A method for optimizing a counter-deforming turbine structure for a turbocharger

Abstract

The application discloses a kind of reverse deformation turbine structure optimization methods for turbocharger, comprising: step S1, the original design model of turbine impeller is constructed;Step S2, the turbine original design blade of original design model is extracted blade profile control line processing, obtains the blade profile control line data of discrete point group composition impeller blade;Step S3, the overall coordinate contraction coefficient of turbine impeller is defined;Blade reverse deformation local coordinate contraction coefficient is defined to blade data;Step S4, obtains blade discrete reverse deformation blade profile control data point;Step S5, using blade discrete reverse deformation blade profile control data point, reconstructs to generate reverse deformation casting model and casts production, finally obtains the same turbine impeller casting product as original design model;The turbine designed by the reverse deformation turbine structure optimization method of the application can effectively solve the deformation difference problem between the final physical object and the design model of the turbocharger turbine impeller in the precise casting link.

Description

TECHNICAL FIELD

[0001] The present application relates to the turbocharger technical field, in particular to a reverse deformation turbine structure optimization method for turbocharger. BACKGROUND

[0002] The turbocharger is to utilize the exhaust gas energy of the engine to push the turbine in the turbocharger turbine box, and the turbine drives the coaxial compressor impeller, and the compressor impeller rotates to compress and pressurize the air, and the pressurized air is pressed into the engine through the gas collection of the compressor shell, so that the engine combustion is more sufficient, and the output power is increased.

[0003] The turbine impeller in the turbocharger is in contact with the high-temperature gas of the engine, and the main structure includes a central hub and circumferentially distributed turbine blades. The spatial shape of the turbine blade is curved, and the manufacturing method is a precision casting integral forming technology.

[0004] During the entire process of precision casting of the turbine blade, there are two main processes of wax mold shrinkage and casting alloy shrinkage, so that the final result is that the turbine impeller product appears shrinkage problem compared with the design model, for example, as shown in Figure 1 、 Figure 2 The original design model 100 of the turbine impeller has shrinkage problem after precision casting to form the precision casting blade shrinkage model 101. In the usual design and manufacturing process, a uniform shrinkage rate is set for the turbine impeller model, that is, the turbine impeller manufacturing model is enlarged according to the proportion compared with the design model, and the final product is consistent with the design model after shrinkage in the precision manufacturing link.

[0005] However, due to the cantilever structure of the turbine blade, it is found in the final product detection that the turbine hub has high compliance with the design model, but the turbine blade has different degrees of deformation, and the blade space position deviates from the design model.

[0006] The deformation position is the cantilever edge of the blade, and the height direction of the blade changes, and compared with the original design model, the cantilever height direction of the blade deforms downward. The deviation of the blade space position directly leads to the deviation of the turbine aerodynamic performance, which affects the design performance target.

[0007] Through the analysis of the precision casting process, the casting deformation is inevitable, so how to obtain the turbine product consistent with the design model?

[0008] Therefore, it is urgent to develop a technology to solve the above technical problems. SUMMARY

[0009] The present application relates to the turbocharger technical field, in particular to a reverse deformation turbine structure optimization method for turbocharger.

[0010] To this end, the application provides an anti-deformation turbine structure optimization method for a turbocharger, comprising the following steps:

[0011] Step S1, constructing an original design model of a turbine impeller and defining structural sizes of a meridian plane of the original design model;

[0012] The turbine impeller comprises a turbine impeller hub;

[0013] A plurality of turbine original design blades are distributed around an upper surface of the turbine impeller hub;

[0014] Step S2, performing extraction blade profile control line processing on turbine original design blades of the original design model to obtain turbine blade extraction blade profile control lines, and performing discrete point processing on the turbine blade extraction blade profile control lines to obtain turbine blade profile control line data (X, Y, Z) composed of discrete points;

[0015] Step S3, defining overall coordinate contraction coefficients (Kx, Ky, Kz) of the turbine impeller; and defining blade anti-deformation local coordinate contraction coefficient K 反 for the turbine blade data;

[0016] Step S4, obtaining blade discrete anti-deformation blade profile control data points (X 反 , Y 反 , Z 反 ) according to the blade discrete blade profile data points (X, Y, Z) and according to the overall coordinate contraction coefficients and the blade anti-deformation local coordinate contraction coefficient K 反 ;

[0017] Step S5, using the blade discrete anti-deformation blade profile control data points (X 反 , Y 反 , Z 反 ) to reconstruct anti-deformation blade profile control lines, and further to construct a generated anti-deformation casting model, using the model to perform casting production, and finally obtaining a turbine impeller casting product identical to the original design model;

[0018] The anti-deformation casting model comprises a turbine impeller, and the turbine impeller comprises a turbine impeller hub;

[0019] A plurality of anti-deformation turbine blades are distributed around an upper surface of the turbine impeller hub;

[0020] The data points on the blade profile control lines of the anti-deformation turbine blades are the blade discrete anti-deformation blade profile control data points (X 反 , Y 反 , Z 反 .

[0021] From the above technical solutions provided by the present application, compared with the prior art, the present application provides an anti-deformation turbine structure optimization method for a turbocharger, which is scientific in design, and the designed turbine has the anti-deformation structure feature of the turbocharger turbine blade, can effectively solve the deformation difference problem between the final physical object and the design model of the turbocharger turbine impeller in the precision casting link, and has great practical significance.

[0022] It should be noted that by applying the anti-deformation design method of the turbine blade provided by the present application, the turbine impeller after precision casting can obtain the same product as the original model, the consistency of the turbine impeller is greatly improved, the performance of the original design model can be obtained, and it has great significance for the design of the turbocharger turbine impeller.

[0023] For the present application, the anti-deformation design of the turbine blade is adopted, by increasing the local anti-deformation design of the turbine blade on the basis of uniform casting shrinkage, the deformation design in the opposite direction of the shrinkage deformation direction of the blade is increased, so that the final casting product after shrinkage deformation conforms to the design model, the anti-deformation design method of the turbine impeller provided by the present application effectively solves the process technical problem of the consistency of the casting product and the original design model. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 is a schematic diagram of an original design model of a turbine impeller;

[0025] Figure 2 is a schematic diagram of a comparison between the original design model of the turbine impeller and the product model after precision casting;

[0026] In the figure, 100 is the original design model, and 101 is the blade shrinkage deformation model after precision casting;

[0027] Figure 3 is a schematic diagram of a comparison between the original design model of the turbine impeller and the anti-deformation casting model;

[0028] In the figure, 100 is the original design model, and 200 is the anti-deformation casting model (i.e. the anti-deformation model of the precision casting blade);

[0029] Figure 4 is a schematic diagram of extracting a blade profile control line of the original design model of the turbine impeller,

[0030] In the figure, 401 is a blade hub blade profile control line

[0031] 402 is a blade shroud blade profile control line;

[0032] 403 is a blade profile control line of the middle layer of the impeller;

[0033] Figure 5A schematic diagram for extracting discrete data points (X, Y, Z) of a blade profile control line;

[0034] Figure 6 A schematic diagram for calculating inverse deformation blade discrete data (X 反 ,Y 反 ,Z 反 ) of original blade profile discrete points (X, Y, Z);

[0035] Figure 7 A schematic diagram for defining meridian plane structure size of a turbine wheel original design model;

[0036] Rs is a blade meridian plane shroud radius value;

[0037] H is a blade meridian plane shroud height value;

[0038] Rh is a blade meridian plane hub radius value;

[0039] Ah is a blade meridian plane shroud height direction inverse deformation correction distance;

[0040] 1 is a turbine wheel hub;

[0041] 2 is a turbine original design blade;

[0042] 3 is an inverse deformation turbine blade;

[0043] 4 is a turbine blade extracted blade profile control line. DETAILED DESCRIPTION

[0044] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application.

[0045] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0046] In the description of the present patent, it is necessary to point out that, unless otherwise explicitly specified and limited, the terms "mount", "connect", "connect", "set" should be understood broadly, for example, it can be fixedly connected, set, or it can be detachably connected, set, or integrally connected, set. For those skilled in the art, the specific meaning of the above terms in the present patent can be understood according to the specific circumstances.

[0047] In addition, the terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise explicitly specified and limited.

[0048] The present application provides an anti-deformation turbine structure optimization method for a turbocharger, comprising the following steps:

[0049] Step S1, constructing an original design model 100 of a turbine impeller, and defining the structure size of the original design model meridian plane, see Figure 7 shown;

[0050] The turbine impeller comprises a turbine impeller hub 1.

[0051] A plurality of turbine original design blades 2 are distributed around the upper surface of the turbine impeller hub 1.

[0052] In step S1, the structure size included in the original design model meridian plane is as follows:

[0053] Rs is the blade meridian plane shroud radius value of the turbine original design blade 2;

[0054] H is the blade meridian plane shroud height value of the turbine original design blade 2;

[0055] Rh is the blade meridian plane hub radius value of the turbine original design blade 2;

[0056] Delta h is the anti-deformation correction distance of the turbine original design blade 2 in the blade meridian plane shroud height direction;

[0057] In step S1, in actual operation, Delta h is the value of blade deformation, which can be determined according to the shrinkage change value in the height direction of the blade in the actual casting process. For example, the value of Delta h is 0.3mm.

[0058] Step S2, the turbine original design blade 2 of the original design model is subjected to the extraction of the blade profile control line processing, the turbine blade extraction blade profile control line 4 is obtained, and the turbine blade extraction blade profile control line 4 is subjected to the discrete point processing, the blade profile control line data (X, Y, Z) composed of discrete points is obtained, the blade profile data points are a group of discrete data points representing the blade profile curve, the number of data points is determined according to the discrete point degree of the blade profile control line, the data points can be more or less, but the minimum data points need to meet that the blade profile control line can be regenerated through the discrete data points, see Figure 4 、 5 ,

[0059] In step S3, the blade profile control line data composed of discrete points includes the blade hub blade profile control line 401, the blade shroud blade profile control line 402 and the blade profile control line 403 of the intermediate layer of the blade;

[0060] Step S3, the overall coordinate contraction coefficient (Kx, Ky, Kz) of the turbine wheel is defined, which is used for the overall coordinate contraction model calculation of the turbine wheel hub 1 and the blade, and the overall contraction coefficient of each turbine wheel is a single fixed value; for the blade data, the blade inverse deformation local coordinate contraction coefficient K 反 is defined.

[0061] In step S3, it needs to be explained that the contraction coefficients in three directions can be the same, or can be set to be different according to the process requirement.

[0062] In step S3, in the specific implementation, the contraction coefficients in three directions can be the same, and the specific values are (1.02, 1.02, 1.02), which are used for the overall coordinate contraction model calculation of the turbine wheel hub and the blade.

[0063] In step S3, it also needs to be explained that the blade inverse deformation local coordinate contraction coefficient K 反 is related to the meridian structure size of the turbine wheel and the inverse deformation correction distance Δh.

[0064] In step S3, the blade inverse deformation local coordinate contraction coefficient K 反 is calculated according to the following formula:

[0065]

[0066] Wherein, R is the calculation value of the blade profile control line discrete data points (X, Y, Z) of the original design model in the meridian plane, which is calculated according to the following formula:

[0067]

[0068] Rs is the blade meridian shroud radius value of the turbine original design blade 2;

[0069] H is the blade meridian shroud height value of the turbine original design blade 2;

[0070] Rh is the blade meridian hub radius value of the turbine original design blade 2;

[0071] Ah is the blade meridian shroud height direction inverse deformation correction distance of the turbine original design blade 2;

[0072] K 反 is the inverse deformation local coordinate contraction coefficient of each original model impeller blade surface control line discrete data point (X, Y, Z) obtained by calculation through the above formula, which is one-to-one corresponding to each discrete data point (X, Y, Z) and is a group of calculation values. That is, if there are 100 groups of discrete points (X, Y, Z), there are 100 corresponding K 反 calculation values, which are used to correct the Z value of the local coordinate value of the impeller blade.

[0073] Step S4, according to the blade discrete blade surface data points (X, Y, Z), and according to the impeller overall coordinate contraction coefficient and the blade inverse deformation local coordinate contraction coefficient K 反 , the blade discrete inverse deformation blade surface control data points (X 反 , Y 反 , Z 反 ) are obtained;

[0074] In step S4, X 反 = X·K x ;

[0075] Y 反 = Y·K y ;

[0076]

[0077] Wherein: R is the calculation value of the impeller blade surface control line discrete data point (X, Y, Z) of the original design model in the meridian plane, which is obtained by calculation through the following formula

[0078] Rs is the blade meridian shroud radius value of the turbine original design blade 2;

[0079] H is the blade meridian shroud height value of the turbine original design blade 2;

[0080] Rh is the blade meridian hub radius value of the turbine original design blade 2;

[0081] Ah is the blade meridian shroud height direction inverse deformation correction distance of the turbine original design blade 2;

[0082] X 反 To obtain the corresponding inverse deformation coordinate value of the X-direction coordinate by multiplying the overall coordinate shrinkage coefficient Kx with the original discrete blade profile data point X;

[0083] Y 反 To obtain the corresponding inverse deformation coordinate value of the Y-direction coordinate by multiplying the overall coordinate shrinkage coefficient Ky with the original discrete blade profile data point Y;

[0084] Z 反 To obtain the local coordinate shrinkage coefficient K, the global coordinate shrinkage coefficient Kz is first multiplied by the original discrete blade profile data point Z, and then calculated in the previous step. 反 Multiplying them together, we finally obtain the corresponding anti-deformation coordinate value of the Z-direction coordinate. The calculation method of the Z-direction coordinate is different from that of the X and Y directions. The main difference is that after the overall coordinate shrinkage calculation of the blade data points, the local coordinate shrinkage calculation of the blade Z-direction is added, which realizes the anti-deformation design of the turbine blade.

[0085] Discrete anti-deformation blade profile control data points (X 反 Y 反 Z 反 The above formulas are used to calculate the values ​​of 100 discrete points (X, Y, Z). For example, if there are 100 discrete points (X, Y, Z), the corresponding discrete points (X, Y, Z) can be calculated using the above formulas. 反 Y 反 Z 反 ), using (X 反 Y 反 Z 反 The data points can be used to regenerate the anti-deformation blade profile control lines, and then construct the anti-deformation turbine casting model. See [link / reference]. Figure 6 As shown.

[0086] Step S5, use the discrete anti-deformation blade profile control data points (X) 反 Y 反 Z 反 The anti-deformation blade profile control lines are reconstructed, and then an anti-deformation casting model 200 is generated. This model is used for casting production, and finally a turbine impeller casting product with the same design model as the original design model is obtained.

[0087] The anti-deformation casting model includes a turbine impeller, which includes a turbine impeller hub 1;

[0088] Multiple anti-deformation turbine blades 3 are distributed around the upper surface of the turbine impeller hub 1;

[0089] The data points on the blade profile control line of the anti-deformation turbine blade 3 are the discrete anti-deformation blade profile control data points (X).反 , Y 反 , Z 反 ).

[0090] Based on the above technical solutions, for the present application, the same design product as the original design model can be obtained after precision casting of the turbine impeller, ensuring the realization of the design performance target of the turbine impeller, improving the consistency of the product, and having important practical significance.

[0091] It should be noted that, although the present application is proposed by supercharger turbine precision casting design, this blade reverse deformation method can also be applied to supercharger compressor impellers obtained using casting methods. Further application and extension, this method can be applied to the production of turbine machinery with cantilever blade parts having a casting process (process shrinkage deformation).

[0092] In summary, compared with the prior art, the present application provides a reverse deformation turbine structure optimization method for a turbocharger, which is designed scientifically, and the designed turbine has the reverse deformation structure characteristics of the supercharger turbine blade, which can effectively solve the deformation difference problem between the final physical product and the design model of the supercharger turbine impeller in the precision casting link, and has great practical significance.

[0093] It should be noted that, by applying the reverse deformation design method of the turbine blade provided by the present application, the same product as the original model can be obtained after precision casting of the turbine impeller, the consistency of the turbine impeller is greatly improved, the performance of the original design model can be obtained, and the design of the supercharger turbine impeller has great significance.

[0094] For the present application, reverse deformation design of turbine blades is adopted, by increasing local reverse deformation design of turbine blades on the basis of uniform casting shrinkage rate, deformation design is increased in the opposite direction of shrinkage deformation of the blade, so that the final casting product conforms to the design model after shrinkage deformation, the reverse deformation design method of the turbine impeller provided by the present application effectively solves the process technical problem of consistency between the casting product and the original design model.

[0095] The above is only the preferred embodiment of the present application, it should be noted that, for those skilled in the art, without departing from the principles of the present application, a number of improvements and refinements can be made, these improvements and refinements should also be considered as the protection scope of the present application.

Claims

1. A method for optimizing the anti-deformation turbine structure of a turbocharger, characterized in that, Includes the following steps: Step S1: Construct the original design model (100) of the turbine impeller and define the structural dimensions of the meridional plane of the original design model; The turbine impeller includes a turbine impeller hub (1); Multiple turbine blades (2) of the original turbine design are distributed around the upper surface of the turbine impeller hub (1); Step S2: Extract the blade profile control lines from the original turbine blade (2) of the original design model to obtain the extracted blade profile control lines (4) of the turbine blade, and perform discrete point processing on the extracted blade profile control lines (4) of the turbine blade to obtain the impeller blade profile control line data (X, Y, Z) composed of discrete points. Step S3: Define the overall coordinate shrinkage coefficients (Kx, Ky, Kz) of the turbine impeller; define the local coordinate shrinkage coefficients for blade anti-deformation based on the impeller blade data. ; Step S4: Based on the discrete blade profile data points (X, Y, Z), and based on the overall impeller coordinate shrinkage coefficient and the blade anti-deformation local coordinate shrinkage coefficient... To obtain the discrete inverse deformation blade profile control data points ( , , ); Step S5, use the discrete anti-deformation blade profile control data points ( , , ), reconstruct the anti-deformation blade profile control line, and then construct and generate the anti-deformation casting model (200). Use this model for casting production, and finally obtain the turbine impeller casting product that is the same as the original design model; The anti-deformation casting model includes a turbine impeller, which includes a turbine impeller hub (1). Multiple anti-deformation turbine blades (3) are distributed around the upper surface of the turbine impeller hub (1); The data points on the blade profile control line of the anti-deformation turbine blade (3) are the discrete anti-deformation blade profile control data points. , , ); In step S3, the local coordinate shrinkage coefficient of the blade in reverse deformation The calculation formula is as follows: ； In step S4, ; ； ； Where: R is the calculated value of the discrete data points (X, Y, Z) of the impeller blade profile control line in the meridional plane of the original design model, and its value is obtained by the following formula: ； Rs is the radius of the meridional shroud of the turbine blade (2) in the original design. H is the height of the meridional shroud of the turbine blade (2) in the original design. Rh is the hub radius value of the meridional plane of the turbine blade (2) in the original design. Δh is the anti-deformation correction distance in the direction of the blade meridional shroud height of the original turbine blade design (2).

2. The method for optimizing the anti-deformation turbine structure for a turbocharger as described in claim 1, characterized in that, In step S3, the impeller blade profile control line data composed of discrete points includes the blade hub blade profile control line (401), the blade shroud blade profile control line (402), and the impeller intermediate layer blade profile control line (403).

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