CN107060992A - One kind is combined concentrically birotor exhaust turbocharging system structure - Google Patents
One kind is combined concentrically birotor exhaust turbocharging system structure Download PDFInfo
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- CN107060992A CN107060992A CN201710309251.1A CN201710309251A CN107060992A CN 107060992 A CN107060992 A CN 107060992A CN 201710309251 A CN201710309251 A CN 201710309251A CN 107060992 A CN107060992 A CN 107060992A
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- pressure stage
- turbine
- passing valve
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Classifications
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- 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
- F02B37/013—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
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- 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
- 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
- F02B37/12—Control of the pumps
- F02B37/16—Control of the pumps by bypassing charging air
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- 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
- F02B37/12—Control of the pumps
- F02B37/16—Control of the pumps by bypassing charging air
- F02B37/162—Control of the pumps by bypassing charging air by bypassing, e.g. partially, intake air from pump inlet to pump outlet
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- 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
- F02B37/12—Control of the pumps
- F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
- F02B37/183—Arrangements of bypass valves or actuators therefor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
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- 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
Birotor exhaust turbocharging system structure is combined concentrically the invention provides one kind, the structure refers to two compressor impellers and two turbine rotors using concentric shafts structure assembly in one, outer shaft and interior axle connect turbine and compressor impeller respectively, two boosters can be realized coaxial not synchronized, it is mutually combined motion, dual-air compressor impeller realizes serial or parallel connection air inlet with double turbines by regulating system, reaches and improves pressure ratio, widens working range and improve the purpose of structural compactness.
Description
Technical field
The invention belongs to turbocharging technology field, birotor exhaust gas turbocharge system is combined concentrically more particularly, to one kind
System structure.
Background technology
Exhaust-driven turbo-charger exhaust-gas turbo charger is that the energy for discharging waste gas using engine drives to compress fresh air in cylinder,
Under the conditions of same engine discharge capacity, increase air input of engine by air, to match the more fuel oils of engine spray, it is fully fired
Burn, reach and put forward high-power purpose, be widely used at present on the internal-combustion piston engines such as gasoline engine, diesel engine.
With engine power density reinforcing and Abgasgesetz it is increasingly strict, single stage supercharging can not meet engine
Full territorial environment work requirements, conventional single stage supercharging pressure ratio is low, and its pressure ratio, which is improved, can bring that range of flow is narrow, reliability
The problem of nargin declines；
Therefore, two grades of (or multistage) adjustable pressurization systems are occurred in that, by adjusting the series and parallel realized to many boosters
Combination, reaches the purpose of high pressure ratio and wide range of flow, but due to using many boosters, at the same also bring weight increase,
The distinct issues such as bulky, system total efficiency is low, single-vortex double-pressure range of flow is narrow, pipeline arrangement complexity.
The content of the invention
In view of this, the present invention is directed to propose one kind is combined concentrically birotor exhaust turbocharging system structure, using same
Two groups of compressor impellers and turbine are combined by heart axle, and air inlet reasonable in design and exhaust passage are carried out using by-pass structure
Regulation, so as to realize compact conformation, pressure ratio height and the wide advantage of range of flow simultaneously.
To reach above-mentioned purpose, the technical proposal of the invention is realized in this way：
One kind is combined concentrically birotor exhaust turbocharging system structure, including the double pressures linked together by concentric shafts
Compressor wheel and double turbines, form two-stage exhaust gas turbocharge structure；
The dual-air compressor impeller is respectively low-pressure stage compressor impeller and hiigh pressure stage compressor impeller, described pair of turbine point
Wei not hiigh pressure stage turbine and lower pressure stage turbine, low-pressure stage compressor impeller and lower pressure stage turbine the composition lower pressure stage turbine-pressure
Mechanism of qi structure, the hiigh pressure stage compressor impeller and hiigh pressure stage turbine constitute hiigh pressure stage turbine-air compressor structure.
Further, the hiigh pressure stage turbine uses radial-flow type or mixed-flow, and the lower pressure stage turbine uses axial-flow type.
Further, the hiigh pressure stage turbine-air compressor structure is arranged on lower pressure stage turbine-air compressor structure in concentric shafts
Inner side formed hiigh pressure stage occupy in arrangement；Or, the hiigh pressure stage turbine-air compressor structure is arranged on low pressure in concentric shafts
The outside of level turbine-air compressor structure forms hiigh pressure stage and occupies outer arrangement.
Further, the low-pressure stage compressor impeller and hiigh pressure stage compressor impeller use centrifugal, and low-pressure stage pressure
Compressor wheel and hiigh pressure stage compressor impeller are arranged or dorsad arranged in the same direction.
Further, the concentric shafts include interior axle and outer shaft, and the interior axle is solid shafting, and outer shaft is hollow shaft, and set
On the outside of interior axle；The dual-air compressor impeller is combined with double turbines by interior axle and outer shaft, and realization is not coaxial synchronized,
Intercouple motion.
Further, the outer shaft is arranged on inside boosting system arrangement by outer axle bearing, and the outer axle bearing is floating
Dynamic bearing or ball bearing；The interior axle is arranged on inside boosting system arrangement by inner shaft bearing, and inner shaft bearing is ball axle
Hold, and inner shaft bearing is arranged on the overall inner side or middle part or outside of boosting system arrangement.
Further, the low-pressure stage compressor impeller end passage is provided with calm the anger generator terminal low-pressure stage by-passing valve, the high pressure
Level compressor impeller end passage is provided with generator terminal hiigh pressure stage by-passing valve of calming the anger；The hiigh pressure stage turbine end passage is provided with turbine end high pressure
Level by-passing valve, lower pressure stage turbine end passage is provided with turbine end low-pressure stage by-passing valve；
When calming the anger, generator terminal low-pressure stage by-passing valve and turbine end low-pressure stage by-passing valve are closed, generator terminal of calming the anger hiigh pressure stage by-passing valve and
When turbine end hiigh pressure stage by-passing valve is opened, then lower pressure stage turbine-air compressor structure works independently；
When calming the anger, generator terminal hiigh pressure stage by-passing valve and turbine end hiigh pressure stage by-passing valve are closed, generator terminal of calming the anger low-pressure stage by-passing valve and
When turbine end low-pressure stage by-passing valve is opened, then hiigh pressure stage turbine-air compressor structure works independently；
When generator terminal low-pressure stage by-passing valve of calming the anger, turbine end low-pressure stage by-passing valve, generator terminal of calming the anger hiigh pressure stage by-passing valve and turbine
End hiigh pressure stage four by-passing valves of by-passing valve are when being turned off, and two-stage exhaust gas turbocharge structure works simultaneously, and realize series connection air inlet,
Two-step supercharging.
Relative to prior art, the present invention has the advantage that：
The present invention is closely combined two groups of compressor impellers and turbine using concentric shafts, and two boosters can be realized
It is coaxially not synchronized, motion is mutually combined, dual-air compressor impeller is realized serial or parallel connection air inlet by regulating system with double turbines, reached
To improve pressure ratio, widen working range and improve structural compactness purpose.
The present invention is closely combined two groups of compressor impellers and turbine using concentric shafts, air inlet reasonable in design and row
Gas passage, is adjusted using by-pass structure, so as to realize that compact conformation, pressure ratio are high and range of flow is wide simultaneously；Can with it is many
The ordnance engine for planting model is matched, and effectively improves the power density of engine.
Brief description of the drawings
The accompanying drawing for constituting the part of the present invention is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not constitute inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 occupies scheme schematic diagram built in interior compressor impeller bearing in the same direction for the hiigh pressure stage of the present invention；
Fig. 2 occupies interior compressor impeller bearing middle scheme schematic diagram in the same direction for the hiigh pressure stage of the present invention；
Fig. 3 occupies interior compressor impeller external bearings scheme schematic diagram in the same direction for the hiigh pressure stage of the present invention；
Fig. 4 occupies interior compressor impeller dorsad scheme schematic diagram built in bearing for the hiigh pressure stage of the present invention；
Fig. 5 occupies interior compressor impeller dorsad bearing middle scheme schematic diagram for the hiigh pressure stage of the present invention；
Fig. 6 occupies interior compressor impeller dorsad external bearings scheme schematic diagram for the hiigh pressure stage of the present invention；
Fig. 7 occupies scheme schematic diagram built in outer compressor impeller bearing in the same direction for the hiigh pressure stage of the present invention；
Fig. 8 occupies outer compressor impeller bearing middle scheme schematic diagram in the same direction for the hiigh pressure stage of the present invention；
Fig. 9 occupies outer compressor impeller external bearings scheme schematic diagram in the same direction for the hiigh pressure stage of the present invention；
Figure 10 occupies outer compressor impeller dorsad scheme schematic diagram built in bearing for the hiigh pressure stage of the present invention；
Figure 11 occupies outer compressor impeller dorsad bearing middle scheme schematic diagram for the hiigh pressure stage of the present invention；
Figure 12 occupies outer compressor impeller dorsad external bearings scheme schematic diagram for the hiigh pressure stage of the present invention；
Description of reference numerals (by taking Fig. 1 as an example)：
1- calms the anger generator terminal hiigh pressure stage by-passing valve；2- low-pressure stage compressor impellers；3- interior axles；4- calm the anger generator terminal low-pressure stage bypass
Valve；5- inner shaft bearings；6- hiigh pressure stage compressor impellers；The outer axle bearings of 7-；8- outer shafts；9- turbine end hiigh pressure stage by-passing valves；10- is high
Arbitrarily downgrade turbine；11- lower pressure stage turbines；12- turbine end low-pressure stage by-passing valves.
Embodiment
It should be noted that in the case where not conflicting, the embodiment in the present invention and the feature in embodiment can phases
Mutually combination.
Describe the present invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
The present invention is combined concentrically birotor exhaust turbocharging system structure, including pair linked together by concentric shafts
Compressor impeller and double turbines, form two-stage exhaust gas turbocharge structure；The dual-air compressor impeller is respectively that low-pressure stage is calmed the anger
Machine impeller 2 and hiigh pressure stage compressor impeller 6, described pair of turbine is respectively hiigh pressure stage turbine 10 and lower pressure stage turbine 11, described low
Arbitrarily downgrade compressor impeller 2 and lower pressure stage turbine 11 constitutes lower pressure stage turbine-air compressor structure, the hiigh pressure stage compressor impeller 6
Hiigh pressure stage turbine-air compressor structure is constituted with hiigh pressure stage turbine 10.
Hiigh pressure stage turbine-the air compressor structure is arranged on the inner side shape of lower pressure stage turbine-air compressor structure in concentric shafts
Interior arrangement is occupied into hiigh pressure stage；Or, the hiigh pressure stage turbine-air compressor structure be arranged on concentric shafts on lower pressure stage turbine-
The outside of air compressor structure forms hiigh pressure stage and occupies outer arrangement.When the hiigh pressure stage turbine-air compressor structure occupies outer arrangement, enter
Gas passage is fairly simple rationally；When being arranged in occupying, then the small axle of steamboat is realized, the big axle of bull wheel, mechanical efficiency is higher.
The low-pressure stage compressor impeller 2 and hiigh pressure stage compressor impeller 6 use centrifugal, and low-pressure stage compressor impeller
2 and hiigh pressure stage compressor impeller 6 can take in the same direction arrangement or dorsad arrange.If both stage impellers are arranged in the same direction, gas channel
It is fairly simple；If both stage impellers are dorsad arranged, structure is compact.
The concentric shafts include interior axle 3 and outer shaft 8, and the interior axle 3 is solid shafting, and outer shaft 8 is hollow shaft, and is sleeved on interior
The outside of axle 3；The dual-air compressor impeller is combined with double turbines by interior axle 3 and outer shaft 8, realizes coaxial not synchronized, phase
Mutual coupling resultant motion.
As described in Fig. 1 to 6, when hiigh pressure stage turbine-air compressor structure occupies interior arrangement, low-pressure stage compressor impeller 2 and low pressure
Level turbine 11 is directly sheathed with interior axle 3, and hiigh pressure stage compressor impeller 6 is directly sheathed with outer shaft 8, and hiigh pressure stage turbine 10 rubs
It is soldered on outer shaft 8；
As described in Fig. 7 to 12, when hiigh pressure stage turbine-air compressor structure occupies outer arrangement, hiigh pressure stage compressor impeller 6 and high pressure
Level turbine 10 is directly sheathed with interior axle 3, and low-pressure stage compressor impeller 2 is directly sheathed with outer shaft 8.
The outer shaft 8 is arranged on inside boosting system arrangement by outer axle bearing 7, and the outer axle bearing 7 can be using floating
Support is formed between bearing or ball bearing, its outside and TC bearings body (bearing body is not drawn in figure)；The interior axle 3
It is arranged on by inner shaft bearing 5 inside boosting system arrangement, inner shaft bearing 5 is ball bearing, and inner shaft bearing 5 is by being arranged on
The inner side or middle part of boosting system arrangement or outside, realize interior axle 3 exhaust turbocharging system structure entirety built in or in
Put or external arrangement.
If built in inner shaft bearing 5, its working speed is the relative rotation speed of outer shaft 8 and interior axle 3, now can be in low-pressure stage whirlpool
Add guide vane before wheel 11, rotate in same direction outer shaft 8 and interior axle 3, to reduce the working speed of inner shaft bearing 5；If inner shaft bearing 5
In put, then its working speed be interior axle 3 absolute rotating speed, can now save guide-vane arrangement；If inner shaft bearing 5 is external,
It is easy to maintenance.Built-in bearing 5 is built-in to be arranged in height and arbitrarily downgrades within impeller, in put and be arranged in height and arbitrarily downgrade between impeller,
It is external to be arranged in beyond impeller of just arbitrarily downgrading.
So, according to two kinds of arrangements (Ju Nei and residence are outer) of hiigh pressure stage turbine-air compressor structure, two stage compressor leaf
Two kinds of arrangements (in the same direction and dorsad) of wheel, arrangement also in the 3 of interior axle 3 (built-in, in put or external), different groups
Amount to form 12 kinds of arrangements, respectively as shown in Figures 1 to 12.
The end passage of low-pressure stage compressor impeller 2 provided with calming the anger generator terminal low-pressure stage by-passing valve 4, by-passing valve conducting for its
Gas channel between the both sides of connection, after it is opened, then the impeller of its conducting will can not be worked due to airflow bypass, respectively
By-passing valve has independent control executing agency, it is possible to achieve individually control, the end passage of hiigh pressure stage compressor impeller 6 is provided with pressure
Mechanism of qi end hiigh pressure stage by-passing valve 1；The end passage of hiigh pressure stage turbine 10 is provided with turbine end hiigh pressure stage by-passing valve 9, the low-pressure stage
The end passage of turbine 11 is provided with turbine end low-pressure stage by-passing valve 12；
When calming the anger generator terminal low-pressure stage by-passing valve 4 and turbine end low-pressure stage by-passing valve 12 is closed, generator terminal of calming the anger hiigh pressure stage bypass
When valve 1 and the opening of turbine end hiigh pressure stage by-passing valve 9, then lower pressure stage turbine-air compressor structure works independently；
When calming the anger generator terminal hiigh pressure stage by-passing valve 1 and turbine end hiigh pressure stage by-passing valve 9 is closed, generator terminal of calming the anger low-pressure stage by-passing valve
4 and turbine end low-pressure stage by-passing valve 12 opening when, then hiigh pressure stage turbine-air compressor structure works independently；
As generator terminal low-pressure stage by-passing valve 4 of calming the anger, turbine end low-pressure stage by-passing valve 12, the and of generator terminal of calming the anger hiigh pressure stage by-passing valve 1
When 9 four by-passing valves of turbine end hiigh pressure stage by-passing valve are turned off, two-stage exhaust gas turbocharge structure works simultaneously, and realizes series connection
Air inlet, two-step supercharging.
The hiigh pressure stage turbine 10 uses radial-flow type or mixed-flow, and the lower pressure stage turbine 11 uses axial-flow type, this knot
Structure gas channel advantages of simple, exhaust energy utilization rate is higher.
The two-stage exhaust gas turbocharge structure of the present invention, due to possessing that compact conformation, pressure ratio be high, that range of flow is wide is excellent
Point, can be matched with the ordnance engine of Multiple Type, and effectively improve the power density of engine.When engine fortune
Row is in High aititude operating mode, it is necessary to which pressure charging system provides higher air inlet pressure ratio, generator terminal of now calming the anger low-pressure stage by-passing valve 4, whirlpool
Wheel end low-pressure stage by-passing valve 12, generator terminal of calming the anger hiigh pressure stage by-passing valve 1 and turbine end hiigh pressure stage by-passing valve 9 are turned off, Cascade System
Air inlet, realizes two-step supercharging, so as to improve air inlet pressure ratio；According to duty requirements, the He of generator terminal hiigh pressure stage by-passing valve 1 of calming the anger is opened
Turbine end hiigh pressure stage by-passing valve 9, closes calm the anger generator terminal low-pressure stage by-passing valve 4, turbine end low-pressure stage by-passing valve 12, then realizes low pressure
Level turbine-air compressor structure works independently；According to duty requirements, calm the anger generator terminal low-pressure stage by-passing valve 4, turbine end low-pressure stage are opened
By-passing valve 12, closing is calmed the anger generator terminal hiigh pressure stage by-passing valve 1 and turbine end hiigh pressure stage by-passing valve 9, then realizes hiigh pressure stage turbine-calm the anger
Machine structure works independently.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
God is with principle, and any modification, equivalent substitution and improvements made etc. should be included in the scope of the protection.
Claims (7)
1. one kind is combined concentrically birotor exhaust turbocharging system structure, it is characterised in that：Including being connected to by concentric shafts
Dual-air compressor impeller together and double turbines, form two-stage exhaust gas turbocharge structure；
The dual-air compressor impeller is respectively low-pressure stage compressor impeller (2) and hiigh pressure stage compressor impeller (6), described pair of turbine
Respectively hiigh pressure stage turbine (10) and lower pressure stage turbine (11), the low-pressure stage compressor impeller (2) and lower pressure stage turbine (11)
Lower pressure stage turbine-air compressor structure is constituted, the hiigh pressure stage compressor impeller (6) and hiigh pressure stage turbine (10) constitute hiigh pressure stage whirlpool
Wheel-air compressor structure.
2. according to claim 1 be combined concentrically birotor exhaust turbocharging system structure, it is characterised in that：The height
Turbine (10) of arbitrarily downgrading uses radial-flow type or mixed-flow, and the lower pressure stage turbine (11) uses axial-flow type.
3. according to claim 1 be combined concentrically birotor exhaust turbocharging system structure, it is characterised in that：The height
The inner side that turbine-air compressor structure of arbitrarily downgrading is arranged on lower pressure stage turbine-air compressor structure in concentric shafts forms hiigh pressure stage Ju Neibu
Put structure；Or, the hiigh pressure stage turbine-air compressor structure is arranged on the outer of lower pressure stage turbine-air compressor structure in concentric shafts
Side forms hiigh pressure stage and occupies outer arrangement.
4. according to claim 1 be combined concentrically birotor exhaust turbocharging system structure, it is characterised in that：It is described low
Compressor impeller (2) and hiigh pressure stage compressor impeller (6) arbitrarily downgrade using centrifugal, and low-pressure stage compressor impeller (2) and high pressure
Level compressor impeller (6) is arranged or dorsad arranged in the same direction.
5. according to claim 1 be combined concentrically birotor exhaust turbocharging system structure, it is characterised in that：It is described same
Heart axle includes interior axle (3) and outer shaft (8), and the interior axle (3) is solid shafting, and outer shaft (8) is hollow shaft, and is sleeved on interior axle (3)
Outside；The dual-air compressor impeller is combined with double turbines by interior axle (3) and outer shaft (8), realizes coaxial not synchronized, phase
Mutual coupling resultant motion.
6. according to claim 5 be combined concentrically birotor exhaust turbocharging system structure, it is characterised in that：
The outer shaft (8) by outer axle bearing 7 be arranged on boosting system arrangement inside, the outer axle bearing 7 be floating bearing or
Ball bearing；The interior axle (3) is arranged on inside boosting system arrangement by inner shaft bearing (5), and inner shaft bearing (5) is ball axle
Hold, and inner shaft bearing (5) is arranged on the overall inner side or middle part or outside of boosting system arrangement.
7. according to claim 1 be combined concentrically birotor exhaust turbocharging system structure, it is characterised in that：It is described low
Compressor impeller (2) of arbitrarily downgrading end passage is provided with generator terminal low-pressure stage by-passing valve (4) of calming the anger, hiigh pressure stage compressor impeller (6) end
Passage is provided with generator terminal hiigh pressure stage by-passing valve (1) of calming the anger；Hiigh pressure stage turbine (10) the end passage is bypassed provided with turbine end hiigh pressure stage
Valve (9), lower pressure stage turbine (11) end passage is provided with turbine end low-pressure stage by-passing valve (12)；
When generator terminal low-pressure stage by-passing valve (4) and turbine end low-pressure stage by-passing valve (12) closing, generator terminal of calming the anger hiigh pressure stage bypass of calming the anger
When valve (1) and turbine end hiigh pressure stage by-passing valve (9) opening, then lower pressure stage turbine-air compressor structure works independently；
When generator terminal hiigh pressure stage by-passing valve (1) and turbine end hiigh pressure stage by-passing valve (9) closing, generator terminal of calming the anger low-pressure stage by-passing valve of calming the anger
(4) and turbine end low-pressure stage by-passing valve (12) opening when, then hiigh pressure stage turbine-air compressor structure works independently；
When generator terminal low-pressure stage by-passing valve (4) of calming the anger, turbine end low-pressure stage by-passing valve (12), generator terminal of calming the anger hiigh pressure stage by-passing valve (1)
When being turned off with (9) four by-passing valves of turbine end hiigh pressure stage by-passing valve, two-stage exhaust gas turbocharge structure works simultaneously.
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| CN201710309251.1A CN107060992A (en) | 2017-05-04 | 2017-05-04 | One kind is combined concentrically birotor exhaust turbocharging system structure |
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| CN201710309251.1A CN107060992A (en) | 2017-05-04 | 2017-05-04 | One kind is combined concentrically birotor exhaust turbocharging system structure |
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Cited By (4)
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| CN107631552A (en) * | 2017-08-21 | 2018-01-26 | 中国科学院理化技术研究所 | A kind of ammonia liquefaction system |
| CN108180070A (en) * | 2017-11-09 | 2018-06-19 | 江苏索特动力工程有限公司 | Variable-area turbocharger |
| CN112901351A (en) * | 2019-12-03 | 2021-06-04 | 上海尚实能源科技有限公司 | Bearing supporting structure of double-rotor gas turbine engine |
| CN115929460A (en) * | 2022-12-08 | 2023-04-07 | 重庆交通大学 | Combined two-stage supercharger suitable for high-altitude aviation piston engine |
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| CN105715361A (en) * | 2014-12-17 | 2016-06-29 | 通用汽车环球科技运作有限责任公司 | Internal combustion engine having a two stage turbocharger |
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| GB2349427A (en) * | 1999-04-21 | 2000-11-01 | Alstom Gas Turbines Ltd | Multi-stage turbocharger having coaxial shafts |
| US20070204615A1 (en) * | 2006-03-06 | 2007-09-06 | Honeywell International, Inc. | Two-shaft turbocharger |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107631552A (en) * | 2017-08-21 | 2018-01-26 | 中国科学院理化技术研究所 | A kind of ammonia liquefaction system |
| CN108180070A (en) * | 2017-11-09 | 2018-06-19 | 江苏索特动力工程有限公司 | Variable-area turbocharger |
| CN112901351A (en) * | 2019-12-03 | 2021-06-04 | 上海尚实能源科技有限公司 | Bearing supporting structure of double-rotor gas turbine engine |
| CN112901351B (en) * | 2019-12-03 | 2023-11-28 | 上海尚实能源科技有限公司 | Bearing support structure of birotor gas turbine engine |
| CN115929460A (en) * | 2022-12-08 | 2023-04-07 | 重庆交通大学 | Combined two-stage supercharger suitable for high-altitude aviation piston engine |
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Application publication date: 20170818 |