rotating seal | |
| CN103206271B (en) | Turbine shaft seal arrangement | |
| JP5598433B2 (en) | Turbocharger | |
| KR20120004516A (en) | Insulating spacer for ball bearing cartridge | |
| CN210264827U (en) | Turbine rotor and turbocharger | |
| CN210396887U (en) | Turbocharger | |
| CN107288741B (en) | A kind of band gets rid of the turbocharger of tank structure | |
| CN113090337A (en) | Reverse shaft sealing device for double-rotor aircraft engine | |
| CN210889435U (en) | Sealing structure between rotating parts of compressor | |
| CN209875952U (en) | Dynamic sealing device suitable for high speed and high pressure and aircraft | |
| CN110159419A (en) | Turbocharger | |
| CN108019243A (en) | A kind of integral bearing A seating turbine | |
| CN218376590U (en) | Bearing cooling device of air bearing turbocharger | |
| CN115217536B (en) | Intermediate fulcrum bearing cavity structure of counter-rotating turbine | |
| CN115030784A (en) | Bearing cooling device of air bearing turbocharger | |
| CN201037539Y (en) | Rotary air preheater end axle sealing device | |
| CN210829412U (en) | Radial steam turbine main shaft end bearing structure | |
| CN111396197A (en) | Air separator of gas turbine | |
| CN217652953U (en) | Solar thermal energy power generation high temperature molten salt pump middle bearing seat subassembly structure | |
| CN2929194Y (en) | Small turbocharger with mixed flow turbine and water cooling bearing | |
| CN220204131U (en) | Sliding bearing, star wheel mechanism and single screw compressor | |
| CN109707467B (en) | Carbon deposition prevention turbocharger | |
| CN218953379U (en) | High-reliability turbocharger rotor system | |
| CN220227532U (en) | Radial shaft sleeve structure of high-speed centrifugal air compressor | |
| CN212003353U (en) | Air separator of gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |