A positioning machining method for a turbine housing

Abstract

The present invention relates to a positioning and machining method for a turbine housing. The present invention includes using the plane where the end hole of the middle housing of the turbine housing to be machined is located and the central axis as the plane reference and the central axis reference respectively, selecting a point on the intake flange plane of the turbine housing to be machined as the rotation reference, and machining the outlet flange end face and the outlet flange end hole respectively. The positioning and machining method for a turbine housing according to the present invention reduces the influence of positioning errors on the machining of castings. By setting the rotation reference on the intake flange plane, the influence of positioning errors on machining is greatly reduced, the machining process can be made more accurate and stable, thereby improving the machining quality. This method of converting the rotation reference of the turbine housing is applicable to all turbine housings, without being restricted by specific shapes or dimensions. Therefore, it has wide applicability, can be applied to the machining processes of various turbine housings, the operation process is simple, does not require complex equipment and process adjustments, is easy to implement and operate, is of great significance for improving machining quality and efficiency, and is easy to implement.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine housing processing, and in particular to a positioning processing method for a turbine housing. Background Art

[0002] During the existing turbine housing processing, castings that pass the 3D scanning inspection may have defects such as black skin and hole deviation after processing. By re-performing 3D scanning inspection and analysis on the processing rejects, it is found that there are certain problems during the automatic clamping process of the processing tooling.

[0003] Taking the processing of a casting as an example, through 3D simulation analysis of the casting, it is found that when the error of the rotation reference is 0.3 mm, the rotation angle of the casting around the central axis is 0.45°. This will result in a reduction of 1 mm in the machining allowance of the back angle of the intake flange, thereby increasing the risk of machining black skin defects.

[0004] Therefore, when processing a turbine housing, it is very important to ensure the accuracy and precision of the processing positioning reference. Especially for the rotational machining of the turbine housing around the central axis, the error of the rotation reference will directly affect the machining quality and the generation of defects. Therefore, special attention should be paid to the control of the rotation reference during the processing, and corresponding measures should be taken to avoid machining problems and defects caused by the rotation reference error. Summary of the Invention

[0005] For this reason, the present invention provides a positioning processing method for a turbine housing, which reduces the influence of the positioning error on the machining quality of the casting.

[0006] To solve the above technical problems, the present invention provides a positioning processing method for a turbine housing, including:

[0007] Taking the plane where the end hole of the middle shell of the turbine housing to be processed is located and the central axis as the plane reference and the central axis reference respectively, selecting a point on the intake flange plane of the turbine housing to be processed as the rotation reference, and machining the end face of the exhaust flange and the end hole of the exhaust flange respectively.

[0008] In an embodiment of the present invention, it further includes machining the intake pipe orifice with the plane reference, the central axis reference and the rotation reference as the positioning.

[0009] In an embodiment of the present invention, the intake pipe orifice has a back lug.

[0010] In an embodiment of the present invention, it further includes: positioning with the intake pipe orifice, the end face of the exhaust flange and the end hole of the exhaust flange as the reference, and machining the end face of the middle shell and the end hole of the middle shell.

[0011] In one embodiment of the present invention, it further includes: positioning with the end face of the intermediate shell, the end hole of the intermediate shell, and the back tab of the air inlet pipe orifice as references, and respectively machining the air inlet flange plane, the side of the air inlet flange, and the back corner of the air inlet flange.

[0012] In one embodiment of the present invention, it further includes: positioning with the air inlet flange plane, the end face of the intermediate shell, and the end hole of the intermediate shell as references, and machining the end tab of the intermediate shell.

[0013] In one embodiment of the present invention, it further includes: positioning with the air inlet flange plane, the end face of the intermediate shell, and the end hole of the intermediate shell as references, and machining the bushing hole and the valve seat surface.

[0014] In one embodiment of the present invention, the plane reference is determined by three points at the hole end of the end hole of the intermediate shell.

[0015] In one embodiment of the present invention, the central axis reference is determined by three points inside the hole of the end hole of the intermediate shell.

[0016] In one embodiment of the present invention, the rotation reference is a concave point near the air inlet on the air inlet flange plane.

[0017] The above technical solution of the present invention has the following advantages compared with the prior art:

[0018] For a method for positioning and machining a turbine shell of the present invention, the influence of positioning error on the machining of the casting is reduced. By setting the rotation reference on the air inlet flange plane, the influence of positioning error on the machining is greatly reduced. Through calculation and simulation analysis, it is found that when the rotation reference error is 0.3 mm, the rotation angle of the casting around the central axis is only 0.12°, and the machining allowance of the back corner of the air inlet flange is reduced by 0.27 mm. Therefore, under the same positioning error, the difference from the existing machining result is 4 times, which can make the machining process more accurate and stable, thereby improving the machining quality.

[0019] The present invention is applicable to all turbine shells and has good applicability. This method of converting the rotation reference of the turbine shell can be applied to all turbine shells without being restricted by specific shapes or sizes. Therefore, it has wide applicability and can be applied to the machining processes of various turbine shells.

[0020] The operation process of the present invention is simple, does not require complex equipment and process adjustments, is easy to implement and operate, is of great significance for improving machining quality and efficiency, and is easy to implement. Description of the Drawings

[0021] In order to make the content of the present invention easier to be clearly understood, the following further describes the present invention in detail according to the specific embodiments of the present invention and in conjunction with the drawings.

[0022] Figure 1 It is the front view of the turbine housing to be processed in the present invention.

[0023] Figure 2 It is the perspective view of the turbine housing to be processed in the present invention from the first perspective.

[0024] Figure 3 It is the perspective view of the turbine housing to be processed in the present invention from the second perspective.

[0025] Description of the reference numerals in the accompanying drawings of the specification:

[0026] 1. Intermediate housing end hole;

[0027] 2. Intake flange plane;

[0028] 3. Exhaust flange end face;

[0029] 4. Exhaust flange end hole;

[0030] 5. Inlet pipe port;

[0031] 6. Rear lug;

[0032] 7. Intermediate housing end face;

[0033] 8. Intake flange side;

[0034] 9. Intermediate housing end lug;

[0035] 10. Bushing hole;

[0036] 11. Valve seat surface. Detailed implementation manners

[0037] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, so that those skilled in the art can better understand the present invention and be able to implement it, but the specific embodiments cited shall not be construed as a limitation to the present invention.

[0038] In the present invention, when directions (up, down, left, right, front and rear) are described, it is only for the convenience of describing the technical solution of the present invention, rather than indicating or implying that the technical features referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0039] In the present invention, the meaning of "several" is one or more, the meaning of "multiple" is two or more, and understandings such as "greater than", "less than", "exceeding" do not include the present number; understandings such as "above", "below", "within" include the present number. In the description of the present invention, if "first" and "second" are described, they are only for the purpose of distinguishing technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the technical features indicated or implicitly indicating the sequence relationship of the technical features indicated.

[0040] In the present invention, unless otherwise clearly defined, terms such as "arrangement", "installation", "connection", etc. should be understood in a broad sense. For example, it can be directly connected, or indirectly connected through an intermediate medium; it can be fixedly connected, or detachably connected, or integrally formed; it can be mechanically connected, or electrically connected or capable of communicating with each other; it can be the communication inside two components or the interaction relationship between two components. Those skilled in the art can reasonably determine the specific meaning of the above terms in the present invention in combination with the specific content of the technical solution.

[0041] Refer to Figures 1 to 3 As shown, a positioning and machining method for a turbine housing of the present invention includes the following steps:

[0042] S1. Take the plane where the intermediate housing end hole 1 of the turbine housing to be machined is located and the central axis as the plane reference and the central axis reference respectively, select a point on the intake flange plane 2 of the turbine housing to be machined as the rotation reference G, and machine the outlet flange end face 3 and the outlet flange end hole 4 respectively; by taking the plane where the intermediate housing end hole 1 is located and the central axis as the reference, the machining accuracy and alignment of the turbine housing can be ensured, thereby improving the performance and service life of the turbine housing.

[0043] S2. With the plane reference, the central axis reference and the rotation reference as the positioning, machine the intake pipe orifice 5 and the back lug 6; with the plane reference, the central axis reference and the rotation reference as the positioning, the machining accuracy of the intake pipe orifice 5 and the back lug 6 can be ensured, thereby improving the sealing performance and service life of the turbine housing.

[0044] S3. Take the intake pipe orifice 5, the outlet flange end face 3 and the outlet flange end hole 4 as the reference for positioning, and machine the intermediate housing end face 7 and the intermediate housing end hole 1; the machining accuracy of the intermediate housing end face 7 and the intermediate housing end hole 1 can be ensured, thereby improving the structural strength and service life of the turbine housing.

[0045] S4. Take the intermediate housing end face 7, the intermediate housing end hole 1 and the back lug 6 of the intake pipe orifice 5 as the reference for positioning, and machine the intake flange plane 2, the intake flange side 8 and the intake flange back corner respectively; the machining accuracy of the intake flange plane 2, the intake flange side 8 and the intake flange back corner can be ensured, thereby improving the sealing performance and service life of the turbine housing.

[0046] S5. Take the intake flange plane 2, the intermediate housing end face 7 and the intermediate housing end hole 1 as the reference for positioning, and machine the intermediate housing end lug 9; the machining accuracy of the intermediate housing end lug 9 can be ensured, thereby improving the structural strength and service life of the turbine housing.

[0047] S6. Position with reference to the intake flange plane 2, the end face 7 of the intermediate housing, and the end hole 1 of the intermediate housing, and machine the bushing hole 10 and the valve seat surface 11. This can ensure the machining accuracy of the bushing hole 10 and the valve seat surface 11, thereby improving the sealing performance and service life of the turbine housing.

[0048] In some embodiments, the plane reference is determined by three points (Z1, Z2, Z3) at the hole end of the end hole 1 of the intermediate housing. By using three points to determine the plane reference, the accuracy and stability during the machining process of the turbine housing can be ensured, thereby improving the performance and service life of the turbine housing.

[0049] In some embodiments, the central axis reference is determined by three points (F1, F2, F3) inside the end hole 1 of the intermediate housing. By using three points to determine the central axis reference, the accuracy and stability during the machining process of the turbine housing can be ensured, thereby improving the performance and service life of the turbine housing.

[0050] In some embodiments, the rotation reference (G) is a concave point near the air inlet on the intake flange plane 2.

[0051] By setting the rotation reference on the intake flange plane 2, compared with the existing rotation reference in the end hole of the intake flange (when the error of the rotation reference is 0.3 mm, the casting rotates around the central axis by an angle of 0.45°. This will cause the machining allowance of the back angle of the intake flange to be reduced by 1 mm, thereby increasing the risk of machining black skin defects), the influence of the positioning error on machining is greatly reduced. Through calculation and simulation analysis, it is found that in the present invention, when the rotation reference error is 0.3 mm, the rotation angle of the casting around the central axis is only 0.12°, and the machining allowance of the back angle of the intake flange is reduced by 0.27 mm. Therefore, under the same positioning error, the difference from the existing machining result is 4 times, which can make the machining process more accurate and stable, thereby improving the machining quality.

[0052] Finally, it should be noted that the above specific embodiments are only used to illustrate the technical solutions of the present invention and are not restrictive. Although the present invention has been described in detail with reference to the examples, those of ordinary skill in the art should understand that the technical solutions of the present invention can be modified or equivalently replaced without departing from the spirit and scope of the technical solutions of the present invention, and they should all be covered within the scope of the claims of the present invention.

Claims

1. A positioning machining method for a turbine housing, characterized in that, Including: Taking the plane where the end hole of the middle shell of the turbine housing to be processed is located and the central axis as the plane reference and the central axis reference respectively, selecting a point on the intake flange plane of the turbine housing to be processed as the rotation reference, and machining the outlet flange end face and the outlet flange end hole respectively; Positioning with the plane reference, the central axis reference and the rotation reference, and machining the intake pipe orifice; The intake pipe orifice has a back lug; Positioning with the intake pipe orifice, the outlet flange end face and the outlet flange end hole as the reference, and machining the middle shell end face and the middle shell end hole; Positioning with the middle shell end face, the middle shell end hole and the back lug of the intake pipe orifice as the reference, and machining the intake flange plane, the intake flange side and the intake flange back corner respectively; Positioning with the intake flange plane, the middle shell end face and the middle shell end hole as the reference, and machining the middle shell end lug; Positioning with the intake flange plane, the middle shell end face and the middle shell end hole as the reference, and machining the bushing hole and the valve seat surface; The plane reference is determined by three points at the hole end of the middle shell end hole; The central axis reference is determined by three points inside the middle shell end hole; The rotation reference is a concave point near the intake port on the intake flange plane.

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