CN102536432A - Counter-rotating turbine combination device and engine system with same - Google Patents
Counter-rotating turbine combination device and engine system with same Download PDFInfo
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- CN102536432A CN102536432A CN2012100318636A CN201210031863A CN102536432A CN 102536432 A CN102536432 A CN 102536432A CN 2012100318636 A CN2012100318636 A CN 2012100318636A CN 201210031863 A CN201210031863 A CN 201210031863A CN 102536432 A CN102536432 A CN 102536432A
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- 230000000712 assembly Effects 0.000 claims description 25
- 238000000429 assembly Methods 0.000 claims description 25
- 230000008878 coupling Effects 0.000 claims description 6
- 238000010168 coupling process Methods 0.000 claims description 6
- 238000005859 coupling reaction Methods 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 5
- 238000011084 recovery Methods 0.000 claims description 5
- 238000013459 approach Methods 0.000 claims description 4
- 239000000446 fuel Substances 0.000 abstract description 8
- 230000008901 benefit Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 19
- 239000000567 combustion gas Substances 0.000 description 8
- 239000000463 material Substances 0.000 description 5
- 239000002912 waste gas Substances 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000008676 import Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
- F01N5/00—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy
- F01N5/04—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy the devices using kinetic energy
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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
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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
- F02B41/00—Engines characterised by special means for improving conversion of heat or pressure energy into mechanical power
- F02B41/02—Engines with prolonged expansion
- F02B41/10—Engines with prolonged expansion in exhaust turbines
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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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a counter-rotating turbine combination device, which comprises a charging turbine and a power turbine. The power turbine and the charging turbine are coupled with each other, rotating axes of the power turbine and the charging turbine are the same but opposite in rotating direction, and inlet angles of blades of a rotor of the power turbine are matched with outlet angles of blades of the charging turbine so that outlet air flow of the charging turbine is capable of applying work after entering the rotor of the power turbine. Compared with the conventional turbine combination device, the counter-rotating turbine combination device has the advantages that guide vanes between the charging turbine and the power turbine are omitted, the turbine combination device is more compact in structure, flowing loss caused by the guide vanes is avoided, energy utilization rate of exhaust gas of the engine is increased, so that the total efficiency of the turbine combination device is increased and fuel economy of the engine is improved. The invention further discloses an engine system provided with the counter-rotating turbine combination device.
Description
Technical field
The present invention relates to I. C. engine exhaust energy-recuperation system field, especially relate to a kind of counter rotating turbine integrated apparatus and have the engine system of this device.
Background technique
In internal-combustion engine, turbine is compound to be used to reclaim the I. C. engine exhaust energy, improves the efficiency of internal combustion engine.Be in series with charging turbine and power turbine in the Turbocompound engine drive outlet pipe; Charging turbine is used for the work of drive pressure mechanism of qi; Increase density of the induced air; Improve the cylinder power per liter, power turbine is used to reclaim exhaust energy and changes it into mechanical work output, improves motor total output and fuel economy.Power turbine generally is installed in the downstream of charging turbine, and the overall efficiency of charging turbine and power turbine has material impact to the performance of motor.
The coupling of charging turbine and power turbine is mainly based on flow matches at present; The design of charging turbine and power turbine is relatively independent; Do not consider the coupling in charging turbine exit flow field and power turbine inlet flow field; Therefore at the inlet of power turbine guide vane need be installed, the air-flow of charging turbine outlet is adjusted, get into the rotor acting of power turbine with the angle that is fit to guarantee air-flow.
Summary of the invention
The present invention is based on the discovery of inventor to the following fact: the guide vane between the outlet of charging turbine and the inlet of power turbine has increased the axial length of turbo-compound system; Cause the turbo-compound system volume bigger; And can produce loss during air-flow process guide vane, reduce the efficient of turbo-compound system.
For this reason, one object of the present invention is to propose a kind of counter rotating turbine integrated apparatus, and said counter rotating turbine integrated apparatus is guaranteeing to have cancelled guide vane when airflow smooth passes through, and compact structure and efficient are high.
Another object of the present invention is to propose a kind of engine system with above-mentioned counter rotating turbine integrated apparatus.
Counter rotating turbine integrated apparatus according to first aspect present invention embodiment comprises: charging turbine; And power turbine; Said power turbine and said charging turbine coupled arrangement; And the spin axis of said power turbine and said charging turbine is identical and sense of rotation is opposite, and the blade inlet angle of said power turbine is configured to the blade outlet angle coupling of said charging turbine so that the exit flow of said charging turbine directly gets in the rotor of said power turbine at a predetermined angle does work.
Counter rotating turbine integrated apparatus according to the embodiment of the invention; Be configured to the blade outlet angle of charging turbine coupling so that the exit flow of charging turbine directly gets in the rotor of power turbine at a predetermined angle does work through blade inlet angle power turbine; Compare with traditional turbine integrated apparatus, cancelled the guide vane between charging turbine and the power turbine, more compact structure; And the flow losses of having avoided guide vane to cause; Improve the engine exhaust energy utilization ratio, thereby improve the overall efficiency of turbine integrated apparatus, improve the fuel economy of motor.
In addition, counter rotating turbine integrated apparatus according to the present invention also has following additional technical feature:
In one embodiment of the invention, said charging turbine is a radial turbine.
In another embodiment of the present invention, said charging turbine is a combined flow turbine.
According to some embodiments of the present invention, said power turbine is an axial-flow turbine.
Preferably, the blade outlet angle of said power turbine is constructed such that the exit flow of said power turbine flows out to approach axial speed.Thereby the outlet kinetic energy that reduces power turbine runs off.
A kind of engine system according to second aspect present invention embodiment comprises: motor; According to first aspect present invention embodiment's counter rotating turbine integrated apparatus, wherein said charging turbine is installed in the downstream of gas exhaust manifold of motor receiving the air-flow that said motor is discharged, and said power turbine is arranged in the downstream of said charging turbine; Gas compressor, said gas compressor are connected with said charging turbine and are driven so that the air-flow that gets into it is carried out supercharging by said charging turbine; Intercooler, said intercooler are connected between the cylinder of said gas compressor and motor with the cooling of the air-flow after the said supercharging and be sent in the cylinder of said motor; And hydraulic couplers, the input shaft of said hydraulic couplers links to each other with said power turbine, and output shaft links to each other with the bent axle of motor and is passed to said bent axle with the recovery merit with said power turbine.
According to the engine system of the embodiment of the invention,, make the engine system compact structure through the counter rotating turbine integrated apparatus is set; Make full use of discarded energy; Improve the engine fuel Economy, reduce discharge of harmful gases, improve the overall performance of engine system.
According to some embodiments of the present invention, engine system further comprises: first transmitting assemblies, said first transmitting assemblies are connected between the input shaft and said power turbine of said hydraulic couplers.
According to further embodiment of the present invention, engine system further comprises: second transmitting assemblies, said second transmitting assemblies are connected between the output shaft and said bent axle of said hydraulic couplers.
Alternatively, said first transmitting assemblies and said second transmitting assemblies are respectively the one-level gear-driven assembly.
Engine system according to the embodiment of the invention; Charging turbine is connected with gas compressor is coaxial; Air-flow carries out supercharging to charging turbine drive pressure mechanism of qi in the gas compressor to getting into; Air-flow after the supercharging enters in the cylinder of motor after the intercooler cooling, increases density of the induced air, improves the cylinder power per liter of motor.Waste gas after the engine operation enters in the blade of charging turbine simultaneously, flows out charging turbine then vertically, behind the cavity through bluff body and outer wall formation; Enter into power turbine vertically, power turbine changes the energy of combustion gas into mechanical work, and power turbine is connected with the input shaft of hydraulic couplers through first transmitting assemblies; The output shaft of hydraulic couplers links to each other with the bent axle of motor through second transmitting assemblies; The recovery merit of power turbine is delivered on the bent axle the most at last, improves motor total output and fuel economy, simultaneously owing to cancelled traditional guide vane; Flow losses have been reduced; Improve turbine integrated apparatus efficient, thereby improved the overall performance of engine system, made the engine system more compact structure simultaneously.
Additional aspect of the present invention and advantage part in the following description provide, and part will become obviously from the following description, or recognize through practice of the present invention.
Description of drawings
Above-mentioned and/or additional aspect of the present invention and advantage obviously with are easily understood becoming embodiment's the description from combining figs, wherein:
Fig. 1 is the sectional view according to the counter rotating turbine integrated apparatus of the embodiment of the invention;
Fig. 2 is the blade profile schematic representation of the counter rotating turbine integrated apparatus of radial turbine for charging turbine shown in Figure 1;
Fig. 3 is the blade profile schematic representation of the counter rotating turbine integrated apparatus of combined flow turbine for charging turbine shown in Figure 1; With
Fig. 4 is the schematic representation according to the engine system of the embodiment of the invention.
Embodiment
Describe embodiments of the invention below in detail, said embodiment's example is shown in the drawings, and wherein identical from start to finish or similar label is represented identical or similar elements or the element with identical or similar functions.Be exemplary through the embodiment who is described with reference to the drawings below, only be used to explain the present invention, and can not be interpreted as limitation of the present invention.
In description of the invention; It will be appreciated that; The orientation of indications such as term " " center ", " vertically ", " laterally ", " on ", D score, " preceding ", " back ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", " outward " or position relation are for based on orientation shown in the drawings or position relation; only be to describe with simplifying for the ease of describing the present invention; rather than the device or the element of indication or hint indication must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limitation of the present invention.In addition, term " first ", " second " only are used to describe purpose, and can not be interpreted as indication or hint relative importance.In addition, in description of the invention, except as otherwise noted, the implication of " a plurality of " is two or more.
In description of the invention, need to prove that only if clear and definite regulation and qualification are arranged in addition, term " installation ", " linking to each other ", " connection " should be done broad understanding, for example, can be to be fixedly connected, also can be to removably connect, or connect integratedly; Can be mechanical connection, also can be to be electrically connected; Can be directly to link to each other, also can link to each other indirectly through intermediary, can be the connection of two element internals.For those of ordinary skill in the art, can concrete condition understand above-mentioned term concrete implication in the present invention.
Disclosing of hereinafter provides many various embodiment or example to be used for realizing different structure of the present invention.Of the present invention open in order to simplify, hereinafter the parts and the setting of specific examples are described.Certainly, they only are example, and purpose does not lie in restriction the present invention.In addition, the present invention can be in different examples repeat reference numerals and/or letter.This repetition is in order to simplify and purpose clearly, itself not indicate the relation between various embodiments that discuss of institute and/or the setting.In addition, various specific technology and the examples of material that the invention provides, but those of ordinary skills can recognize the property of can be applicable to of other technologies and/or the use of other materials.
In addition; First characteristic of below describing second characteristic it " on " structure can comprise that first and second characteristics form the embodiment of direct contact; Can comprise that also additional features is formed on the embodiment between first and second characteristics, such first and second characteristics possibly not be direct contacts.
Following with reference to a kind of counter rotating turbine integrated apparatus 100 of figure 1-Fig. 3 description according to first aspect present invention embodiment, this counter rotating turbine integrated apparatus 100 is arranged on and is used to reclaim engine exhaust energy, the energy that promptly combustion gas had in the engine system 200.
Counter rotating turbine integrated apparatus 100 according to the embodiment of the invention; As shown in Figure 1; Comprise: charging turbine 1 and power turbine 2; Wherein, Power turbine 2 and charging turbine 1 coupled arrangement, and the spin axis of power turbine 2 and charging turbine 1 is identical and sense of rotation is opposite, the blade inlet angle of power turbine 2 rotors (scheme not shown) are configured to blade outlet angle (scheme not shown) with charging turbine 1 and mate that the rotor of power turbine 2 is interior to do work so that the exit flow of charging turbine 1 directly gets at a predetermined angle.
Shown in the arrow of Fig. 1, combustion gas at first enters in the blade 10 of charging turbine 1, flows out charging turbine 1 then vertically, behind the cavity 22 through bluff body 20 and outer wall 21 formation, gets into power turbine 2 vertically, flows out power turbine 2 at last.
Counter rotating turbine integrated apparatus 100 according to the embodiment of the invention; Be configured to the blade outlet angle of charging turbine 1 coupling so that the exit flow of charging turbine 1 directly gets in the rotor of power turbine 2 at a predetermined angle does work through blade inlet angle power turbine 2 rotors; Compare with traditional turbine integrated apparatus, cancelled the guide vane between charging turbine and the power turbine, more compact structure; And the flow losses of having avoided guide vane to cause; Improve the engine exhaust energy utilization ratio, thereby improve the overall efficiency of turbine integrated apparatus 100, and improved the fuel economy of motor.
In one embodiment of the invention, charging turbine 1 is a radial turbine, and power turbine 2 is an axial-flow turbine.
At this moment, as shown in Figure 2, the blade 10 linear velocity U of charging turbine 1
0And U
1Straight up, the blade 23 linear velocity U of power turbine 2
2And U
3Straight down.Motor 3 exhausts are with relative velocity W
0Get into the blade 10 of charging turbine 1, with relative velocity W
1Flow out the blade 10 of charging turbine 1.For charging turbine 1 exit flow and power turbine 2 inlet blade profiles are complementary, with blade 10 established angles (with axial angle) of charging turbine 1 outlet design big (greater than 50 °), make blade 10 exit flow absolute velocity C
1With axially have than mitre, be partial to a side identical with power turbine 2 sense of rotation.Behind the cavity 22 of air-flow through bluff body 20 and outer wall 21 formation, with absolute velocity C
2Arrive blade 23 leading edges of power turbine 2.Because C
2With axially have than mitre, and power turbine 2 and charging turbine 1 switched in opposite, air-flow gets into the relative velocity W of power turbine 2 blades 23 leading edges
2Less with axial angle.Through suitable design to power turbine 2 inlet blade profiles, can make air-flow get into power turbine 2 rotor blades with suitable angle, make power turbine 2 have higher efficient.In blade 23 outlet ports of power turbine 2, make air-flow to approach axial absolute velocity C through the design that exports blade angle
3Flow out, reduce the outlet kinetic energy rejection as far as possible.
In another embodiment of the present invention, charging turbine 1 also can be combined flow turbine, and power turbine 2 is an axial-flow turbine.
At this moment; As shown in Figure 3, the blade profile of blade 10 imports of charging turbine 1 and axially at angle, the angle of air-flow deflection in charging turbine 1 is big than radial turbine; Thereby increase the acting amount of gas to charging turbine 1, more multipotency is assigned in the charging turbine 1.Airflow gets into outside the angle difference of charging turbine 1; Promptly as shown in Figure 1, when charging turbine 1 was radial turbine, the waste gas that motor 3 is discharged was in the blade 10 that radially enters into charging turbine 1; When charging turbine 1 is combined flow turbine; The waste gas that motor 3 is discharged enters in the blade 10 of charging turbine 1 along predetermined angle of inclination, and the flow principles of combustion gas when flow principles is radial turbine with charging turbine 1 in turbine integrated apparatus 100 is identical, just is not described in detail here.
Further, the blade outlet angle of power turbine 2 is constructed such that the exit flow of power turbine 2 flows out to approach axial speed, runs off thereby reduce outlet kinetic energy as far as possible.
Following with reference to a kind of engine system 200 of figure 1-Fig. 4 description according to second aspect present invention embodiment.
Engine system 200 according to the embodiment of the invention; As shown in Figure 4; Comprise: motor 3, counter rotating turbine integrated apparatus 100, gas compressor 4, intercooler 5 and hydraulic couplers 6, wherein, counter rotating turbine integrated apparatus 100 is the counter rotating turbine integrated apparatus 100 according to first aspect present invention embodiment; Wherein charging turbine 1 be installed in motor 3 the downstream of gas exhaust manifold 31 receiving the air-flow that motor 3 is discharged, and power turbine 2 is arranged in the downstream of charging turbine 1.Gas compressor 4 is connected with charging turbine 1 and is driven so that the air-flow that gets into it is carried out supercharging by charging turbine 1.Intercooler 5 is connected between the cylinder 32 of gas compressor 4 and motor 3 with the cooling of the air-flow after the supercharging and be sent in the cylinder 32 of motor 3.The input shaft 60 of hydraulic couplers 6 links to each other with power turbine 2, and output shaft 61 links to each other with the bent axle 30 of motor 3 and is passed to bent axle 30 with the recovery merit with power turbine 2.
As shown in Figure 4; Motor 3 comprises bent axle 30, gas exhaust manifold 31, cylinder 32 and intake manifold 33; Bent axle 30 is used to import the power of motor 3, and intake manifold 33 is used for to a plurality of cylinder 32 air feed, and gas exhaust manifold 31 is used to discharge the waste gas after motor 3 is worked.Combustion gas enters into charging turbine 1 from gas exhaust manifold 31; Promote charging turbine 1 rotary work; This moment, 4 work of charging turbine 1 drive pressure mechanism of qi were to carry out supercharging to the air-flow that gets into gas compressor 4; Air-flow after the supercharging enters in the intercooler 5, and the air-flow after 5 pairs of superchargings of intercooler cools off, and cooled air communication is crossed in the cylinder 32 that intake manifold 33 is sent to motor 3.Simultaneously; As shown in Figure 1; Combustion gas enters into the power turbine 2 that is coupled with charging turbine 1 from charging turbine 1; Power turbine 2 changes the energy of combustion gas into mechanical work and outputs on the hydraulic couplers 6, and last hydraulic couplers 6 will reclaim merit and be delivered on the bent axle 30 to motor 3 power to be provided.
According to the engine system 200 of the embodiment of the invention,, make engine system 200 compact structures through counter rotating turbine integrated apparatus 100 is set; Make full use of exhaust energy; Improve the engine fuel Economy, and reduce discharge of harmful gases, improve the overall performance of engine system 200.
According to some embodiments of the present invention; Engine system 200 further comprises: first transmitting assemblies 7 and second transmitting assemblies 8; Wherein, First transmitting assemblies 7 is connected between the input shaft 60 and power turbine 2 of hydraulic couplers 6, and second transmitting assemblies 8 is connected between the output shaft 61 and bent axle 30 of hydraulic couplers 6.
Wherein, alternatively, first transmitting assemblies 7 and second transmitting assemblies 8 are respectively the one-level gear-driven assembly.Certainly, the present invention is not limited to this, and in other embodiments of the invention, first transmitting assemblies 7 and second transmitting assemblies 8 can also be secondary, three grades or multi-stage gear transmitting assemblies, for example planetary gears.
Engine system 200 according to the embodiment of the invention; Charging turbine 1 and 4 coaxial connections of gas compressor; Air-flow carries out supercharging in 4 pairs of entering gas compressors 4 of charging turbine 1 drive pressure mechanism of qi; Air-flow after the supercharging enters in the cylinder 32 of motor 3 after intercooler 5 coolings, increases density of the induced air, improves cylinder 32 power per liter of motor 3.Waste gas after motor 3 work simultaneously enters in the blade 10 of charging turbine 1, flows out charging turbine 1 then vertically, behind the cavity 22 through bluff body 20 and outer wall 21 formation; Enter into power turbine 2 vertically, power turbine 2 changes the energy of combustion gas into mechanical work, and power turbine 2 is connected with the input shaft 60 of hydraulic couplers 6 through first transmitting assemblies 7; The output shaft 61 of hydraulic couplers 6 links to each other with the bent axle 30 of motor 3 through second transmitting assemblies 8; The recovery merit of power turbine 2 is delivered on the bent axle 30 the most at last, improves motor 3 total outputs and fuel economy, simultaneously owing to cancelled traditional guide vane; Flow losses have been reduced; Improve turbine integrated apparatus 100 efficient, thereby improved the overall performance of engine system 200, made engine system 200 more compact structure simultaneously.
In the description of this specification, the description of reference term " embodiment ", " some embodiments ", " illustrative examples ", " example ", " concrete example " or " some examples " etc. means the concrete characteristic, structure, material or the characteristics that combine this embodiment or example to describe and is contained at least one embodiment of the present invention or the example.In this manual, the schematic statement to above-mentioned term not necessarily refers to identical embodiment or example.And concrete characteristic, structure, material or the characteristics of description can combine with suitable manner in any one or more embodiments or example.
Although illustrated and described embodiments of the invention; Those having ordinary skill in the art will appreciate that: under the situation that does not break away from principle of the present invention and aim, can carry out multiple variation, modification, replacement and modification to these embodiments, scope of the present invention is limited claim and equivalent thereof.
Claims (9)
1. a counter rotating turbine integrated apparatus is characterized in that, comprising:
Charging turbine; With
Power turbine; Said power turbine and said charging turbine coupled arrangement; And the spin axis of said power turbine and said charging turbine is identical and sense of rotation is opposite, and the blade inlet angle of said power turbine is configured to the blade outlet angle coupling of said charging turbine so that the exit flow of said charging turbine directly gets in the rotor of said power turbine at a predetermined angle does work.
2. counter rotating turbine integrated apparatus according to claim 1 is characterized in that, said charging turbine is a radial turbine.
3. counter rotating turbine integrated apparatus according to claim 1 is characterized in that, said charging turbine is a combined flow turbine.
4. according to claim 2 or 3 described counter rotating turbine integrated apparatuss, it is characterized in that said power turbine is an axial-flow turbine.
5. counter rotating turbine integrated apparatus according to claim 4 is characterized in that, the blade outlet angle of said power turbine is constructed such that the exit flow of said power turbine flows out to approach axial speed.
6. an engine system is characterized in that, comprising:
Motor;
According to each described counter rotating turbine integrated apparatus among the claim 1-5, wherein said charging turbine is installed in the downstream of gas exhaust manifold of motor receiving the air-flow that said motor is discharged, and said power turbine is arranged in the downstream of said charging turbine;
Gas compressor, said gas compressor are connected with said charging turbine and are driven so that the air-flow that gets into it is carried out supercharging by said charging turbine;
Intercooler, said intercooler are connected between the cylinder of said gas compressor and motor with the cooling of the air-flow after the said supercharging and be sent in the cylinder of said motor; And
Hydraulic couplers, the input shaft of said hydraulic couplers links to each other with said power turbine, and output shaft links to each other with the bent axle of motor and is passed to said bent axle with the recovery merit with said power turbine.
7. engine system according to claim 6 is characterized in that, further comprises:
First transmitting assemblies, said first transmitting assemblies are connected between the input shaft and said power turbine of said hydraulic couplers.
8. engine system according to claim 7 is characterized in that, further comprises:
Second transmitting assemblies, said second transmitting assemblies are connected between the output shaft and said bent axle of said hydraulic couplers.
9. engine system according to claim 8 is characterized in that, said first transmitting assemblies and said second transmitting assemblies are respectively the one-level gear-driven assembly.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100318636A CN102536432A (en) | 2012-02-13 | 2012-02-13 | Counter-rotating turbine combination device and engine system with same |
| PCT/CN2013/071577 WO2013120449A1 (en) | 2012-02-13 | 2013-02-08 | Composite apparatus with contra-rotating turbines and engine system including same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100318636A CN102536432A (en) | 2012-02-13 | 2012-02-13 | Counter-rotating turbine combination device and engine system with same |
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| Publication Number | Publication Date |
|---|---|
| CN102536432A true CN102536432A (en) | 2012-07-04 |
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| CN2012100318636A Pending CN102536432A (en) | 2012-02-13 | 2012-02-13 | Counter-rotating turbine combination device and engine system with same |
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| WO (1) | WO2013120449A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013120449A1 (en) * | 2012-02-13 | 2013-08-22 | 清华大学 | Composite apparatus with contra-rotating turbines and engine system including same |
| CN104533620A (en) * | 2014-10-30 | 2015-04-22 | 西安交通大学 | Compact gas turbine device adopting low-combustion value gas fuel |
| CN106948926A (en) * | 2017-05-11 | 2017-07-14 | 大连依勒斯涡轮增压技术有限公司 | A kind of compact two-stage turbine machine |
| CN109113792A (en) * | 2018-10-30 | 2019-01-01 | 常胜 | Recombination boosting turbine |
| WO2021032210A1 (en) * | 2019-08-22 | 2021-02-25 | 上海必修福企业管理有限公司 | Turbofan transducer, power generation system thereof, and power generation method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE102018109138A1 (en) * | 2018-04-17 | 2019-10-17 | Abb Turbo Systems Ag | Turbocharger with integrated turbine |
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| WO2013120449A1 (en) * | 2012-02-13 | 2013-08-22 | 清华大学 | Composite apparatus with contra-rotating turbines and engine system including same |
| CN104533620A (en) * | 2014-10-30 | 2015-04-22 | 西安交通大学 | Compact gas turbine device adopting low-combustion value gas fuel |
| CN106948926A (en) * | 2017-05-11 | 2017-07-14 | 大连依勒斯涡轮增压技术有限公司 | A kind of compact two-stage turbine machine |
| CN109113792A (en) * | 2018-10-30 | 2019-01-01 | 常胜 | Recombination boosting turbine |
| WO2021032210A1 (en) * | 2019-08-22 | 2021-02-25 | 上海必修福企业管理有限公司 | Turbofan transducer, power generation system thereof, and power generation method |
Also Published As
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| WO2013120449A1 (en) | 2013-08-22 |
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