CN102094704A - Multi-nozzle type variable flow rate supercharging device - Google Patents
Multi-nozzle type variable flow rate supercharging device Download PDFInfo
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- 239000002912 waste gas Substances 0.000 description 12
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- 238000007599 discharging Methods 0.000 description 4
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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
- 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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Abstract
The invention discloses a multi-nozzle type variable flow rate supercharging device which comprises a volute casing, wherein the volute casing is internally provided with an air inlet and a volute air inlet passageway which is communicated with the air inlet, and the volute air inlet passageway is internally provided at least one intermediate baffle plate. The multi-nozzle type variable flow rate supercharging device provided by the invention has a simple air inlet regulating and controlling mechanism, the control mode is easy to realize, the reliability is high, and the problems of the existing vane type variable turbocharger in the aspects of reliability and efficiency and too low efficiency of a tongue shape baffle plate variable cross section charger are solved effectively.
Description
Technical field
The present invention relates to a kind of variable cross section pressurized machine, relate to a kind of multi nozzle formula changeable flow supercharging device that satisfies the working condition requirement of the high low speed of motor by the co-operation between the different cross section runner specifically, belong to field of internal combustion engine.
Technical background
Pressurized machine is widely used in modern motor at present, in order to satisfy performance and the emission request under each operating mode of motor, pressurized machine must have the can regulate function of boost pressure and exhaust pressure, and the variable cross section pressurized machine becomes the emphasis of domestic and international research and development thus.Rotary vane type variable-area turbocharger (VNT) and ligulate baffle plate variable-area turbocharger be simple in structure because of it, and can effectively widen the matching range of turbosupercharger and motor, the adjusting of realization boost pressure and exhaust pressure and being widely used.
The structural representation of rotary vane type variable-area turbocharger as shown in Figure 1, the turbine portion branch of rotary vane type turbosupercharger comprises spiral case 2, spiral case nozzle 3, turbine wheel 7 three parts.Nozzle vane 6 is installed on the nozzle ring supporting disk 5, driving mechanism 4 changes spiral case nozzle 3 circulation areas and outlet waste gas angle by the angle of swing of control nozzle vane 6, make waste gas blow to the periphery of turbine wheel 7 according to design point of view, promote turbine wheel 7 high speed rotating, finish acting process to turbine wheel 7, and then drive the air compression acting that 1 pair of gas compressor axially enters gas compressor 1, and improved the density of the induced air of the air that enters cylinder, realize the purpose of supercharging.
The rotary vane type variable-area turbocharger changes the inlet flow area of turbine by the angle of swing of control nozzle vane 6, and control is convenient, but exists some defectives in the application process of reality:
Motor is under big flow operating mode, and the aperture of nozzle vane 6 increases, and nearer apart from the turbine blade leading edge, exhaust gas particle can cause bigger wearing and tearing to nozzle vane 6.Motor is under low flow rate condition, and the aperture of nozzle vane 6 is 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.
About combustion gas row Wen Gaoda 650～850 degree of motor, abominable, the strong vibration of turbocharger operation environment has proposed very high requirement to the reliability of driving mechanism 3, but up to now driving mechanism 3 reliability problems are never effectively solved.
Ligulate baffle plate variable-area turbocharger is also once because of simple in structure, being convenient to control is widely used, at publication number is CN 101418708A, name is called in the patent of invention of exhaust-gas turbocharger, elaborated the working principle of ligulate baffle plate variable cross section pressurized machine, regulate the aperture of ligulate baffle plate by controlling device, the inlet-duct area of annular inlet is changed, when the ligulate baffle plate when the direction of leaving turbine is rotated, the inlet-duct area of ring runner reduces, the airspeed that enters turbine increases, improved kinetic energy, otherwise speed reduces, and kinetic energy reduces, and as required the ligulate baffle plate is regulated, reach needed kinetic energy, satisfy the performance requirement of each operating mode of motor.But ligulate baffle plate variable cross section pressurized machine also exists some shortcomings: controlling device is comparatively complicated on installation and processing realizes, and topmost ligulate baffle plate is when changing the air inlet runner cross section, the flow circuits of fluid is had greatly changed, flow losses have been increased, and form stronger eddy current at ligulate baffle plate rear portion, make the efficient of pressurized machine lower.
Summary of the invention
The problem to be solved in the present invention is at problem and the ligulate baffle plate variable cross section efficiency of turbocharger excessively low problem of rotary vane type variable geometry turbocharger in the existence aspect reliability and the efficient, provide a kind of simple in structure, cost is low, reliability is high, and has the multi nozzle formula changeable flow supercharging device that higher efficient is taken into account the efficient and the negotiability of big flow simultaneously under small flow.
In order to address the above problem, the present invention by the following technical solutions:
A kind of multi nozzle formula changeable flow supercharging device comprises spiral case, and the volute air inlet runner that is provided with suction port in the spiral case and is communicated with suction port is provided with at least one intermediate clapboard in the volute air inlet runner.
Below be further improvement of these options of the present invention:
Described intermediate clapboard circumferentially is provided with along spiral case.
Further improve:
The quantity of described intermediate clapboard is one, intermediate clapboard is partitioned into jet pipe inner flow passage and jet pipe outer flow passage with the volute air inlet runner, described jet pipe outer flow passage is provided with air intake valve near the position of suction port, air inlet adjustment mechanism can regulate the aperture of air intake valve according to the actual conditions of motor, realizes the selection of jet pipe runner and to the control of exhaust gas flow.
Further improve:
Described intermediate clapboard is away from the air inlet regional perspective that forms jet pipe inner flow passage and jet pipe outer flow passage between end of suction port and the spiral case respectively.
Further improve:
The air inlet regional perspective of jet pipe inner flow passage is any angle between 0～360 degree, and the air inlet regional perspective of jet pipe outer flow passage is any angle between 360～0 degree, and the air inlet regional perspective sum of jet pipe inner flow passage and jet pipe outer flow passage is 360 degree.
The present invention adopts such scheme, motor is under the low speed operating mode, air intake valve is in closed condition, all acting gas only does work to turbine through the jet pipe inner flow passage, because the air inlet sectional area diminishes, can effectively promote the suction pressure of turbine, improve the available energy in the waste gas, and the discharge area of nozzle diminishes, the air inlet angle of turbine can be controlled at than higher efficiency band, by the lifting of waste gas available energy and the raising of low speed turbine efficiency, can effectively increase the turbine output under the low engine speed operating mode, satisfy the low-speed performance of motor and reach the purpose that reduces discharging.
Under motor high speed operating mode, air intake valve is in opening state, the aperture of air intake valve is regulated according to the actual conditions of motor by the air intake valve control mechanism, by the control that the selection of different jet pipe runners and different exhaust gas flows are distributed, to satisfy the performance requirement of motor high speed.
The another kind of improvement:
Described intermediate clapboard is two, and two intermediate clapboards are partitioned into three runners with the whole volute air inlet runner in the spiral case: jet pipe inner flow passage, jet pipe outer flow passage and jet pipe intermediate flow channel.
Further improve: described jet pipe intermediate flow channel and jet pipe outer flow passage are provided with air intake valve respectively near the suction port place.
Further improve: the air inlet regional perspective of jet pipe inner flow passage is any angle between 0～360 degree, the any angle of the air inlet regional perspective of jet pipe outer flow passage between 360～0 degree, the any angle of the air inlet regional perspective of jet pipe intermediate flow channel between 0～360 degree, the sum of the air inlet regional perspective of described jet pipe inner flow passage and jet pipe outer flow passage and jet pipe intermediate flow channel are 360 degree.
The present invention adopts such scheme, when motor under the low speed operating mode, each inlet valve is in closed condition, all acting gas only does work to turbine through the jet pipe inner flow passage, because the air inlet sectional area diminishes, can effectively promote the suction pressure of turbine, improve the available energy in the waste gas, and the discharge area of nozzle diminishes, the air inlet angle of turbine can be controlled at than higher efficiency band, by the lifting of waste gas available energy and the raising of low speed turbine efficiency, can effectively increase the turbine output under the low engine speed operating mode, satisfy the low-speed performance of motor and reach the purpose that reduces discharging.
Motor is under the middling speed operating mode, and the air intake valve that only is installed in the jet pipe intermediate flow channel is opened, and the air intake valve in the jet pipe outer flow passage is in closed condition.
Motor is under high-speed working condition, and the air intake valve and the air intake valve in the jet pipe outer flow passage that are installed in the jet pipe intermediate flow channel are all opened.
Valve control mechanism is realized to the selection of jet pipe runner and the control of different flow distribution, to satisfy the performance requirement of motor under the high speed operating mode by the work in combination of control two air intake valves.
The another kind of improvement:
Described intermediate clapboard radially is provided with along spiral case, and the volute air inlet runner is partitioned into parallel jet pipe left side runner and the right runner of jet pipe, adopt this kind arrangement after, each jet pipe runner all can be realized non-full admission, also can realize full admission simultaneously.
Further improve: in the right runner of jet pipe along spiral case intermediate clapboard axially is set, the right runner of jet pipe is partitioned into inside and outside two runners.
This kind jet pipe arrangement is existing to be arranged in parallel and to have up and down and arrange that jet pipe left side runner both can have been realized circumferentially air inlet of part, also can realize full admission, and the right runner of jet pipe can be realized circumferentially air inlet of part.
The another kind of improvement:
Described intermediate clapboard is two, intersects mutually vertically to be provided with, and the volute air inlet runner is partitioned into four jet pipe runners.
After adopting this kind arrangement, make structure become more flexible, existing being arranged in parallel also has layout up and down between the jet pipe, can realize the circumferential air inlet of part of each jet pipe.Certainly we still can set the jet pipe runner of other numbers according to the actual needs, to satisfy different engine performance designing requirement.
The present invention adopts the turbine air intake structure of the variable amount of damming of multi nozzle formula effectively to solve the problem and the low excessively problem of ligulate baffle plate variable cross section efficiency of turbocharger of the existence of present rotary vane type variable geometry turbocharger aspect reliability and efficient by to the designing and developing of spiral case jet pipe runner.
After adopting multi nozzle formula changeable flow turbine, motor is under the down-off operating mode, air intake valve is in closed condition, have only jet pipe inner flow passage participation work,, can effectively promote the turbine suction pressure because the air inlet sectional area diminishes, improve the available energy in the waste gas, the acting ability of turbine is strengthened, and the exit area of nozzle when adopting circumferential partial-air admission rear engine low speed diminishes during than full admission, the air inlet angle of turbine is controlled at than higher efficiency band.By the lifting of waste gas available energy and the raising of low speed turbine efficiency, can effectively increase the turbine output under the motor low flow rate condition, boost pressure is raise, satisfy the requirement of low engine speed boost pressure, improve the low-speed performance of motor and reach the purpose that reduces engine emission.
Under the motor high speed, air intake valve is in opening state, jet pipe inner flow passage and jet pipe outer flow passage are worked together, the air intake valve control mechanism is realized the performance requirement of motor under high speed satisfied in the selection of jet pipe runner and the control of exhaust gas flow distribution by the opening angle of control air intake valve.
Turbine volute structure among the present invention and common pressurized machine worm frame are basic identical, simple in structure, and inheritance is good, and cost is low, realize through engineering approaches easily fast.Air inlet adjustment control mechanism among the present invention is simple, and control mode realizes easily, the reliability height.
In sum, can effectively satisfy the supercharging requirement of the full operating mode scope of motor after the employing multi nozzle formula changeable flow pressurization system, big variation does not take place in the supercharger integrated structure of the type, 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 the structural representation of the rotary vane type variable-area turbocharger in the background technique of the present invention;
Accompanying drawing 2 is structural representations of the multi nozzle changeable flow turbine in the embodiments of the invention 1;
Accompanying drawing 3 is the structural representations after the air inlet zone angle [alpha] of the multi nozzle changeable flow turbine in the embodiments of the invention 2 changes;
Accompanying drawing 4 is the multi nozzle changeable flow turbine structural representations under motor high speed operating mode in the embodiments of the invention 2;
Accompanying drawing 5 is the multi nozzle changeable flow turbine inlet cross-section structural representations in embodiments of the invention 1 and 2;
Accompanying drawing 6 is structural representations of the multi nozzle changeable flow turbine in the embodiments of the invention 3;
Accompanying drawing 7 is the multi nozzle changeable flow turbine inlet cross-section structural representations in embodiments of the invention 3 and 4;
Accompanying drawing 8 is the structural representations after the air inlet zone angle [alpha] of the multi nozzle changeable flow turbine in the embodiments of the invention 4 changes;
Accompanying drawing 9 is the multi nozzle changeable flow turbine structural representations under the medium engine speed operating mode in the embodiments of the invention 4;
Accompanying drawing 10 is the multi nozzle changeable flow turbine structural representations under the high engine speeds operating mode in the embodiments of the invention 4;
Accompanying drawing 11 is multi nozzle changeable flow turbine inlet cross-section structural representations in the embodiments of the invention 5;
Accompanying drawing 12 is multi nozzle changeable flow turbine inlet cross-section structural representations in the embodiments of the invention 6;
Accompanying drawing 13 is multi nozzle changeable flow turbine inlet cross-section structural representations in the embodiments of the invention 7.
Among the figure: the 1-gas compressor; The 2-spiral case; 3-spiral case nozzle; The 4-driving mechanism; 5-nozzle ring supporting disk; The 6-nozzle vane; The 7-turbine wheel; 8,81-intermediate clapboard; The 9-air intake valve; 10-jet pipe inner flow passage; 11-jet pipe outer flow passage; 12-jet pipe intermediate flow channel; 13-jet pipe left side runner; The right runner of 14-jet pipe; α-air inlet regional perspective.
Embodiment
Embodiment 1, as accompanying drawing 2, shown in Figure 5, a kind of multi nozzle formula changeable flow supercharging device, comprise spiral case 2, the volute air inlet runner that is provided with suction port in the spiral case 2 and is communicated with suction port, be circumferentially with the intermediate clapboard 8 of an arc in the volute air inlet runner along spiral case, described intermediate clapboard 8 is partitioned into jet pipe inner flow passage 10 and jet pipe outer flow passage 11 with the volute air inlet runner, and described jet pipe inner flow passage 10 and jet pipe outer flow passage 11 are all realized circumferentially air inlet of part.
Described jet pipe outer flow passage 11 is provided with air intake valve 9 near the position of suction port.
Described intermediate clapboard 8 is cast as one with spiral case 2, the air inlet zone angle [alpha] that intermediate clapboard 8 forms jet pipe inner flow passage 10 and jet pipe outer flow passage 11 away from distributing between end of suction port and the spiral case 2, the air inlet zone angle [alpha] of described jet pipe inner flow passage 10 is 30 degree, and the air inlet zone angle [alpha] of corresponding jet pipe outer flow passage 11 is 330 degree.
As shown in Figure 3, motor is under the low speed operating mode, air intake valve 9 is in closed condition, all acting gas is only through 10 pairs of turbine actings of jet pipe inner flow passage, because the air inlet sectional area diminishes, can effectively promote the suction pressure of turbine, improve the available energy in the waste gas, and the discharge area of nozzle diminishes, the air inlet angle of turbine can be controlled at than higher efficiency band, by the lifting of waste gas available energy and the raising of low speed turbine efficiency, can effectively increase the turbine output under the low engine speed operating mode, satisfy the low-speed performance of motor and reach the purpose that reduces discharging.
As shown in Figure 4, under motor high speed operating mode, air intake valve 9 is in opening state, the aperture of air intake valve 9 is regulated according to the actual conditions of motor by the air intake valve control mechanism, by the control that the selection of different jet pipe runners and different exhaust gas flows are distributed, to satisfy the performance requirement of motor high speed.
The present invention is directed to the demand of motor, finished the exploitation of multi nozzle formula changeable flow pressurization system turbine part, effectively utilized exhaust energy, taken into account the boost demand under low engine speed and the high speed operating mode variable-area turbocharger.The type multi nozzle formula changeable flow air inlet turbine can adopt the casting and the processing technique of existing common pressurized machine to finish.
Among the foregoing description 1 and the embodiment 2, can be by the reasonable separation of intermediate clapboard 8, realization is to the change of jet pipe inner flow passage 10 and jet pipe outer flow passage 11 air inlet regional perspectives, the air inlet zone angle [alpha] of jet pipe inner flow passage 10 is any angle between 0～360 degree, the air inlet zone angle [alpha] of jet pipe outer flow passage 11 is any angle between 360～0 degree, and the air inlet regional perspective sum of the air inlet regional perspective of jet pipe inner flow passage 10 and jet pipe outer flow passage 11 is 360 degree.
Embodiment 3, the present embodiment difference from Example 1 is to be provided with at spiral case 2 intermediate clapboard 8 of two arcs, as accompanying drawing 6, shown in Figure 7, two intermediate clapboards 8 are cast as one with spiral case 2, and two intermediate clapboards are partitioned into three runners with the whole volute air inlet runner in the spiral case 2: jet pipe inner flow passage 10, jet pipe outer flow passage 11, jet pipe intermediate flow channel 12.
The air inlet zone angle [alpha] of described jet pipe inner flow passage 10 is 35 degree, and the air inlet zone angle [alpha] of jet pipe intermediate flow channel 12 is 35 degree, and the air inlet zone angle [alpha] of corresponding jet pipe outer flow passage 11 is 290 degree.
Described jet pipe intermediate flow channel 12 and jet pipe outer flow passage 11 are provided with air intake valve 9 respectively near the suction port place, valve control mechanism is regulated the aperture of each air intake valve by the performance requirement of Under Different Work Condition of Engine, realization is satisfied the performance requirement of each operating mode of motor to the control of jet pipe runner and exhaust gas flow distribution.
Embodiment 4, the present embodiment difference from Example 2 is to be provided with at spiral case 2 intermediate clapboard 8 of two arcs, as accompanying drawing 7, shown in Figure 8, two intermediate clapboards 8 are cast as one with spiral case 2, and two intermediate clapboards are partitioned into three runners with the whole volute air inlet runner in the spiral case 2: jet pipe inner flow passage 10, jet pipe outer flow passage 11, jet pipe intermediate flow channel 12.
The air inlet zone angle [alpha] of described jet pipe inner flow passage 10 is 225 degree, and the air inlet zone angle [alpha] of jet pipe intermediate flow channel 12 is 90 degree, and the air inlet zone angle [alpha] of corresponding jet pipe outer flow passage 11 is 45 degree.
As shown in Figure 8, when motor under the low speed operating mode, each inlet valve 9 is in closed condition, all acting gas is only through 10 pairs of turbine actings of jet pipe inner flow passage, because the air inlet sectional area diminishes, can effectively promote the suction pressure of turbine, improve the available energy in the waste gas, and the discharge area of nozzle diminishes, the air inlet angle of turbine can be controlled at than higher efficiency band, by the lifting of waste gas available energy and the raising of low speed turbine efficiency, can effectively increase the turbine output under the low engine speed operating mode, satisfy the low-speed performance of motor and reach the purpose that reduces discharging.
As shown in Figure 9, motor is under the middling speed operating mode, and the air intake valve 9 that only is installed in the jet pipe intermediate flow channel 12 is opened, and the air intake valve 9 in jet pipe outer flow passage 11 is in closed condition.
As shown in Figure 10, motor is under high-speed working condition, and the air intake valve 9 and the air intake valve in jet pipe outer flow passage 11 9 that are installed in the jet pipe intermediate flow channel 12 are all opened.
Valve control mechanism is realized to the selection of jet pipe runner and the control of different flow distribution, to satisfy the performance requirement of motor under the high speed operating mode by the work in combination of control two air intake valves.
The present invention is directed to the demand of motor, finished the exploitation of multi nozzle formula changeable flow pressurization system turbine part, effectively utilized exhaust energy, taken into account the boost demand under low engine speed and the high speed operating mode variable-area turbocharger.The type multi nozzle formula changeable flow air inlet turbine can adopt the casting and the processing technique of existing common pressurized machine to finish.
Among the foregoing description 3 and the embodiment 4, can be by the reasonable separation of two intermediate clapboards 8, realization is to the change of the air inlet zone angle [alpha] of jet pipe inner flow passage 10 and jet pipe outer flow passage 11 and jet pipe intermediate flow channel 12, the air inlet zone angle [alpha] of jet pipe inner flow passage 10 is any angle between 0～360 degree, the any angle of air inlet zone angle [alpha] between 360～0 degree of jet pipe outer flow passage 11, the any angle of air inlet zone angle [alpha] between 0～360 degree of jet pipe intermediate flow channel 12, the sum of the air inlet regional perspective of the air inlet regional perspective of described jet pipe inner flow passage 10 and the air inlet regional perspective of jet pipe outer flow passage 11 and jet pipe intermediate flow channel 12 is 360 degree.
Embodiment 5, in embodiment 1 and embodiment 2, as shown in figure 11, can also in the volute air inlet runner, intermediate clapboard 8 radially be set along spiral case, intermediate clapboard 8 is partitioned into parallel jet pipe left side runner 13 and the right runner 14 of jet pipe with the volute air inlet runner, after adopting this kind arrangement, each jet pipe runner all can be realized non-full admission, also can realize full admission simultaneously.
Embodiment 7, on embodiment 1 and embodiment's 2 basis, as shown in figure 13, described intermediate clapboard 8 is two, intersects mutually vertically to be provided with, and the volute air inlet runner is partitioned into four jet pipe runners, after adopting this kind arrangement, make structure become more flexible, existing being arranged in parallel also has layout up and down between the jet pipe, can realize the circumferential air inlet of part of each jet pipe.Certainly we still can set the jet pipe runner of other numbers according to the actual needs, to satisfy different engine performance designing requirement.
The present invention is directed to the demand of motor to variable-area turbocharger, finished the exploitation of multi nozzle formula changeable flow pressurization system turbine part, effectively utilized exhaust energy, taken into account the boost demand under low engine speed and the high speed operating mode, the type multi nozzle formula changeable flow air inlet turbine can adopt the casting and the processing technique of existing common pressurized machine to finish.
Claims (11)
1. a multi nozzle formula changeable flow supercharging device comprises spiral case (2), and the volute air inlet runner that is provided with suction port and is communicated with suction port in the spiral case (2) is characterized in that: be provided with at least one intermediate clapboard (8) in the volute air inlet runner.
2. multi nozzle formula changeable flow supercharging device according to claim 1, it is characterized in that: described intermediate clapboard (8) circumferentially is provided with along spiral case.
3. multi nozzle formula changeable flow supercharging device according to claim 2, it is characterized in that: the quantity of described intermediate clapboard (8) is one, intermediate clapboard (8) is partitioned into jet pipe inner flow passage (10) and jet pipe outer flow passage (11) with the volute air inlet runner, and described jet pipe outer flow passage (11) is provided with air intake valve (9) near the position of suction port.
4. according to claim 2 or 3 described multi nozzle formula changeable flow supercharging devices, it is characterized in that: described intermediate clapboard (8) is away from the air inlet regional perspective (α) that forms jet pipe inner flow passage (10) and jet pipe outer flow passage (11) between end of suction port and the spiral case (2) respectively.
5. multi nozzle formula changeable flow supercharging device according to claim 4, it is characterized in that: the air inlet regional perspective (α) of jet pipe inner flow passage (10) is any angle between 0～360 degree, the air inlet regional perspective (α) of jet pipe outer flow passage (11) is any angle between 360～0 degree, and the air inlet regional perspective sum of the air inlet regional perspective of jet pipe inner flow passage (10) and jet pipe outer flow passage (11) is 360 degree.
6. multi nozzle formula changeable flow supercharging device according to claim 2, it is characterized in that: described intermediate clapboard (8) is two, and two intermediate clapboards are partitioned into three runners with the whole volute air inlet runner in the spiral case (2): jet pipe inner flow passage (10), jet pipe outer flow passage (11), jet pipe intermediate flow channel (12).
7. multi nozzle formula changeable flow supercharging device according to claim 6 is characterized in that: described jet pipe intermediate flow channel (12) and jet pipe outer flow passage (11) are provided with air intake valve (9) respectively near the suction port place.
8. according to claim 6 or 7 described multi nozzle formula changeable flow supercharging devices, it is characterized in that: the air inlet regional perspective (α) of jet pipe inner flow passage (10) is any angle between 0～360 degree, the air inlet regional perspective (α) of jet pipe outer flow passage (11) is any angle between 0～360 degree, the any angle of the air inlet regional perspective (α) of jet pipe intermediate flow channel (12) between 0～360 degree, the sum of the air inlet regional perspective of the air inlet regional perspective of described jet pipe inner flow passage (10) and jet pipe outer flow passage (11) and the air inlet regional perspective of jet pipe intermediate flow channel (12) are 360 degree.
9. multi nozzle formula changeable flow supercharging device according to claim 1, it is characterized in that: described intermediate clapboard (8) radially is provided with along spiral case, and the volute air inlet runner is partitioned into parallel jet pipe left side runner (13) and the right runner (14) of jet pipe.
10. multi nozzle formula changeable flow supercharging device according to claim 9 is characterized in that: in the right runner of jet pipe (14) along spiral case intermediate clapboard (81) axially is set, jet pipe right side runner (14) is partitioned into inside and outside two runners.
11. multi nozzle formula changeable flow supercharging device according to claim 1, it is characterized in that: described intermediate clapboard (8) is two, intersects mutually vertically to be provided with, and the volute air inlet runner is partitioned into four jet pipe runners.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110029166 CN102094704A (en) | 2011-01-27 | 2011-01-27 | Multi-nozzle type variable flow rate supercharging device |
| PCT/CN2011/000598 WO2012100387A1 (en) | 2011-01-27 | 2011-04-06 | Multi-nozzle type variable-flow boosting apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110029166 CN102094704A (en) | 2011-01-27 | 2011-01-27 | Multi-nozzle type variable flow rate supercharging device |
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| CN102094704A true CN102094704A (en) | 2011-06-15 |
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| CN 201110029166 Pending CN102094704A (en) | 2011-01-27 | 2011-01-27 | Multi-nozzle type variable flow rate supercharging device |
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Cited By (9)
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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 |
| CN102606233A (en) * | 2012-03-19 | 2012-07-25 | 康跃科技股份有限公司 | Variable-section spiral case with blade nozzle ring |
| WO2013131214A1 (en) * | 2012-03-08 | 2013-09-12 | Wang Hang | Mixed variable flow volute |
| CN103696814A (en) * | 2013-11-14 | 2014-04-02 | 汉捷机械部件（常州）有限公司 | Three-channel volute with variable section |
| CN108267295A (en) * | 2017-12-25 | 2018-07-10 | 中国航天空气动力技术研究院 | A kind of flow control jet pipe |
| CN110360155A (en) * | 2019-08-01 | 2019-10-22 | 全浩铖 | A kind of more flow-guiding channel centrifugal pumps or radial fan shell |
| CN110454240A (en) * | 2019-08-28 | 2019-11-15 | 天津大学 | A partially air-intake axial-flow supercritical carbon dioxide turboexpander |
| CN111989482A (en) * | 2019-04-12 | 2020-11-24 | 朴行济 | Impeller assembly for hydroelectric power generation device |
| CN120000181A (en) * | 2024-12-26 | 2025-05-16 | 中国人民解放军空军特色医学中心 | Pilot physiological state monitoring and control system based on brain-computer interaction |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4389845A (en) * | 1979-11-20 | 1983-06-28 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Turbine casing for turbochargers |
| US4443153A (en) * | 1979-08-23 | 1984-04-17 | Dibelius Guenther | Controlled exhaust-type supercharger turbine |
| CN101519997A (en) * | 2008-02-29 | 2009-09-02 | 三菱重工业株式会社 | Variable geometry turbine and turbocharger |
| CN101936214A (en) * | 2010-08-03 | 2011-01-05 | 康跃科技股份有限公司 | Pulse variable passage way turbine device |
| CN201916047U (en) * | 2011-01-27 | 2011-08-03 | 康跃科技股份有限公司 | A multi-nozzle type variable flow booster device |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4384821A (en) * | 1981-10-14 | 1983-05-24 | Wallace Murray Corporation | Free floating divider wall turbine housing |
| US5094587A (en) * | 1990-07-25 | 1992-03-10 | Woollenweber William E | Turbine for internal combustion engine turbochargers |
| CN101598038B (en) * | 2009-07-03 | 2012-05-09 | 康跃科技股份有限公司 | Two-layer flow path variable area turbine of turbine supercharger |
-
2011
- 2011-01-27 CN CN 201110029166 patent/CN102094704A/en active Pending
- 2011-04-06 WO PCT/CN2011/000598 patent/WO2012100387A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4443153A (en) * | 1979-08-23 | 1984-04-17 | Dibelius Guenther | Controlled exhaust-type supercharger turbine |
| US4389845A (en) * | 1979-11-20 | 1983-06-28 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Turbine casing for turbochargers |
| CN101519997A (en) * | 2008-02-29 | 2009-09-02 | 三菱重工业株式会社 | Variable geometry turbine and turbocharger |
| CN101936214A (en) * | 2010-08-03 | 2011-01-05 | 康跃科技股份有限公司 | Pulse variable passage way turbine device |
| CN201916047U (en) * | 2011-01-27 | 2011-08-03 | 康跃科技股份有限公司 | A multi-nozzle type variable flow booster device |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| WO2013131214A1 (en) * | 2012-03-08 | 2013-09-12 | Wang Hang | Mixed variable flow volute |
| CN102606233A (en) * | 2012-03-19 | 2012-07-25 | 康跃科技股份有限公司 | Variable-section spiral case with blade nozzle ring |
| CN103696814A (en) * | 2013-11-14 | 2014-04-02 | 汉捷机械部件（常州）有限公司 | Three-channel volute with variable section |
| CN105507965A (en) * | 2013-11-14 | 2016-04-20 | 汉捷机械部件（常州）有限公司 | Operating method of variable-section three-channel volute |
| CN108267295B (en) * | 2017-12-25 | 2019-10-18 | 中国航天空气动力技术研究院 | A flow control nozzle |
| CN108267295A (en) * | 2017-12-25 | 2018-07-10 | 中国航天空气动力技术研究院 | A kind of flow control jet pipe |
| CN111989482A (en) * | 2019-04-12 | 2020-11-24 | 朴行济 | Impeller assembly for hydroelectric power generation device |
| CN111989482B (en) * | 2019-04-12 | 2022-04-05 | 朴行济 | Impeller assembly for hydroelectric power generation device |
| CN110360155A (en) * | 2019-08-01 | 2019-10-22 | 全浩铖 | A kind of more flow-guiding channel centrifugal pumps or radial fan shell |
| CN110454240A (en) * | 2019-08-28 | 2019-11-15 | 天津大学 | A partially air-intake axial-flow supercritical carbon dioxide turboexpander |
| CN110454240B (en) * | 2019-08-28 | 2024-09-06 | 天津大学 | Partial air inlet axial flow type supercritical carbon dioxide turbine expander |
| CN120000181A (en) * | 2024-12-26 | 2025-05-16 | 中国人民解放军空军特色医学中心 | Pilot physiological state monitoring and control system based on brain-computer interaction |
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