CN101985897A - Complex turbine device with variable section - Google Patents
Complex turbine device with variable section Download PDFInfo
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- CN101985897A CN101985897A CN2010102799538A CN201010279953A CN101985897A CN 101985897 A CN101985897 A CN 101985897A CN 2010102799538 A CN2010102799538 A CN 2010102799538A CN 201010279953 A CN201010279953 A CN 201010279953A CN 101985897 A CN101985897 A CN 101985897A
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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
- F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
- F02B37/225—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits air passages
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- 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
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
- F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
- F01D5/048—Form or construction
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- 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
- F01D9/026—Scrolls for radial machines or engines
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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
- F02B37/02—Gas passages between engine outlet and pump drive, e.g. reservoirs
- F02B37/025—Multiple scrolls or multiple gas passages guiding the gas to the pump drive
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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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- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
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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)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a complex turbine device with a variable section, comprising a double flow channel turbine volute, wherein the double flow channel turbine volute is provided with two air flow passageways; the double flow channel turbine volute is provided with a volute air outlet and a volute air inlet which are communicated with the air flow passageways; a complex turbine impeller is arranged in the double flow channel turbine volute; and the complex turbine impeller is formed by compounding two turbine impellers which correspond to the two air flow passageways one by one. In the invention, the variable section function can be achieved by design and development of the turbine of a turbocharger and by using the complex turbine device, thereby effectively solving the defects of poor reliability and high cost of a vane type turbocharger with the variable section, effectively improving the efficiency of the turbine of an engine in low speed and increasing the torque output of the turbine.
Description
Technical field
The present invention relates to a kind of novel turbine device, relate to a kind of turbo charged variable cross section composite turbine device that is used for specifically, can effectively take into account the low speed and the high-speed boosting requirement of motor, belong to the supercharging of internal combustion engine field.
Background technique
Along with the progressively raising of emission standard, pressurized machine is widely used in modern motor.In order to satisfy under all operating modes of motor performance and the emission request under the low speed operating mode particularly, pressurized machine must provide higher boost pressure, and having the can regulate function of engine charge pressure and exhaust pressure, the variable cross section pressurized machine has become the research and development emphasis in supercharging field.At present generally adopt the structure that increases rotatable blade at turbine volute nozzle place to satisfy the requirement of variable cross section, compare with exhaust gas bypass type pressurized machine with constant cross-section, it can widen the matching range of turbosupercharger and motor effectively, realizes the can regulate function of boost pressure and exhaust pressure.
Rotary vane type variable cross section supercharger structure schematic representation as shown in Figure 1, the turbine portion branch of rotary vane type variable cross section pressurized machine comprises turbine volute 20, spiral case nozzle 22, turbine wheel 24 3 parts.The waste gas that motor is discharged arrives spiral case nozzle 22 through turbine volute intake duct 26, one group of rotatable nozzle vane 23 is installed at the nozzle place, driving mechanism 19 changes the circulation area of nozzle and the angle of exit flow by the angle of control nozzle vane 23, make air-flow enter turbine wheel 24 actings by design point of view, turbine wheel drives coaxial mounted compressor impeller 29 high speed rotating, participate in send into cylinder after the compresses fresh air in burning, realize the purpose of supercharging.
Rotary vane type variable cross section pressurized machine changes the turbine circulation area by the angle that changes nozzle vane, and control is convenient.But find that in the application of reality there are some shortcomings in this rotary vane type variable geometry turbocharger.Under big flow operating mode, the aperture of nozzle vane increases, and the trailing edge of nozzle vane is nearer apart from the leading edge of turbine blade, and the particle in the waste gas can cause bigger wearing and tearing to nozzle vane.Under low flow rate condition, the nozzle vane aperture is very little, the circumferential speed height of jet expansion air-flow and radial velocity is low at this moment, and the turbine air inlet angle is very big, and turbine becomes pure action turbine, and turbine efficiency descends.The flow area at nozzle place changes acutely on the other hand, and restriction loss is bigger, thereby turbine efficiency is further descended.In addition, turbocharger operation is in the rugged environment of a high temperature, strong vibration, too complex mechanical construction makes the reliability and the life-span of improving rotary vane type variable cross section pressurized machine become difficult unusually, too complex mechanical construction also causes high cost, has limited the market of the type variable cross section pressurized machine and has used.
Therefore wish design a kind of simple in structure, cost is low, reliability is high, and when small flow, have greater efficiency, than the novel changable cross section turbine structure of high pulling torque, solve the problem that the turbosupercharger of present rotation blade structure exists aspect reliability, cost and efficient, satisfy motor requirement to boost pressure under each operating mode.
Summary of the invention
The problem to be solved in the present invention is that the above-mentioned defective at rotary vane type variable cross section pressurized machine provides a kind of turbo charged variable cross section composite turbine device that is used for, and can improve turbine in the efficient in low engine speed district and the response characteristic of moment of torsion and turbine rotor.
In order to address the above problem, the present invention by the following technical solutions:
A kind of variable cross section composite turbine device, comprise the double flow channel turbine volute, described double flow channel turbine volute is provided with two air-flow paths, the double flow channel turbine volute is provided with spiral case air outlet and the spiral case suction port that is communicated with air-flow path, in the double flow channel turbine volute, be provided with the composite turbine impeller, described composite turbine impeller is composited by two turbine wheels, and two turbine wheels and two air-flow paths be corresponding matching one by one.
Below be the invention further improvement of these options:
Described turbine wheel comprises one-level turbine wheel and two-stage turbine impeller, and described one-level turbine wheel is fixed in the outer fringe position of two-stage turbine impeller.
Further improve:
Described one-level turbine wheel comprises one-level turbine inlet portion and one-level turbine intermediate portion; The two-stage turbine impeller comprises two-stage turbine import department and two-stage turbine intermediate portion, and described one-level turbine intermediate portion and two-stage turbine import department are affixed, the shared turbine outlet portion of one-level turbine wheel and two-stage turbine impeller.
Further improve:
The inlet diameter of described one-level turbine wheel is greater than the inlet diameter of two-stage turbine impeller; The entrance width of one-level turbine wheel is less than the entrance width of two-stage turbine impeller.
The entrance width of firsts and seconds turbine inlet portion and inlet diameter require to design according to the specific performance of motor, the entrance width of one-level import department and inlet diameter performance and the emission request when satisfying low engine speed is design object, the entrance width of two-stage turbine import department and inlet diameter match with the one-level turbine wheel, performance and emission request when satisfying high rotating speed in the motor are design object, and satisfy the through-current capability requirement of constant engine point, avoid pressurized machine hypervelocity and boost pressure too high.
Further improve:
Described one-level turbine wheel is arranged near wheel disk of turbine one side, and the two-stage turbine impeller is arranged near runner band one side.
Further improve: described wheel disk of turbine is a hollow out type wheel disc, adopts this structure can obtain less turbine rotor rotary inertia, improves the booster response characteristic of turbosupercharger.
The another kind of improvement: described wheel disk of turbine is semiclosed wheel disc, and the flow losses that adopt after this structure gap by the wheel disc back to cause reduce, and turbine efficiency improves, and can also improve the intensity of turbine wheel simultaneously.
The another kind of improvement:
Described air-flow path comprises small flow channels and big runner, and described small flow channels matches with the one-level turbine, and big runner matches with two-stage turbine.
Further improve:
The circulation area of described small flow channels is less than the circulation area of big runner, and the outlet of two runners is and column distribution.
Further improve:
The distance of the outlet of described small flow channels and turbine spin axis is greater than the outlet of big runner and the distance of turbine spin axis, and the exit width of small flow channels is less than the exit width of big runner.
Further improve:
Be provided with midfeather between described small flow channels and the big runner, described midfeather and double flow channel turbine volute are cast as one.
Further improve:
The sectional shape of described midfeather is wing, and it is linear structure that the midfeather end is positioned at big runner one side, and it is arcuate structure that the midfeather end is positioned at small flow channels one side.
The thickness of above-mentioned midfeather is by the one-level turbine intermediate portion axial length decision of composite turbine, when thickness is big, for alleviating the weight of double flow channel turbine volute, economical with materials, stress excessive when avoiding temperature variation is concentrated, and the inside of midfeather can be made as hollow-core construction.
Further improve:
Small flow channels is positioned at the side away from the spiral case air outlet, and big runner is positioned at the side near the spiral case air outlet, and described one-level turbine wheel is arranged on the side near wheel disk of turbine, and the two-stage turbine impeller is arranged on the side near runner band.
The another kind of improvement:
Small flow channels is positioned at the side near the spiral case air outlet, and described big runner is positioned at the side away from the spiral case air outlet, and described one-level turbine wheel is arranged on the side near runner band, and the two-stage turbine impeller is arranged on the side near wheel disk of turbine.
Further improve:
Nozzle place at big runner is provided with air vane guide, and described air vane guide tilts to install, and described air vane guide tilts to the turbine sense of rotation, enters turbine to guarantee air-flow angle in accordance with regulations.Exhaust energy utilization ratio when adopting this kind technological scheme can improve the motor high speed, and the backflow that two-stage turbine inlet produces when effectively stoping low engine speed enters big runner.
The another kind of improvement:
Nozzle place in small flow channels is provided with air vane guide, and described air vane guide tilts to install, and described air vane guide tilts to the turbine sense of rotation, flows into turbine to guarantee air-flow direction in accordance with regulations.Turbine efficiency when adopting this kind technological scheme to improve low engine speed, the exhaust energy utilization ratio when improving low engine speed.
The another kind of improvement:
Nozzle place at small flow channels and big runner is provided with air vane guide respectively, described air vane guide tilts to install, described air vane guide tilts to the turbine sense of rotation, to guarantee that air-flow direction in accordance with regulations flows into turbine, the backflow that two-stage turbine inlet produced when the air vane guide at big runner nozzle place can effectively stop low engine speed enters big runner.Adopt this kind technological scheme can improve under the most of operating mode of motor, satisfy the supercharging requirement of each operating mode of motor the utilization ratio of exhaust energy.
The present invention is by designing and developing turbocharger turbine, adopt the composite turbine device to realize the variable cross section function, solved the high deficiency of poor reliability, cost of rotary vane type variable cross section pressurized machine effectively, the efficient of turbine and the moment of torsion output that increases turbine in the time of can effectively improving low engine speed.
When low engine speed, the exhausted air quantity that motor is discharged is less, and the air inlet adjustment valve cuts out, and all exhausts all enter small flow channels, enters the one-level turbine inlet portion acting of composite turbine through small flow channels.Small flow channels has less actual internal area, can effectively improve the suction pressure of turbine volute import, increases the exhaust energy that enters turbine; One-level turbine inlet portion has less air inlet width, and less air inlet width makes that the inlet-duct area of one-level turbine inlet portion is less, and excessive turbine air inlet angle in the time of can effectively avoiding low engine speed reduces the air inlet incidence loss of turbine inlet; One-level turbine inlet portion has bigger inlet diameter again, under the constant situation of rotating speed, can obtain higher rim velocity, too small U/C in the time of can effectively avoiding low engine speed, make turbine be operated in efficient region, adopt bigger inlet diameter can obtain bigger turbine moment of torsion simultaneously, improve the acting ability of turbine.By the increase of turbine air inlet energy and the raising of turbine efficiency, make full use of the energy in the waste gas, improve the power and the moment of torsion output of turbine, the boost pressure when improving low engine speed is also avoided too high exhaust back pressure.Because the small flow channels circulation area is little, the one-level turbine wheel has big inlet diameter, can improve the booster response characteristic of pressurized machine simultaneously, reduce the influence of supercharging sluggishness.The composite turbine device of being invented can effectively promote the low engine speed performance and reduce discharging.
During high rotating speed, the exhausted air quantity that motor is discharged is more in motor, and the air inlet adjustment valve is opened, the aperture of valve control mechanism control air inlet adjustment valve, and reasonable distribution enters the gas flow of big or small runner.Because the negotiability difference of big or small runner, the acting ability of one-level turbine and two-stage turbine is different with negotiability, enter the ratio of the fluid of big or small runner by change, can effectively regulate the exhaust pressure of motor and the power output of turbine, satisfy performance and the emission request of motor under the high speed operating mode.
Double flow channel turbine volute structure among the present invention and common double runner turbine volute structure are more or less the same, and be simple in structure, inheritance good, qualified casting is higher; Composite turbine impeller among the present invention can obtain high pneumatic efficiency and high structural strength by modern CFD, FEA analysis of technology and optimization; Composite turbine device among the present invention can adopt existing casting and process equipment to produce, the low and quick easily through engineering approaches that realizes of cost.Air inlet adjustment control mechanism among the present invention is simple, and control mode realizes easily, the reliability height.
In sum, adopt the composite turbine device can satisfy the supercharging requirement of the full operating mode scope of motor effectively, big variation does not take place in the supercharger integrated structure of the type, do not need to increase novel production device or repacking existing equipment, cost is low, realize having the vast market promotional value easily, can obtain good effect.
The present invention will be further described below in conjunction with drawings and Examples:
Description of drawings
Accompanying drawing 1 is a rotary vane type variable cross section supercharger structure schematic representation in the background technique of the present invention;
Accompanying drawing 2 is structural representations of composite turbine device in the embodiment of the invention 1;
Accompanying drawing 3 is meridional channel structural representations of composite turbine device in the embodiment of the invention 1;
Accompanying drawing 4 is the composite turbine blade wheel structure schematic representation that adopt hollow out type wheel disc in the embodiment of the invention 1;
Accompanying drawing 5 is the composite turbine blade wheel structure schematic representation that adopt semiclosed wheel disc in the embodiment of the invention 1;
Accompanying drawing 6 is composite turbine structural representations in the embodiment of the invention 2;
Accompanying drawing 7 is composite turbine structural representations in the embodiment of the invention 3;
Accompanying drawing 8 is composite turbine structural representations in the embodiment of the invention 4;
Accompanying drawing 9 is composite turbine structural representations in the embodiment of the invention 5.
Among the figure: 1-composite turbine impeller; 2-double flow channel turbine volute; 3-air inlet adjustment valve; 4-spiral case suction port; 5-one-level turbine wheel; 6-two-stage turbine impeller; The 7-small flow channels; The big runner of 8-; 9-one-level turbine inlet portion; 10-one-level turbine intermediate portion; 11-two-stage turbine import department; 12-two-stage turbine intermediate portion; 13-turbine outlet portion; 14-spiral case air outlet; The 15-midfeather; The 16-air vane guide; The 17-compressor casing; The 18-middle case; The 19-driving mechanism; The 20-turbine volute; 21-nozzle ring supporting disk; 22-spiral case nozzle; The 23-nozzle vane; The 24-turbine wheel; 25-spiral case relief opening; 26-spiral case air inlet runner; The 27-floating bearing; The 28-turbine rotor shaft; The 29-compressor impeller; 30-hollow out type wheel disc; The semiclosed wheel disc of 31-; The 32-upper body; The 33-connecting bolt; The 34-lower case; The 35-valve control mechanism; A1-turbine spin axis; The entrance width of b1-one-level turbine wheel; The entrance width of b2-two-stage turbine impeller; The inlet diameter of D1-one-level turbine wheel; The inlet diameter of D2-two-stage turbine impeller.
Embodiment
As shown in Figure 3, described turbine wheel comprises one-level turbine wheel 5 and two-stage turbine impeller 6, and described one-level turbine wheel 5 is fixed in the outer fringe position of two-stage turbine impeller 6.
Described one-level turbine wheel 5 comprises one-level turbine inlet portion 9 and one-level turbine intermediate portion 10; Two-stage turbine impeller 6 comprises two-stage turbine import department 11 and two-stage turbine intermediate portion 12, and described one-level turbine intermediate portion 10 is affixed with two-stage turbine import department 11, one-level turbine wheel 5 and two-stage turbine impeller 6 shared turbine outlet portions 13.
The inlet diameter D1 of described one-level turbine wheel is greater than the inlet diameter D2 of two-stage turbine impeller; The entrance width b1 of one-level turbine wheel is less than the entrance width b2 of two-stage turbine impeller.
The entrance width of firsts and seconds turbine inlet portion and inlet diameter require to design according to the specific performance of motor, the entrance width b1 of one-level import department and inlet diameter D1 performance and the emission request when satisfying low engine speed is design object, the entrance width b2 of two-stage turbine import department and inlet diameter D2 match with the one-level turbine wheel, performance and emission request when satisfying high rotating speed in the motor are design object, and satisfy the through-current capability requirement of constant engine point, avoid pressurized machine hypervelocity and boost pressure too high.
The small flow channels 7 of described double flow channel turbine volute 2 and big runner 8 are rationally separated by midfeather 15, and described midfeather 15 is cast as one with double flow channel turbine volute 2.The sectional shape of described midfeather 15 is wing, and it is straight line that the midfeather end is positioned at big runner 8 one sides, and it is arc that the midfeather end is positioned at small flow channels 7 one sides, matches with the one-level turbine intermediate portion 10 of composite turbine impeller; The thickness of midfeather is by the axial length decision of the one-level turbine intermediate portion 10 of composite turbine, and when thickness was big, the inside of midfeather was made as hollow-core construction.
As shown in Figure 4, the wheel disc of described composite turbine impeller 1 can be hollow out type wheel disc 30, adopts this structure can obtain less turbine rotor rotary inertia, improves the booster response characteristic of turbosupercharger.
When low engine speed, the exhausted air quantity that motor is discharged is less, and air inlet adjustment valve 3 cuts out, and all exhausts all enter small flow channels 7, enters one-level turbine inlet portion 9 actings of composite turbine through small flow channels 7.Small flow channels 7 has less actual internal area, can effectively improve the suction pressure of turbine volute import, increases the exhaust energy that enters turbine; One-level turbine inlet portion 9 has less air inlet width b1, and less air inlet width makes that the inlet-duct area of one-level turbine inlet portion 9 is less, and excessive turbine air inlet angle in the time of can effectively avoiding low engine speed reduces the air inlet incidence loss of turbine inlet; One-level turbine inlet portion 9 has bigger inlet diameter D1 again, under the constant situation of rotating speed, can obtain higher rim velocity, too small U/C in the time of can effectively avoiding low engine speed, make turbine be operated in efficient region, adopt bigger inlet diameter can obtain bigger turbine moment of torsion simultaneously, improve the acting ability of turbine.By the increase of turbine air inlet energy and the raising of turbine efficiency, make full use of the energy in the waste gas, improve the power and the moment of torsion output of turbine, the boost pressure when improving low engine speed is also avoided too high exhaust back pressure.Because small flow channels 7 circulation areas are little, the one-level turbine has big inlet diameter D1, can improve the booster response characteristic of turbine simultaneously.Described composite turbine device can effectively promote the low engine speed performance and reduce discharging.
During high rotating speed, the exhausted air quantity that motor is discharged is more in motor, and air inlet adjustment valve 3 is opened, the aperture of valve control mechanism 35 control air inlet adjustment valves 3, and reasonable distribution enters the gas flow of big or small runner.Because the negotiability difference of big or small runner, the acting ability of one-level turbine and two-stage turbine is different with negotiability, enter the ratio of the fluid of big or small runner by change, can effectively regulate the exhaust pressure of motor and the power output of turbine, satisfy performance and the emission request of motor under the high speed operating mode.
Patent of the present invention is at the demand of motor to variable-area turbocharger, finished the exploitation of composite turbine device, adopt the compound mode of two-stage turbine, turbine suction pressure when having improved low engine speed has also improved turbine efficiency, the low speed torque and the output power of motor have been improved, improve the booster response characteristic of motor, taken into account the boost demand under low engine speed and the high speed operating mode simultaneously.The type composite turbine device can adopt the casting and the processing technique of existing common pressurized machine to finish.
In the foregoing description 1, as shown in Figure 5, the wheel disc of described composite turbine impeller 1 also can be semiclosed wheel disc 31, and the flow losses that adopt after this structure gap by the wheel disc back to cause reduce, turbine efficiency improves, and can also improve the intensity of turbine wheel simultaneously.
After adopting this configuration, can eliminate the flow losses that gap, wheel disc back causes, the efficient of one-level turbine when further improving low engine speed.Because one-level turbine inlet diameter D1 is bigger, for easy for installation, double flow channel turbine volute 2 adopts split casting, the double flow channel turbine volute is divided into upper body 32 and lower case 34 two-part, casting and leave machining allowance respectively at the sealing surface place, the bolt 33 fastening Placements that add sealing gasket are adopted in sealing surface processing back, adjust corresponding pressurized machine assembly technology simultaneously.
Patent of the present invention is at the demand of motor to variable-area turbocharger, finished the exploitation of composite turbine device, adopt the compound mode of two-stage turbine, turbine suction pressure when having improved low engine speed has also improved turbine efficiency, the low speed torque and the output power of motor have been improved, improve the booster response characteristic of motor, taken into account the boost demand under low engine speed and the high speed operating mode simultaneously.The type composite turbine device can adopt the casting and the processing technique of existing common pressurized machine to finish.
Patent of the present invention is at the demand of motor to variable-area turbocharger, finished the exploitation of composite turbine device, adopt the compound mode of two-stage turbine, turbine suction pressure when having improved low engine speed has also improved turbine efficiency, the low speed torque and the output power of motor have been improved, improve the booster response characteristic of motor, taken into account the boost demand under low engine speed and the high speed operating mode simultaneously.The type composite turbine device can adopt the casting and the processing technique of existing common pressurized machine to finish.
Claims (14)
1. variable cross section composite turbine device, comprise double flow channel turbine volute (2), described double flow channel turbine volute (2) is provided with two air-flow paths, double flow channel turbine volute (2) is provided with spiral case air outlet (14) and the spiral case suction port (4) that is communicated with air-flow path, in double flow channel turbine volute (2), be provided with composite turbine impeller (1), it is characterized in that: described composite turbine impeller (1) is composited by two turbine wheels, and two turbine wheels and two air-flow paths be corresponding matching one by one.
2. variable cross section composite turbine device according to claim 1 is characterized in that: described turbine wheel comprises one-level turbine wheel (5) and two-stage turbine impeller (6), and described one-level turbine wheel (5) is fixed in the outer fringe position of two-stage turbine impeller (6).
3. variable cross section composite turbine device according to claim 2 is characterized in that: described one-level turbine wheel (5) comprises one-level turbine inlet portion (9) and one-level turbine intermediate portion (10); Two-stage turbine impeller (6) comprises two-stage turbine import department (11) and two-stage turbine intermediate portion (12), described one-level turbine intermediate portion (10) is affixed with two-stage turbine import department (11), one-level turbine wheel (5) and the shared turbine outlet portion of two-stage turbine impeller (6) (13).
4. according to claim 2 or 3 described variable cross section composite turbine devices, it is characterized in that: described one-level turbine wheel (5) is arranged near wheel disk of turbine one side, and two-stage turbine impeller (6) is arranged near runner band one side.
5. variable cross section composite turbine device according to claim 4 is characterized in that: described wheel disk of turbine is a hollow out type wheel disc (30).
6. variable cross section composite turbine device according to claim 4 is characterized in that: described wheel disk of turbine is semiclosed wheel disc (31).
7. variable cross section composite turbine device according to claim 2, it is characterized in that: described air-flow path comprises small flow channels (7) and big runner (8), described small flow channels (7) matches with one-level turbine (5), and big runner (8) matches with two-stage turbine (6).
8. variable cross section composite turbine device according to claim 7, it is characterized in that: the distance of the outlet of described small flow channels (7) and turbine spin axis (A1) is greater than the outlet of big runner (8) and the distance of turbine spin axis (A1), and the exit width of small flow channels (7) is less than the exit width of big runner (8).
9. variable cross section composite turbine device according to claim 8, it is characterized in that: be provided with midfeather (15) between described small flow channels (7) and the big runner (8), described midfeather (15) is cast as one with double flow channel turbine volute (2), the sectional shape of described midfeather (15) is wing, it is linear structure that the midfeather end is positioned at big runner (8) one sides, and it is arcuate structure that the midfeather end is positioned at small flow channels (7) one sides.
10. variable cross section composite turbine device according to claim 9, it is characterized in that: small flow channels (7) is positioned at the side away from spiral case air outlet (14), big runner (8) is positioned at the side near spiral case air outlet (14), described one-level turbine wheel (5) is arranged on the side near wheel disk of turbine, and two-stage turbine impeller (6) is arranged on the side near runner band.
11. variable cross section composite turbine device according to claim 10, it is characterized in that: small flow channels (7) is positioned at the side near spiral case air outlet (14), described big runner (8) is positioned at the side away from spiral case air outlet (14), described one-level turbine wheel (5) is arranged on the side near runner band, and two-stage turbine impeller (6) is arranged on the side near wheel disk of turbine.
12. variable cross section composite turbine device according to claim 11 is characterized in that: the nozzle place at big runner (8) is provided with air vane guide (16), and described air vane guide (16) tilts to install.
13. variable cross section composite turbine device according to claim 11 is characterized in that: the nozzle place of small flow channels (7) is provided with air vane guide (16), described air vane guide (16) tilts to install.
14. variable cross section composite turbine device according to claim 11 is characterized in that: the nozzle place at small flow channels (7) and big runner (8) is provided with air vane guide (16) respectively, and described air vane guide (16) tilts to install.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102799538A CN101985897A (en) | 2010-09-14 | 2010-09-14 | Complex turbine device with variable section |
| PCT/CN2010/001789 WO2012034258A1 (en) | 2010-09-14 | 2010-11-08 | Variable-section composite turbine apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102799538A CN101985897A (en) | 2010-09-14 | 2010-09-14 | Complex turbine device with variable section |
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| CN101985897A true CN101985897A (en) | 2011-03-16 |
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| CN2010102799538A Pending CN101985897A (en) | 2010-09-14 | 2010-09-14 | Complex turbine device with variable section |
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| WO (1) | WO2012034258A1 (en) |
Cited By (9)
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| WO2012094781A1 (en) * | 2011-01-12 | 2012-07-19 | Wang Hang | Axial-radial-flow composite turbocharger with a variable section |
| WO2013049971A1 (en) * | 2011-10-08 | 2013-04-11 | Zhu Zhifu | Volute device of variable geometry pulse gas inlet turbine |
| WO2013166627A1 (en) * | 2012-05-07 | 2013-11-14 | Wang Hang | Double-area turbine of turbine boosting |
| CN104870777A (en) * | 2013-01-04 | 2015-08-26 | 博格华纳公司 | Variable pivot center VTG vanes and vane pack assembly |
| CN106437880A (en) * | 2016-08-31 | 2017-02-22 | 无锡康明斯涡轮增压技术有限公司 | Turbine end structure for turbocharger |
| CN107250521A (en) * | 2015-03-05 | 2017-10-13 | 博格华纳公司 | Compressor assembly for motor vehicles |
| CN110735673A (en) * | 2019-11-18 | 2020-01-31 | 大连海事大学 | kinds of double-channel volute |
| CN112360763A (en) * | 2020-09-22 | 2021-02-12 | 东风汽车集团有限公司 | Turbocharger |
| CN114458416A (en) * | 2022-01-28 | 2022-05-10 | 东风商用车有限公司 | Floating type variable cross-section impeller structure in oil-gas separation system |
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| US10662904B2 (en) | 2018-03-30 | 2020-05-26 | Deere & Company | Exhaust manifold |
| US11073076B2 (en) | 2018-03-30 | 2021-07-27 | Deere & Company | Exhaust manifold |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012094781A1 (en) * | 2011-01-12 | 2012-07-19 | Wang Hang | Axial-radial-flow composite turbocharger with a variable section |
| WO2013049971A1 (en) * | 2011-10-08 | 2013-04-11 | Zhu Zhifu | Volute device of variable geometry pulse gas inlet turbine |
| WO2013166627A1 (en) * | 2012-05-07 | 2013-11-14 | Wang Hang | Double-area turbine of turbine boosting |
| CN104870777A (en) * | 2013-01-04 | 2015-08-26 | 博格华纳公司 | Variable pivot center VTG vanes and vane pack assembly |
| CN104870777B (en) * | 2013-01-04 | 2018-07-03 | 博格华纳公司 | Variable pivoting centre VTG blades and blade dial bundle LMS |
| US10036274B2 (en) | 2013-01-04 | 2018-07-31 | Borgwarner Inc. | Variable pivot center VTG vanes and vane pack assembly |
| CN107250521A (en) * | 2015-03-05 | 2017-10-13 | 博格华纳公司 | Compressor assembly for motor vehicles |
| CN106437880A (en) * | 2016-08-31 | 2017-02-22 | 无锡康明斯涡轮增压技术有限公司 | Turbine end structure for turbocharger |
| CN110735673A (en) * | 2019-11-18 | 2020-01-31 | 大连海事大学 | kinds of double-channel volute |
| CN112360763A (en) * | 2020-09-22 | 2021-02-12 | 东风汽车集团有限公司 | Turbocharger |
| CN114458416A (en) * | 2022-01-28 | 2022-05-10 | 东风商用车有限公司 | Floating type variable cross-section impeller structure in oil-gas separation system |
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| Publication number | Publication date |
|---|---|
| WO2012034258A1 (en) | 2012-03-22 |
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Application publication date: 20110316 |