CN110159419A - Turbocharger - Google Patents
Turbocharger Download PDFInfo
- Publication number
- CN110159419A CN110159419A CN201910374125.3A CN201910374125A CN110159419A CN 110159419 A CN110159419 A CN 110159419A CN 201910374125 A CN201910374125 A CN 201910374125A CN 110159419 A CN110159419 A CN 110159419A
- Authority
- CN
- China
- Prior art keywords
- axis
- middle casing
- turbine rotor
- cavity
- exhaust gas
- 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.)
- Pending
Links
- 230000004888 barrier function Effects 0.000 claims abstract description 37
- 238000007789 sealing Methods 0.000 claims description 41
- 229910000997 High-speed steel Inorganic materials 0.000 claims description 6
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 6
- 229910052750 molybdenum Inorganic materials 0.000 claims description 6
- 239000011733 molybdenum Substances 0.000 claims description 6
- 239000010687 lubricating oil Substances 0.000 abstract description 11
- 239000007789 gas Substances 0.000 description 28
- 239000003921 oil Substances 0.000 description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 6
- 229910052799 carbon Inorganic materials 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 230000003068 static effect Effects 0.000 description 5
- 239000006071 cream Substances 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 239000000306 component Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 239000010425 asbestos Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000001965 increasing effect Effects 0.000 description 2
- 239000011261 inert gas Substances 0.000 description 2
- 239000010721 machine oil Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910052895 riebeckite Inorganic materials 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 239000000872 buffer Substances 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000006735 deficit Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 229910052743 krypton Inorganic materials 0.000 description 1
- DNNSSWSSYDEUBZ-UHFFFAOYSA-N krypton atom Chemical compound [Kr] DNNSSWSSYDEUBZ-UHFFFAOYSA-N 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 229910052754 neon Inorganic materials 0.000 description 1
- GKAOGPIIYCISHV-UHFFFAOYSA-N neon atom Chemical compound [Ne] GKAOGPIIYCISHV-UHFFFAOYSA-N 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000008275 solid aerosol Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 229910052724 xenon Inorganic materials 0.000 description 1
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a kind of turbocharger, at least part of turbine rotor is located at outside middle casing, one end of turbine rotor and one end of axis are fixed, and one end of axis is supported on one end of middle casing, middle casing is equipped with axial through-hole, axis passes through the through-hole of middle casing, seal assembly is equipped between one end and middle casing of axis, the other end of axis is connect with pinch roller, one end that turbine rotor and axis are fixed is equipped with the first cavity, the axis is sealed to form first annular seal space the oral area of the first cavity after one end of axis and turbine rotor is fixed, seal the first barrier medium that a part for obstructing turbine rotor and axis directly carries out hot transmitting up for safekeeping in first annular seal space, seal assembly is transmitted to according to by turbine rotor and axis to reduce the heat of exhaust gas, the thermal coefficient of first barrier medium is less than axis and turbine rotor Thermal coefficient.Cause the leakage of lubricating oil the invention can avoid the failure of seal assembly.
Description
Technical field
The present invention relates to technical field of engines, in particular to a kind of turbocharger.
Background technique
Hoisting power in the case where engine structure can not be changed using turbocharger, reduce fuel consumption rate, contracting
The size and weight of puffer are the important means that Modern Engine improves dynamic property and economy.Improving burning condition
While, it can also reduce the discharge of solid aerosol in exhaust gas, carbon monoxide, oxynitrides.
It often will appear oil leakage phenomenon during turbocharger operation, this is determined by the unique structure of turbocharger
Fixed.The turbocharger applied on various engines at present generallys use floating bearing structure, i.e., the bearing of booster and
There are small gaps between each other for rotor, bearing and middle casing.When turbine rotor high speed rotation, the lubricating oil of high pressure
Just be full of these gaps, in floating bearing in inside and outside two layers of formation high pressure oil film, floating bearing with armature spindle rotating Vortex, turn
Speed can achieve the half of armature spindle revolving speed.Due to double-layer oil film to be formed, the lubricating oil of high pressure can enter middle casing simultaneously
It is flowed along axial ends is turned, once sealing structure failure will result in booster oil leak.Oil leakage phenomenon, machine oil occur for booster
Consumption increases, engine power declines.Sealing ring is the core component of seal structure of turbocharger.And gasoline engine exhaust temperature
Degree is higher than diesel engine, and high temperature can allow the machine oil of turbine end to be easier to be carbonized.
Turbine end carbon distribution can wear sealing ring, and seal wears cause turbine end sealing structure to fail in turn.Booster leakage
Oil, floating bearing do not become high pressure oil film inside and outside two layers, to aggravate the abrasion between bearing and rotor, middle casing, lead
Turbocharger impairment and engine performance is caused to reduce.Thus, it is a kind of stabilization of turbocharger design, reliable sealing structure, is
Prevent the effective means of booster oil leak.
Summary of the invention
The purpose of the present invention is to provide the turbine increasings that reduction is obtained in a kind of heat transfer to seal assembly for making exhaust gas
Depressor, to avoid seal assembly failure and cause the leakage of lubricating oil.
The technical solution for solving above-mentioned technical problem is as follows:
At least part of turbocharger, including turbine rotor, axis, middle casing, pinch roller, turbine rotor is located at centre
Hull outside, one end of turbine rotor and one end of axis are fixed, and one end of axis is supported on one end of middle casing, middle casing
It is equipped with axial through-hole, axis passes through the through-hole of middle casing, and seal assembly, axis are equipped between one end and middle casing of axis
The other end connect with pinch roller, the fixed one end of turbine rotor and axis is equipped with the first cavity, and one end of axis and turbine rotor is fixed
The axis is sealed to form first annular seal space the oral area of the first cavity afterwards, has sealed up for safekeeping in first annular seal space for obstructing whirlpool
A part of wheel rotor and axis directly carries out the first barrier medium of hot transmitting, to reduce the heat of exhaust gas according to passing through turbine rotor
And axis is transmitted to seal assembly, the thermal coefficient of the first barrier medium is less than the thermal coefficient of axis and turbine rotor.
At least part of turbocharger, including turbine rotor, axis, middle casing, pinch roller, turbine rotor is located at centre
Hull outside, one end of turbine rotor and one end of axis are fixed, and one end of axis is supported on one end of middle casing, middle casing
It is equipped with axial through-hole, axis passes through the through-hole of middle casing, and seal assembly, axis are equipped between one end and middle casing of axis
The other end connect with pinch roller, one end of turbine rotor fixing axle is equipped with the first cavity, sealed up for safekeeping in the first cavity for every
From the first barrier medium that turbine rotor and axis directly carry out hot transmitting, with reduce the heat of exhaust gas according to by turbine rotor and
Axis is transmitted to seal assembly, and the thermal coefficient of the first barrier medium is less than the thermal coefficient of axis and turbine rotor.
At least part of turbocharger, including turbine rotor, axis, middle casing, pinch roller, turbine rotor is located at centre
Hull outside, one end of turbine rotor and one end of axis are fixed, and one end of axis is supported on one end of middle casing, middle casing
It is equipped with axial through-hole, axis passes through the through-hole of middle casing, and seal assembly, axis are equipped between one end and middle casing of axis
The other end connect with pinch roller, further include that the heat of exhaust gas is isolated to be directly transferred to the insulating assembly of middle casing one end, should be every
Hot component is fixed on one end of middle casing, and insulating assembly is between turbine rotor and middle casing；
Insulating assembly includes the first heat insulating member and the second heat insulating member, the first heat insulating member and the second heat insulating member it
Between be formed with the second cavity, at least seal a part for obstructing exhaust gas and middle casing up for safekeeping in the second cavity and directly carry out
Second barrier medium of heat transmitting, to reduce the heat of exhaust gas by being transmitted to seal assembly on middle casing.
Advantages of the present invention are as follows: after the fixed one end of turbine rotor and axis is equipped with the first cavity, turbine rotor be used for axis
After being fixed, first annular seal space can be formed between turbine rotor and axis.Not only make the contact surface of turbine rotor and axis in this way
Product reduces, and heat is transmitted to the also few of sealing ring.Moreover, the first barrier medium sealed up for safekeeping in the first cavity is in static shape
State, the thermal conductivity ratio turbine rotor and axis of the first static barrier medium will be small, and will not generate convective heat transfer, therefore,
This structure helps to be further reduced the heat that seal assembly is transmitted to from turbine rotor, axis, to make at seal assembly
Temperature is reduced, and lubricating oil carbon distribution and seal assembly is avoided to fail.
Detailed description of the invention
Fig. 1 is the outline structural diagram of existing turbine rotor；
Fig. 2 is the schematic diagram of the section structure of existing turbine rotor；
Fig. 3 is the sectional structure chart of turbocharger of the invention；
Fig. 4 is the outline structural diagram of the turbine rotor in the present invention；
Fig. 5 is the schematic diagram of the section structure of the first turbine rotor in the present invention；
Fig. 6 is the schematic diagram of the turbine rotor and axis connection in the present invention；
Fig. 7 is the schematic diagram of the section structure of second of turbine rotor in the present invention；
1 is turbine rotor, and 10 be wheel hub, and 11 be the first blade, and 12 be the second blade, and 13 be exhaust outlet, and 14 be space, 15
It is the first barrier medium for the first cavity, 16；
2 be axis, and 20 be the first annular groove, and 21 be the second annular groove, and 22 be the first sealing ring, and 23 be the second sealing ring；
3 be middle casing, and 30 be channel, and 31 be shoe cream room；
4 be pinch roller；
5 be the first heat insulating member, and 6 be the second heat insulating member, and 7 be the second cavity, and 8 be third cavity.
Specific embodiment
First embodiment:
As shown in figure 3, the turbocharger in the present invention, including turbine rotor 1, axis 2, middle casing 3, pinch roller 4, below
Relationship to every part and between them is described in detail:
As shown in Figures 3 to 5, at least part of turbine rotor 1 is located at the outside of middle casing 3, the turbine rotor 1
Including wheel hub 10, receive the pressure of exhaust gas and make wheel hub rotate multiple first blades 11, receive the pressure of exhaust gas and make wheel hub
Multiple second blades 12 of rotation, the first blade 11 and the second blade 12 are alternately arranged along the circumferential direction of wheel hub, the second blade 12
One end and one end of the first blade 11 be located on the same circumference of wheel hub 10, the second blade 12 is small along the size of 10 axial direction of wheel hub
In the first blade 11 size axial along wheel hub 10, i.e. the length of the second blade 12 is adjacent less than the length of the first blade 11
The exhaust outlet 13 formed between two the first blades 11 concedes space 14.
As depicted in figs. 1 and 2, for turbine rotor in the prior art, regardless of how many first blade 11, but
Each first blade 11 is identical (i.e. the length of blade is identical), these first blades 11 along the axial size of wheel hub 10
The top of wheel hub 10 is extended to from the bottom of wheel hub, i.e., one end of all first blades 11 is located on the first circumference of wheel hub 10,
The other end of all first blades 11 is located on the second circumference of wheel hub 10, between the other end of two adjacent first blades 11
Exhaust outlet 13 is formed, however the spacing between the other end of two adjacent first blades 11 is smaller, the exhaust outlet 13 of formation is more
It is narrow, cause the resistance of exhaust to increase.
As shown in Figures 3 to 5, in the present embodiment, by the Design of length of the second blade 12 at the length less than the first blade 11
Degree, the exhaust outlet 13 formed between two neighboring first blade 11 concede space 14, and which adds the width of exhaust outlet 13
Degree, so that the obstruction when flowing to air-flow is reduced, for the turbine rotor 1 with the identical blade of quantity, this implementation
The structure of example compared with prior art, can be such that the transfer efficiency of turbine rotor 1 is promoted.And if whirlpool in the prior art
The size for taking turns the exhaust outlet of rotor is larger, i.e. spacing between two the first blades 11 is larger, for such structure, this
Embodiment adds the second blade 12 between two the first blades, after adding the second blade 12, neither influences the ruler of exhaust outlet
It is very little, and the pressure area that stress receives exhaust gas is increased, so that the transfer efficiency of turbine rotor 1 is promoted.
As shown in Figures 3 to 6, one end of turbine rotor 1 and one end of axis 2 are fixed, and turbine rotor 1 and axis 2 preferentially use
Friction welding (FW) is fixed, and one end of axis is supported on one end of middle casing 3, and middle casing 3 is equipped with axial through-hole, and axis 2 passes through
The through-hole of middle casing 3, is equipped with seal assembly between one end and middle casing of axis 3, and the other end of axis 2 is connect with pinch roller 4.
Axis 2 connects on the circumferential surface of one end of turbine rotor 1 at least provided with the first annular groove 20 and the second annular groove 21, and the seal assembly includes
First sealing ring 22 and the second sealing ring 23, the first sealing ring 22 are mounted in the first annular groove 20, the installation of the second sealing ring 23
In the second annular groove 21, the first sealing ring 22 and the second sealing ring 23 cooperate with the wall surface of the hole of the through-hole of middle casing 3 respectively, from
And axis 2 and middle casing 3 are sealed, prevent lubricating oil from leaking.
As shown in Figures 3 to 6, two stage property annular grooves are at least provided on the axis 2 in the present embodiment, and in each annular groove
Sealing ring is installed, it is therefore intended that: the exhaust gas temperature of internal combustion engine discharge is very high, and (temperature that exhaust gas is discharged in gasoline engine is arranged than diesel engine
The temperature of exhaust gas can be higher out), after exhaust gas acts on turbine rotor 1, heat is transmitted to one end of axis 2 by turbine rotor 1,
Therefore, after the heat of 2 one end of axis increases, the lubricating oil for flowing to 2 one end of axis is allowed to be easier to be carbonized and cause carbon distribution on sealing ring,
Carbon distribution can wear sealing ring, cause the sealing structure of 2 one end of axis to fail, lead to booster oil leak.There are two seals by design
Ring structure, the first sealing ring 22 meet the needs of sealing function, and the further lift-off seal performance of the second sealing ring 23 is prevented because close
Seal ring wears and sealing structure is caused to fail.
As shown in Figures 3 to 6, the use M2 molybdenum high speed steel of the seal assembly is made.First sealing ring 22 and
Two sealing rings 23 are made of M2 molybdenum high speed steel.M2 molybdenum high speed steel has the characteristics that hardness and wearability are good.Turbocharging
Device during the work time, looks up from axis, and entire middle casing 3 is not completely motionless, and in 4 axial force of pinch roller, turbine wheel shaft
Stop under thrust to power and thrust bearing, small offset constantly occurs.The axial generation minor shifts of middle casing 3, first
Sealing ring 22 and the second sealing ring 23 instantaneously can also rub with middle casing 3, thus the material that wearability need to be selected good adds
Work sealing ring.And gasoline engine delivery temperature is higher than diesel engine, booster turbine end continually introduces the high temperature of engine exhaust, machine
Oily coking, carbon distribution can be further worn out sealing ring.M2 molybdenum high speed steel has carbide inhomogeneities small higher excellent with toughness
Point can preferably cope with the operating condition.Thus, sealing ring is made of M2 molybdenum high speed steel, can effectively increase sealing
The service life of ring improves the reliability of booster sealing.
As shown in Figures 3 to 6, middle casing 3 is equipped with the channel 30 for lubricating oil flow, during the entrance in channel 30 is located at
Between shell 3 outer peripheral surface on, channel 30 is connected to the axial through-hole on middle casing 3, in the inside of middle casing 3, is equipped with
Shoe cream room 31, the shoe cream room 31 store a part of lubricating oil, to be always needed for axis 2 provides lubrication, shoe cream room 31 leans on paraxial 2
End equipped with seal assembly.
As shown in Figures 3 to 6, one end that turbine rotor 1 and axis 2 are fixed is equipped with the first cavity 15, axis 2 and turbine rotor 1
One end it is fixed after the axis 2 oral area of first cavity 15 is sealed to form first annular seal space, sealed in first annular seal space
There is the first barrier medium 16 that a part for obstructing turbine rotor and axis directly carries out hot transmitting, to reduce the heat of exhaust gas
Amount is transmitted to seal assembly according to by turbine rotor and axis, and the thermal coefficient of the first barrier medium 16 is less than axis 2 and turbine
The thermal coefficient of rotor 1.
As shown in Figures 3 to 6, gasoline engine delivery temperature is high, and exhaust gas is directly blown on turbine rotor 1, and heat is constantly from the
One blade 11 and the second blade 12 are transmitted to the lower wheel hub 10 of temperature, and heat is transmitted on axis 2 by wheel hub 10.Conventional turbine
1 process of rotor, 1 blade blank face of turbine rotor are flat, and are solid after 2 friction welding (FW) of axis.Heat is by axis 2 and turbine
The contact surface of rotor 1 is transmitted on sealing ring, the lubricating oil (turbine end) for flowing to 2 one end of axis can be allowed to be easier to be carbonized, carbon distribution meeting
Wear sealing ring.In the present embodiment, after the fixed one end of turbine rotor 1 and axis 2 is equipped with the first cavity 15, turbine rotor 1 with
After carrying out friction welding (FW) for axis 2, first annular seal space can be formed between turbine rotor 1 and axis 2.Not only make turbine rotor 1 in this way
Reduce with the contact area of axis 2, heat is transmitted to the also few of sealing ring.Moreover, sealing the first barrier in the first cavity 15 up for safekeeping
Medium 16 (gas) is in static state, and the thermal conductivity ratio turbine rotor 1 and axis 2 of the first static barrier medium 16 will
It is small, and convective heat transfer will not be generated, therefore, this structure, which helps to be further reduced from turbine rotor 1, axis 2, is transmitted to sealing
The heat of component avoids seal assembly from failing so that the temperature at seal assembly be made to obtain.
First obstructs medium 16 as air or inert gas, and in the present embodiment, the first barrier medium 16 preferentially selects air,
Thermal coefficient of the air at 100 DEG C is 0.031W/mK.Inert gas can be helium (He), neon (Ne), argon (Ar), krypton
(Kr), any one in xenon (Xe), certainly, other gases that the first barrier medium 16 can also be low using thermal coefficient, example
Such as carbon dioxide, nitrogen.First barrier medium 16 can also use solid, such as asbestos, thermal coefficient at 100 DEG C of asbestos
For 0.15W/mK.After first barrier medium 16 can also select liquid, such as water, water to absorb the heat that turbine rotor 1 transmits
Water vapour is converted to, thermal coefficient of the water vapour at 100 DEG C is 0.025W/mK.
As shown in figure 3, further including that the heat of isolation exhaust gas is directly transferred to the insulating assembly of middle casing one end, this is heat-insulated
Component is fixed on one end of middle casing 3, and insulating assembly is between turbine rotor 1 and middle casing 3.Insulating assembly includes
First heat insulating member 5 and the second heat insulating member 6 are formed with the second cavity between the first heat insulating member 5 and the second heat insulating member 6
7, it at least seals a part for obstructing exhaust gas and middle casing 3 up for safekeeping in the second cavity 7 and directly carries out the second of hot transmitting
Medium is obstructed, seal assembly is transmitted to by middle casing 3 to reduce the heat of exhaust gas.
As shown in figure 3, the first heat insulating member 5 includes the first endless member, one end of first endless member 5 is equipped with first
Annular groove；Second heat insulating member 6 includes the second endless member, and the second endless member is formed after being mounted on the oral area of first annular slot
Second cavity 7.Third cavity 8 is formed between the second endless member and middle casing 3, is sealed up for safekeeping in third cavity useful
Medium is obstructed in the third that a part of barrier exhaust gas and middle casing directly carries out hot transmitting, is passed through with reducing the heat of exhaust gas
Seal assembly is transmitted on middle casing.The material of second barrier medium and third barrier medium and above-mentioned first barrier medium 16
It is identical.
As shown in figure 3, by the first heat insulating member 5 and the second heat insulating member 6 in the present embodiment, the first heat insulating member 5 with
After middle casing 3 assembles, the second cavity 7 is formed between the first heat insulating member 5 and the second heat insulating member 6.Second barrier medium
Air is preferentially used with third barrier medium, utilizes leading for air static between the first heat insulating member 5 and the second heat insulating member 6
Hot coefficient is low, and does not generate convective heat transfer, and the middle casing 3 that turbine heat is transmitted on the outside of sealing ring can be effectively reduced.This reality
The seal assembly applied in example is made of the first heat insulating member 5 and the second heat insulating member 6, is combined to the second cavity 7 to be formed, third
Cavity 8 and the second barrier medium and third obstruct medium, effectively reduce the temperature at turbine end seal assembly, avoid close
Sealing assembly failure.
Second embodiment:
As shown in Figure 3 and Figure 7, one end of 1 fixing axle 2 of turbine rotor is equipped with the first cavity 15, seals in the first cavity 15
Have and directly carry out the first barrier medium 16 of hot transmitting for turbine rotor 1 and axis 2 to be isolated, to reduce the heat of exhaust gas according to logical
It crosses turbine rotor 1 and axis 2 is transmitted to seal assembly, the thermal coefficient of the first barrier medium 16 is less than axis 2 and turbine rotor 1
Thermal coefficient.Remaining structure is identical with the first embodiment, and details are not described herein.
3rd embodiment:
As shown in figure 3, being different from the first embodiment in: further include be isolated exhaust gas heat be directly transferred to centre
The insulating assembly of shell one end, which is fixed on one end of middle casing, and insulating assembly is located at turbine rotor 1 in
Between between shell 3；Insulating assembly includes the first heat insulating member 5 and the second heat insulating member 6, the first heat insulating member 5 and second every
It is formed with the second cavity 7 between thermal part 6, at least seals one for obstructing exhaust gas and middle casing up for safekeeping in the second cavity 7
Part directly carries out the second barrier medium of hot transmitting, to reduce the heat of exhaust gas by being transmitted to sealing group on middle casing 3
Part.
For several embodiments of above-mentioned turbocharger, the purpose realized is for making the heat of exhaust gas to pass
Being delivered on seal assembly is reduced, to avoid the failure of seal assembly and cause the leakage of lubricating oil.
Claims (10)
1. at least part of turbocharger, including turbine rotor, axis, middle casing, pinch roller, turbine rotor is located at middle case
Outside body, one end of turbine rotor and one end of axis are fixed, and one end of axis is supported on one end of middle casing, on middle casing
Equipped with axial through-hole, axis passes through the through-hole of middle casing, and seal assembly is equipped between one end and middle casing of axis, axis
The other end is connect with pinch roller, which is characterized in that the fixed one end of turbine rotor and axis is equipped with the first cavity, axis and turbine rotor
The axis is sealed to form first annular seal space the oral area of the first cavity after one end is fixed, seals up for safekeeping in first annular seal space useful
The first barrier medium of hot transmitting is directly carried out in a part of barrier turbine rotor and axis, to reduce the heat of exhaust gas according to passing through
Turbine rotor and axis are transmitted to seal assembly, and the thermal coefficient of the first barrier medium is less than the thermally conductive system of axis and turbine rotor
Number.
2. turbocharger according to claim 1, which is characterized in that the seal assembly include the first sealing ring and
Second sealing ring.
3. turbocharger according to claim 2, which is characterized in that the seal assembly uses M2 molybdenum high speed steel
It is made.
4. turbocharger according to claim 1, which is characterized in that the first barrier medium is first gas.
5. turbocharger according to claim 1, which is characterized in that further include be isolated exhaust gas heat be directly transferred to
The insulating assembly of middle casing one end, which is fixed on one end of middle casing, and insulating assembly is located at turbine rotor
Between middle casing.
6. turbocharger according to claim 5, which is characterized in that insulating assembly includes the first heat insulating member and second
Heat insulating member is formed with the second cavity between the first heat insulating member and the second heat insulating member, at least seals up for safekeeping in the second cavity
There is a part for obstructing exhaust gas and middle casing directly to carry out the second barrier medium of hot transmitting, to reduce the heat of exhaust gas
Seal assembly is transmitted to by middle casing.
7. turbocharger according to claim 6, which is characterized in that the first heat insulating member includes the first endless member,
One end of first endless member is equipped with first annular slot；Second heat insulating member includes the second endless member, the second endless member
Second cavity is formed after being mounted on the oral area of first annular slot.
8. turbocharger according to claim 7, which is characterized in that the shape between the second endless member and middle casing
At third cavity, a part for obstructing exhaust gas and middle casing directly carries out hot transmitting is sealed up for safekeeping in third cavity
Three barrier media, are transmitted to seal assembly by middle casing to reduce the heat of exhaust gas.
9. at least part of turbocharger, including turbine rotor, axis, middle casing, pinch roller, turbine rotor is located at middle case
Outside body, one end of turbine rotor and one end of axis are fixed, and one end of axis is supported on one end of middle casing, on middle casing
Equipped with axial through-hole, axis passes through the through-hole of middle casing, and seal assembly is equipped between one end and middle casing of axis, axis
The other end is connect with pinch roller, which is characterized in that one end of turbine rotor fixing axle is equipped with the first cavity, seals up for safekeeping in the first cavity
Have for being isolated turbine rotor and axis directly carries out the first barrier medium of hot transmitting, to reduce the heat of exhaust gas according to passing through turbine
Rotor and axis are transmitted to seal assembly, and the thermal coefficient of the first barrier medium is less than the thermal coefficient of axis and turbine rotor.
10. at least part of turbocharger, including turbine rotor, axis, middle casing, pinch roller, turbine rotor is located at centre
Hull outside, one end of turbine rotor and one end of axis are fixed, and one end of axis is supported on one end of middle casing, middle casing
It is equipped with axial through-hole, axis passes through the through-hole of middle casing, and seal assembly, axis are equipped between one end and middle casing of axis
The other end connect with pinch roller, which is characterized in that further include be isolated exhaust gas heat be directly transferred to middle casing one end every
Hot component, which is fixed on one end of middle casing, and insulating assembly is between turbine rotor and middle casing；
Insulating assembly includes the first heat insulating member and the second heat insulating member, the shape between the first heat insulating member and the second heat insulating member
At there is the second cavity, at least seals a part for obstructing exhaust gas and middle casing up for safekeeping in the second cavity and directly carry out hot biography
The the second barrier medium passed, to reduce the heat of exhaust gas by being transmitted to seal assembly on middle casing.
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| CN201910374125.3A CN110159419A (en) | 2019-05-07 | 2019-05-07 | Turbocharger |
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| CN201910374125.3A CN110159419A (en) | 2019-05-07 | 2019-05-07 | Turbocharger |
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| CN110159419A true CN110159419A (en) | 2019-08-23 |
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| CN201910374125.3A Pending CN110159419A (en) | 2019-05-07 | 2019-05-07 | Turbocharger |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114909192A (en) * | 2021-02-10 | 2022-08-16 | 通用汽车环球科技运作有限责任公司 | Turbocharger with anti-coking coating |
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