CN201301731Y - Turbo-charger with rotary nozzle ring - Google Patents
Turbo-charger with rotary nozzle ring Download PDFInfo
- Publication number
- CN201301731Y CN201301731Y CN 200820100844 CN200820100844U CN201301731Y CN 201301731 Y CN201301731 Y CN 201301731Y CN 200820100844 CN200820100844 CN 200820100844 CN 200820100844 U CN200820100844 U CN 200820100844U CN 201301731 Y CN201301731 Y CN 201301731Y
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- Prior art keywords
- blade
- nozzle ring
- back segment
- nozzle
- circular arc
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- Expired - Lifetime
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Abstract
The utility model relates to a turbo-charger with a rotary nozzle ring, which comprises an air intake scroll casing(1), a nozzle ring vane(2), an impeller(3)and a nozzle ring underpan (4). The turbo-charger is characterized in that the nozzle ring vane(2) includes a vane front segment(5)fixedly connected with the nozzle ring underpan (4) and a vane rear segment capable of rotating on the nozzle ring underpan (4). The turbo-charger greatly lowers the torsion moment necessary for rotating the vane rear segment, so the dimension of a control actuator can be reduced, and the service life and the reliability can be improved, thus improving the performance of the internal-combustion engine.
Description
Technical field
The utility model relates to a kind of by changing the device that flow is regulated or controlled, and particularly relates to a kind of turbosupercharger that adopts nozzle vane.
Background technique
The turbine structure that can revolve the nozzle ring turbosupercharger is made up of air inlet volute, the nozzle blade and the impeller that can rotate around the axle center.Working principle is:, throughput low hour at rotary speed of diesel engine, and swivel nozzle ring blade dwindles the nozzle ring aperture, increases the airspeed and the incident angle that enter impeller, has improved wheel speed, increases the outlet pressure of gas compressor; At the rotary speed of diesel engine height, when throughput is big, swivel nozzle ring blade is opened giant ring aperture, reaches the purpose that reduces compressor delivery pressure.Because locomotive is road vehicle tens of times with diesel engine with the flow of observing marine diesel engine, control required moment of final controlling element and power also will increase tens of times when employing can be revolved nozzle ring, and control final controlling element size is big, and impact force is also big during counterrotating.For this reason, can adopt increase lobe numbers and two measures of shortening blade chord length.But, increasing lobe numbers and make control execution device complexity, design difficulty increases, and operating life and reliability reduce; Shorten the blade chord length and make the nozzle ring cascade solidity well below best cascade solidity value, the nozzle ring cascade loss increases; Shorten the blade chord length and also make the nozzle ring leaf grating can't constitute venturi, control effect and control accuracy when having reduced the nozzle ring rotation significantly.Though the therefore existing nozzle ring turbosupercharger of revolving can be used on diesel engine at road vehicle, be difficult at locomotive and observe on the ship and use.
The model utility content
The purpose of this utility model is to provide a kind of required moment of final controlling element and little revolved nozzle ring turbosupercharger of power controlled.
The purpose of this utility model is achieved through the following technical solutions: comprise air inlet volute, nozzle blade, impeller and nozzle ring chassis, it is characterized in that: described nozzle blade comprise the blade leading portion of fixedlying connected that split is provided with described nozzle ring chassis and can be on described nozzle ring chassis the rotating blades back segment.Blade leading portion and blade back segment are split type.Certainly, if select suitable material, blade leading portion and blade also can be wholely set in theory.
The concrete annexation of described blade back segment and described nozzle ring base can be: described blade back segment flexibly connects by rotating shaft and described nozzle ring chassis, so the blade back segment can rotate on the nozzle ring base; The circular hole that described rotating shaft is passed on the described nozzle ring chassis stretches out outside the nozzle ring runner, with the revolved nozzle ring control final controlling element rigid joint of pressurized machine, needed torsional moment when rotating with transmitting control blade back segment.
For reducing windage loss, and be convenient to the rotation of blade back segment, the front end of described blade leading portion is the evagination circular arc, and tail end is interior concave circular arc; The front end of described blade back segment and tail end are the evagination circular arc.
For further being convenient to the rotation of blade back segment, the circular arc of the circular arc of blade back segment front end and blade leading portion tail end is an isocentric circular arc; The radius of blade back segment front end circular arc is less than the radius of blade leading portion tail end circular arc; Described rotating shaft is arranged on the center of circle of described blade back segment front end circular arc.
For simplifying the structure of pressurized machine, described blade leading portion and described nozzle ring chassis are set to one; Described blade back segment and described rotating shaft are set to one.
For increasing the adjustment range of described nozzle vane throat area, the length of described blade leading portion is less than the length of described blade back segment.
For reduce the loss of air-flow in the control air-flow, the pitch of described nozzle blade is 0.6 ~ 0.9 with the ratio of the chord length of described nozzle blade, and the pitch of described nozzle blade is preferably 0.71 with the ratio of the chord length of described nozzle blade.Described pitch is that rotating shaft core is with respect to the circumference circle at place, turbine center and the ratio of nozzle blade quantity.
For increasing the rotation area of described blade back segment, the established angle of described nozzle vane is 45 ° ~ 85 °.As shown in Figure 2, during pressurized machine work, throat area for a change, the blade back segment control final controlling element control under around the shaft the axle center rotate with respect to the impeller center, when blade back segment when the axle center rotates to a certain special position around the shaft, the blade back segment has a least radius R with respect to the impeller center, makes the tangent line of the front end circular arc of blade leading portion with the point on this least radius R upper blade back segment, and the angle of this tangent line and rotating shaft center and the turbine line of centres is the established angle γ of described nozzle vane.
For avoiding nozzle blade to close the damage of back fully to motor, also be provided with the limit stoper that prevents that described blade back segment from closing fully on the described nozzle ring base, described limit stoper can be a boss, also can be screw, perhaps the device of other equivalences.
The beneficial effects of the utility model are:
(1) because nozzle blade comprises blade leading portion and the blade back segment that split is provided with, the blade leading portion is fixedlyed connected with the nozzle ring base, the blade back segment can rotate around the nozzle ring base, therefore air-flow is torn open and is changeed the aerodynamic force and the moment of torsion major part of bringing out and born by the nozzle ring chassis by the blade leading portion in the nozzle ring leaf grating, only need the rotation blade back segment to get final product and adjust throat area, thereby reduced the needed torsional moment of swivel nozzle ring blade significantly, make control final controlling element size decreases, operating life and reliability improve; On the other hand, the leaf structure angle of blade leading portion front end can be determined according to spiral case flow outlet angle, therefore can guarantee that air-flow imports the leaf grating conduit with the air inlet angle of attack of the best with air-flow forever, thereby avoided the negative angle of attack loss of nozzle ring when little aperture, helped further improving the low speed segment performance of internal-combustion engine;
(2) because flowing in the conduit part of blade back segment composition must be that acceleration expansion flows, the gas pressure of rotation blade profile part internal surface (pressure side) must be higher than the pressure of rotation blade profile part outer surface (suction surface), therefore, no matter be big aperture or little aperture position, the direction of the moment of torsion that aerodynamic brings out in the nozzle ring remains constant, always tend to make blade opening to increase, " zero " moment of torsion phenomenon of having avoided nozzle ring to occur at some special state; On the other hand, the blade back segment can rotate around the nozzle ring base, therefore low in engine speed, throughput hour, can control blade back segment shell very easily and dwindle the venturi aperture, increase the airspeed and the incident angle that enter impeller, thereby improve wheel speed, increase the outlet pressure of gas compressor, and, also can control blade back segment shell very easily and increase the venturi aperture, thereby the outlet pressure of reduction gas compressor at the internal-combustion engine rotational speed height, when throughput is big;
(3) because the front end of described blade leading portion is the evagination circular arc, and tail end is interior concave circular arc, and the front end of described blade back segment and tail end are the evagination circular arc, therefore can reduces windage loss, and be convenient to the rotation of blade back segment, thus the adjustment of the more convenient throat area of energy;
(4) because the circular arc of blade back segment front end and the circular arc of blade leading portion tail end are isocentric circular arc, the radius of blade back segment front end circular arc is less than the radius of blade leading portion tail end circular arc, described rotating shaft is arranged on the center of circle of described blade back segment front end circular arc, therefore can further be convenient to the rotation of blade back segment, thereby further facilitate the adjustment of throat area;
(5), thereby improve the performance of internal-combustion engine because the length of described blade leading portion less than the length of described blade back segment, therefore can increase the adjustment range of nozzle vane throat area;
(6) because the ratio of the pitch of described nozzle blade and the chord length of described nozzle blade is 0.6 ~ 0.9, therefore in the control air-flow, has also reduced the loss of air-flow, thereby further improved the performance of internal-combustion engine;
(7) pitch of described nozzle blade is 0.71 with the ratio recommendation of the chord length of described nozzle blade, can further improve the performance of internal-combustion engine;
(8) because the established angle of described nozzle blade is 45 ° ~ 85 °, therefore can increases the rotation area of described blade back segment, thereby can further improve the performance of internal-combustion engine;
(9), therefore can simplify the structure of pressurized machine, thereby reduce manufacture cost, and make that the assembling of nozzle ring is simpler because described blade leading portion and described nozzle ring chassis are set to one, and described blade back segment and described rotating shaft are set to one;
(10) owing to also be provided with the limit stoper that prevents that described blade back segment from closing fully on the described nozzle ring base, so nozzle ring can not cut out fully, thereby avoided nozzle blade to close the damage of back to motor fully, improved the reliability of system.
Description of drawings
Fig. 1 is the utility model embodiment 1 a structural representation;
Fig. 2 is the structure diagram of nozzle blade among Fig. 1;
Fig. 3 is the A-A cutaway view Amplified image of Fig. 2;
Nozzle ring schematic representation when Fig. 4 is the utility model embodiment 2 a pressurized machine declared working condition;
Nozzle ring schematic representation when Fig. 5 is the utility model embodiment 2 a pressurized machine nozzle blade maximum opening operating mode;
Nozzle ring schematic representation when Fig. 6 is the nearly closed condition operating mode of the utility model embodiment 2 pressurized machine nozzle blade;
Embodiment
Embodiment 1: as shown in Figure 1 to Figure 3, a kind of road vehicle use for diesel engine can be revolved the nozzle ring turbosupercharger, comprise air inlet volute 1, nozzle blade 2, impeller 3 and nozzle ring chassis 4, described nozzle blade 2 comprise the blade leading portion 5 of fixedlying connected with described nozzle ring chassis 4 and on described nozzle ring chassis 4 rotating blades back segment 6, the length of described blade leading portion 5 is less than the length of described blade back segment 6; Described blade back segment 6 flexibly connects by rotating shaft 7 and described nozzle ring chassis 4; The circular hole 4a that described rotating shaft 7 is passed on the described nozzle ring chassis 4 stretches out outside the nozzle ring runner, revolved nozzle ring control final controlling element rigid joint with pressurized machine, needed torsional moment (as shown in Figure 3, arrow is represented torque direction) when rotating with transmitting control blade back segment; The front end of described blade leading portion 5 is evagination circular arc 5a, and tail end is interior concave circular arc 5b; The front end of described blade back segment 6 and tail end are evagination circular arc 6a, 6b; The circular arc 5b of the circular arc 6a of blade back segment 6 front ends and blade leading portion 5 tail ends is an isocentric circular arc; The radius of blade back segment 6 front end circular arc 6a is less than the radius of blade leading portion 5 tail end circular arc 5b; Described rotating shaft 7 is arranged on the center of circle of described blade back segment 6 front end circular arcs; Described blade leading portion 5 is set to one with described nozzle ring chassis 4; Described blade back segment 6 is set to one with described rotating shaft 7; The length b of blade leading portion 5
1Be 9.28, the length b of blade back segment 6
2Be 15.29, the length b of blade leading portion 5
1Be blade total length (segment length b before the blade
1With segment length b behind the blade
2Sum) 38%, blade length overall (b
1With b
2Sum), promptly chord length is 24.57mm; Nozzle ring pitch t is 19.62mm, pitch t and chord length (b
1With b
2Sum) ratio is 0.80; For avoiding nozzle ring to close the damage of back to motor fully, though nozzle ring can not cut out automatically owing to aerodynamic force in this example, still design has a limit stoper (not shown) that prevents that described blade back segment from closing fully on the relevant position.
In the present embodiment, blade leading portion import leaf structure angle is 73 °; Minimum established angle γ
MinValue is 65 °; Established angle γ when nozzle ring cuts out fully
MaxBe 85 °, close the damage of back to motor, this routine blade angle maximum value γ fully for avoiding nozzle ring
MaxBe set to 81 °, and on 81 ° of positions, should design a limit stoper; This routine specified established angle γ
OPTBe 71 °, corresponding throat aperture is 4.8mm.The established angle adjustable range is-6.0～+ 10, and the throat area during specified established angle is A, and the throat area during minimum established angle is A
Max,
Embodiment 2: as shown in Figure 5, blade leading portion import leaf structure angle is 71 °; When pressurized machine during in declared working condition, the specified established angle of blade is that γ is 61 °, and the corresponding aperture O of throat is 18.45mm; , throughput low hour when rotary speed of diesel engine, control final controlling element swivel nozzle ring blade back segment dwindles nozzle ring aperture (increase blade angle), increase the airspeed and the incident angle that enter impeller, improved wheel speed, increase the outlet pressure of gas compressor.As shown in Figure 6, the blade angle maximum value is 72 °; When the rotary speed of diesel engine height, when throughput is big, control final controlling element swivel nozzle ring back segment blade is opened giant ring aperture (reducing blade angle), reaches the purpose that reduces compressor delivery pressure, and as shown in Figure 5, blade angle γ minimum value is 48 °; If the throat area during specified established angle is A, the throat area during minimum established angle is A
Max, in this example
Different is that the pressurized machine in the present embodiment is that a kind of marine fishing ship use for diesel engine can be revolved the nozzle ring turbosupercharger for present embodiment and embodiment 1.Other structures of present embodiment are identical with embodiment 1.
Embodiment 3: different is for present embodiment and embodiment 1, shown in nozzle blade pitch with shown in the ratio of chord length of nozzle blade be 0.65, the specified established angle γ of described nozzle vane
OPTIt is 65 °.Other structures of present embodiment are identical with embodiment 1.
Embodiment 4: different is for present embodiment and embodiment 1, shown in nozzle blade pitch with shown in the ratio of chord length of nozzle blade be 0.7, the specified established angle γ of described nozzle vane
OPTIt is 70 °.Other structures of present embodiment are identical with embodiment 1.
Embodiment 5: different is for present embodiment and embodiment 1, shown in nozzle blade pitch with shown in the ratio of chord length of nozzle blade be 0.8, the specified established angle γ of described nozzle vane
OPTIt is 75 °.Other structures of present embodiment are identical with embodiment 1.
Embodiment 6: different is for present embodiment and embodiment 1, shown in nozzle blade pitch with shown in the ratio of chord length of nozzle blade be 0.85, the specified established angle γ of described nozzle vane
OPTIt is 55 °.Other structures of present embodiment are identical with embodiment 1.
Embodiment 7: different is for present embodiment and embodiment 1, shown in nozzle blade pitch with shown in the ratio of chord length of nozzle blade be 0.9, the specified established angle γ of described nozzle vane
OPTIt is 50 °.Other structures of present embodiment are identical with embodiment 1.
Embodiment 8: different is for present embodiment and embodiment 1, shown in nozzle blade pitch with shown in the ratio of chord length of nozzle blade be 0.88, the specified established angle γ of described nozzle vane
OPTIt is 45 °.Other structures of present embodiment are identical with embodiment 1.
The utility model includes but not limited to above embodiment, if nozzle blade comprise the blade leading portion of fixedlying connected with described nozzle ring chassis and can be on described nozzle ring chassis the rotating blades back segment, all drop in the protection domain of the present utility model.
Claims (10)
1, a kind of nozzle ring turbosupercharger of revolving, comprise air inlet volute (1), nozzle blade (2), impeller (3) and nozzle ring chassis (4), it is characterized in that: described nozzle blade (2) comprises the blade leading portion (5) of fixedlying connected with described nozzle ring chassis (4) and can go up rotating blades back segment (6) on described nozzle ring chassis (4).
2, the nozzle ring turbosupercharger of revolving as claimed in claim 1 is characterized in that: described blade back segment (6) flexibly connects by rotating shaft (7) and described nozzle ring chassis (4); The circular hole (4a) that described rotating shaft (7) is passed on the described nozzle ring chassis (4) stretches out outside the nozzle ring runner.
3, the nozzle ring turbosupercharger of revolving as claimed in claim 2 is characterized in that: the front end of described blade leading portion (5) is evagination circular arc (5a), and tail end is interior concave circular arc (5b); The front end of described blade back segment (6) and tail end be the evagination circular arc (6a, 6b).
4, the nozzle ring turbosupercharger of revolving as claimed in claim 3 is characterized in that: the circular arc (6a) of blade back segment (6) front end is an isocentric circular arc with the circular arc (5b) of blade leading portion (5) tail end; The radius of blade back segment (6) front end circular arc (6a) is less than the radius of blade leading portion (5) tail end circular arc (5b); Described rotating shaft (7) is arranged on the center of circle of described blade back segment (6) front end circular arc.
5, as the described nozzle ring turbosupercharger of revolving of any one claim of claim 1 to 4, it is characterized in that: described blade leading portion (5) is set to one with described nozzle ring chassis (4); Described blade back segment (6) is set to one with described rotating shaft (7).
6, as the described nozzle ring turbosupercharger of revolving of any one claim of claim 1 to 4, it is characterized in that: the length of described blade leading portion (5) is less than the length of described blade back segment (6).
7, the nozzle ring turbosupercharger of revolving as claimed in claim 6 is characterized in that: the pitch of described nozzle blade is 0.6 ~ 0.9 with the ratio of the chord length of described nozzle blade.
8, the nozzle ring turbosupercharger of revolving as claimed in claim 7 is characterized in that: the pitch of described nozzle blade is 0.71 with the ratio of the chord length of described nozzle blade.
9, the nozzle ring turbosupercharger of revolving as claimed in claim 6 is characterized in that: the established angle of described nozzle vane is 45 ° ~ 85 °.
10, the nozzle ring turbosupercharger of revolving as claimed in claim 6 is characterized in that: also be provided with the limit stoper that prevents that described blade back segment from closing fully on the described nozzle ring base (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200820100844 CN201301731Y (en) | 2008-12-04 | 2008-12-04 | Turbo-charger with rotary nozzle ring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200820100844 CN201301731Y (en) | 2008-12-04 | 2008-12-04 | Turbo-charger with rotary nozzle ring |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201301731Y true CN201301731Y (en) | 2009-09-02 |
Family
ID=41085355
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200820100844 Expired - Lifetime CN201301731Y (en) | 2008-12-04 | 2008-12-04 | Turbo-charger with rotary nozzle ring |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201301731Y (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103206266A (en) * | 2013-04-15 | 2013-07-17 | 无锡科博增压器有限公司 | Efficient guide ring for turbocharger |
| CN104895839A (en) * | 2015-04-22 | 2015-09-09 | 南京航空航天大学 | Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof |
| WO2016078444A1 (en) * | 2014-11-20 | 2016-05-26 | 康跃科技股份有限公司 | Variable geometry wastegate turbine meeting the requirements of egr circulation and guide vane assembly |
| CN111140341A (en) * | 2019-12-20 | 2020-05-12 | 中国北方发动机研究所(天津) | Segmented adjustable blade vaned diffuser structure |
-
2008
- 2008-12-04 CN CN 200820100844 patent/CN201301731Y/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103206266A (en) * | 2013-04-15 | 2013-07-17 | 无锡科博增压器有限公司 | Efficient guide ring for turbocharger |
| WO2016078444A1 (en) * | 2014-11-20 | 2016-05-26 | 康跃科技股份有限公司 | Variable geometry wastegate turbine meeting the requirements of egr circulation and guide vane assembly |
| CN104895839A (en) * | 2015-04-22 | 2015-09-09 | 南京航空航天大学 | Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof |
| CN111140341A (en) * | 2019-12-20 | 2020-05-12 | 中国北方发动机研究所(天津) | Segmented adjustable blade vaned diffuser structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20090902 |