CN116502364B - Design method of radial turbine applied to turbocharger - Google Patents
Design method of radial turbine applied to turbocharger Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 48
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Abstract
本发明涉及径向透平设计技术领域，具体涉及一种应用于涡轮增压器中的径向透平的设计方法，包括：通过三维反设计法产生非纤维化后掠式前缘叶片；使用两条线将非纤维化后掠式前缘叶片的子午面划分为三个部分，第一条线位于靠近前缘10%‑20%位置处，第二条线位于顶盖中间位置且呈垂直分布；对划分后的非纤维化后掠式前缘叶片进行部分纤维化设计；最终得到部分纤维化后掠式前缘叶片。本发明产生的透平为部分纤维叶片的设计，可保证叶片在透平最大应力处是完全纤维化的，从而解决了最大应力问题；本发明产生的透平的前缘为后掠式设计，可有效的提高叶片在高温高压下的气动效率，从而有效提高从内燃气废气中获取的能量。
The invention relates to the technical field of radial turbine design, and specifically relates to a design method for a radial turbine used in a turbocharger, which includes: generating non-fiberized swept leading edge blades through a three-dimensional inverse design method; using Two lines divide the meridian plane of the non-fiber swept leading edge blade into three parts. The first line is located 10%-20% close to the leading edge, and the second line is located vertically in the middle of the top cover. Distribution; perform partial fiberization design on the divided non-fiberized swept leading edge blades; finally obtain a partially fiberized swept leading edge blade. The turbine produced by the present invention is designed with partial fiber blades, which can ensure that the blades are completely fiberized at the maximum stress point of the turbine, thereby solving the maximum stress problem; the leading edge of the turbine produced by the present invention is a swept-back design. It can effectively improve the aerodynamic efficiency of the blades under high temperature and high pressure, thereby effectively improving the energy obtained from the internal gas exhaust gas.
Description
Technical Field
The invention relates to the technical field of radial turbine design, in particular to a design method of a radial turbine 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 radial turbine applied to the turbocharger is provided, can meet the requirement of the maximum stress and can effectively improve the turbine aerodynamic efficiency under the condition of high temperature and high pressure.
In order to achieve the above object, the present invention is realized by the following technical scheme:
the design method of the radial turbine applied to the 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 function of the periodic potential of the electrodes,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 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 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, the 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 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 method of designing a 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 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,the radial, tangential and axial coordinates respectively,/>for the period speed +.>As a function of the periodic potential of the electrodes,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.
Referring to fig. 5, another embodiment of the present invention provides a design device for a 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 design apparatus for a radial turbine 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 and executed by the processor to implement the steps of a method of designing a 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 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 (7)
1. A method of designing a 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;
dividing the meridian plane of the non-fibrous sweepback type front edge blade into three parts, wherein the first part is between the front 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 tail edge of the blade;
the method for designing the partial fibrosis of the divided non-fibrosis swept-back front 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 top cover part of the third part is kept unchanged, and the blade wrap angles of the rest parts of the third part are recalculated according to the blade wrap angles of the top cover part, wherein the blade wrap angles of the rest parts ensure that the blade wrap angles are equal at the same axial distance;
the method of partial fibrosis further comprises: 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;
the result is a partially fibrillated swept leading edge blade.
2. A method of designing a 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 vane 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. The method of claim 2, wherein the blade meridian plane is a projection of three-dimensional blade xyz coordinates on an rz plane, i.e., 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. The method for designing a radial turbine for use in a turbocharger according to claim 2, wherein the method for calculating the velocity field is specifically as follows: 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 function of the periodic potential of the electrodes,for a sawtooth function->Is a periodic average ring size distribution.
5. A design apparatus for a 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.
6. A design apparatus for a 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, 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 radial turbine applied to a turbocharger as claimed in any one of claims 1 to 4.
7. A storage medium having stored thereon a computer program, which when executed by a processor, implements the steps of a method of designing a radial turbine for use in a turbocharger according to any one of claims 1 to 4.
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