CN116502364A - Design method of special radial turbine applied to turbocharger - Google Patents
Design method of special radial turbine applied to turbocharger Download PDFInfo
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Abstract
The invention relates to the technical field of radial turbine design, in particular to a design method of a special radial turbine applied to a turbocharger, which comprises the following steps: generating a non-fiberized swept-back leading edge blade by a three-dimensional inverse design method; dividing the meridian plane of the non-fibrosis swept-back type front edge blade into three parts by using two lines, wherein the first line is positioned at a position which is close to the front edge by 10% -20%, and the second line is positioned at the middle position of the top cover and is vertically distributed; carrying out partial fibrosis design on the divided non-fibrosis swept-back front blade; the result is a partially fibrillated swept leading edge blade. The turbine generated by the invention is designed for part of fiber blades, so that the blades can be ensured to be completely fiberized at the maximum stress of the turbine, thereby solving the problem of maximum stress; the front edge of the turbine generated by the invention is of a sweepback design, so that the pneumatic efficiency of the blade at high temperature and high pressure can be effectively improved, and the energy obtained from the internal combustion gas and waste gas can be effectively improved.
Description
Technical Field
The invention relates to the technical field of radial turbine design, in particular to a special radial turbine design method applied to a turbocharger.
Background
Turbochargers have been widely used in the automotive, marine, and other industries. The turbine in the turbocharger consists of a turbine wheel and a turbine, and the basic principle is that: the turbine converts thermal energy contained in high-temperature and high-pressure exhaust gas discharged from an engine (internal combustion engine) into kinetic energy, thereby driving a compressor on the same shaft to work, and then the compressor compresses air to improve the air inlet pressure of the internal combustion engine, thereby improving the combustion efficiency of the internal combustion engine. Turbines can be classified into axial flow, radial and mixed flow according to the direction of the flow path, wherein radial turbines are most suitable for use in small automotive turbochargers. As the name implies, the radial turbine has a radial inlet direction and an axial outlet direction.
The first difficulty with radial turbine design is the stress problem. Since radial turbines operate under high temperature and pressure conditions, this places high demands on the material strength and maximum stress level of the turbine. To address the stress problem, conventional turbine designs have always employed a method called radial fiber vane. Radial fiber blades refer to turbine blades whose angular distribution is always equal in a direction perpendicular to the axis of rotation. In other words, the wrap angle contours of the radial fiber blades on the meridian plane are always vertically distributed, and the radial fiber blades can effectively minimize the blade bending stress and control the blade maximum stress assuming that the rotation axis is in the horizontal direction.
A second difficulty with radial turbine design is that the turbine inlet air (engine exhaust) is pulsed at a high frequency, with temperature and pressure rapidly changing over time, which is necessary to maximize the aerodynamic efficiency of the turbine at high temperature and pressure in order to maximize the utilization of the thermal energy (internal energy) in the engine exhaust. This is because the thermal energy (internal energy) in the exhaust gas of an internal combustion engine is proportional to its temperature and pressure, and the power that the turbine can extract and supply to the compressor is equal to the product of the thermal energy of the exhaust gas of the internal combustion engine and the turbine. Recent scientific studies have shown that in order to maximize the efficiency of a turbine under high temperature and high pressure intake conditions, the most effective approach is to employ a turbine blade design called a swept-back leading edge blade angle. As the name suggests, the swept-back leading edge blade angle means that the leading edge blade angle of the turbine is offset in the direction opposite to the rotation direction of the blades, and the design can effectively improve the efficiency of the turbine under the high-temperature and high-pressure air inlet condition, thereby improving the efficiency of the whole turbocharger. However, the design of the sweepback leading edge blade angle cannot be generated by the traditional full radial fiber blade, and the sweepback leading edge blade angle which does not meet the radial fiber condition has a very large stress concentration problem, so that the turbine impeller has the problem of rapid failure due to fatigue stress and has no practical application value.
Therefore, conventional radial turbine designs fail to meet both the conditions of a fully radial fiber blade to meet stress requirements and the conditions of a swept-back leading edge blade angle turbine design to maximize turbine efficiency at high temperature and high pressure inlet air.
Disclosure of Invention
Aiming at the problem that the traditional radial turbine design cannot simultaneously meet the requirement of the stress on the complete radial fiber blades and the design of the sweepback leading edge blade angle turbine for maximizing the turbine efficiency in high-temperature and high-pressure air intake, the design method of the special radial turbine applied to the turbocharger is provided, the maximum stress requirement can be met, and the turbine aerodynamic efficiency under the high-temperature and high-pressure condition can be effectively improved.
In order to achieve the above object, the present invention is realized by the following technical scheme:
a design method of a special radial turbine applied to a turbocharger specifically comprises the following steps:
generating a non-fiberized swept-back leading edge blade by a three-dimensional inverse design method;
dividing the meridian plane of the non-fibrous sweepback type front edge blade into three parts by using two lines, wherein the first line is positioned at a position which is close to the front edge and is 10% -20%, and the second line is positioned at the middle position of the top cover and is vertically distributed;
carrying out partial fibrosis design on the divided non-fibrosis swept-back front blade;
the result is a partially fibrillated swept leading edge blade.
As a preferred embodiment of the present invention, the method for producing a non-fibrillated swept-back leading edge blade by the three-dimensional inverse design method specifically includes:
inputting the radial plane of the blade, the thickness distribution of the blade, the load distribution of the blade and the working condition information of the blade to obtain an initial three-dimensional blade;
designing the load distribution of the blade to ensure that the load of the front edge of the blade is positive, and ensuring that the wrap angle of the front edge blade of the initial three-dimensional blade is sweepback;
entering iterative loop calculation, and calculating a speed field of the blade through a blade meridian plane, blade thickness distribution and blade load distribution; calculating a blade shape from a speed field of the blade;
comparing the blade shapes of the front iteration and the rear iteration, judging whether convergence conditions are met, and if so, outputting the blade shape as a non-fibrous sweepback front blade; if the calculated speed field is not satisfied, the speed field is recalculated, and the iterative calculation of the next round is carried out.
As a preferable scheme of the invention, the blade meridian plane is a projection of the xyz coordinate of the three-dimensional blade on the rz plane, namely the meridian plane; the thickness distribution of the blade is that of the blade on a meridian plane; the blade load distribution is the load distribution of the blade on a meridian plane; the blade working condition information comprises rotating speed, flow and expansion ratio.
As a preferred scheme of the present invention, the method for calculating the velocity field specifically includes: and decomposing the velocity field into a circumferential average velocity and a periodic velocity for solving, wherein the calculation formula of the circumferential average velocity is as follows:
wherein,,、/>radial and axial coordinates respectively; />For circumferential average radial speed +.>Is the circumferentially average axial velocity; />For density (I)>As a circumferentially averaged flow function;
for blocking factor, ++>Wherein->For the tangential thickness of the blade->The number of the blades;
the calculation formula of the cycle speed is as follows:
wherein,,radial, tangential and axial coordinates, respectively, < >>For the period speed +.>As a periodic potential function>For a sawtooth function->Is a periodic average ring size distribution.
As a preferred embodiment of the present invention, the meridian plane of the non-fibrous swept-back leading edge blade is divided into three parts, the first part is between the leading edge of the blade and a first line, the second part is between the first line and a second line, and the third part is between the second line and the trailing edge of the blade.
As a preferred scheme of the invention, the method for carrying out partial fibrosis design on the divided non-fibrosis swept-back front edge blade specifically comprises the following steps:
keeping the blade wrap angle of the first portion unchanged;
recalculating the blade wrap angle of the third portion to fibrillate the wrap angle, specifically: the blade wrap angle of the cap portion of the third portion remains unchanged, and the blade wrap angles of the remaining portions of the third portion are recalculated based on the blade wrap angles of the cap portion, the blade wrap angles of the remaining portions ensuring that the blade wrap angles are equal over the same axial distance.
As a preferred embodiment of the present invention, the method for partial fibrosis further comprises: and recalculating the blade wrap angle of the second part by a difference value and extrapolation method to ensure that the newly generated blade wrap angle smoothly connects the blade shape distribution of the first part and the third part.
A design apparatus for a particular radial turbine for use in a turbocharger, said apparatus comprising: the device comprises a sweepback front edge module, a dividing module, a partial fiberizing module and an output module;
the sweepback type front edge module is used for generating a non-fibrous sweepback type front edge blade through a three-dimensional reverse design method and comprises an information input unit, an iterative calculation unit and a convergence judgment unit;
the information input unit is used for inputting information of a radial plane of the blade, thickness distribution of the blade, load distribution of the blade and working condition of the blade, and designing the load distribution of the blade to meet the condition that the load of the front edge of the blade is positive; the iterative computation unit is used for iterative loop computation, the speed field of the blade is computed through the meridian plane of the blade, the thickness distribution of the blade and the load distribution of the blade, and the shape of the blade is computed through the speed field of the blade; the convergence judging unit is used for comparing the blade shapes of the front iteration and the rear iteration, judging whether convergence conditions are met, if yes, outputting the blade shape as a non-fibrous sweepback front blade, and if not, recalculating a speed field and carrying out iterative calculation of the next round;
the dividing module is used for dividing the meridian plane of the non-fibrous sweepback type front edge blade into three parts by using two lines, wherein the first part is between the front edge of the blade and the first line, the second part is between the first line and the second line, and the third part is between the second line and the tail edge of the blade;
the partial fibrosis module is used for recalculating the blade wrap angle of the third part to enable the wrap angle to be fibrotic, recalculating the blade wrap angle of the second part through a difference value and extrapolation method, and ensuring that the newly generated blade wrap angle is smoothly connected with the blade shape distribution of the first part and the third part;
the output module is used for outputting partial fiberized sweepback leading edge blade.
A design apparatus for a particular radial turbine for use in a turbocharger, comprising a processor and a memory having stored therein at least one instruction, at least one program, code set or instruction set, the at least one instruction, at least one program, code set or instruction set being loaded and executed by the processor to implement the steps of a design method for a particular radial turbine for use in a turbocharger as described above.
A storage medium having stored thereon a computer program which, when executed by a processor, implements the steps of a design method for a specific radial turbine for use in a turbocharger as described above.
The beneficial effects of the invention are as follows: the turbine generated by the invention is designed for part of fiber blades, and the maximum stress of the blades can be controlled within a reasonable range, because the maximum stress of the turbine usually occurs at the position close to the tail edge at the outlet, and the turbine design generated by the invention can ensure that the blades are completely fibrillated at the part, thereby solving the problem of the maximum stress; the front edge of the turbine generated by the invention is of a sweepback design, so that the pneumatic efficiency of the blade at high temperature and high pressure can be effectively improved, and the energy obtained from the internal combustion gas and waste gas can be effectively improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the description of the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art. Wherein:
FIG. 1 is a flow chart of the method of the present invention;
FIG. 2 is a flow chart of a non-fibrillated swept leading edge blade design in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram of a partial fiberization design in accordance with an embodiment of the invention;
FIG. 4 is a flow chart of a partially fiberized swept-back leading edge blade design according to an embodiment of the invention;
FIG. 5 is a block diagram of the apparatus of the present invention;
fig. 6 is a structural diagram of the apparatus of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments, which are obtained by a person skilled in the art based on the described embodiments of the invention, fall within the scope of protection of the invention.
Referring to fig. 1 and 3, an embodiment of the present invention provides a method for designing a special radial turbine applied to a turbocharger, which specifically includes:
generating a non-fiberized swept-back leading edge blade by a three-dimensional inverse design method;
dividing the meridian plane of the non-fibrosis swept-back type front edge blade into three parts by using two lines, wherein the first line is positioned at a position which is close to the front edge by 10% -20%, and the second line is positioned at the middle position of the top cover and is vertically distributed;
carrying out partial fibrosis design on the divided non-fibrosis swept-back front blade;
the result is a partially fibrillated swept leading edge blade.
In one embodiment, as shown in FIG. 2, a method of producing a non-fibrillated swept-back leading edge blade by a three-dimensional inverse design method specifically includes:
inputting blade meridian plane, blade thickness distribution, blade load distribution, blade working condition information and the like, wherein the blade meridian plane is the projection of the xyz coordinate of the three-dimensional blade on the rz plane, and the rz plane is the meridian plane; the thickness distribution of the blade is the thickness distribution of the blade on a meridian plane; the load distribution of the blade is the load distribution of the blade on a meridian plane; the blade working condition information comprises rotating speed, flow, expansion ratio and the like, so as to obtain an initial three-dimensional blade;
the traditional turbine blade load is always negative, and in order to ensure that the wrap angle of the front edge blade of the initial three-dimensional blade is swept back, the blade load distribution is designed to meet the condition that the load of the front edge of the blade is positive;
entering iterative loop calculation, and calculating a speed field of the blade through a blade meridian plane, blade thickness distribution and blade load distribution; calculating a blade shape from a speed field of the blade;
comparing the blade shapes of the front iteration and the rear iteration, judging whether convergence conditions are met, and if so, outputting the blade shape as a non-fibrous sweepback front blade; if the calculated speed field is not satisfied, the speed field is recalculated, and the iterative calculation of the next round is carried out.
In one embodiment, the method for calculating the velocity field specifically includes: and decomposing the velocity field into a circumferential average velocity and a periodic velocity for solving, wherein the calculation formula of the circumferential average velocity is as follows:
wherein,,、/>radial and axial coordinates respectively; />For circumferential average radial speed +.>Is the circumferentially average axial velocity; />For density (I)>As a circumferentially averaged flow function;
for blocking factor, ++>Wherein->For the tangential thickness of the blade->The number of the blades;
the calculation formula of the cycle speed is as follows:
wherein,,radial, tangential and axial coordinates, respectively, < >>For the period speed +.>As a periodic potential function>For a sawtooth function->Is a periodic average ring size distribution.
The turbine blade produced from this method is three-dimensional (non-radial fiber blade) but has its leading edge blade angle swept back, so this design has better aerodynamic efficiency under high temperature and pressure conditions, but because of the non-radial fiber blade, there is an overstress problem, and to solve the stress problem, the meridian plane of the blade can be divided into three sections.
In one embodiment, as shown in FIG. 3, the meridian plane of the non-fibrillated swept-forward edge blade is divided into three sections, the first section being between the blade leading edge and a first line, the second section being between the first line and a second line, and the third section being between the second line and the blade trailing edge.
In one embodiment, as shown in fig. 4, the method for partially fiberizing a divided non-fiberized swept-back leading edge blade specifically includes:
the wrap angle of the blade of the first part is kept unchanged, so that the advantages of the design of the sweepback front edge can be kept;
recalculating the blade wrap angle of the third portion to fibrillate the wrap angle, specifically: the blade wrap angle of the cap portion of the third portion remains unchanged, and the blade wrap angle of the remaining portion of the third portion is recalculated based on the blade wrap angle of the cap portion, the blade wrap angles of the remaining portion ensuring that the blade wrap angles are equal (equivalent to radial fiber conditions) at the same axial distance.
In one embodiment, the method of partial fibrosis further comprises: and recalculating the blade wrap angle of the second part by a difference value and extrapolation method to ensure that the newly generated blade wrap angle smoothly connects the blade shape distribution of the first part and the third part.
As shown in fig. 5, another embodiment of the present invention provides a design device for a special radial turbine applied to a turbocharger, specifically including: the device comprises a sweepback front edge module, a dividing module, a partial fiberizing module and an output module;
the sweepback type front edge module is used for generating a non-fibrous sweepback type front edge blade by a three-dimensional reverse design method and comprises an information input unit, an iterative calculation unit and a convergence judgment unit; the information input unit is used for inputting information of a blade meridian plane, blade thickness distribution, blade load distribution and blade working conditions, and designing the blade load distribution to meet the condition that the load of the front edge of the blade is positive; the iterative calculation unit is used for iterative loop calculation, calculating the speed field of the blade through the meridian plane of the blade, the thickness distribution of the blade and the load distribution of the blade, and calculating the shape of the blade through the speed field of the blade; the convergence judging unit is used for comparing the blade shapes of the front iteration and the back iteration, judging whether convergence conditions are met, if yes, outputting the blade shape as a non-fibrous sweepback front blade, and if not, recalculating a speed field and carrying out iterative calculation of the next round;
the dividing module is used for dividing the meridian plane of the non-fibrosis swept-back type front edge blade into three parts by using two lines, wherein the first part is between the front edge of the blade and the first line, the second part is between the first line and the second line, and the third part is between the second line and the tail edge of the blade;
the partial fibrosis module is used for recalculating the blade wrap angle of the third part to enable the wrap angle of the third part to be fibrotic, recalculating the blade wrap angle of the second part through a difference value and extrapolation method, and ensuring that the newly generated blade wrap angle is smoothly connected with the blade shape distribution of the first part and the third part;
the output module is used for outputting the partially fiberized swept-back leading edge blade.
As shown in FIG. 6, a further embodiment of the present invention provides a special radial turbine design apparatus for use in a turbocharger, which may be a server, including a processor, memory, network interface, and database connected by a system bus. The processor is used for providing computing and control capabilities; the memory stores at least one instruction, at least one program, code set, or instruction set that is loaded into and executed by the processor to implement the steps of a design method for a particular radial turbine for use in a turbocharger as described above. The memory comprises a nonvolatile storage medium, an internal memory, the nonvolatile storage medium stores an operating system, a computer program and a database, the internal memory provides an environment for the operating system and the computer program in the nonvolatile storage medium to run, and the database is used for storing a configuration template and can also be used for storing target webpage data. The network interface is used for communicating with an external terminal through a network connection.
It will be appreciated by those skilled in the art that the structure shown in fig. 6 is merely a block diagram of a portion of the structure associated with the present application and does not constitute a limitation of the apparatus to which the present application is applied, and that a particular apparatus may include more or less components than those shown in the drawings, or may combine certain components, or have a different arrangement of components.
In one embodiment, a storage medium is also provided, which may be read-only memory, a magnetic or optical disk, or the like. On which a computer program is stored which, when being executed by a processor, implements the steps of a method of designing a particular radial turbine for use in a turbocharger as described above.
In the above embodiments, it may be implemented in whole or in part by software, hardware, firmware, or any other combination. When implemented in software, may be embodied in whole or in part in the form of a computer program product comprising one or more computer instructions. When the computer program instructions are loaded and executed on a computer, the processes or functions in accordance with the present application are produced in whole or in part.
In summary, the turbine produced by the present invention is a partial fiber blade design, the maximum stress of which can be controlled within a reasonable range, because the maximum stress of the turbine usually occurs near the trailing edge at the outlet, while the turbine design produced by the present invention ensures that the blade is fully fibrillated at this portion, thereby solving the maximum stress problem; the front edge of the turbine generated by the invention is of a sweepback design, so that the pneumatic efficiency of the blade at high temperature and high pressure can be effectively improved, and the energy obtained from the internal combustion gas and waste gas can be effectively improved.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily think of various changes or substitutions within the technical scope of the present application, and these should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A method of designing a particular radial turbine for use in a turbocharger, the method comprising: generating a non-fiberized swept-back leading edge blade by a three-dimensional inverse design method;
dividing the meridian plane of the non-fibrous sweepback type front edge blade into three parts by using two lines, wherein the first line is positioned at a position which is close to the front edge and is 10% -20%, and the second line is positioned at the middle position of the top cover and is vertically distributed;
carrying out partial fibrosis design on the divided non-fibrosis swept-back front blade;
the result is a partially fibrillated swept leading edge blade.
2. A method of designing a special radial turbine for use in a turbocharger according to claim 1, wherein said method of three-dimensional inverse design produces a non-fibrillated swept-back leading edge blade comprising:
inputting the radial plane of the blade, the thickness distribution of the blade, the load distribution of the blade and the working condition information of the blade to obtain an initial three-dimensional blade;
designing the load distribution of the blade to ensure that the load of the front edge of the blade is positive, and ensuring that the wrap angle of the front edge blade of the initial three-dimensional blade is sweepback;
entering iterative loop calculation, and calculating a speed field of the blade through a blade meridian plane, blade thickness distribution and blade load distribution; calculating a blade shape from a speed field of the blade;
comparing the blade shapes of the front iteration and the rear iteration, judging whether convergence conditions are met, and if so, outputting the blade shape as a non-fibrous sweepback front blade; if the calculated speed field is not satisfied, the speed field is recalculated, and the iterative calculation of the next round is carried out.
3. A method of designing a particular radial turbine for use in a turbocharger as claimed in claim 2, wherein said vane meridian plane is a three-dimensional vanexyzCoordinates atrzProjection onto a plane, saidrzThe plane is meridian plane; the thickness distribution of the blade is that of the blade on a meridian plane; the blade load distribution is the load distribution of the blade on a meridian plane; the blade working condition information comprises rotating speed, flow and expansion ratio.
4. A method for designing a special radial turbine for use in a turbocharger according to claim 2, wherein the method for calculating the velocity field is specifically: and decomposing the velocity field into a circumferential average velocity and a periodic velocity for solving, wherein the calculation formula of the circumferential average velocity is as follows: wherein (1)>、/>Radial and axial coordinates respectively; />For circumferential average radial speed +.>Is the circumferentially average axial velocity; />For density (I)>As a circumferentially averaged flow function;
for blocking factor, ++>Wherein->For the tangential thickness of the blade->The number of the blades;
the calculation formula of the cycle speed is as follows:wherein,,radial, tangential and axial coordinates, respectively, < >>For the period speed +.>As a periodic potential function>For a sawtooth function->Is a periodic average ring size distribution.
5. A method of designing a particular radial turbine for use in a turbocharger according to claim 1, wherein the meridian plane of the non-fibrillated swept-back leading edge vane is divided into three sections, a first section being between the vane leading edge and a first line, a second section being between the first line and a second line, and a third section being between the second line and the vane trailing edge.
6. A method of designing a special radial turbine for use in a turbocharger according to claim 5, wherein said method of partially fiberizing said divided non-fiberized swept leading edge blades specifically comprises:
keeping the blade wrap angle of the first portion unchanged;
recalculating the blade wrap angle of the third portion to fibrillate the wrap angle, specifically: the blade wrap angle of the cap portion of the third portion remains unchanged, and the blade wrap angles of the remaining portions of the third portion are recalculated based on the blade wrap angles of the cap portion, the blade wrap angles of the remaining portions ensuring that the blade wrap angles are equal over the same axial distance.
7. A method of designing a particular radial turbine for use in a turbocharger as claimed in claim 6, wherein said method of partially fiberizing further comprises: and recalculating the blade wrap angle of the second part by a difference value and extrapolation method to ensure that the newly generated blade wrap angle smoothly connects the blade shape distribution of the first part and the third part.
8. A design apparatus for a particular radial turbine for use in a turbocharger, said apparatus comprising: the device comprises a sweepback front edge module, a dividing module, a partial fiberizing module and an output module;
the sweepback type front edge module is used for generating a non-fibrous sweepback type front edge blade through a three-dimensional reverse design method and comprises an information input unit, an iterative calculation unit and a convergence judgment unit;
the information input unit is used for inputting information of a radial plane of the blade, thickness distribution of the blade, load distribution of the blade and working condition of the blade, and designing the load distribution of the blade to meet the condition that the load of the front edge of the blade is positive; the iterative computation unit is used for iterative loop computation, the speed field of the blade is computed through the meridian plane of the blade, the thickness distribution of the blade and the load distribution of the blade, and the shape of the blade is computed through the speed field of the blade; the convergence judging unit is used for comparing the blade shapes of the front iteration and the rear iteration, judging whether convergence conditions are met, if yes, outputting the blade shape as a non-fibrous sweepback front blade, and if not, recalculating a speed field and carrying out iterative calculation of the next round;
the dividing module is used for dividing the meridian plane of the non-fibrous sweepback type front edge blade into three parts by using two lines, wherein the first part is between the front edge of the blade and the first line, the second part is between the first line and the second line, and the third part is between the second line and the tail edge of the blade;
the partial fibrosis module is used for recalculating the blade wrap angle of the third part to enable the wrap angle to be fibrotic, recalculating the blade wrap angle of the second part through a difference value and extrapolation method, and ensuring that the newly generated blade wrap angle is smoothly connected with the blade shape distribution of the first part and the third part;
the output module is used for outputting partial fiberized sweepback leading edge blade.
9. A design apparatus for a specific radial turbine applied to a turbocharger, comprising a processor and a memory, wherein at least one instruction, at least one program, code set, or instruction set is stored in the memory, and wherein the at least one instruction, the at least one program, the code set, or the instruction set is loaded and executed by the processor to implement the steps of a design method for a specific radial turbine applied to a turbocharger as claimed in any one of claims 1 to 7.
10. A storage medium having stored thereon a computer program, which when executed by a processor, implements the steps of a method of designing a specific radial turbine for use in a turbocharger according to any one of claims 1 to 7.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060067829A1 (en) * | 2004-09-24 | 2006-03-30 | Vrbas Gary D | Backswept titanium turbocharger compressor wheel |
| US20150113982A1 (en) * | 2013-10-24 | 2015-04-30 | Honeywell International Inc. | Axial turbine wheel with curved leading edge |
| CN106640210A (en) * | 2016-09-14 | 2017-05-10 | 西安交通大学苏州研究院 | Method for designing three-dimensional molded lines of radial-axial-flow expansion turbine impeller blade |
| US20190316596A1 (en) * | 2016-12-22 | 2019-10-17 | Ihc Holland Ie B.V. | Impeller with rotor blades for centrifugal pump |
| CN111486116A (en) * | 2020-04-15 | 2020-08-04 | 浙江上风高科专风实业有限公司 | Method and system for designing three-dimensional flow impeller of low-specific-speed centrifugal blower |
| CN112069630A (en) * | 2020-11-11 | 2020-12-11 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor, blade, two-dimensional blade profile design method of blade and computer equipment |
| WO2021129261A1 (en) * | 2019-12-26 | 2021-07-01 | 浙江理工大学 | Blade load distribution-based method for designing centrifugal-pump compound impeller |
| CN114519238A (en) * | 2022-01-18 | 2022-05-20 | 中国航发湖南动力机械研究所 | Full three-dimensional modeling method and device for high-performance impeller mechanical blade and electronic equipment |
| US20220266981A1 (en) * | 2019-11-13 | 2022-08-25 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method and Device for Expanding the Flight Envelope of a Commercial Aircraft |
| CN115994423A (en) * | 2022-12-15 | 2023-04-21 | 西安交通大学 | Cross-tone leaf pattern design method based on Bezier curve and related device |
-
2023
- 2023-04-28 CN CN202310481674.7A patent/CN116502364B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060067829A1 (en) * | 2004-09-24 | 2006-03-30 | Vrbas Gary D | Backswept titanium turbocharger compressor wheel |
| US20150113982A1 (en) * | 2013-10-24 | 2015-04-30 | Honeywell International Inc. | Axial turbine wheel with curved leading edge |
| CN106640210A (en) * | 2016-09-14 | 2017-05-10 | 西安交通大学苏州研究院 | Method for designing three-dimensional molded lines of radial-axial-flow expansion turbine impeller blade |
| US20190316596A1 (en) * | 2016-12-22 | 2019-10-17 | Ihc Holland Ie B.V. | Impeller with rotor blades for centrifugal pump |
| US20220266981A1 (en) * | 2019-11-13 | 2022-08-25 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method and Device for Expanding the Flight Envelope of a Commercial Aircraft |
| WO2021129261A1 (en) * | 2019-12-26 | 2021-07-01 | 浙江理工大学 | Blade load distribution-based method for designing centrifugal-pump compound impeller |
| CN111486116A (en) * | 2020-04-15 | 2020-08-04 | 浙江上风高科专风实业有限公司 | Method and system for designing three-dimensional flow impeller of low-specific-speed centrifugal blower |
| CN112069630A (en) * | 2020-11-11 | 2020-12-11 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor, blade, two-dimensional blade profile design method of blade and computer equipment |
| CN114519238A (en) * | 2022-01-18 | 2022-05-20 | 中国航发湖南动力机械研究所 | Full three-dimensional modeling method and device for high-performance impeller mechanical blade and electronic equipment |
| CN115994423A (en) * | 2022-12-15 | 2023-04-21 | 西安交通大学 | Cross-tone leaf pattern design method based on Bezier curve and related device |
Non-Patent Citations (1)
| Title |
|---|
| 伊卫林;黄鸿雁;韩万金;: "轴流压气机叶片优化设计", 热能动力工程, no. 02 * |
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