CN101949326A - Variable section double-channel air intake turbine - Google Patents
Variable section double-channel air intake turbine Download PDFInfo
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- CN101949326A CN101949326A CN2010102801576A CN201010280157A CN101949326A CN 101949326 A CN101949326 A CN 101949326A CN 2010102801576 A CN2010102801576 A CN 2010102801576A CN 201010280157 A CN201010280157 A CN 201010280157A CN 101949326 A CN101949326 A CN 101949326A
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- 238000000926 separation method Methods 0.000 abstract description 2
- 239000002912 waste gas Substances 0.000 description 11
- 230000006872 improvement Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- 230000008859 change Effects 0.000 description 6
- 239000007789 gas Substances 0.000 description 6
- 238000005266 casting Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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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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- 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
- 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
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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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
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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)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a variable section double-channel air intake turbine, comprising a turbine volute, wherein the turbine volute is provided with a volute nozzle; a turbine wheel is installed in the turbine volute; the turbine volute is provided with a volute air intake channel; a middle wall is arranged in the volute air intake channel and separates the volute air intake channel into a small volute air intake channel and a big volute air intake channel; and the radial section of the middle wall is of arc structure, with radian of 60-180 degrees. The turbine changes the position of the end of the middle wall on the circumference through reasonable separation of the middle wall, thus changing the corresponding air intake area angles of the big and small channels and being capable of realizing that the air intake area angle of the small volute air intake channel changes between 60 degrees and 180 degrees and the corresponding air intake area angle of the big volute air intake channel changes between 300 degrees and 180 degrees.
Description
Technical field
The present invention relates to a kind of variable cross section pressurized machine, relate to the different variable cross section double flow channel air inlet turbine of a kind of actual internal area specifically, can take into account the high low speed supercharging requirement of motor effectively, 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 performance and the emission request under all operating modes of motor, pressurized machine must have the can regulate function of boost pressure and exhaust pressure.Along with the enforcement of state's four Abgasgesetzs, the variable cross section pressurized machine has become the emphasis of domestic and international research and development.Generally adopt at present the structure that increases rotation blade at turbine volute nozzle place to satisfy the requirement of variable cross section, compare with the conventional turbine pressurized machine, 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 geometry turbocharger structural representation as shown in Figure 1, rotary vane type turbo-charger impeller part and turbine part, impeller partly comprises compressor casing 1, compressor impeller 13 is installed in compressor casing 1, rotor shaft 12 is installed on the compressor impeller 13, described turbine portion branch comprises spiral case 4, spiral case nozzle 6, turbine wheel 8 three parts, be connected by middle case 2 between described compressor casing 1 and the spiral case 4, nozzle vane 7 is installed in the spiral case 4, and described nozzle vane 7 is installed on the nozzle ring supporting disk 5.
The waste gas that motor is discharged arrives spiral case nozzle 6 through turbine inlet 10, driving mechanism 3 is regulated the circulation area of nozzle and the angle of outlet waste gas by control nozzle vane 7, make waste gas be distributed to the periphery of turbine wheel 8 by design point of view, promote turbine wheel 8 high speed rotating, waste gas is finished merit to turbine after spiral case relief opening 9 is discharged.Under the support of middle case 2 internal float dynamic bearings 11, drive compressor impeller 13 high speed rotating by rotor shaft 12, the air that axially enters gas compressor is compressed.Air after the compression participates in burning through being admitted to cylinder after the collection of compressor casing 1, realizes the purpose of supercharging.
The rotary vane type variable-area turbocharger changes the turbine circulation area by the angle that changes nozzle vane, and control is convenient.But find that by the application of reality there are some shortcomings in this rotary vane type variable geometry turbocharger:
When motor during in big flow operating mode, the aperture of nozzle vane 7 increases, and nozzle vane 7 is nearer apart from the turbine blade leading edge, and exhaust gas particle can cause bigger wearing and tearing to nozzle vane 7.When motor during at low flow rate condition, nozzle vane 7 apertures are very little, the circumferential speed height of jet expansion air-flow at this moment, and turbine becomes action turbine, and the aerodynamic loss of gas flow is also relatively more serious in addition, thereby efficiency of turbocharger is descended.
The waste gas that motor is discharged has the delivery temperature about 600～700 degree, and the trend of further lifting is arranged, and exhaust high temperature all has strict requirement to nozzle vane 7, nozzle ring supporting disk 5, driving mechanism 3.Abominable, the strong vibration of turbocharger operation environment all has very high requirement to the reliability of driving mechanism 3 in addition.The reliability of driving mechanism 3 is relatively poor to be the technical problem of also not resolving fully till now.
The cost of rotary vane type variable cross section pressurized machine is very high, and this makes many motors producer hang back to its expensive price.Cost and age limit the market of the type variable cross section pressurized machine.
Therefore wish design a kind of simple in structure, cost is low, reliability is high, and the novel changable cross section turbine structure that when small flow, has greater efficiency, solve the problem that the turbosupercharger of present rotation blade structure exists aspect reliability 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 at the efficient of traditional rotary blade type variable-area turbocharger and the relatively poor problem of reliability, provide a kind of simple in structure, cost is low, reliability is high, control variable cross section double flow channel air inlet turbine easily.
In order to address the above problem, the present invention adopts technological scheme:
A kind of variable cross section double flow channel air inlet turbine, comprise turbine volute, described turbine volute is provided with the spiral case nozzle, turbine wheel is installed in the turbine volute, described turbine volute is provided with the spiral case air inlet runner, is provided with midfeather in the spiral case air inlet runner, and described midfeather is separated into spiral case air inlet small flow channels and the big runner of spiral case air inlet with the spiral case air inlet runner, the radial cross section of described midfeather is an arcuate structure, and its radian is 60 °～180 °.
Below be the utility model for further improvement of these options:
A wherein end and the turbine volute of described midfeather are affixed, and described spiral case air inlet small flow channels is being communicated with near midfeather the other end position with the big runner of spiral case air inlet.
Further improve:
The circulation area of described spiral case air inlet small flow channels is less than the circulation area of the big runner of described spiral case air inlet.
Further improve:
Described midfeather and the described turbine volute structure that is cast as one.
Further improve:
Position near the import of spiral case air inlet runner on the described midfeather is provided with by-pass port, and the air inlet adjustment valve is installed on by-pass port, and described air inlet adjustment valve and air inlet adjustment control mechanism are in transmission connection.
Described air inlet adjustment control mechanism can be regulated the aperture of described air inlet adjustment valve according to the actual conditions of motor, realizes the selection of spiral case air inlet runner and the control of negotiability.
The another kind of improvement:
Described spiral case air inlet small flow channels can be positioned at the big runner of spiral case air inlet inboard, and when described spiral case air inlet small flow channels was positioned at the inboard, circulation was lost minimum and had good accelerating performance in the spiral case during low engine speed;
The another kind of improvement:
Described spiral case air inlet small flow channels is positioned at the big runner of the spiral case air inlet outside, and when described spiral case air inlet small flow channels was positioned at the outside, it is very fast that the big runner of spiral case air inlet prolongs circumferential contraction, can realize less turbine monnolithic case size.
The another kind of improvement:
The nozzle place of the big runner of described spiral case air inlet is provided with several air vane guides, and several air vane guides are the semicircle arcuation to be arranged, and tilts to install along the turbine sense of rotation.
The another kind of improvement:
Nozzle place in spiral case air inlet small flow channels is provided with several air vane guides, and several air vane guides are the semicircle arcuation to be arranged, and tilts to install along the turbine sense of rotation.
The another kind of improvement:
The nozzle location of described turbine volute is provided with several air vane guides, and it is circle-shaped evenly distributed that several air vane guides are, and tilts to install along the turbine sense of rotation.
Described air vane guide tilts to the turbine sense of rotation, flows into turbine to guarantee air-flow direction in accordance with regulations.
The present invention is by the reasonable separation of described midfeather, the end that changes midfeather is in the position that makes progress in week, thereby change the corresponding air inlet regional perspective of big or small runner, the air inlet regional perspective that can realize described spiral case air inlet small flow channels changes between the 60-180 degree, and the air inlet regional perspective of the big runner of corresponding described spiral case air inlet changes between the 300-180 degree.
After adopting variable cross section double flow channel air inlet turbine, under the low engine speed operating mode, the air inlet adjustment valve is in closed condition, and all engine exhausts enter spiral case air inlet small flow channels.Because the actual internal area of spiral case air inlet small flow channels is little and for air inlet, can effectively promote the turbine suction pressure, improves the available energy in the waste gas; Because spiral case air inlet small flow channels adopts air inlet, turbine wheel air inlet area under low engine speed, the big runner closed condition of spiral case air inlet dwindles, less than half of the turbine wheel air inlet area under the full admission state, the air inlet angle of turbine can be controlled in the efficient region about 70 degree, compare with rotary vane type variable cross section pressurized machine, excessive air inlet incidence loss when having avoided low speed, the turbine efficiency in the time of can effectively improving low speed.The raising of turbine efficiency when lifting by the waste gas available energy and low speed, the turbine output when effectively increasing low engine speed makes boost pressure raise the higher boost pressure demand when satisfying low engine speed; Because the volume of spiral case air inlet small flow channels is little, the waste gas that motor is discharged can enter turbine wheel fast simultaneously, and the flow path that effectively shortens air-flow improves the acceleration individual features of motor to eliminate the influence that turbo lag brings.By the effect of above two aspects, effectively improve the low engine speed performance and reduce discharging.
Under motor high speed operating mode, the air inlet adjustment valve is in opening state, and spiral case air inlet small flow channels and the big runner of spiral case air inlet are worked together.Because the engine exhaust flow that enters spiral case air inlet small flow channels and the big runner of spiral case air inlet is subjected to the control of air inlet adjustment valve opening, causes actual turbine volute actual internal area and turbine wheel air inlet variable area.Under identical turbine volute air inlet total discharge, if the air inlet adjustment valve opening is little, the exhaust that enters spiral case air inlet small flow channels is many and to enter the exhaust of the big runner of spiral case air inlet few, and actual turbine volute actual internal area is relative less with turbine wheel air inlet area; If the air inlet adjustment valve opening is big, the exhaust that enters spiral case air inlet small flow channels is few and to enter the exhaust of the big runner of spiral case air inlet many, and actual turbine volute actual internal area and turbine wheel air inlet area are relatively large.Aperture by control mechanism control air inlet adjustment valve, realize the fluid passage selection and the assignment of traffic of big or small air inlet runner, turbine volute actual internal area and turbine wheel air inlet area that control is actual, can effectively control the exhaust pressure and the boost pressure of motor, to satisfy motor boost demand under the high speed operating mode.Simultaneously, total air inlet area of total actual internal area of big or small spiral case air inlet runner and turbine satisfies the negotiability demand under the constant engine operating mode, avoids motor to cross the hypervelocity of supercharging and pressurized machine.
The present invention is simple in structure, and inheritance is good, and cost is low, realizes fast easily through engineering approaches can effectively satisfying the supercharging requirement of the full operating mode scope of motor.
The present invention will be further described below in conjunction with drawings and Examples:
Description of drawings
Accompanying drawing 2 is the structural representation of the embodiment of the invention 1;
Accompanying drawing 3 is that K-K in the accompanying drawing 2 is to sectional view;
Accompanying drawing 5 is 180 turbine structure schematic representation when spending for the air inlet zone angle [alpha] of spiral case air inlet small flow channels in the embodiment of the invention 1;
Accompanying drawing 7 is the turbine structure schematic representation behind the location swap of spiral case air inlet size runner in the embodiment of the invention 2;
Accompanying drawing 8 is the structural representation that air vane guide is installed at the nozzle place of the big runner of spiral case air inlet in the embodiment of the invention 3;
Accompanying drawing 9 be the nozzle place of spiral case air inlet small flow channels in the embodiment of the invention 4 install air vane guide structural representation;
Accompanying drawing 10 for the nozzle place of spiral case air inlet size runner in the embodiment of the invention 5 install simultaneously air vane guide structural representation.
Among the figure: the 1-compressor casing; The 2-middle case; The 3-driving mechanism; The 4-turbine volute; 5-nozzle ring supporting disk; 6-spiral case nozzle; The 7-nozzle vane; The 8-turbine wheel; 9-spiral case relief opening; 10-spiral case air inlet runner; The 11-floating bearing; The 12-turbine rotor shaft; The 13-compressor impeller; 14-turbine case cover plate; 15-air inlet adjustment valve; 16-air inlet adjustment control mechanism; The 17-support rim; 18-spiral case air inlet small flow channels; The big runner of 19-spiral case air inlet; The 20-midfeather; The 21-air vane guide; The 22-by-pass port.
Embodiment
The radial cross section of described midfeather 20 is an arcuate structure, a wherein end and the turbine volute 4 of described midfeather 20 are affixed, described spiral case air inlet small flow channels 18 is being communicated with near midfeather 20 the other end positions with the big runner 19 of spiral case air inlet, its radian can change between 60 °～180 °, realizes the change of the air inlet regional perspective of spiral case air inlet small flow channels 18 and the big runner 19 of spiral case air inlet in the position that makes progress in week by the end that changes midfeather 20.
Position near 10 imports of spiral case air inlet runner on the described midfeather 20 is provided with by-pass port 22, and air inlet adjustment valve 15 is installed on by-pass port 22, and described air inlet adjustment valve 15 is in transmission connection with air inlet adjustment control mechanism 16.
Turbine case is provided with turbine case cover plate 14, and turbine case cover plate 14 is used for preventing the leakage of gas in air inlet adjustment valve 15 opening processes, plays the effect of sealing.Also be provided with support rim 17 on the turbine case, support rim 17 is bolted to connection to be used for laying air inlet adjustment control mechanism 16 with actuator bracket.Make air inlet adjustment valve 15 form different apertures by air inlet adjustment control mechanism 16, control enters the gas flow of spiral case air inlet small flow channels 18 and the big runner 19 of spiral case air inlet, realizes the selection of runner and the control of negotiability.
Motor is under the low speed operating mode, air inlet adjustment valve 15 is in closed condition, this moment, all engine exhausts entered spiral case air inlet small flow channels 18, because the actual internal area of spiral case air inlet small flow channels 18 is little and be air inlet, can effectively promote the suction pressure of turbine volute 4, improve the available energy in the waste gas; Because spiral case air inlet small flow channels 18 adopts air inlet, under low engine speed, air inlet adjustment valve 15 closed conditions, turbine wheel air inlet area is less, less than half of the turbine wheel air inlet area under the full admission state, the air inlet angle of turbine can be controlled in the efficient region about 70 degree, compare excessive air inlet incidence loss when having avoided low speed, the turbine efficiency in the time of can effectively improving low speed with rotary vane type variable cross section pressurized machine.The raising of turbine efficiency when lifting by the waste gas available energy and low speed, the turbine output when effectively increasing low engine speed makes boost pressure raise the higher boost pressure demand when satisfying low engine speed; Because the volume of spiral case air inlet small flow channels 8 is little, the waste gas that motor is discharged can enter turbine wheel 8 fast simultaneously, and the flow path that effectively shortens air-flow improves the acceleration individual features of motor to eliminate the influence that turbo lag brings.By the effect of above two aspects, effectively improve the low engine speed performance and reduce discharging.
As Fig. 4, shown in Figure 5, spiral case air inlet small flow channels 18 can be carried out the specific aim design with the big runner 19 of spiral case air inlet according to the different requirements of motor at the air inlet regional perspective that makes progress in week.
Realize the change of the air inlet regional perspective of spiral case air inlet small flow channels 18 and the big runner 19 of spiral case air inlet by the position of end on circumferential direction that changes midfeather 20, α is the air inlet regional perspective of spiral case air inlet small flow channels 18, β is the air inlet regional perspective of the big runner 19 of spiral case air inlet, β=360-α.
The air inlet regional perspective of spiral case air inlet small flow channels 18 can change between the 60-180 degree, and the air inlet regional perspective of the corresponding big runner 19 of spiral case air inlet can change between the 300-180 degree.
As shown in Figure 6, motor is under high speed, and air inlet adjustment valve 15 is in opening state, and the big runner 19-of spiral case air inlet small flow channels 18 and spiral case air inlet plays work.Because the engine exhaust flow that enters spiral case air inlet small flow channels 18 and the big runner 19 of spiral case air inlet is subjected to the control of air inlet adjustment valve 15 apertures, causes actual turbine volute actual internal area and turbine wheel air inlet variable area.Under identical turbine volute air inlet total discharge, if air inlet adjustment valve 15 apertures are little, the exhaust that enters spiral case air inlet small flow channels 18 is many and to enter the exhaust of the big runner 19 of spiral case air inlet few, and actual turbine volute actual internal area is relative less with turbine wheel air inlet area; If air inlet adjustment valve 15 apertures are big, the exhaust that enters spiral case air inlet small flow channels 18 reduces and the exhaust that enters the big runner 19 of spiral case air inlet increases, and actual turbine volute actual internal area and turbine wheel air inlet area are relatively large.Aperture by air inlet adjustment control mechanism 16 control air inlet adjustment valves 15, realize the fluid passage selection and the assignment of traffic of big or small air inlet runner, turbine volute actual internal area and turbine wheel air inlet area that control is actual, can effectively control the exhaust pressure and the boost pressure of motor, to satisfy motor boost demand under the high speed operating mode.Simultaneously, total air inlet area of total actual internal area of big or small spiral case air inlet runner and turbine wheel satisfies the negotiability demand under the constant engine operating mode, avoids motor to cross the hypervelocity of supercharging and pressurized machine.
Patent of the present invention has been finished the exploitation of variable cross section double flow channel air inlet turbine at the demand of motor to variable-area turbocharger, has effectively utilized exhaust energy, has taken into account the boost demand under low engine speed and the high speed operating mode.The type variable cross section double flow channel air inlet turbine can adopt the casting and the process equipment of existing common pressurized machine to finish.
Embodiment 2, as shown in Figure 7, among the embodiment 1, can also be with the location swap of big runner of spiral case air inlet and spiral case air inlet small flow channels, and readjusted the position of air inlet adjustment control mechanism, remaining part is identical.
Spiral case air inlet small flow channels 18 is positioned at the big runner of spiral case air inlet 19 outsides, and motor has only spiral case air inlet small flow channels 18 to realize air inlet when low speed.Motor is when high speed, form different apertures by air inlet adjustment control mechanism 16 control air inlet adjustment valves 15, control enters the gas flow of spiral case air inlet small flow channels 18 and the big runner 19 of spiral case air inlet, realize the selection of runner and the control of negotiability, realize and the coupling of motor under high speed.
Spiral case air inlet small flow channels 18 is positioned at the big runner of spiral case air inlet 19 outsides, because the big runner 19 of spiral case air inlet is bigger than the actual internal area of spiral case air inlet small flow channels 18, it also than comparatively fast, can realize less turbine monnolithic case size in the dimensional contraction that makes progress in week.
Patent of the present invention has been finished the exploitation of variable cross section double flow channel air inlet turbine at the demand of motor to variable-area turbocharger, has effectively utilized exhaust energy, has taken into account the boost demand under low engine speed and the high speed operating mode.The type variable cross section double flow channel air inlet turbine can adopt the casting and the processing technique of existing common pressurized machine to finish.
Embodiment 3, as shown in Figure 8, in embodiment 1, can be provided with several air vane guides 21 at the nozzle place of the big runner 19 of spiral case air inlet, several air vane guides 21 are the semicircle arcuation and arrange, and, enter turbine with the exit flow angle in accordance with regulations that guarantees the big runner 19 of spiral case air inlet along turbine sense of rotation inclination installation.Exhaust energy utilization ratio when adopting this kind technological scheme can improve the motor high speed, and the exit flow of the end of spiral case air inlet small flow channels 18 enters the big runner 19 of spiral case air inlet when effectively stoping low engine speed.
Embodiment 5, as shown in figure 10, in embodiment 1, can be provided with several air vane guides 21 at the nozzle location of turbine volute, several air vane guides 21 are circle-shaped evenly distributed, and, enter turbine with the exit flow angle in accordance with regulations that guarantees spiral case air inlet small flow channels 18 and the big runner 19 of spiral case air inlet along turbine sense of rotation inclination installation.
Adopt this kind technological scheme can improve under the most of operating mode of motor, improved turbine efficiency, satisfy the supercharging requirement of each operating mode of motor the utilization of exhaust energy.
Patent of the present invention has been finished the exploitation of variable cross section double flow channel air inlet turbine at the demand of motor to variable-area turbocharger, has effectively utilized exhaust energy, has taken into account the boost demand under low engine speed and the high speed operating mode.The type variable cross section double flow channel air inlet turbine can adopt the casting and the processing technique of existing common pressurized machine to finish.
We have been described in detail invention according to the national patent method now, can discern the improvement or the replacement of specific embodiment disclosed herein for those skilled in the art.These modifications are within the spirit and scope of the present invention.
Claims (10)
1. variable cross section double flow channel air inlet turbine, comprise turbine volute (4), described turbine volute (4) is provided with spiral case nozzle (6), turbine wheel (8) is installed in the turbine volute (4), described turbine volute (4) is provided with spiral case air inlet runner (10), be provided with midfeather (20) in the spiral case air inlet runner (10), described midfeather (20) is separated into spiral case air inlet small flow channels (18) and the big runner of spiral case air inlet (19) with spiral case air inlet runner (10), it is characterized in that: the radial cross section of described midfeather (20) is an arcuate structure, and its radian is 60 °～180 °.
2. variable cross section double flow channel air inlet turbine according to claim 2, it is characterized in that: a wherein end and the turbine volute (4) of described midfeather (20) are affixed, and described spiral case air inlet small flow channels (18) is being communicated with near midfeather (20) the other end position with the big runner of spiral case air inlet (19).
3. variable cross section double flow channel air inlet turbine according to claim 1 and 2, it is characterized in that: the circulation area of described spiral case air inlet small flow channels (18) is less than the circulation area of the big runner of described spiral case air inlet (19).
4. variable cross section double flow channel air inlet turbine according to claim 3 is characterized in that: described midfeather (20) and described turbine volute (4) structure that is cast as one.
5. variable cross section double flow channel air inlet turbine according to claim 4, it is characterized in that: the position that described midfeather (20) is gone up near spiral case air inlet runner (10) import is provided with by-pass port (22), air inlet adjustment valve (15) is installed on by-pass port (22), and described air inlet adjustment valve (15) is in transmission connection with air inlet adjustment control mechanism (16).
6. variable cross section double flow channel air inlet turbine according to claim 5 is characterized in that: described spiral case air inlet small flow channels (18) is positioned at the big runner of spiral case air inlet (19) inboard.
7. variable cross section double flow channel air inlet turbine according to claim 5 is characterized in that: described spiral case air inlet small flow channels (18) is positioned at the big runner of spiral case air inlet (19) outside.
8. variable cross section double flow channel air inlet turbine according to claim 3, it is characterized in that: the nozzle place of the big runner of described spiral case air inlet (19) is provided with several air vane guides (21), several air vane guides (21) are the semicircle arcuation to be arranged, and tilts to install along the turbine sense of rotation.
9. variable cross section double flow channel air inlet turbine according to claim 3, it is characterized in that: be provided with several air vane guides (21) at the nozzle place of spiral case air inlet small flow channels (18), several air vane guides (21) are the semicircle arcuation to be arranged, and tilts to install along the turbine sense of rotation.
10. variable cross section double flow channel air inlet turbine according to claim 3, it is characterized in that: the nozzle location of described turbine volute is provided with several air vane guides (21), several air vane guides (21) are circle-shaped evenly distributed, and tilt to install along the turbine sense of rotation.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102801576A CN101949326A (en) | 2010-09-14 | 2010-09-14 | Variable section double-channel air intake turbine |
| PCT/CN2011/000597 WO2012034347A1 (en) | 2010-09-14 | 2011-04-06 | Variable-section dual intake channel turbine |
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| CN2010102801576A CN101949326A (en) | 2010-09-14 | 2010-09-14 | Variable section double-channel air intake turbine |
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| CN101949326A true CN101949326A (en) | 2011-01-19 |
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Cited By (12)
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| CN102383877A (en) * | 2011-10-08 | 2012-03-21 | 康跃科技股份有限公司 | Volute device of variable geometry pulse gas inlet turbine |
| WO2012034347A1 (en) * | 2010-09-14 | 2012-03-22 | Zhu Zhifu | Variable-section dual intake channel turbine |
| CN102536354A (en) * | 2011-12-29 | 2012-07-04 | 康跃科技股份有限公司 | Variable passage volute device |
| CN102562185A (en) * | 2011-12-26 | 2012-07-11 | 康跃科技股份有限公司 | Two-channel variable-section volute device with flow-guiding blades |
| CN102562186A (en) * | 2012-01-11 | 2012-07-11 | 康跃科技股份有限公司 | Sectional type volute with guide vanes |
| WO2013127033A1 (en) * | 2012-02-29 | 2013-09-06 | Wang Hang | Multi-layer variable geometry volute apparatus |
| CN104389643A (en) * | 2014-11-20 | 2015-03-04 | 康跃科技股份有限公司 | Exhaust gas bypass turbine with guide vanes |
| CN105715360A (en) * | 2014-12-17 | 2016-06-29 | 霍尼韦尔国际公司 | Adjustable-trim centrifugal compressor, and turbocharger having same |
| CN110735673A (en) * | 2019-11-18 | 2020-01-31 | 大连海事大学 | kinds of double-channel volute |
| CN111396138A (en) * | 2020-04-29 | 2020-07-10 | 北京动力机械研究所 | Efficient centripetal turbine suitable for inert mixed working medium |
| WO2021005042A1 (en) * | 2019-07-09 | 2021-01-14 | Cummins Ltd | Turbine assembly for a turbocharger |
| CN113931734A (en) * | 2021-10-18 | 2022-01-14 | 天津北方天力增压技术有限公司 | Turbocharger with variable runner casing |
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| JP7537454B2 (en) * | 2022-03-09 | 2024-08-21 | トヨタ自動車株式会社 | Turbocharger |
| JP7537453B2 (en) * | 2022-03-09 | 2024-08-21 | トヨタ自動車株式会社 | Turbocharger |
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| WO2012034347A1 (en) * | 2010-09-14 | 2012-03-22 | Zhu Zhifu | Variable-section dual intake channel turbine |
| CN102383877A (en) * | 2011-10-08 | 2012-03-21 | 康跃科技股份有限公司 | Volute device of variable geometry pulse gas inlet turbine |
| US20140219786A1 (en) * | 2011-10-08 | 2014-08-07 | Zhifu ZHU | Volute device for turbine |
| CN102562185A (en) * | 2011-12-26 | 2012-07-11 | 康跃科技股份有限公司 | Two-channel variable-section volute device with flow-guiding blades |
| CN102562185B (en) * | 2011-12-26 | 2014-10-22 | 康跃科技股份有限公司 | Two-channel variable-section volute device with flow-guiding blades |
| CN102536354A (en) * | 2011-12-29 | 2012-07-04 | 康跃科技股份有限公司 | Variable passage volute device |
| CN102562186A (en) * | 2012-01-11 | 2012-07-11 | 康跃科技股份有限公司 | Sectional type volute with guide vanes |
| CN102562186B (en) * | 2012-01-11 | 2015-03-04 | 康跃科技股份有限公司 | Sectional type volute with guide vanes |
| WO2013127033A1 (en) * | 2012-02-29 | 2013-09-06 | Wang Hang | Multi-layer variable geometry volute apparatus |
| CN105298551A (en) * | 2014-11-20 | 2016-02-03 | 康跃科技股份有限公司 | Waste gas bypass turbine motor with guide vanes |
| CN104389643A (en) * | 2014-11-20 | 2015-03-04 | 康跃科技股份有限公司 | Exhaust gas bypass turbine with guide vanes |
| CN104389643B (en) * | 2014-11-20 | 2016-03-02 | 康跃科技股份有限公司 | With the exhaust gas bypass turbo machine of stator |
| CN105715360A (en) * | 2014-12-17 | 2016-06-29 | 霍尼韦尔国际公司 | Adjustable-trim centrifugal compressor, and turbocharger having same |
| CN105715360B (en) * | 2014-12-17 | 2019-10-25 | 盖瑞特交通一公司 | The adjustable centrifugal compressor of trim and the turbocharger with the compressor |
| WO2021005042A1 (en) * | 2019-07-09 | 2021-01-14 | Cummins Ltd | Turbine assembly for a turbocharger |
| US11891921B2 (en) | 2019-07-09 | 2024-02-06 | Cummins Ltd | Turbine assembly |
| CN110735673A (en) * | 2019-11-18 | 2020-01-31 | 大连海事大学 | kinds of double-channel volute |
| CN110735673B (en) * | 2019-11-18 | 2021-10-26 | 大连海事大学 | Double-channel volute |
| CN111396138A (en) * | 2020-04-29 | 2020-07-10 | 北京动力机械研究所 | Efficient centripetal turbine suitable for inert mixed working medium |
| CN111396138B (en) * | 2020-04-29 | 2022-08-09 | 北京动力机械研究所 | Efficient centripetal turbine suitable for inert mixed working medium |
| CN113931734A (en) * | 2021-10-18 | 2022-01-14 | 天津北方天力增压技术有限公司 | Turbocharger with variable runner casing |
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| WO2012034347A1 (en) | 2012-03-22 |
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