CN106948926A - A kind of compact two-stage turbine machine - Google Patents
A kind of compact two-stage turbine machine Download PDFInfo
- Publication number
- CN106948926A CN106948926A CN201710329809.2A CN201710329809A CN106948926A CN 106948926 A CN106948926 A CN 106948926A CN 201710329809 A CN201710329809 A CN 201710329809A CN 106948926 A CN106948926 A CN 106948926A
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- CN
- China
- Prior art keywords
- turbine
- stage
- compact
- wheel shaft
- casing
- 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
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- 239000002912 waste gas Substances 0.000 claims abstract description 23
- 239000007789 gas Substances 0.000 claims abstract description 12
- 230000008676 import Effects 0.000 claims abstract description 8
- 238000005096 rolling process Methods 0.000 claims description 15
- 238000009434 installation Methods 0.000 claims description 8
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 241000233855 Orchidaceae Species 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- 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
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/004—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust drives arranged in series
-
- 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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- 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
- F01D25/30—Exhaust heads, chambers, or the like
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
-
- 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
- F01D9/00—Stators
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/048—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial admission
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention discloses a kind of compact two-stage turbine machine, including turbine wheel shaft, fixed cover is located on turbine wheel shaft successively vertically first turbine and two-stage turbine, and cover at the casing in the outside of first turbine and two-stage turbine, radial nozzles ring is provided with the import of first turbine, provided with axial nozzle ring at the import of two-stage turbine, guide housing between level is provided between axial nozzle ring and first turbine, the guide channel for guiding waste gas to enter axial nozzle ring is formed between level between guide housing and the inwall of casing, first turbine is radial-flow turbine or mixed flow turbine, two-stage turbine is axial flow turbine.Two turbine drives same axises of such a compact two-stage turbine machine, output Effective power is all supplied to compressor by waste gas after two-stage turbine does work, so as to so that compressor obtains more energy, improve the pressure ratio of turbine apparatus, exhaust gas utilization rate is higher, meanwhile, first turbine, two-stage turbine are arranged in same casing, structure is more compact, can reduce space-consuming.
Description
Technical field
The present invention relates to supercharging of internal combustion engine technical field, more particularly to a kind of compact two-stage turbine machine.
Background technology
In recent years, with energy prices rise and non-renewable resources it is increasingly in short supply, energy-conservation turns into country
It is capable of the key factor of sustainable development.If not optimizing traditional energy utilization patterns, it is impossible to resource is more effectively utilized,
Whole resource environment will be made exacerbated, and cause the rapid exhaustion of the energy.
Turbocharger is one of important component of internal combustion engine, all diesel engine and part of gasoline machine, gas engine
Be provided with turbocharger, with the continuous innovation of supercharging technology, booster will be more and more with machine amount.With application
The requirement of the increasingly complicated and Abgasgesetz of environment is increasingly strict, and traditional turbocharger is faced with formidable challenges, to whirlpool
Take turns the requirement also more and more higher of the exhaust gas utilization rate of booster.
The pressure ratio of turbocharger is an important parameter of the exhaust gas utilization rate for influenceing turbocharger, is generally improved
The method of pressure ratio is realized using two turbocharger of series connection, but this method can produce a series of problem so that increased
Press systems bulky, complex structure, cost and fault rate higher.
Therefore, how to ensure the compact conformation of turbocharger while the pressure ratio of turbocharger is improved, be ability
The current technical issues that need to address of field technique personnel.
The content of the invention
In view of this, it is an object of the invention to provide a kind of compact two-stage turbine machine, it reclaims internal combustion engine waste gas energy
Rate is higher and compact conformation.
To achieve the above object, the present invention provides following technical scheme：
A kind of compact two-stage turbine machine, including turbine wheel shaft, vertically successively fixed cover on the turbine wheel shaft one
Level turbine and two-stage turbine and cover at the first turbine and the two-stage turbine outside casing, the one-level whirlpool
Radial nozzles ring is provided with the import of wheel, provided with axial nozzle ring at the import of the two-stage turbine, the axial nozzle ring with
It is provided between guide housing between level, the level and is formed between the inwall of guide housing and the casing for guiding between the first turbine
Waste gas enters the guide channel of the axial nozzle ring, and the first turbine is radial-flow turbine or mixed flow turbine, two grades of whirlpools
Take turns as axial flow turbine.
Preferably, the radial section area of the guide channel is tapered by the lateral outlet side of air inlet.
Preferably, the first turbine is integrated part with the turbine wheel shaft.
Preferably, the middle part radially protruding of the turbine wheel shaft has installation base, and the intermediate throughholes of the two-stage turbine are by institute
It is inserted in the turbine wheel shaft and is connected to by locking nut on an axial end of the installation base in the one end for stating turbine wheel shaft.
Preferably, also including the guiding and the exit casing of collection for waste gas, the exit casing is provided with bearing block, described
Bearing block is connected to by rolling bearing on the axle journal of the end of the turbine wheel shaft, and the exit casing is connected with exit casing end cap,
The exit casing end cap can limit the rolling bearing jointly with being connected to the step surface of the axle journal on the turbine wheel shaft
Axial displacement.
Preferably, inner flange and outward flange, the interior method are radially sequentially provided with the axial nozzle ring from inside to outside
Orchid is connected to the guide housing flange on guide housing between the level, and the exit casing is provided with first flange and second flange, described
First flange, the outward flange are connected to the casing, and the second flange connects external exhaust gas pipeline.
Preferably, gap is provided between the level between guide housing and the first turbine.
In the compact two-stage turbine machine that the present invention is provided, first turbine and two-stage turbine are set on same turbine wheel shaft.
In use, waste gas enters casing internal from the casing air inlet on casing, radial nozzles ring is collectively forming reduction with casing inner wall
Passage, makes waste expansion enter first turbine after accelerating, radial-flow turbine or mixed flow turbine are that the first order reclaims waste gas work(part, are given up
Gas enters air guide channel after first turbine expansion work, and the axial direction that air guide channel can guide waste gas smoothly to enter next stage is sprayed
Mouth ring, the waste gas after the acceleration of axial nozzle ring enters two-stage turbine, is then discharged from the outlet of two-stage turbine.
Two turbine drives same axises of such a compact two-stage turbine machine, waste gas will be defeated after two-stage turbine does work
Go out Effective power and be all supplied to compressor, so as to so that compressor obtains more energy, improve the pressure ratio of turbocharger,
Exhaust gas utilization rate is higher, meanwhile, first turbine, two-stage turbine are arranged in same casing, and structure is more compact, can be reduced
Space-consuming.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description is briefly described, it should be apparent that, drawings in the following description are only this
The embodiment of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can also basis
The accompanying drawing of offer obtains other accompanying drawings.
Fig. 1 is the structural representation of compact two-stage turbine machine provided by the present invention；
Fig. 2 is the structural representation of turbine wheel shaft provided by the present invention；
Fig. 3 is the structural representation of guide housing between level provided by the present invention；
Fig. 4 is the structural representation of axial nozzle ring provided by the present invention；
Fig. 5 is the structural representation of axial flow turbine provided by the present invention；
Fig. 6 is the structural representation of exit casing provided by the present invention；
Fig. 7 is the sectional view of compact two-stage turbine machine provided by the present invention.
Fig. 1 is into Fig. 7,1- casings, 2- radial nozzles rings, 3- turbine wheel shafts, guide housing between 4- grades, 5- axial directions nozzle ring, 6-
Two-stage turbine, 7- locking nuts, 8- exit casings, 9- rolling bearings, 10- casing air inlets, 11- first turbines, 12- inner flanges,
13- outward flanges, 14- guide housing flanges, 15- bearing blocks, 16- axle journals, 17- exit casing end caps, 18- installation bases, the methods of 19- first
Orchid, 20- second flanges.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
The core of the present invention is to provide a kind of compact two-stage turbine machine, and its recovery internal combustion engine waste gas energy rate is higher and ties
Structure is compact.
Fig. 1 to Fig. 7 is refer to, Fig. 1 is the structural representation of compact two-stage turbine machine provided by the present invention；Fig. 2 is this
Invention provides the structural representation of turbine wheel shaft；Fig. 3 is the structural representation of guide housing between level provided by the present invention；Fig. 4 is this
Invention provides the structural representation of axial nozzle ring；Fig. 5 is the structural representation of axial flow turbine provided by the present invention；Fig. 6 is
The structural representation of exit casing provided by the present invention；Fig. 7 is the sectional view of compact two-stage turbine machine provided by the present invention.
In a kind of specific embodiment of compact two-stage turbine machine provided by the present invention, including turbine wheel shaft 3, vertically successively
First turbine 11 and two-stage turbine 6 and cover at first turbine 11 and two-stage turbine 6 that fixed cover is located on turbine wheel shaft 3
It is provided with the casing 1 in outside, the import of first turbine 11 at radial nozzles ring 2, the import of two-stage turbine 6 provided with axial nozzle ring
5, it is provided between guide housing 4 between level, level and is formed between the inwall of guide housing 4 and casing 1 between axial nozzle ring 5 and first turbine 11
For guiding waste gas to enter the guide channel of axial nozzle ring 5, first turbine 11 is radial-flow turbine or mixed flow turbine, two-stage turbine
6 be axial flow turbine.Wherein, the wheel diameter of axial flow turbine is typically larger than the exit inside diameter of radial-flow turbine and mixed flow turbine, institute
Diameter close to two-stage turbine 6 is less than close to the diameter of first turbine 11 with guide housing between level 4.Between level outside one end of guide housing 4
Shape size is consistent with the outlet profile size of first turbine 11, the appearance and size of the other end and the entrance wheel of axial nozzle ring 5
Wide size is consistent.
Waste gas enters inside casing 1 from the casing air inlet 10 on casing 1, radial nozzles ring 2 and the common shape of the inwall of casing 1
Into reduction passage, waste expansion is set to enter first turbine 11 after accelerating, radial-flow turbine or mixed flow turbine are that the first order reclaims waste gas
Work(part, waste gas enters air guide channel after the expansion work of first turbine 11, and air guide channel can be guided under waste gas smoothly enters
The axial nozzle ring 5 of one-level, the waste gas after the acceleration of axial nozzle ring 5 enters two-stage turbine 6, then from two-stage turbine 6
Outlet discharge.
It can be seen that, such a compact two-stage turbine machine on same turbine wheel shaft 3 by setting first turbine 11 and two-stage turbine
6, output Effective power is all supplied to compressor by this two turbine drives same axises, waste gas after two-stage turbine does work,
So as to which so that compressor obtains more energy, the pressure ratio of raising turbocharger, exhaust gas utilization rate is higher, meanwhile, one-level
Turbine 11, two-stage turbine 6 are arranged in same casing 1, and structure is more compact, can reduce space-consuming.
Wherein, should not be too short in order to ensure that waste gas smoothly enters the axial length of guide housing 4 between axial nozzle ring 5, level,
The velocity attitude that waste gas enters before axial nozzle ring 5 should be made as far as possible axially.Guide housing 4 and axial nozzle ring 5 between level,
Junction between first turbine 11 is smooth, should not there is step appearance, to avoid airflow collision from losing.
Specifically, the radial section of air guide channel can be the ring surface around turbine wheel shaft 3, and radial section area can be with
It is tapered by the lateral outlet side of air inlet, to ensure that waste gas flows under along press strip part.Wherein, for air guide channel, close to one-level whirlpool
The side of wheel 11 is air inlet side, is outlet side close to the side of two-stage turbine 6.
Specifically, first turbine 11 can be integrated part with turbine wheel shaft 3, to ensure between first turbine 11 and turbine wheel shaft 3
Being capable of reliably run-in synchronism.Certainly, first turbine 11 can also be unified into one by friction welding (FW) or other modes with turbine wheel shaft 3
Body.
Specifically, the middle part of turbine wheel shaft 3 can have installation base 18 with radially protruding, and the intermediate throughholes of two-stage turbine 6 are by whirlpool
It is inserted in turbine wheel shaft 3 and is connected to by locking nut 7 on an axial end of installation base 18 in one end of wheel shaft 3.Tighten locking
The axial movement of two-stage turbine 6 can be limited after nut 7, meanwhile, the circumferential support force of locking nut 7 can make two-stage turbine 6
As turbine wheel shaft 3 does circumferential movement jointly.The setting of installation base 18 can facilitate the peace between two-stage turbine 6 and turbine wheel shaft 3
Dress is fixed.
On the basis of each above-mentioned embodiment, the guiding for waste gas can also be included in the compact two-stage turbine machine
With the exit casing 8 of collection, exit casing 8 is provided with bearing block 15, and the bearing block 15 is connected to turbine wheel shaft 3 by rolling bearing 9
On the axle journal 16 of end.Because the wheel disc of axial flow turbine is heavier, it is impossible to be designed as cantilever structure, so being set in exit casing 8
A bearing block 15 is put, the inner ring of rolling bearing 9 is arranged on the outer peripheral face of the axle journal 16 of turbine wheel shaft 3, outside the rolling bearing 9
Circle is arranged in bearing block 15, by rolling bearing 9 come supports turbine shaft 3, meanwhile, it is attached, is safeguarded using rolling bearing 9
Convenient, reliable operation, starting performance is good.Exit casing 8 is connected with exit casing end cap 17, can be specifically connected by bolt.Row
Gas shell end cap 17 can limit the axial displacement of rolling bearing 9, i.e. axle jointly with being connected to the step surface of axle journal 16 on turbine wheel shaft 3
Step surface is formed between the main body of neck 16 and the turbine wheel shaft 3, exit casing end cap 17 is with the step surface respectively positioned at rolling bearing 9
The both sides of axial direction, exit casing end cap 17 can be sealed with being fixed to rolling bearing 9.
Further, turbine wheel shaft 3 can be the multi-diameter shaft for only including a step surface, and turbine wheel shaft is for 3 points by the step surface
Big footpath section and path section, path section are axle journal 16, and first turbine 11, two-stage turbine 6 can be arranged in big footpath section, and are rolled
Dynamic bearing 9 is arranged in path section, and the inner ring diameter with diameter greater than rolling bearing 9 of big footpath section, and the step surface can be to rolling
Dynamic bearing 9 carries out axially position.Certainly, the quantity of step surface can also carry out other settings as needed.
Specifically, inner flange 12 and outward flange 13 can be radially sequentially provided with from inside to outside on axial nozzle ring 5, this is interior
Flange 12 is connected to the guide housing flange 14 on guide housing 4 between level, and exit casing 8 is provided with first flange 19 and second flange 20,
First flange 19, outward flange 13 are connected to casing 1, i.e., axially, and casing 1, outward flange 13 and first flange 19 are set gradually
And link together, the connection external exhaust gas pipeline of second flange 20.Wherein, the axial nozzle ring 5 of one end connection of casing 1, another
End can be fixed on cartridge housing by flange.Connected between each part by flange arrangement, be conducive to improving the convenient of assembly and disassembly
Property, and then it is easy to being smoothed out for maintenance work.
Specifically, gap can be provided between level between guide housing 4 and first turbine 11, to avoid first turbine 11 from being scraped
Wound, it is ensured that turbine safe operation.
The embodiment of each in this specification is described by the way of progressive, and what each embodiment was stressed is and other
Between the difference of embodiment, each embodiment identical similar portion mutually referring to.
Compact two-stage turbine machine provided by the present invention is described in detail above.It is used herein specifically individual
Example is set forth to the principle and embodiment of the present invention, and the explanation of above example is only intended to help to understand the present invention's
Method and its core concept.It should be pointed out that for those skilled in the art, not departing from the principle of the invention
On the premise of, some improvement and modification can also be carried out to the present invention, these are improved and modification also falls into the claims in the present invention
Protection domain in.
Claims (7)
1. a kind of compact two-stage turbine machine, it is characterised in that including turbine wheel shaft (3), vertically successively fixed cover located at described
First turbine (11) and two-stage turbine (6) on turbine wheel shaft (3) and cover at the first turbine (11) and two grades of whirlpools
Take turns and radial nozzles ring (2), the two-stage turbine are provided with the casing (1) in the outside of (6), the import of the first turbine (11)
(6) provided with axial nozzle ring (5) at import, it is provided between the axial nozzle ring (5) and the first turbine (11) between level
Formed between guide housing (4), the level between the inwall of guide housing (4) and the casing (1) for guiding waste gas to enter the axle
To the guide channel of nozzle ring (5), the first turbine (11) is radial-flow turbine or mixed flow turbine, and the two-stage turbine (6) is
Axial flow turbine.
2. compact two-stage turbine machine according to claim 1, it is characterised in that the radial section of the guide channel is
Ring surface around the turbine wheel shaft (3), and radial section area is tapered by the lateral outlet side of air inlet.
3. compact two-stage turbine machine according to claim 1, it is characterised in that the first turbine (11) and the whirlpool
Wheel shaft (3) is integrated part.
4. compact two-stage turbine machine according to claim 1, it is characterised in that the middle part of the turbine wheel shaft (3) is radially
Installation base (18) is protruding with, the intermediate throughholes of the two-stage turbine (6) are inserted in the turbine by one end of the turbine wheel shaft (3)
Axle (3) is simultaneously connected on an axial end of the installation base (18) by locking nut (7).
5. the compact two-stage turbine machine according to Claims 1-4 any one, it is characterised in that also including for giving up
The guiding of gas and the exit casing (8) of collection, the exit casing (8) are provided with bearing block (15), and the bearing block (15) passes through rolling
Dynamic bearing (9) is connected on the axle journal (16) of the end of the turbine wheel shaft (3), and the exit casing (8) is connected with exit casing end cap
(17), the exit casing end cap (17) can jointly limit with being connected to the step surface of the axle journal (16) on the turbine wheel shaft (3)
The axial displacement of the fixed rolling bearing (9).
6. compact two-stage turbine machine according to claim 5, it is characterised in that along footpath on the axial nozzle ring (5)
To inner flange (12) and outward flange (13) is sequentially provided with from inside to outside, the inner flange (12) is connected to guide housing between the level
(4) the guide housing flange (14) on, the exit casing (8) is provided with first flange (19) and second flange (20), described first
Flange (19), the outward flange (13) are connected to the casing (1), and the second flange (20) connects external exhaust gas pipeline.
7. compact two-stage turbine machine according to claim 5, it is characterised in that between the level guide housing (4) with it is described
Gap is provided between first turbine (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710329809.2A CN106948926A (en) | 2017-05-11 | 2017-05-11 | A kind of compact two-stage turbine machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710329809.2A CN106948926A (en) | 2017-05-11 | 2017-05-11 | A kind of compact two-stage turbine machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106948926A true CN106948926A (en) | 2017-07-14 |
Family
ID=59478577
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710329809.2A Pending CN106948926A (en) | 2017-05-11 | 2017-05-11 | A kind of compact two-stage turbine machine |
Country Status (1)
| Country | Link |
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| CN (1) | CN106948926A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6422014B1 (en) * | 2001-09-06 | 2002-07-23 | Caterpillar Inc. | Turbocharger with controllable flow geometry for two stage turbine |
| CN101821481A (en) * | 2007-10-13 | 2010-09-01 | 康明斯涡轮增压技术有限公司 | Turbomachine |
| CN102410056A (en) * | 2010-09-20 | 2012-04-11 | 谭波 | Waste gas turbine |
| CN102536432A (en) * | 2012-02-13 | 2012-07-04 | 清华大学 | Counter-rotating turbine combination device and engine system with same |
| US20120312012A1 (en) * | 2009-11-20 | 2012-12-13 | Andreas Thoss | Multistage charging system for an internal combustion engine |
| AU2014397180A1 (en) * | 2014-06-10 | 2016-11-03 | Volvo Truck Corporation | A turbine system |
| CN206753723U (en) * | 2017-05-11 | 2017-12-15 | 大连依勒斯涡轮增压技术有限公司 | A kind of compact two-stage turbine machine |
-
2017
- 2017-05-11 CN CN201710329809.2A patent/CN106948926A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6422014B1 (en) * | 2001-09-06 | 2002-07-23 | Caterpillar Inc. | Turbocharger with controllable flow geometry for two stage turbine |
| CN101821481A (en) * | 2007-10-13 | 2010-09-01 | 康明斯涡轮增压技术有限公司 | Turbomachine |
| US20120312012A1 (en) * | 2009-11-20 | 2012-12-13 | Andreas Thoss | Multistage charging system for an internal combustion engine |
| CN102410056A (en) * | 2010-09-20 | 2012-04-11 | 谭波 | Waste gas turbine |
| CN102536432A (en) * | 2012-02-13 | 2012-07-04 | 清华大学 | Counter-rotating turbine combination device and engine system with same |
| AU2014397180A1 (en) * | 2014-06-10 | 2016-11-03 | Volvo Truck Corporation | A turbine system |
| CN206753723U (en) * | 2017-05-11 | 2017-12-15 | 大连依勒斯涡轮增压技术有限公司 | A kind of compact two-stage turbine machine |
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Application publication date: 20170714 |