CN210152736U - Exhaust gas turbocharger volute assembly - Google Patents
Exhaust gas turbocharger volute assembly Download PDFInfo
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- CN210152736U CN210152736U CN201920842460.7U CN201920842460U CN210152736U CN 210152736 U CN210152736 U CN 210152736U CN 201920842460 U CN201920842460 U CN 201920842460U CN 210152736 U CN210152736 U CN 210152736U
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- volute
- exhaust gas
- gas turbocharger
- flow guide
- guide structure
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Abstract
The utility model belongs to the technical field of turbo charger, a exhaust gas turbo charger volute subassembly is related to, including the volute, set up the volute runner on the volute, the volute runner is separated for two passageways by the divider wall, and the inlet end inboard of volute runner sets up the volute tongue, and the radial inner circle of volute runner forms the nozzle, it sets up the water conservancy diversion structure to be close to nozzle department on the divider wall. The utility model discloses the product can effectively improve the high all fatigue reliability of booster turbine, and the volute makes simply, can realize through repairing the mould.
Description
Technical Field
The utility model belongs to the technical field of turbo charger, a exhaust gas turbo charger volute subassembly is related to.
Background
Exhaust gas turbochargers are well known devices for supplying atmospheric pressure boost to the intake air intake of an internal combustion engine. A typical supercharger basically comprises a turbine volute and a turbine wheel mounted within the volute, the volute being downstream of the engine exhaust manifold. The rotation of the turbine drives a compression impeller arranged at the other coaxial end to rotate, so that air is compressed and collected by a compressor shell and is conveyed to an engine air inlet main pipe. The turbine shaft is typically supported by a floating bearing and a thrust bearing within an intermediate casing that connects the turbine and compressor.
During the operation of the turbocharger, the turbine housing adjusts the motion track of exhaust gas through a spiral structure in the turbine, so that the exhaust gas can generate and output maximum power when pushing the turbine to rotate, therefore, the shape of a turbine runner plays an important role in the distribution of an exhaust gas pressure field, the turbocharger turbine is influenced by the pressure field, particularly, due to the impact of pressure shock waves at the volute tongue of the turbine runner, turbine blades generate very large vibration stress at the resonant harmonic rotation speed of the turbine blades, and high-cycle fatigue failure of the turbine blades is caused. It is very difficult for current turbine designs to simultaneously meet high performance and resist high excitation forces, and the improvements that can be made are limited.
For a turbine with a fixed nozzle or a variable nozzle, more attention is paid to the excitation force of the turbine blade at the natural frequency, the pressure fluctuation at the inlet of the turbine blade is the excitation source of the turbine blade vibration, the excitation force of different harmonics generated by different nozzle shapes is greatly different, and the important consideration in the design of the volute nozzle is to reduce the excitation force at a certain harmonic by changing the design. During the rotation of the turbine, each time the turbine passes the volute tongue, a pressure fluctuation is generated, so that the turbine blade is an excitation pressure, and for a fixed-section supercharger, the pressure at the volute tongue is the position where the pressure fluctuation is maximum when the turbine rotates for one circle.
Therefore, based on the principle of reducing pressure shock waves at the volute tongue, the optimization of the volute plays a key role in improving the high-cycle fatigue failure of the turbine. The harmonic excitation force of the turbine can be greatly reduced on the basis of the design of the volute through the optimized volute, so that the high-cycle fatigue risk of the turbine is reduced.
Disclosure of Invention
The utility model provides an above-mentioned problem, a waste gas turbocharger volute subassembly is provided, this volute subassembly can effectively improve the high all fatigue reliability of booster turbine, and the volute makes simply, can realize through repairing the mould.
According to the technical scheme of the utility model: the utility model provides an exhaust gas turbocharger volute subassembly, includes the volute, sets up the volute runner on the volute, and the volute runner is separated for two passageways by the divider wall, and the inlet end inboard of volute runner sets up the vortex tongue, and the radial inner circle of volute runner forms nozzle, its characterized in that: and a flow guide structure is arranged on the partition wall close to the nozzle.
As a further improvement of the utility model, the water conservancy diversion structure sets up in dividing wall surface one side or the symmetry sets up in dividing wall surface both sides.
As a further improvement of the utility model, the water conservancy diversion structure sets up in the middle shell side of divider wall and nozzle simultaneously.
As a further improvement of the utility model, the water conservancy diversion structure sets up simultaneously in the middle shell side of volute type line side and volute.
As a further improvement, the diversion structure is arranged on the side of the volute type line.
As a further improvement of the present invention, the flow guiding structure is disposed on the middle shell side of the volute.
As a further improvement, the diversion structure is arranged on the partition wall at a radius of the turbine from 1 time to 2 times of the axis.
As a further improvement of the utility model, the axial dimension of the flow guide structure is 0.1 times to 0.5 times the width of the nozzle.
As a further improvement, the circumferential processing angle range of the flow guide structure is 1 degree to 30 degrees.
As a further improvement of the utility model, the flow guide structure is a protrusion or a groove.
As a further improvement of the utility model, the groove passes through the vortex tongue and is communicated with the high-pressure end and the low-pressure end at the vortex tongue.
As a further improvement of the utility model, the processing surface of the flow guide structure is square or annular.
As a further improvement, the radial section of the flow guide structure is circular.
As a further improvement, the radial section of the flow guide structure is triangular.
The technical effects of the utility model reside in that: the utility model discloses the product can effectively improve the high all fatigue reliability of booster turbine, and the volute makes simply, can realize through repairing the mould.
Drawings
Fig. 1 is a schematic longitudinal section of the present invention.
Fig. 2 is a cross-sectional schematic view of the present invention.
Fig. 3 is a partially enlarged longitudinal cross-sectional view of the present invention.
Detailed Description
The following description will further describe embodiments of the present invention with reference to the accompanying drawings.
In fig. 1 to 3, the nozzle assembly includes a volute 1, a volute flow passage 2, a volute tongue 3, a partition wall 4, a nozzle 5, a volute molded line 6, a protrusion 7, and the like.
As shown in fig. 1-3, the utility model discloses the product is an exhaust gas turbine supercharger volute subassembly, including volute 1, set up volute runner 2 on the volute 1, volute runner 2 is separated for two passageways by divider wall 4, and volute runner 2's inlet end inboard sets up volute tongue 3, and volute runner 2's radial inner circle forms nozzle 5, be close to nozzle 5 department on the divider wall 4 and set up the water conservancy diversion structure.
The utility model discloses water conservancy diversion structure in the product has multiple mode of setting according to actual conditions needs, specifically as follows: the diversion structures are arranged on one side of the surface of the division wall 4 or symmetrically arranged on two sides of the surface of the division wall 4.
The flow guiding structure may be provided on both the dividing wall 4 and the intermediate shell side of the nozzle 5.
The flow guide structure can be arranged on the side of the volute molded line 6 and the side of the middle shell of the volute simultaneously, and the volute molded line 6 is a matching surface of the turbine and the volute.
The flow guide structure can also be arranged on the side of the volute casing molded line 6; the flow guide structure can also be arranged on the middle shell side of the volute; the flow guide structure is arranged on the partition wall 4 at a position 1-2 times of the radius of the turbine away from the axis.
The axial dimension of the flow guide structure is 0.1 to 0.5 times the width of the nozzle 5; the circumferential machining angle range of the flow guide structure is 1 degree to 30 degrees.
The groove penetrates through the vortex tongue 3 and is communicated with a high-pressure end and a low-pressure end at the vortex tongue 3.
The processing surface of the flow guide structure is square or annular; the radial section of the flow guide structure is circular or triangular. It will be appreciated that the primary purpose of the flow directing structure is to achieve a direction of the airflow, which in a particular arrangement may be a protrusion or a recess.
The utility model relates to an exhaust-gas turbine booster volute subassembly, volute 1's effect is through volute runner 2 change engine exhaust flow direction, and volute runner 2 is helical structure to its area begins constantly to reduce from 3 departments of volute tongue, and the waste gas of different jars is divided into two passageways by division wall 4, and the effect of division wall 4 is the waste gas of separating the different jars of engine, thereby can effectively utilize the pulse energy that different jar waste gases produced. The spiral volute flow channel 2 structure enables air flow to rotate and advance, waste gas of two channels respectively passes through the volute tongues 3, the air flow near the volute tongues 3 passes through the protrusions 7, is guided by the volute flow channel 2 and then is converged together at the nozzle 5 and enters the nozzle 5, the nozzle 5 is a smooth circular channel which is machined, and the waste gas impacts a turbine through the nozzle 5 to do work and provides kinetic energy for the end of a compressor. When the air flow passes through the vortex tongue 3 and does not reach the nozzle 5, the air flow is disturbed by the bulge 7, and a vortex is formed at the bulge 7, and the formed vortex can effectively reduce the pressure of the air flow at the position, so that the pressure shock wave at the position of the original vortex tongue 3 can be effectively reduced. Thereby effectively reducing the risk of high cycle fatigue of the turbine blades and improving the reliability life of the supercharger.
As shown in figure 1, the bulge 7 in the product of the utility model is close to the volute tongue, the cross section is rectangular, and the radial processing position of the bulge is more than the outer diameter of the turbine from the axis of the turbine, but less than 2 times of the radius of the turbine. Protruding 7's radial process range is 0.1 times to 1 times's volute nozzle width, and radial process range can produce different effects to reducing 3 pressure shock waves of volute tongue, and the scope is wider more, and the effect is better under the general condition, but the scope is too wide can influence the whole pneumatic performance of volute, so the utility model discloses well protruding 7 radial process range is injectd at 0.1 times to 1 times's volute nozzle width. The utility model discloses well arch 7 is symmetry processing on the division wall, when the pressure shock wave distributes unevenly in the axial, can be according to the pressure shock wave form of reality, and arch 7 can only be protruding in 4 unilateral processing of division wall with not co-altitude processing in the protruding height of both sides even. For not influencing the whole aerodynamic performance of volute, the utility model discloses in inject protruding 7 protruding height at 0.1 to 0.5 times volute nozzle width.
As shown in fig. 1, the protrusion 7 of the present invention is formed on the partition wall 4 and is symmetrically formed. When the pressure shock wave at the volute tongue is not uniform in the axial direction, the bulge 7 can be machined on one side of the partition wall 4, and even the bulge can be machined on the molded line side of the volute nozzle to achieve the effect of reducing the pressure shock wave. For the double-channel volute, the axial arrangement positions of the bulges 7 can be respectively arranged on two sides of the nozzle and two sides of the partition wall 4 in one or more forms according to the characteristics of the pressure shock wave.
As shown in figure 2, the novel design of the utility model is that the bulge 7 is close to the volute tongue, and the processed surface is rectangular. The circumferential angle between the processing initial position of the bulge 7 and the tongue tip of the vortex tongue is 5 degrees. The processing initial position of the bulge 7 is determined according to the pressure shock wave, and can be arranged at any angle in the circumferential direction before and after the vortex tongue. The arrangement position of the projections 7 may also be different for different scroll cases. Protruding 7 circumference processing angle scope can influence the effect that reduces vortex tongue department pressure shock, and the too big whole aerodynamic performance of volute that still can influence of scope, so the utility model discloses well inject protruding 7 circumference processing angle scope and be 1 degree to 30 degrees.
As shown in figure 3, the novel design of the utility model is that the bulge 7 is close to the volute tongue, and the processed surface is rectangular. The machining area of arch 7 can produce different effects to reducing vortex tongue department pressure shock wave, and the area is big more, and the effect is better, but the too big whole pneumatic performance of volute that can influence of area, so the utility model discloses well 7 machining areas of arch inject at the key sectional area of volute 0.1 times to 0.5 times.
As shown in fig. 2, the novel design protrusion 7 feature of the present invention may also be a recessed feature, the machined dimensional definition of which is consistent with the protruding feature. When the groove is characterized, the groove can even cross the volute tongue of the volute to communicate the high-pressure end and the low-pressure end of the airflow in front of and behind the volute tongue. When the airflow flows through the volute tongue to the groove, the airflow pressure at the groove is reduced due to the disturbance of the characteristics of the groove, and part of high-pressure airflow directly flows to the low-pressure part behind the volute tongue through the groove to be mixed with the low-pressure air, so that the pressure of the airflow in front of and behind the volute tongue is balanced, the pressure difference in front of and behind the volute tongue is reduced, and the effect of effectively reducing the pressure shock wave at the volute tongue can be achieved.
As shown in FIG. 2, the new design of the present invention is that the protrusion 7 is close to the volute tongue and is arranged singly in the circumferential direction. The protrusions can be arranged in a plurality of series connection modes except for the circumferential processing range, the circumferential processing range of each protrusion does not need to be consistent, but in order not to influence the overall aerodynamic performance of the scroll, the circumferential processing range of each protrusion is still limited to be 1-30 degrees, and the overall circumferential range of the series protrusions does not exceed 90 degrees.
For a supercharger with a fixed section, engine exhaust enters a nozzle through a volute tongue and then works in a turbine, huge pressure difference is inevitably generated before and behind the volute tongue, and pressure shock waves are generated in serious cases. The pressure shock wave can cause the turbine to produce significant blade vibration at its resonant speed, thereby producing high cycle fatigue failure of the turbine blades. The utility model discloses all utilized the pressure distribution through changing volute tongue department in protruding 7's the design, reached balanced volute tongue front and back pressure to reduce and improve the principle of the pressure shock wave of volute tongue department. Therefore, the input excitation of the turbine is effectively reduced, and the reliability of the high cycle fatigue of the turbine blade is improved.
The above description is intended to be illustrative of the present invention and not to limit the invention, which is defined by the claims, and any modifications within the scope of the present invention are possible.
The utility model has the advantages of simple structure and compactness reasonable, can effectively improve the high tired reliability in week of booster turbine, and volute manufacturing is simple.
Claims (14)
1. The utility model provides an exhaust gas turbocharger volute subassembly, includes volute (1), sets up volute runner (2) on volute (1), and volute runner (2) are separated for two passageways by divider wall (4), and the inlet end inboard of volute runner (2) sets up volute tongue (3), and radial inner circle of volute runner (2) forms nozzle (5), its characterized in that: and a flow guide structure is arranged on the partition wall (4) close to the nozzle (5).
2. The exhaust gas turbocharger volute assembly of claim 1, wherein: the flow guide structures are arranged on one side of the surface of the division wall (4) or symmetrically arranged on two sides of the surface of the division wall (4).
3. The exhaust gas turbocharger volute assembly of claim 1, wherein: the flow guide structure is arranged on the middle shell side of the partition wall (4) and the nozzle (5) at the same time.
4. The exhaust gas turbocharger volute assembly of claim 1, wherein: the flow guide structure is arranged on the molded line (6) side of the volute and the middle shell side of the volute at the same time.
5. The exhaust gas turbocharger volute assembly of claim 1, wherein: the flow guide structure is arranged on the side of the volute molded line (6).
6. The exhaust gas turbocharger volute assembly of claim 1, wherein: the flow guide structure is arranged on the middle shell side of the volute.
7. The exhaust gas turbocharger volute assembly of claim 1, wherein: the flow guide structure is arranged on the partition wall (4) at a position which is 1 time to 2 times of the radius of the turbine from the axis.
8. The exhaust gas turbocharger volute assembly of claim 1, wherein: the axial dimension of the flow guide structure is 0.1 to 0.5 times the width of the nozzle (5).
9. The exhaust gas turbocharger volute assembly of claim 1, wherein: the circumferential machining angle range of the flow guide structure is 1 degree to 30 degrees.
10. The exhaust gas turbocharger volute assembly according to any one of claims 1 to 9, wherein: the flow guide structure is a protrusion or a groove.
11. The exhaust gas turbocharger volute assembly of claim 10 wherein: the groove penetrates through the vortex tongue (3) and is communicated with the high-pressure end and the low-pressure end at the vortex tongue (3).
12. The exhaust gas turbocharger volute assembly of claim 1, wherein: the processing surface of the flow guide structure is square or annular.
13. The exhaust gas turbocharger volute assembly of claim 1, wherein: the radial section of the flow guide structure is circular.
14. The exhaust gas turbocharger volute assembly of claim 1, wherein: the radial section of the flow guide structure is triangular.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920842460.7U CN210152736U (en) | 2019-06-05 | 2019-06-05 | Exhaust gas turbocharger volute assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920842460.7U CN210152736U (en) | 2019-06-05 | 2019-06-05 | Exhaust gas turbocharger volute assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210152736U true CN210152736U (en) | 2020-03-17 |
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ID=69761957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920842460.7U Active CN210152736U (en) | 2019-06-05 | 2019-06-05 | Exhaust gas turbocharger volute assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210152736U (en) |
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2019
- 2019-06-05 CN CN201920842460.7U patent/CN210152736U/en active Active
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