CN100523439C - Composite spray of variable cross-section turbosupercharger - Google Patents
Composite spray of variable cross-section turbosupercharger Download PDFInfo
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- CN100523439C CN100523439C CNB2007100167419A CN200710016741A CN100523439C CN 100523439 C CN100523439 C CN 100523439C CN B2007100167419 A CNB2007100167419 A CN B2007100167419A CN 200710016741 A CN200710016741 A CN 200710016741A CN 100523439 C CN100523439 C CN 100523439C
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Abstract
The invention discloses a compound nozzle of a turbine booster with variable sections, which comprises a power turbine and a nozzle-supporting disk connected axially with the power turbine. On the nozzle-supporting disk, a plurality of compound nozzle blades are provided, which comprise movable and static nozzle blades. The ends of the nozzle blades are provided with a movable-blade-rotating shaft. The movable nozzle blades are rotatably connected with the nozzle-supporting disk through the movable-blade-rotating shaft. By coordinating the movable with the static nozzle blades, gas flow is adjusted. The invention effectively solved the shortcomings associated with the pneumatic adjustment inherent with the singular pneumatic nozzle in prior nozzle type turbine booster with variable sections.
Description
Technical field
The present invention relates to variable-area turbocharger, relate in particular to a kind of combining nozzle of variable-area turbocharger of architecture advances of the rotation blade of adjusting the waste gas airintake directions by the some rotation blades in the turbine shroud that is configured in turbosupercharger, belong to field of internal combustion engine.
Background technique
Turbosupercharger is the waste gas that utilizes motor to discharge, flow into according to certain route in the turbine case of turbosupercharger to drive turbine, and the drive compressor impeller high speed rotating coaxial with turbine, fresh air is compressed the cylinder that enters motor under the compressor impeller action of centrifugal force, because air density is big, thereby increased the aeration quantity of motor, can supply more fuel oil perfect combustion, the power of motor, the consumption rate of having saved fuel oil have been improved, simultaneously because the improvement of combustion condition has reduced CO in the waste gas, HC, NO
XAnd the discharging of harmful substance such as PM, through the guiding function of engine exhaust air-flow also having been reduced synchronously the noise of motor.
For turbosupercharger, we usually wish to flow into by control the exhaust gas flow of turbine, with efficient and the matching range that improves turbosupercharger.Along with the continuous lifting to diesel engine and petrol engine Economy and exhaust index demand, the structure of variable-area turbocharger has progressively satisfied these demands.
Variable nozzle turbocharger is exactly a kind of of variable-area turbocharger.As shown in Figure 1, variable nozzle turbocharger roughly comprises a middle case 2, and the one end connects a compressor casing 1, and the other end connects turbine case 4.Be included in the bearing 8 support rotor axles 19 in the middle casing, rotor shaft can high speed rotating.Power turbine 7 and compressor impeller 9 are connected in the two ends of axle by rotor shaft 19.Power turbine 7 and compressor impeller 9 also are supported on respectively in turbine case 4 and the compressor casing 1.Middle case 2 is connected with turbine case 4 and compressor casing 1 by bolt.The turbo machine part of having represented the known variable nozzle turbocharger among Fig. 2, this turbine portion branch comprises a turbine case 4, and turbine case 4 has one can be used to receive the volute import 20 of waste gas and the volute outlet 21 that is used for direct exhaust to engine exhaust system.A plurality of nozzle vanes 6 are installed in the turbine case 4 after connecting by nozzle ring supporting disk 5, and nozzle ring supporting disk 5 and turbine case nozzle inner walls 22 have formed two nozzle walls of air-flow path.After supporting by rotor shaft 19, power turbine 7 is installed on the radially inner side of nozzle vane 6.A plurality of nozzle vanes 6 are connected according to tilt fixing respectively with a plurality of shift forks 10 respectively, inside or outward radial moving nozzle blade 6 under the drive of driving mechanism 3.Thereby the high-temp waste gas that control enters from turbine case import 20 enters power turbine 7 according to certain angle and aperture, drives compressor impeller 9 rotation pressurized gass.Nozzle ring inwall passage carries out axially locating by supporting sleeve 11, guarantees that nozzle vane 6 can in use freely rotate.
In variable nozzle turbocharger, drive the some swing nozzle vanes that are distributed in the turbine case gas-entered passageway by the control driving mechanism, these nozzle vanes are controlled jointly, change the throat area of vane channel by the different amount of adjusting blade, thereby play the effect that control enters the exhaust energy of turbine.For guaranteeing that variable nozzle turbocharger can work as requested accurately, each blade needs can be according to the control action of exhaust gas flow change position and the translation-angle at the turbine case internal freedom.As shown in Figure 3, represented that known nozzle vane 6 is rotated by the spin axis that driving mechanism 3 drives with respect to power turbine 7 in nozzle ring supporting disk 5.Thereby influence the aperture that adjacent nozzle blade 6 forms a1.A1 shown in Figure 3 is big aperture, and nozzle vane trailing edge 23 is nearest apart from turbine blade import 24, and aerodynamic loss is little.At this moment, the coupling operating mode of pressurized machine and motor is big flow operating mode.As shown in Figure 4, represented that known nozzle vane 6 is rotated by the spin axis that driving mechanism 3 drives with respect to power turbine 7 in nozzle ring supporting disk 5.Thereby influence the aperture that adjacent nozzle blade 6 forms a2.A2 shown in Figure 3 is little aperture, nozzle vane trailing edge 23 apart from turbine blade import 24 distance farthest, aerodynamic loss is big.At this moment, the coupling operating mode of pressurized machine and motor is a low flow rate condition, and aerodynamic loss is big to the efficiency of turbocharger influence.
Known multiple-blade variable nozzle turbocharger comprises a plurality of nozzle vanes that have running shaft, and each blade pass is crossed in the supporting disk that running shaft is installed in turbine case cooperates.Utilize welding or riveted way to form a rotatable integral body, move by control mechanism and driving mechanism then.The variable-nozzle structure of this band rotation blade is widely applied on abroad the variable cross section pressurized machine.
Find that by practical application there are some shortcomings in this variable-nozzle pressurized machine in the Performance Match process.Nozzle vane is the central synchronous rotation with fixing transmission shaft in use, in the big flow operating mode of motor lower blade aperture maximum, the rotation blade trailing edge is at the diametric(al) power turbine of close turbosupercharger, and air-flow can enter the turbine work done smoothly according to guiding.According to demand, at the operating point of engine low rotation speed, small flow, rotation blade aperture minimum is worked under a rational rotating speed to keep pressurized machine, thereby satisfies the boost pressure demand of motor.Because the rotation factor, under little aperture situation, from the power turbine of pressurized machine farthest, the air current flow path is the longest on diametric(al) for the rotation blade trailing edge.Therefore, under low speed, low flow rate condition the windage loss of the type variable cross section pressurized machine big, these windage losses influence for the limited exhaust energy of low engine speed operating mode itself is huge.
Therefore, wish a kind of nozzle of design, be applied to variable nozzle turbocharger to solve slow speed jet blade loss problem.By the nozzle fit adjustment, obtaining, thereby improve low speed matching problem with motor than common rotation blade air-flow drive path more suitably under the low speed operating mode.
Summary of the invention
Problem to be solved by this invention is the pneumatic adjusting narrow limitation that solves blade nozzle in the variable nozzle turbocharger, a kind of combining nozzle of variable-area turbocharger is provided, can effectively solves airflow route problem and the matching effect that improves under low engine speed, the low flow rate condition.
In order to address the above problem, the present invention by the following technical solutions:
A kind of combining nozzle of variable-area turbocharger, comprise power turbine with the coaxial nozzle support dish that is connected of power turbine, described nozzle support dish is provided with several combining nozzle blades, it is characterized in that: described combining nozzle blade is made up of nozzle moving vane and nozzle stator blade, the end of described nozzle moving vane is provided with the moving vane running shaft, described nozzle moving vane is rotationally connected by moving vane running shaft and nozzle support dish, cooperates by dynamic and static blade, realizes gas flow modulation.
Below be further improvement of these options of the present invention:
Described nozzle moving vane and nozzle stator blade have arcuate structure respectively, the outside of described nozzle stator blade has the arc step, described nozzle moving vane is positioned on the arc step and is connected with the nozzle stator blade, the external arc of the external arc of described nozzle moving vane and nozzle stator blade is positioned on the same arc shaped surface, moving vane in the described combining nozzle is by the moving rotation of shift fork dribbling, initial position is influenced by stator blade, opens several angle according to fixed-direction.
Described nozzle support dish is provided with and the consistent leaf grating of nozzle moving vane arc, when the nozzle moving vane opens to maximum angle, described leaf grating and nozzle moving vane are positioned on the same arc shaped surface, dynamic and static blade in the combining nozzle can form different leaf grating combinations, leaf grating cooperates with the combining nozzle moving vane, efficiently solves nozzle vane trailing edge air-flow guiding problem.
Described nozzle support dish is provided with several shift forks away from a side of power turbine, and described shift fork is corresponding one by one with the combining nozzle blade, and described nozzle support dish is provided with the nozzle ring rotating hole, and described moving vane running shaft passes the nozzle ring rotating hole and is connected with shift fork.
The end of described nozzle stator blade is provided with stator blade welding axle, and described stator blade welding axle is fixedlyed connected with the nozzle support dish.
When the relative combining nozzle stator blade of described combining nozzle moving vane does not rotate, form maximum nozzle angle between described combining nozzle blade and the adjacent combining nozzle blade, the moving vane trailing edge is nearest apart from turbine inlet in the described combining nozzle blade, when the relative combining nozzle stator blade of described combining nozzle moving vane rotates to maximum angle, form minimum nozzle angle between described combining nozzle blade and the adjacent combining nozzle blade, the stator blade trailing edge is nearest apart from turbine inlet in the combining nozzle blade.
Beneficial effect:
The present invention is by to the designing and developing of combining nozzle blade, effectively solved air-blast atomizer single in the present nozzle-type variable-area turbocharger intrinsic pneumatic adjusting defective.The method that combining nozzle structure among the present invention adopts dynamic and static nozzle vane to cooperate can form multiple fit angle as required, thereby effective steering flow direction is transferred to the power turbine of turbosupercharger as required with reasonable manner.Sound vanes in the combining nozzle is crossed rational pneumatic design, can effectively improve the matching effect of variable nozzle turbocharger, especially improves the low speed matching effect.Moving vane in the combining nozzle has been realized the regulatory function of single air-blast atomizer as rotation blade; The moving stator blade angle in whole adjustment process of combining nozzle does not change.The flow angle that forms with stator blade before the moving vane rotation is fit to the big flow operating mode of motor; Postrotational moving vane can form the flow angle that is fit to the low engine speed operating mode with stator blade.Therefore when low speed mate, stator blade and adjacent moving vane have formed a rational air-flow path, and simultaneously, the air current flow distance of jet expansion can effectively be shortened in the position of stator blade, the minimizing windage loss.
To sum up, the variable nozzle turbocharger behind the employing combining nozzle can effectively improve the aeroperformance of pressurized machine, and assembly process does not have big variation with original variable-nozzle pressurized machine.Progressively to variable cross section pressurized machine excessive opportunity, the combining nozzle structure has the vast market promotional value, can obtain good effect in present turbosupercharger.
Below in conjunction with drawings and Examples patent of the present invention is further described:
Description of drawings
Accompanying drawing 1 is the structural representation of variable nozzle turbocharger in the background technique;
Accompanying drawing 2 is exploded perspective view of the turbine shroud of the turbosupercharger of employing plain nozzle blade in the background technique;
Accompanying drawing 3 is adjustable nozzle mechanism structural representations under the big flow operating mode of motor in the background technique;
Accompanying drawing 4 is adjustable nozzle mechanism structural representations under the motor low flow rate condition in the background technique;
Accompanying drawing 5 is combining nozzle assembled construction schematic representation in the embodiment of the invention;
Accompanying drawing 6 is structural representations of combining nozzle blade in the embodiment of the invention;
Accompanying drawing 7 is the dynamic and static blade assembled construction of combining nozzle schematic representation in the embodiment of the invention;
Accompanying drawing 8 be in the embodiment of the invention under the big flow operating mode of motor the structural representation of combining nozzle;
Accompanying drawing 9 be in the embodiment of the invention under the motor low flow rate condition structural representation of combining nozzle;
Accompanying drawing 10 is combining nozzle assembled construction schematic representation in the embodiment of the invention 2.
The title of each several part among the figure: 1-compressor casing, the 2-middle case, the 3-driving mechanism, the 4-turbine case, 5-nozzle ring supporting disk, the 6-nozzle vane, the 7-power turbine, the 8-bearing, the 9-compressor impeller, the 10-shift fork, the 11-supporting sleeve, 12-nozzle moving vane, 13-nozzle stator blade, 14-combining nozzle supporting disk, the 15-leaf grating of connecting, 16-nozzle ring rotating hole, 17-moving vane running shaft, 18-stator blade welding axle, the 19-rotor shaft, the import of 20-volute, the outlet of 21-volute, 22-volute nozzle inner walls, 23-nozzle vane edge, the import of 24-turbine blade, 25-combining nozzle blade, 26-moving vane trailing edge, 27-stator blade trailing edge.
Embodiment
Embodiment 1, as shown in Figure 5, a kind of combining nozzle of variable-area turbocharger, comprise power turbine 7 with the power turbine 7 coaxial nozzle support dishes 14 that are connected, nozzle support dish 14 is provided with several combining nozzle blades 25, combining nozzle blade 25 is made up of nozzle moving vane 12 and nozzle stator blade 13, the end of nozzle moving vane 12 is provided with moving vane running shaft 17, nozzle moving vane 12 is rotationally connected by moving vane running shaft 17 and nozzle support dish 14, nozzle stator blade 13 is fixed on the nozzle support dish 14, nozzle moving vane 12 and nozzle stator blade 13 have arcuate structure respectively, as shown in Figure 6, nozzle moving vane 12 can rotate with respect to nozzle stator blade 13 by orbiting vane running shaft 17, thereby realize the working principle of combining nozzle blade, as shown in Figure 7, the outside of nozzle stator blade 13 has the arc step, nozzle moving vane 12 is positioned on the arc step and is connected with nozzle stator blade 13, the external arc of the external arc of nozzle moving vane 12 and nozzle stator blade 13 is positioned on the same arc surface, the end of nozzle moving vane 12 is provided with moving vane running shaft 17, nozzle support dish 14 is provided with several shift forks 10 away from a side of power turbine 7, shift fork 10 is corresponding one by one with combining nozzle blade 25, nozzle support dish 14 is provided with nozzle ring rotating hole 16, and moving vane running shaft 17 passes nozzle ring rotating hole 16 and is connected with shift fork 10.
As shown in Figure 8, driving mechanism drive combining nozzle blade 25 is rotated with respect to the spin axis of power turbine 7, when the nozzle moving vane 12 in the combining nozzle blade 25 does not rotate with respect to stator blade 13, form maximum nozzle angle between combining nozzle blade 25 and the adjacent combining nozzle blade, moving vane trailing edge 26 is nearest apart from turbine inlet 24 in the combining nozzle blade 25, stator blade trailing edge 27 carries out the air-flow guiding, aerodynamic loss is little, at this moment, the coupling operating mode of pressurized machine and motor is big flow operating mode.
As shown in Figure 9, nozzle moving vane 12 in the driving mechanism drive combining nozzle blade 25 is rotated with respect to the spin axis of power turbine 7, when nozzle moving vane 12 rotates with respect to nozzle stator blade 13, form minimum nozzle angle between combining nozzle blade 25 and the adjacent combining nozzle blade, stator blade trailing edge 27 is nearest apart from turbine inlet 24 in the combining nozzle blade 25, the air-flow guiding is carried out in nozzle stator blade 13 and 12 actings in conjunction of adjacent nozzles moving vane.At this moment, combining nozzle efficiently solves the air flow path problem, and aerodynamic loss reduces greatly.Therefore, solve adjustable nozzle pressurized machine and low engine speed small flow and joined the problem that efficient reduces when trying.
Patent of the present invention has been finished the exploitation of the combining nozzle structure of being made up of the sound blade at the demand of variable nozzle turbocharger, the exhaust energy of effectively controlling and having utilized turbosupercharger to introduce.This composite blading can be finished by same type of material and existing casting and processing technique.Sound blade in the combining nozzle adopts solid construction mostly, and the function of sound blade can be according to structure needs mutual alternative.
As shown in Figure 8, driving mechanism drive combining nozzle blade 25 is rotated with respect to the spin axis of power turbine 7, when the nozzle moving vane 12 in the combining nozzle blade 25 does not rotate with respect to nozzle stator blade 13, form maximum nozzle angle between combining nozzle blade 25 and the adjacent combining nozzle blade, moving vane trailing edge 26 is nearest apart from turbine inlet 24 in the combining nozzle blade 25, stator blade trailing edge 27 carries out the air-flow guiding, aerodynamic loss is little, at this moment, the coupling operating mode of pressurized machine and motor is big flow operating mode.
As shown in Figure 9, nozzle moving vane 12 in the driving mechanism drive combining nozzle blade 25 is rotated with respect to the spin axis of power turbine 7, when nozzle moving vane 12 rotates with respect to nozzle stator blade 13, form minimum nozzle angle between combining nozzle blade 25 and the adjacent combining nozzle blade, stator blade trailing edge 27 is nearest apart from turbine inlet 24 in the combining nozzle blade 25, nozzle stator blade 13 and 12 actings in conjunction of adjacent nozzles moving vane, carry out the air-flow guiding, at this moment, combining nozzle efficiently solves the air flow path problem, and aerodynamic loss reduces greatly.Therefore, solve adjustable nozzle pressurized machine and low engine speed small flow and joined the problem that efficient reduces when trying.
As shown in figure 10, nozzle support dish 14 is provided with the leaf grating 15 consistent with nozzle moving vane 12 arcs, when nozzle moving vane 12 opens to maximum angle, described leaf grating 15 is positioned on the same arc shaped surface with nozzle moving vane 12, leaf grating 15 carries out the air-flow guiding jointly with the moving vane trailing edge 26 of nozzle moving vane 12, can further improve the air-flow guiding problem in the combining nozzle structure.Can further reduce aerodynamic loss, improve low speed efficient.
Patent of the present invention is at the demand of variable nozzle turbocharger, finished the exploitation of the combining nozzle structure of forming by the sound blade, the exhaust energy of effectively controlling and having utilized turbosupercharger to introduce, this composite blading can be finished by same type of material and existing casting and processing technique, sound blade in the combining nozzle adopts solid construction mostly, and the function of sound blade can be according to structure needs mutual alternative.
We are described in detail the present invention according to the relevant regulations of national patent method; for improvement or the replacement of those skilled in the art according to specific embodiment disclosed herein; if these modifications are within the spirit and scope of the present invention, should fall into protection domain of the present invention.
Claims (4)
1, a kind of combining nozzle of variable-area turbocharger, comprise power turbine (7) with the coaxial nozzle support dish (14) that is connected of power turbine (7), described nozzle support dish (14) is provided with several combining nozzle blades (25), it is characterized in that: described combining nozzle blade (25) is made up of nozzle moving vane (12) and nozzle stator blade (13), the end of described nozzle moving vane (12) is provided with moving vane running shaft (17), described nozzle moving vane (12) is rotationally connected by moving vane running shaft (17) and nozzle support dish (14), described nozzle stator blade (13) is fixed on the nozzle support dish (14), described nozzle moving vane (12) and nozzle stator blade (13) are arcuate structure, has the arc step on the described nozzle stator blade (13), described nozzle moving vane (12) is positioned on the arc step, described nozzle support dish (14) is provided with the leaf grating (15) consistent with nozzle moving vane (12) arc, when nozzle moving vane (12) when opening to maximum angle, described leaf grating (15) is positioned on the same arc shaped surface with nozzle moving vane (12).
2, the combining nozzle of variable-area turbocharger according to claim 1, it is characterized in that: described nozzle support dish (14) is provided with several shift forks (10) away from a side of power turbine (7), and described moving vane running shaft (17) passes nozzle support dish (14) and is connected with shift fork (10).
3, the combining nozzle of variable-area turbocharger according to claim 2 is characterized in that: the end of described nozzle stator blade (13) is provided with stator blade welding axle (18), and described stator blade welding axle (18) is fixedlyed connected with nozzle support dish (14).
4, the combining nozzle of variable-area turbocharger according to claim 3, it is characterized in that: the relative nozzle stator blade (13) of described nozzle moving vane (12) is not when rotating, moving vane trailing edge (26) is nearest apart from turbine inlet (24) in the described combining nozzle blade (25), nozzle stator blade (13) is when rotating to maximum angle relatively for described nozzle moving vane (12), and stator blade trailing edge (27) is nearest apart from turbine inlet (24) in the combining nozzle blade (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100167419A CN100523439C (en) | 2007-08-02 | 2007-08-02 | Composite spray of variable cross-section turbosupercharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100167419A CN100523439C (en) | 2007-08-02 | 2007-08-02 | Composite spray of variable cross-section turbosupercharger |
Publications (2)
| Publication Number | Publication Date |
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| CN101109295A CN101109295A (en) | 2008-01-23 |
| CN100523439C true CN100523439C (en) | 2009-08-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2007100167419A Expired - Fee Related CN100523439C (en) | 2007-08-02 | 2007-08-02 | Composite spray of variable cross-section turbosupercharger |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101634233B (en) * | 2009-08-20 | 2011-07-20 | 康跃科技股份有限公司 | Pneumatic nozzle of variable geometry turbocharger (VGT) |
| CN101949305B (en) * | 2010-09-07 | 2013-06-05 | 康跃科技股份有限公司 | Turbocharger composite nozzle device |
| CN102080578B (en) * | 2011-01-12 | 2014-07-30 | 康跃科技股份有限公司 | Compound turbo supercharging device having variable cross-section axial radial flows |
| CN102297016B (en) * | 2011-08-15 | 2012-12-12 | 无锡凯迪增压器配件有限公司 | Turbocharger for double-vane nozzle systems |
| CN103742204A (en) * | 2013-12-30 | 2014-04-23 | 汉捷机械部件（常州）有限公司 | Adjustable turbine |
| CN109595041B (en) * | 2017-09-30 | 2021-10-19 | 中国航发商用航空发动机有限责任公司 | Variable-circulation large-bypass-ratio turbofan engine |
| CN109209525B (en) * | 2018-11-23 | 2021-11-26 | 府谷科创源能源科技股份有限公司 | High back pressure steam turbine set |
| CN110761847B (en) * | 2019-10-30 | 2022-02-25 | 辽宁工程技术大学 | Split sliding type adjustable nozzle ring of turbocharger |
| CN113350925B (en) * | 2021-07-06 | 2022-05-17 | 江苏量为石科技股份有限公司 | Dust exhaust device of power equipment dust remover |
-
2007
- 2007-08-02 CN CNB2007100167419A patent/CN100523439C/en not_active Expired - Fee Related
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| CN101109295A (en) | 2008-01-23 |
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