CN116044514B - Turbine and turbocharger - Google Patents
Turbine and turbocharger Download PDFInfo
- Publication number
- CN116044514B CN116044514B CN202310257985.5A CN202310257985A CN116044514B CN 116044514 B CN116044514 B CN 116044514B CN 202310257985 A CN202310257985 A CN 202310257985A CN 116044514 B CN116044514 B CN 116044514B
- Authority
- CN
- China
- Prior art keywords
- turbine
- blade
- leading edge
- region
- front edge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application discloses a turbine and a turbocharger, wherein the turbine comprises a hub and a plurality of blades, and the blades are circumferentially distributed around the axis of the hub; the front edge of the blade is in a curved shape, and the curvature of the front edge is in an increasing change trend and then in a decreasing change trend from the root of the blade to the top of the blade; the position where the curvature of the front edge is suddenly changed is an inflection point position, a vertical distance between the top of the front edge and the inflection point position is defined as h1, and a vertical distance between the root of the front edge and the inflection point position is defined as h2, wherein h1= (0.65-1) h2. Through the improvement to the blade structure of turbine, effectively improved the secondary flow phenomenon of turbine entrance department, can reduce the loss, improve the efficiency of turbo charger.
Description
Technical Field
The present application relates to the field of turbocharging technologies, and in particular, to a turbine and a turbocharger.
Background
Turbocharging is generally used in engine systems to increase the amount of intake air to improve the power performance of the engine. The turbocharger is arranged on an exhaust pipe of the engine, the turbine is driven to rotate by utilizing the inertial impulsive force of the exhaust gas discharged by the engine, and the turbine drives the impeller coaxial with the turbine to rotate, so that air is compressed to increase the air inflow.
In practical application, the phenomenon of secondary flow is easy to generate at the turbine inlet, the loss at the turbine inlet is large, and the efficiency of the turbocharger is not high.
Disclosure of Invention
The utility model provides an object provides a turbine and turbo charger, through the improvement to the blade structure of turbine, effectively improved the secondary flow phenomenon of turbine entrance, can reduce the loss, improve turbo charger's efficiency.
In order to solve the technical problems, the application provides a turbine, which comprises a hub and blades, wherein a plurality of blades are circumferentially distributed around the axis of the hub; the front edge of the blade is in a curved shape, and the curvature of the front edge is in an increasing change trend and then in a decreasing change trend from the root of the blade to the top of the blade; the position where the curvature of the front edge is suddenly changed is an inflection point position, a vertical distance between the top of the front edge and the inflection point position is defined as h1, and a vertical distance between the root of the front edge and the inflection point position is defined as h2, wherein h1= (0.65-1) h2.
The front edge of the blade of the turbine is set to be in a bent shape, and the curvature of the bent shape is designed to be firstly enlarged and then reduced from the root to the top of the blade, so that the inlet attack angle of the turbine inlet can be as uniform as possible, the position relationship of the position where the curvature of the front edge is suddenly changed on the height of the whole blade is combined, the phenomenon that secondary flow is generated due to the non-uniformity of the flow field in the height direction of the blade is effectively improved, the loss of the turbine inlet is reduced, and the working efficiency of the turbine is improved.
The turbine as described above, defines a lateral distance a1 between a top center of the leading edge and a bottom center of the leading edge, wherein |a1/(h1+h2) |+.0.25.
The turbine as described above, the maximum lateral distance between the bottom center of the leading edge and the inflection point position is defined as a2, |a1/(h1+h2) |a2/(h1+h2) |0.4.
The turbine as described above, the blade includes a leading edge region having a cross-sectional shape that conforms to the shape of the leading edge.
According to the turbine, the front edge area is an area between 20% -25% of the streamline length from the front edge to the blade along the streamline direction of the blade.
The turbine as described above, the blade further comprises a transition region and a main body region, the transition region being located between the leading edge region and the main body region, the cross-sectional shape of the transition region smoothly transitioning from the leading edge region to the main body region.
The cross-section of the main body region of the turbine as described above is rectilinear.
In the turbine described above, the curvature of the leading edge is gradually increased and then gradually decreased.
The invention also provides a turbocharger comprising a turbine and a turbine housing, the turbine being located within the turbine housing; the turbine is any one of the above turbines.
Since the above-described turbine has the above-described technical effects, a turbocharger including the turbine also has the same technical effects, and a discussion thereof will not be repeated here.
Drawings
FIG. 1 is a schematic view of a turbine in an embodiment provided herein;
FIG. 2 is a schematic view of the configuration of the leading edge of the individual blade of FIG. 1;
FIG. 3 is a schematic view of the meridian plane structure of the single blade of FIG. 1;
fig. 4 is a flow field distribution diagram of a turbine provided in an embodiment of the present application and an existing turbine at an inlet.
Reference numerals illustrate:
turbine 10, hub 11, blades 12, leading edge 12a, trailing edge 12b, leading edge region 121.
Detailed Description
In order to provide a better understanding of the present application, those skilled in the art will now make further details of the present application with reference to the drawings and detailed description.
Referring to fig. 1 and 2, fig. 1 is a schematic structural diagram of a turbine according to an embodiment provided in the present application; FIG. 2 is a schematic view of the configuration of the leading edge of the individual blade of FIG. 1.
In the present embodiment, the turbine 10 includes a hub 11 and blades 12, wherein the blades 12 are provided in plurality, and the plurality of blades 12 are arranged in an axial direction around an axis of the hub 11, each blade 12 has a leading edge 12a and a trailing edge 12b, the leading edge 12a refers to a front end face of the blade 12, the trailing edge 12b refers to a rear end face of the blade 12, the leading edge 12a is near an inlet of the turbine 10, and the trailing edge 12b is near an outlet of the turbine 10.
In this embodiment, the leading edge 12a of the blade 12 has a curved shape, and as shown in fig. 2, the curvature of the leading edge 12a increases in the direction from the root of the blade 12 to the tip of the blade 12, and then decreases in the direction.
The root of the blade 12 refers to the end of the blade 12 that is connected to the hub 11, and the tip of the blade 12 refers to the end of the blade 12 that is relatively far from 11.
The blade 12 has a certain thickness, it is understood that the blade 12 has two surfaces in the thickness direction, namely a pressure surface and a suction surface, and specifically, the front edge 12a of the blade 12 is two curved lines corresponding to the thickness direction, and the curved shape of the front edge 12a is also understood to be that the two lines of the front edge 12a in the thickness direction of the blade 12 are both curved lines, and the curvature of the curved lines is a changing trend that the curvature is increased first and then reduced.
After the arrangement, the inlet air attack angle of the inlet of the turbine 10 can be uniform as much as possible in the height direction of the blade 12 (namely, the direction from the root of the blade 12 to the top of the blade 12), because the inlet air attack angle of the turbine 10 is the difference value between the speed angle of the blade 12 and the blade angle, the speed angle of the inlet air flow in the height direction of the blade 12 is uneven, and the shape of the front edge 12a is set to be a bending structure, so that the blade angle is a variable value rather than a fixed value in the height direction of the blade 12, the inlet air attack angle is uniform, the secondary flow phenomenon generated by the uneven flow field at the inlet of the turbine 10 in the height direction of the blade 12 can be effectively improved, the loss of the inlet of the turbine 10 is reduced, and the working efficiency of the turbine 10 can be improved.
In a specific application, the position where the curvature of the leading edge 12a suddenly changes is an inflection point position S, as marked by a dashed line in fig. 2, that is, the curvature of the leading edge 12a tends to increase from the root of the blade 12 to the inflection point position S, and the curvature of the leading edge 12a tends to decrease from the inflection point position S to the top of the blade 12.
In actual installation, the curvature of the leading edge 12 tends to gradually increase from the root of the blade 12 to the inflection point position S, and the curvature of the leading edge 12 tends to gradually decrease from the inflection point position S to the top of the blade 12, so that the chance of occurrence of the secondary flow phenomenon can be reduced.
A vertical distance h1 between the top of the leading edge 12a and the inflection point position S is defined, and a vertical distance h2 between the root of the leading edge 12a and the inflection point position S is defined, h1= (0.65 to 1) h2.
In this way, the location of the abrupt change in curvature of the leading edge 12a over the entire height of the blade 12 can be determined, which is more advantageous in improving the secondary flow phenomenon due to flow field non-uniformities at the inlet of the turbine 10.
In practical applications, simulations or experiments may be performed according to the application environment and improvement requirements of the turbine 10 to determine the aforementioned relative relationship between h1 and h2, which is not limited to the above-described relationship.
Specifically, the dimension of the leading edge 12a in the thickness direction of the blade 12 tends to decrease from the root of the blade 12 toward the tip of the blade 12.
Further, a lateral distance a1 is defined between the top center of the leading edge 12a and the bottom center of the leading edge 12a, where |a1/(h1+h2) |+.0.25.
The lateral distance here refers to the distance in a direction perpendicular to the height of the blade 12.
The above arrangement makes it possible to determine the degree of bending of the leading edge 12a, ensure structural strength and rigidity of the blade 12, and ensure the service life and operational reliability of the turbine 10, while reducing the generation of secondary flow.
Further, defining the maximum lateral distance a2 between the bottom center of the leading edge 12a and the inflection point position S, as previously described, the blade 12 has a certain thickness, herein referred to as the maximum dimension of the bottom center of the leading edge 12a and the inflection point position S in the thickness direction of the blade 12.
Wherein |a1/(h1+h2) | is less than or equal to |a2/(h1+h2) | is less than or equal to 0.4.
With this arrangement, the degree of curvature of the leading edge 12a, and in particular the maximum curvature of the leading edge 12a, can be further determined, whereby the degree of curvature change of the leading edge 12a can be clarified in conjunction with the aforementioned arrangement of the parameters, thereby determining the specific shape of the leading edge 12a.
In practical applications, simulations or experiments may be performed according to the application environment and the improvement requirement of the turbine 10 to determine the aforementioned relative relationship between a1 and a2 and the height of the blade 12 (i.e., h1+h2), which is not limited to the above-mentioned relationship.
The leading edge 12a of the blade 12 in this embodiment may also be understood as an arcuate configuration.
In particular applications, the cross-sectional shape of the leading edge region of blade 12 also conforms to the shape of leading edge 12a. The leading edge region herein refers to a region of the blade 12 near the inlet of the turbine 10, and obviously includes the leading edge 12a.
It has been found through practical studies that the flow field non-uniformity at the inlet of the turbine 10 affects not only the front edge 12a but also a distance extending from the inlet to the outlet, so that the secondary flow phenomenon at the inlet of the turbine 10 can be further improved by configuring the area near the front edge 12a to be in conformity with the front edge 12a.
As shown in fig. 3, the radial shape of a single blade 12 of the turbine 10 is shown, the length of the blade 12 is dimensionless along the streamline direction, the position of the inlet of the turbine 10 is defined as 0, the position of the outlet of the turbine 10 is defined as 1, and according to simulation, the inlet of the turbine 10 generally affects between 20% and 25% of the streamline length, so that, in actual setting, the aforementioned leading edge area is defined as the area between 20% and 25% of the streamline length from the leading edge 12a to the blade 12. That is, the curved shape or camber of the leading edge 12a is required to remain along the streamline of the blade 12 to a position that is 20% -25% of the streamline length of the blade 12.
As shown in fig. 3, the positions of the root side and the tip side of the blade 12, which respectively occupy 0.2 to 0.25 of the total streamline length, are calculated, and after connection, the position a is obtained, and the leading edge region is located between the inlet of the turbine 10 and the position a.
In practical application, if it is determined that the inlet will affect other ranges of the length of the streamline, the flow line can be correspondingly set, and the flow line is not limited to 20% -25%.
In particular arrangements, the blade 12 also includes a transition region and a body region, the transition region being located between the leading edge region and the body region, the cross-sectional shape of the transition region transitioning smoothly from the leading edge region to the body region.
Generally, the cross section of the main body region of the blade 12 of the turbine 10 applied to the engine is in a straight line shape, that is, the cross section of the transition region near the front edge region is similar to the shape of the front edge 12a, the cross section near the main body region is in a straight line shape, and the transition region is arranged to make a smooth transition between the front edge region and the main body region, so that the influence on the flow field is reduced as much as possible, and the working efficiency of the turbine 10 is ensured.
Referring to fig. 4 together, fig. 4 is a schematic flow field distribution diagram of a turbine provided in an embodiment of the present application and a conventional turbine at an inlet.
The front edge of the blade of the existing turbine is of a linear structure, simulation analysis is carried out on the existing turbine and the turbine of the embodiment of the application, as shown in fig. 4, a left graph in fig. 4 is flow field distribution of a turbine inlet of the embodiment, a right graph is flow field distribution of the existing turbine inlet, and different gray scales in the graph indicate static entropy distribution. As can be seen from the figure, with the turbine structure of this embodiment, the entropy increase at the turbine inlet is reduced, the vortex trend at the inlet is also significantly reduced, and the loss is reduced.
The invention also provides a turbocharger which can be applied to an engine to increase the air inflow and improve the power performance of the engine, and comprises a turbine shell and a turbine arranged in the turbine shell, wherein the turbine can adopt the turbine described in the embodiment. Other constructions of turbochargers may be implemented based on the prior art and are not described in detail herein.
Since the above-described turbine has the above-described technical effects, a turbocharger including the turbine also has the same technical effects, and a discussion thereof will not be repeated here.
The above description is provided for a turbine and turbocharger. Specific examples are set forth herein to illustrate the principles and embodiments of the present application, and the description of the examples above is only intended to assist in understanding the methods of the present application and their core ideas. It should be noted that it would be obvious to those skilled in the art that various improvements and modifications can be made to the present application without departing from the principles of the present application, and such improvements and modifications fall within the scope of the claims of the present application.
Claims (7)
1. A turbine including a hub and a plurality of blades arranged circumferentially about an axis of the hub; the method is characterized in that the front edge of the blade is in a bent shape, and the curvature of the front edge is in an increasing change trend and then in a decreasing change trend from the root of the blade to the top of the blade;
the position where the curvature of the front edge is suddenly changed is an inflection point position, a vertical distance between the top of the front edge and the inflection point position is defined as h1, and a vertical distance between the root of the front edge and the inflection point position is defined as h2, wherein h1= (0.65-1) h2;
defining a lateral distance between a top center of the leading edge and a bottom center of the leading edge as a1, wherein |a1/(h1+h2) |is less than or equal to 0.25;
defining the maximum transverse distance between the bottom center of the front edge and the inflection point position as a2, |a1/(h1+h2) |a2/(h1+h2) |be less than or equal to 0.4;
the root of the blade refers to one end of the blade connected with the hub, and the top of the blade refers to one end of the blade relatively far away from the hub.
2. The turbine of claim 1, wherein the blade includes a leading edge region having a cross-sectional shape that conforms to a shape of the leading edge; the leading edge region refers to a section of the blade near the turbine inlet, the leading edge region including the leading edge.
3. The turbine of claim 2, wherein the leading edge region is a region between 20% and 25% of the streamline length of the blade from the leading edge along the streamline of the blade.
4. The turbine of claim 3, wherein the blade further comprises a transition region and a body region, the transition region being located between the leading edge region and the body region, the cross-sectional shape of the transition region transitioning smoothly from the leading edge region to the body region.
5. The turbine of claim 4, wherein the cross-section of the body region is rectilinear.
6. The turbine of claim 1, wherein the curvature of the leading edge is tapered and then tapered.
7. A turbocharger comprising a turbine and a turbine housing, the turbine being located within the turbine housing; the turbine according to any one of claims 1 to 6.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310257985.5A CN116044514B (en) | 2023-03-17 | 2023-03-17 | Turbine and turbocharger |
| PCT/CN2023/120957 WO2024192995A1 (en) | 2023-03-17 | 2023-09-25 | Turbine and turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310257985.5A CN116044514B (en) | 2023-03-17 | 2023-03-17 | Turbine and turbocharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116044514A CN116044514A (en) | 2023-05-02 |
| CN116044514B true CN116044514B (en) | 2023-07-18 |
Family
ID=86120312
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310257985.5A Active CN116044514B (en) | 2023-03-17 | 2023-03-17 | Turbine and turbocharger |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN116044514B (en) |
| WO (1) | WO2024192995A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116044514B (en) * | 2023-03-17 | 2023-07-18 | 潍柴动力股份有限公司 | Turbine and turbocharger |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4691002B2 (en) * | 2006-11-20 | 2011-06-01 | 三菱重工業株式会社 | Mixed flow turbine or radial turbine |
| JP2011226403A (en) * | 2010-04-21 | 2011-11-10 | Ihi Corp | Impeller of radial turbine |
| US8672637B2 (en) * | 2010-08-17 | 2014-03-18 | Hamilton Sundstrand Corporation | Air turbine starter turbine blade airfoil |
| US9988909B2 (en) * | 2011-04-25 | 2018-06-05 | Honeywell International, Inc. | Hub features for turbocharger wheel |
| EP2940271B2 (en) * | 2012-12-27 | 2023-06-14 | Mitsubishi Heavy Industries, Ltd. | Radial turbine rotor blade |
| US9200518B2 (en) * | 2013-10-24 | 2015-12-01 | Honeywell International Inc. | Axial turbine wheel with curved leading edge |
| DE102016102732A1 (en) * | 2016-02-17 | 2017-08-17 | Volkswagen Aktiengesellschaft | Mixed-flow turbine wheel of an exhaust gas turbocharger and exhaust gas turbine with such a turbine wheel |
| JP6583946B2 (en) * | 2016-03-02 | 2019-10-02 | 三菱重工エンジン＆ターボチャージャ株式会社 | Turbine wheel, radial turbine, and turbocharger |
| WO2017168766A1 (en) * | 2016-03-31 | 2017-10-05 | 三菱重工業株式会社 | Rotary machine blade, supercharger, and method for forming flow field of same |
| CN111611658B (en) * | 2020-05-22 | 2022-05-17 | 西北工业大学 | A kind of air turbine starter turbine blade and design method thereof |
| AU2020478845B2 (en) * | 2020-11-25 | 2023-08-31 | Mitsubishi Electric Corporation | Turbofan and air-conditioning apparatus |
| CN116044514B (en) * | 2023-03-17 | 2023-07-18 | 潍柴动力股份有限公司 | Turbine and turbocharger |
-
2023
- 2023-03-17 CN CN202310257985.5A patent/CN116044514B/en active Active
- 2023-09-25 WO PCT/CN2023/120957 patent/WO2024192995A1/en unknown
Also Published As
| Publication number | Publication date |
|---|---|
| WO2024192995A1 (en) | 2024-09-26 |
| CN116044514A (en) | 2023-05-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5179161B2 (en) | Gas turbine engine including multiple curved stator vanes and method of assembling the same | |
| CN102454633B (en) | Axial compressor | |
| CN107061321B (en) | Using the compressor of the variable asymmetric vaned diffuser of established angle and consistency coupling | |
| CN113153446B (en) | Turbine guider and centripetal turbine with high expansion ratio | |
| CN110939601B (en) | A turbocharger compressor impeller with high performance blades | |
| CN110657126B (en) | Non-axisymmetric hub structure for controlling flow in centrifugal impeller, centrifugal impeller | |
| CN116044514B (en) | Turbine and turbocharger | |
| CN110608196B (en) | Wedge-shaped diffuser with half-blade high and small blades | |
| CN210949272U (en) | Small blade independently designed wedge-shaped integral diffuser | |
| CN112576313A (en) | Turbocharger turbine wheel for improving natural vibration frequency of turbine blade and design method | |
| CN105257590B (en) | Half Tandem Blades To An Aeroengine and its design method | |
| CN102182519B (en) | Self-jet flow secondary flow control structure of turbine stator vane | |
| CN112283161B (en) | Axial compressor and compressor rotor blade thereof | |
| CN114909325A (en) | Low-noise axial flow fan blade and axial flow fan | |
| CN114151195A (en) | A Novel Exhaust Diffuser Structure That Can Improve Aerodynamic Performance | |
| CN211550074U (en) | Turbocharger compressor impeller with high-performance blades | |
| CN113090580A (en) | Centrifugal impeller blade with S-shaped front edge and modeling method thereof | |
| CN112943686A (en) | Centrifugal compressor impeller and design method thereof | |
| CN215860865U (en) | Blade, impeller and fan | |
| CN216044606U (en) | Compressor impeller for fuel cell air compressor | |
| CN112283160B (en) | Compressor rotor blade and design method thereof | |
| RU191663U1 (en) | Centrifugal impeller of a gas turbine engine | |
| CN203067037U (en) | Turbine of turbocharger | |
| CN216741633U (en) | 3.6m 2-grade water-cooled low-pressure final-stage movable blade | |
| CN203081511U (en) | Turbocharger turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |