KR20110111509A - Fabrication method for nozzle vane - Google Patents

Abstract

A method of manufacturing a nozzle vane having a blade portion and a shaft portion protruding from a predetermined cross section of the blade portion, wherein the blade portion and the shaft portion are formed in a die for forming a shaft portion having a first insert portion having a shape in which the shaft portion is projected in the axial direction. The pre-molded shaft portion of the compact member having pre-molded wing portions and pre-molded shaft portions each having a plurality of dimensions and approximate dimensions are inserted, and the pre-molded shaft portion is pressed in the axial direction to form the shaft portion. The small member after the first step is inserted into a die for forming a wing part, in which a second insertion part having a shape in which the nozzle vane is projected in a direction substantially orthogonal to the wing surface of the wing part is formed; The manufacturing method of the nozzle vane provided with the 2nd process of shape | molding the said wing part by pressing a wing | tip part before shaping | molding in the direction orthogonal to the wing surface.

Description

Fabrication method for nozzle vane

This invention relates to the manufacturing method of the nozzle vane which has a blade | wing part and the shaft part which protruded from the predetermined cross section of the blade | wing part.

This application claims priority based on Japanese Patent Application No. 2009-42164 for which it applied to Japan on February 25, 2009, and uses the content here.

Background Art Conventionally, nozzle vanes having a blade and a shaft portion protruding from a predetermined cross section of the blade are known, for example, used in a variable displacement turbocharger.

The variable displacement turbocharger is a supercharger that can improve the performance of the engine over a wide range from low to high rotation range. The turbocharger has a rotary blade that rotates by the flow of exhaust gas discharged from the engine, and a variable nozzle that surrounds the rotary blade and forms an annular shape and supplies exhaust gas to the rotary blade. The variable nozzle has a pair of substantially annular plate-shaped members disposed to face each other, and a plurality of nozzle vanes provided between the pair of plate-shaped members. The nozzle vanes are pivotally rotatably supported by the pair of plate members, and are provided at substantially equal intervals in the circumferential direction of the pair of plate members.

The diameter of the flow path of the variable nozzle is changed by rotating the nozzle vane about its axis and changing the distance between each wing. By selecting an appropriate flow path diameter of the variable nozzle in accordance with the engine speed, that is, the flow rate of the exhaust gas discharged from the engine, the performance of the engine can be improved over a wide range from the low rotation region to the high rotation region.

However, in order to maintain the operation and performance of the variable capacity turbocharger, it is important to manufacture nozzle vanes with high precision.

For example, in order to rotate a nozzle vane smoothly, it is necessary to limit the diameter and roundness of the shaft part within appropriate precision. In addition, when the nozzle vane has a pair of shaft portions projecting from both end faces of the wing portion, it is necessary to ensure concentricity in the pair of shaft portions with appropriate precision.

In addition, when the gap between the plate member of the variable nozzle and the vane end face of the nozzle vane becomes large, the flow rate of the exhaust gas leaking out of the gap increases, which reduces the efficiency of the turbocharger.

Therefore, it is necessary to limit the width of the wing section in the axial direction of the axial section and the orthogonality between the axial direction and the cross section of the wing section within an appropriate precision.

In order to secure the precision, a cutting process is used in the final process of manufacturing the nozzle vane.

Patent Document 1 discloses a method for producing a nozzle vane.

In the manufacturing method of the nozzle vane disclosed by patent document 1, the small member which has several dimensions slightly larger than the nozzle vane of a finished product from the metal plate which has a predetermined plate | board thickness by a punching process or a press process first. Next, the small member is cut by a cutting process to manufacture nozzle vanes. In the cutting process, the shaft section of the nozzle vane and the end surface of the blade section are cut. Through this step, the diameter of the shaft section, the width of the blade section, and the like are limited within the appropriate precision.

Patent Document 1: Japanese Patent Application Laid-Open No. 2007-23840 (19 pages, FIG. 10)

However, since the cutting process requires more work time and requires more hands than the press process, there is a problem that the manufacturing cost of the nozzle vane increases by using such a cutting process.

This invention is made | formed in view of such a situation, and an object of this invention is to provide the manufacturing method of the nozzle vane which can ensure appropriate precision, without using a cutting process.

MEANS TO SOLVE THE PROBLEM In order to solve the said subject, this invention employ | adopts the following means.

This invention is a manufacturing method of the nozzle vane which has a wing | blade part and the axial part which protruded in the predetermined | prescribed cross section of the wing | blade part, The wing | blade part is formed in the metal mold | die for shaft part shaping | molding with the 1st insertion part of the shape which projected the axial part in the axial direction. And the pre-molded shaft portion of a small member having pre-molded wing portions and pre-molded shaft portions each having various dimensions and approximate dimensions, and the pre-molded shaft portion in the axial direction. The small member after the first step is inserted into a die for forming a wing part, which has a first step of pressing and shaping the shaft part, and a second insertion part having a shape in which the nozzle vane is projected in a direction substantially orthogonal to the wing surface of the wing part. And a second step of forming a wing by pressing the wing before molding in a direction substantially perpendicular to the wing surface.

In the first step of the present invention employing such a method, the pre-molding shaft portion is expanded in a direction orthogonal to the axial direction and thickened by pressing the pre-molding shaft portion in the axial direction. At this time, the shaft portion before molding is inserted into the first insertion portion of the shaft molding die, and the shaft portion before molding does not extend beyond the inner shape of the first insertion portion. Therefore, by pressing until the outer circumferential surface of the pre-molding shaft portion contacts the inner circumferential surface of the first inserting portion, the pre-molding shaft portion is plastically deformed into the same shape as the inner shape of the first inserting portion.

Moreover, the 1st insertion part has a shape which projected the axial part in the nozzle vane of a finished product to the axial direction. Accordingly, the shaft portion before molding is pressed into the first insertion portion to be shaped into the same shape as the shaft portion in the nozzle vane of the finished product.

Subsequently, in the second step of the present invention, the pre-molding wing portion is expanded in the wing surface direction by pressing the pre-molding wing portion in a direction substantially perpendicular to the wing surface. At this time, the wing | blade part before shaping | molding is inserted in the 2nd insertion part of the metal mold | die for wing part shaping | molding, and a wing | blade part before shaping | molding does not extend beyond the internal shape of a 2nd insertion part. Therefore, by pressing until the end portion of the wing portion before molding comes into contact with the inner surface of the second insertion portion, the wing portion before molding is plastically deformed into the same shape as the inner shape of the second insertion portion. The second insertion portion has a shape in which the nozzle vanes of the finished product are projected in a direction substantially perpendicular to the blade surface. Therefore, the pre-molding blade portion is pressed into the second insertion portion to be shaped into the same shape as the blade portion in the nozzle vane of the finished product.

In the present invention, the nozzle vanes each have a shaft portion protruding coaxially in opposite directions on both ends of the wing portion, and in the first step, the pair of pre-shaft shaft portions are respectively inserted into the pair of molds for forming the shaft portion, The method of pressing a shaft part before shaping | molding to an axial direction and shaping a pair of shaft part is employ | adopted.

In this invention which employ | adopts such a method, the center axis | shaft of the 1st insertion part in a pair of shaft part shaping | molding die provided in the same positional relationship with a pair of shaft part in the nozzle vane of a finished product extends to the same axis. Therefore, in the present invention, the pair of shaft portions formed by pressing the pair of pre-molding shaft portions in the axial direction extend on the same axis.

According to the present invention, the following effects can be obtained.

According to the present invention, there is an effect that a nozzle vane having an appropriate precision can be manufactured without using a cutting process.

1: A is a top view which shows the structure of the nozzle vane in this embodiment.
1B is a side view illustrating the configuration of the nozzle vane in the present embodiment.
2A is a plan view showing the configuration of the small member in the present embodiment.
2B is a side view illustrating the configuration of the small member in the present embodiment.
3: A is sectional drawing which shows the structure of the 1st shaft part shaping | molding die and 2nd shaft part shaping | molding die in this embodiment.
FIG. 3B is a view seen from the direction A in FIG. 3A.
4: A is a top view which shows the structure of the metal mold | die for wing part shaping | molding in this embodiment.
FIG. 4B is a sectional view seen from the BB line direction in FIG. 4A.
4C is a cross-sectional view seen from the CC line direction in FIG. 4A.
5 is a schematic view showing a state in which a small member is disposed in the second recessed portion.
6 is a schematic view showing molding of the first shaft portion and the second shaft portion.
7A is a plan view showing a state in which a small member is disposed in the hole for the small member.
FIG. 7B is a sectional view seen from the DD line direction in FIG. 7A.
FIG. 7C is a sectional view seen from the EE line direction in FIG. 7A.
8 is a schematic view showing the shaping of the wing section.
FIG. 9 is a schematic view showing one modification of the mold for forming the second shaft portion shown in FIG. 3A.
FIG. 10A is a cross-sectional view showing a modification of the wing forming mold shown in FIG. 4B. FIG.
FIG. 10B is a sectional view seen from the FF line direction in FIG. 10A.
FIG. 11 is a cross-sectional schematic diagram illustrating a variable displacement turbocharger provided with nozzle vanes in the present embodiment.

EMBODIMENT OF THE INVENTION Hereinafter, embodiment of this invention is described with reference to drawings.

The structure of the nozzle vane 1 and the small member 2 in this embodiment is demonstrated with reference to FIGS. 1A-2B.

1: A is a top view which shows the structure of the nozzle vane 1 in this embodiment. 1B is a side view illustrating the configuration of the nozzle vane in the present embodiment. 2A is a plan view showing the configuration of the small member 2 in the present embodiment. 2B is a side view illustrating the configuration of the small member in the present embodiment.

The nozzle vane 1 is a variable vane used in the variable displacement turbocharger 10 shown in FIG.

The variable displacement turbocharger is a supercharger capable of improving the performance of an engine (not shown) over a wide range from a low rotational region to a high rotational region. As illustrated in FIG. 11, the turbocharger rotates by the flow of exhaust gas discharged from the engine, and surrounds the rotary blade 23 to form a substantially annular shape to supply exhaust gas to the rotary blade. It has a variable nozzle 50. The variable nozzle 50 has a plurality of nozzle vanes 1 between a pair of substantially annular plate members 51 and 52 arranged to face each other. The nozzle vanes 1 are rotatably supported by the pair of plate members 51 and 52 and are provided at substantially equal intervals in the circumferential direction of the pair of plate members 51 and 52.

The flow path diameter of the variable nozzle 50 is changed by rotating the plurality of nozzle vanes 1. In order to improve the performance of the engine over a wide range from the low rotation region to the high rotation region, an appropriate flow path diameter of the variable nozzle 50 may be selected according to the engine rotation speed, that is, the flow rate of the exhaust gas discharged from the engine.

As shown in FIG. 1A, the nozzle vanes 1 have a wing 11, which is a wing-shaped member forming a substantially rectangular shape, and a first end face 12 and a second, which are sections of the wing 11 that face each other. It has the 1st shaft part 14 and the 2nd shaft part 15 which protrude in the direction opposite to the cross section 13, respectively. The nozzle vane 1 is made of a metal material that is heat resistant and plastically deformable, and the wing portion 11, the first shaft portion 14, and the second shaft portion 15 are integrally molded.

As shown in FIG. 1B, the wing portion 11 has a wing shape when viewed from the axial direction of the first shaft portion 14, and both wing surfaces of the wing portion 11 are convexly formed convex wing surfaces 16. ) And a concave wing surface 17 formed concave. The first end face 12 and the second end face 13 are planes parallel to each other. Both the first shaft portion 14 and the second shaft portion 15 are cylindrical shafts, and the second shaft portion 15 is formed longer than the first shaft portion 14.

While the nozzle vane 1 is required to be smoothly rotatable about the first shaft portion 14 and the second shaft portion 15, the first end face 12 and the second end face 13 and the aforementioned variable nozzle It is also required to reduce the leakage of the exhaust gas in the gap between the pair of plate members 51 and 52 at 50. Thus, for example, the width of the wing portion 11 in the axial direction, the orthogonality between the first end surface 12 and the second end surface 13 and the axial direction, the first shaft portion 14 and the second shaft portion 15. It is necessary to limit the diameter, the roundness, and the concentricity between the first shaft portion 14 and the second shaft portion 15 within the same appropriate precision.

The small member 2 is a member of the previous stage of the nozzle vane 1, which is formed by a pressing process described later. The pre-molded wing portion 21 and the pre-molded wing portion 21, which are wing-shaped members forming a substantially rectangular shape, are formed. Has a pre-molded first shaft portion 24 and a pre-molded first shaft portion 24 and a pre-molded second shaft portion 25, respectively protruding in opposite directions from the pre-molded first end face 22 and the pre-molded second end face 23. have. Both wing surfaces of the pre-molding wing part 21 consist of the convex wing surface 26 formed convexly and the concave wing surface 27 before shaping formed concave.

The small member 2 is molded in various dimensions approximating the various dimensions of the nozzle vane 1. More specifically, the thickness of the wing part 21 before shaping | molding is formed thicker than the thickness of the wing part 11 in the nozzle vane 1. The width of the pre-molded wing portion 21 in the axial direction of the first shaft portion 24 before molding is formed to be slightly narrower than the width of the wing portion 11, and the length of the pre-molded wing portion 21 is the wing portion ( It is formed shorter than the length of 11). The first shaft portion 24 and the second shaft portion 25 before molding are slightly thinner and longer than the first shaft portion 14 and the second shaft portion 15, respectively.

The small member 2 is molded using, for example, a casting process such as die casting or a metal powder injection molding method (metal injection molding).

Next, the structure of the 1st shaft part shaping | molding die 5, the 2nd shaft part shaping | molding die 6, and the wing shaping | molding die 7 in this embodiment is demonstrated with reference to FIGS. 3A-4C. Shall be.

3: A is sectional drawing which shows the structure of the 1st shaft part shaping | molding die 5 and the 2nd shaft part shaping | molding die 6 in this embodiment. FIG. 3B is a view seen from the direction A in FIG. 3A. 4: A is a top view which shows the structure of the metal mold | die 7 for wing part shaping | molding in this embodiment. FIG. 4B is a sectional view seen from the B-B line direction in FIG. 4A. FIG. 4C is a cross-sectional view seen from the C-C line direction in FIG. 4A.

The 1st shaft part shaping | molding die 5 and the 2nd shaft part shaping | molding die 6 are the 1st shaft part 14 and the 2nd shaft part from the 1st shaft part 24 before molding and the 2nd shaft part 25 before molding. 15) is a mold for molding each.

As shown in FIG. 3A, the first opposing face 51 and the second opposing face 61, which are planes facing each other, are formed in the first shaft forming die 5 and the second shaft forming die 6, respectively. It is. The first opposing surface 51 and the second opposing surface 61 are convex for positioning between the first shaft forming die 5 and the second shaft forming die 6 in the plane direction thereof. It has the part 52 and the recessed part 62, respectively. The convex portion 52 and the concave portion 62 are formed to be able to fit without gaps and to be detachably free from each other.

At least one of the 1st shaft part shaping | molding die 5 and the 2nd shaft part shaping | molding die 6 is connected with the drive part not shown, and the 1st shaft part shaping | molding die 5 and the 1st part are operated by operation | movement of the drive part. The biaxial molding die 6 can repeat the contact with each other.

On the first opposing surface 51, a second concave portion 53 having a depth approximately equal to the width in the axial direction of the wing portion 21 before molding is formed. The 2nd recessed part 53 has the recessed part opposing surface 54 which is a plane facing the 2nd shaft part shaping | molding die 6. The space | interval between the recessed part opposing surface 54 and the 2nd opposing surface 61 when the 1st opposing surface 51 and the 2nd opposing surface 61 abuts is the axis | shaft of the wing part 21 before shaping | molding. It is slightly wider than the width in the direction. A first hole portion (first insertion portion) 55 penetrating in the thickness direction is formed in the concave portion facing surface 54. The shape of the 1st hole part 55 seen from the penetrating direction is the same circular shape which projected the 1st shaft part 14 of the nozzle vane 1 to the axial direction, and the inner peripheral surface of the 1st hole part 55 is It has the same shape as the outer circumferential surface of the first shaft portion 14.

On the surface facing the second concave portion 53 of the second opposing surface 61, a second hole portion (first insertion portion) 65 penetrating in the thickness direction is formed. The shape of the 2nd hole part 65 seen from the penetrating direction is the same circular shape which projected the 2nd shaft part 15 of the nozzle vane 1 to the axial direction, and the inner peripheral surface of the 2nd hole part 65 is It has the same shape as the outer circumferential surface of the second shaft portion 15. In addition, when the convex part 52 fits into the recessed part 62, the 2nd hole part 65 has the same axis as the center axis of the 1st hole part 55 and the 2nd hole part 65 in the same axis. It is installed in the position to be.

A first shaft pusher 57 (see FIG. 5) is disposed on the side opposite to the second shaft molding die 6 of the first hole 55, and the first shaft portion for molding the first shaft is formed. A second pusher 67 (see FIG. 5) is disposed on the side opposite to the mold 5. The first shaft pusher 57 has a substantially cylindrical shape, and is formed to have a thickness that can be inserted into the first hole 55 without any gap. The second shaft pusher 67 has a substantially cylindrical shape, and is formed to have a thickness that can be inserted into the second hole 65 without any gap.

As shown in FIG. 4A and FIG. 4B, the wing part shaping | molding die 7 is a metal mold | die for shaping the wing | blade part 11 from the wing | blade part 21 before shaping | molding.

The wing part molding die 7 has a small member hole portion (second insertion portion) 71 which is substantially rectangular and penetrates in the thickness direction.

The inner side surface of the small member hole part 71 is the 3rd opposing surface 72 and the 4th opposing surface 73 which are a pair of plane which mutually opposes, and the 5th opposing surface 74 which is another pair of plane which opposes each other. ) And the sixth opposing surface 75. The third concave portion 76 and the fourth concave portion 77 are formed on the third opposing surface 72 and the fourth opposing surface 73, respectively. Both inner surfaces of the small member hole portion 71 including the third recessed portion 76 and the fourth recessed portion 77 are formed in parallel in the thickness direction of the wing forming die 7.

The shape of the hole 71 for the small member including the third recessed portion 76 and the fourth recessed portion 77 is similar to that of projecting the nozzle vane 1 in a direction substantially perpendicular to the convex wing surface 16. It is in substantially the same shape. In more detail, the space | interval between the 3rd opposing surface 72 and the 4th opposing surface 73 is formed equal to the width | variety of the wing part 11 in an axial direction. The interval between the fifth opposing face 74 and the sixth opposing face 75 is formed longer than the length of the wing 11. The third concave portion 76 and the fourth concave portion 77 have the same shape as the projection of the first shaft portion 14 and the second shaft portion 15 in the direction substantially orthogonal to the convex wing surface 16, respectively. The first shaft portion 14 and the fourth shaft portion 77 may be fitted with the first shaft portion 14 and the second shaft portion 15 without gaps.

The third concave portion 76 and the fourth concave portion 77 are planes that equally divide the third concave portion 76 in a direction parallel to the fifth opposing surface 74, and the fourth concave portion 77 in the direction. The plane which divides into () is provided in the position used as the same plane (plane S). The third opposing face 72 and the fourth opposing face 73 are perpendicular to the plane S. As shown in FIG.

Convex wing surface side pushers 78 (see FIGS. 7B and 7C) and concave wing surface side pushers 79 (see FIGS. 7B and 7C) are disposed on both sides of the small member hole portion 71 in the thickness direction. It is. The pressing surface of the convex wing surface side pusher 78 has the same shape as the convex wing surface 16, and the pressing surface of the concave wing surface side pusher 79 has the same shape as the concave wing surface 17. As shown in FIG.

Subsequently, the manufacturing method of the nozzle vane 1 which concerns on this embodiment is demonstrated with reference to FIGS.

5 is a schematic view showing a state where the small member 2 is disposed in the second recessed portion 53. 6 is a schematic view showing the shaping of the first shaft portion 14 and the second shaft portion 15. FIG. 7: A is a top view which shows the state in which the small member 2 was arrange | positioned in the hole part 71 for small members. FIG. 7B is a cross sectional view taken along the line D-D in FIG. 7A. FIG. 7C is a sectional view seen from the E-E line direction in FIG. 7A. FIG.

8 is a schematic diagram showing the shaping of the blade 11.

First, the small member 2 which is the member of the previous stage of the nozzle vane 1 is shape | molded.

As described above, the small member 2 is molded using, for example, a casting process such as die casting or a metal powder injection molding method.

Next, the 1st shaft part 14 and the 2nd shaft part 15 of the nozzle vane 1 are shape | molded (1st process).

As shown in FIG. 5, the first shaft forming die 5 and the second shaft forming die 6 are separated from each other by the operation of the driving unit, and the first shaft portion 24 before molding is formed in the first hole 55. ) Is inserted into the second concave portion 53 to arrange the wing portion 21 before molding. Next, the first shaft forming die 5 and the second shaft forming die 6 are brought close to each other by the operation of the driving unit, and the second shaft portion 25 is inserted into the second hole 65 before the molding. While making the first opposing surface 51 and the second opposing surface 61 abut.

In this state, the gap between the concave portion facing surface 54 and the second facing surface 61 is slightly wider than the width in the axial direction of the wing portion 21 before molding, so that the wing portion 21 before molding is removed. No pressure is applied from the die 5 for forming the first shaft portion and the die 6 for forming the second shaft portion.

Subsequently, the first shaft portion 24 before molding and the second shaft portion 25 before molding are pressed in the axial direction to plastically deform.

As shown in FIG. 6, the 1st shaft part 24 before shaping | molding and the 2nd shaft part 25 before shaping | molding are carried out from each cross-sectional side by the 1st shaft part pusher 57 and the 2nd shaft part pusher 67, respectively. Press in the axial direction.

By pressing the first shaft portion 24 before molding in the axial direction, the first shaft portion 24 before molding is expanded in a direction perpendicular to the axial direction and thickened. At this time, the first shaft portion 24 before molding is inserted into the first hole portion 55, and the first shaft portion 24 before molding does not extend beyond the internal shape of the first hole portion 55. Therefore, by pressing until the outer circumferential surface of the first shaft portion 24 before molding contacts the inner circumferential surface of the first hole portion 55, the first shaft portion 24 before molding has the same shape as the inner shape of the first hole portion 55. Plastic deformation. The inner circumferential surface of the first hole portion 55 has the same shape as the outer circumferential surface of the first shaft portion 14 in the nozzle vane 1. Therefore, before shaping | molding, the 1st shaft part 24 is pressed in the 1st hole part 55, and is shape | molded in the same shape as the 1st shaft part 14 in the nozzle vane 1.

In addition, similar to the first shaft portion 24 before molding, the second shaft portion 25 before molding also has the same shape as the second shaft portion 15 in the nozzle vane 1 by being pressed in the axial direction in the second hole 65. Is molded into.

Moreover, since the central axis of each of the first hole part 55 and the second hole part 65 extends in the same axis, the first hole part 55 and the second hole part 65 arranged in such a positional relationship. The central axes of the first shaft portion 14 and the second shaft portion 15, which are shaped by the same, also extend on the same axis.

As a result, the diameters of the first shaft portion 14 and the second shaft portion 15, the roundness, and the concentricity between the first shaft portion 14 and the second shaft portion 15 can be limited within the appropriate accuracy.

By the above, the process (1st process) of shape | molding the 1st shaft part 14 and the 2nd shaft part 15 of the nozzle vane 1 is completed.

Next, the blade part 11 of the nozzle vane 1 is shape | molded (2nd process).

As shown in FIG. 7A, the small member 2 after the said 1st process is inserted and arrange | positioned in the small member hole part 71 of the wing part shaping | molding die 7. At this time, the first shaft portion 14 and the second shaft portion 15 formed in the first process are inserted into the third concave portion 76 and the fourth concave portion 77 without any gaps. Further, a predetermined gap is formed between the first end face 22 and the third opposing face 72 before molding and between the second end face 23 and the fourth opposing face 73 before molding.

Subsequently, as shown in FIGS. 7B and 7C, the preformed wing 21 is pressed from both wing surfaces in a direction substantially orthogonal to the preformed convex wing surface 26 to plastically deform.

As shown in FIG. 8, the pre-molding wing part 21 is pressed by the convex wing surface side pusher 78 and the concave wing surface side pusher 79 on both wing surfaces.

The pre-molding wing portion 21 is expanded in the wing surface direction by pressing the pre-molding wing portion 21 on both wing surfaces in a direction substantially perpendicular to the pre-molding convex wing surface 26. At this time, the wing part 21 before shaping | molding is inserted in the hole part 71 for small members, and the wing part 21 before shaping | molding does not expand beyond the internal shape of the hole part 71 for small members. Therefore, the first cross section 22 and the second cross section 23 before the molding of the wing part 21 before the molding are the third opposing surface 72 and the fourth opposing surface 73 of the hole 71 for the small member. ), The pre-molding wing portion 21 is plastically deformed into the same shape as the inner shape of the hole 71 for the small member. Moreover, the small member hole part 71 has the shape which projected the nozzle vane 1 in the direction substantially orthogonal to the convex wing surface 16. As shown in FIG. Therefore, the pre-molding wing part 21 is pressed into the hole for 71 for small members, and is shape | molded in substantially the same shape as the wing part 11 in the nozzle vane 1.

As a result, the width | variety in the axial direction of the blade | wing part 11, or the orthogonality between the 1st end surface 12 and the 2nd end surface 13, and an axial direction can be limited within appropriate precision.

By the above, the process (2nd process) of shape | molding the blade part 11 of the nozzle vane 1 is completed.

Therefore, according to this embodiment, the following effects can be acquired.

According to this embodiment, there exists an effect that the nozzle vane 1 with an appropriate precision can be manufactured even without using a cutting process.

In addition, the operation sequence shown in the above-mentioned embodiment or all the shapes, combinations, etc. of each structural member are an example, and can be variously changed based on a process condition, a design request, etc. in the range which does not deviate from the well-known of this invention.

For example, in the above embodiment, the nozzle vane 1 is a variable vane used for the variable displacement turbocharger 10, but the present invention is not limited to this purpose, but the general vane of the general variable vane having a vane portion and an axial portion is provided. You may use for manufacture.

Moreover, in the said embodiment, although the nozzle vane 1 has the 1st shaft part 14 and the 2nd shaft part 15 which are a pair of shaft parts, even if one shaft part protrudes from the predetermined cross section of the wing part 11, good.

Moreover, in the said embodiment, when shaping | molding the 1st shaft part 14 and the 2nd shaft part 15, the 1st shaft part pusher 57 and the 2nd shaft part pusher 67 which are a pair of pushers were used, You may shape the 1st shaft part 14 and the 2nd shaft part 15 using the same structure.

FIG. 9 is a schematic view showing one modification of the mold 6 for forming the second shaft portion shown in FIG. 3A.

As shown in FIG. 9, 65 A of 2nd hole parts of 6 A of 2nd shaft part shaping | molding dies do not penetrate in the thickness direction, but have bottom surface 65B. The depth of the second hole 65A, that is, the length from the second opposing face 61 to the bottom face 65B is slightly shorter than the length of the second shaft 25 before molding. The spacing between the concave opposing face 54 and the second opposing face 61 when the convex part 52 and the concave part 62 are fitted is greater than the width in the axial direction of the wing part 21 before molding. Slightly wider.

Even with the structure shown in FIG. 9, the 1st shaft part 14 and the 2nd shaft part 15 can be shape | molded simultaneously by pressing the small member 2 with the 1st shaft part pusher 57. FIG. 9, the structure of the 1st shaft part shaping | molding die 5 and the 2nd shaft part shaping | molding die 6A may be reversed.

Moreover, in the said embodiment, when forming the wing part 11, the pair of pushers which used the convex wing surface side pusher 78 and the concave wing surface side pusher 79 were used, but it uses a structure like FIG. 10A and FIG. You may shape the part 11.

FIG. 10A is a schematic view showing a modification of the wing forming mold 7 shown in FIG. 4B. FIG. 10B is a cross sectional view taken along the line F-F in FIG. 10A. FIG.

As shown in Figs. 10A and 10B, the small member hole 71A of the 7A of the wing molding die has a bottom surface 71B without penetrating in the thickness direction. The bottom face 71B has the same shape as the concave wing surface 17 of the nozzle vane 1. Moreover, the 3rd recessed part 76 and the 4th recessed part 77 penetrate in the thickness direction as they are, in order not to pressurize the 1st shaft part 14 and the 2nd shaft part 15 at the time of pressing.

According to the structure shown to FIG. 10A and FIG. 10B, the blade part 11 can be shape | molded by pressing by the convex wing surface side pusher 78. FIG.

Moreover, in the said embodiment, since the space | interval between the 5th opposing surface 74 and the 6th opposing surface 75 of the wing part shaping | molding die 7 is formed longer than the length of the wing | blade part 11, the wing part after shaping | molding Although it is difficult to limit the length of (11) to within a high precision, the length of the blade part 11 after shaping | molding can be limited to an appropriate precision by making the said space | interval into the predetermined length of the blade part 11.

Moreover, although the wing | blade shaping | molding die 7 was used in the said embodiment, you may make the wing | blade shaping | molding die 7 common with the 1st shaft shaping | molding die 5 and the 2nd shaft shaping | molding die 6. . For example, the shape of the space formed by the 2nd recessed part 53 and 2nd opposing surface 61 shown in FIG. 3A is the same as the hole part 71 for small members shown in FIGS. 4A-4C. After forming the 1st shaft part 14 and the 2nd shaft part 15 by a 1st process, the convex wing surface side in the direction substantially orthogonal to the convex wing surface 26 before shaping | molding as it is shown in FIG. The wing | blade part 11 may be shape | molded by pushing the wing | blade part 21 before shaping | molding by the pusher 78 and the recessed wing surface side pusher 79. FIG.

Industrial availability

According to the present invention, a nozzle vane with appropriate precision can be manufactured without using a cutting process.

One… Nozzle vane
11 ... Wing
12... First section
13... Second section
14... First shaft
15... Second shaft
16... Convex wing surface
17... Concave wing surface
2… Small parts
21 ... Wing before molding
24 ... First Shaft Before Molding
25... Second Shaft Before Molding
26... Convex wing face before molding
27 ... Concave wing surface before molding
5... 1st Shaft Mold Mold
55... First hole (first insert)
6... Mold for forming second shaft
65... 2nd hole part (1st insertion part)
7 ... Wing mold
71 ... Small part insertion hole (second insertion part)

Claims (5)

A method of manufacturing a nozzle vane having a blade portion and a shaft portion protruding from a predetermined cross section of the blade portion,
A preformed wing portion and a preformed shaft portion, each of which has a plurality of dimensions approximating the wing portion and the various dimensions of the shaft portion mold in the shaft portion mold having the first insertion portion having a shape projecting the shaft portion in the axial direction. A first step of molding the shaft portion by inserting the pre-molding shaft portion of the compact member having a shape and pressing the pre-molding shaft portion in the axial direction;
The small member after the first step is inserted into a wing forming mold having a second insertion portion having a shape in which the nozzle vane is projected in a direction substantially orthogonal to the wing surface of the wing portion, and the wing before the molding is inserted into the wing portion. The manufacturing method of the nozzle vane provided with the 2nd process of shape | molding the said wing | blade part by pressing in the direction orthogonal to a surface. The method of claim 1,
The nozzle vanes, the shaft portion is protruded in the same axis in the direction opposite to the both end surfaces of the wing,
In the first step, a nozzle vane manufacturing method for inserting a pair of pre-shaft shaft portions into a pair of molds for forming the shaft portion, respectively, and pressing the pair of pre-shaft shaft portions in an axial direction to form the pair of shaft portions. The method according to claim 1 or 2,
A method of manufacturing a nozzle vane, wherein the shaft portion formed in the first step is inserted without gaps into a third recessed portion and a fourth recessed portion formed in the blade forming mold. The method according to claim 1 or 2,
A pair of pushers movable in the axial direction is used when pressing the shaft portion before molding in the axial direction, and in a direction substantially perpendicular to the blade surface when pressing the blade portion before molding in a direction substantially perpendicular to the blade surface. Method for producing nozzle vanes using a pair of movable pushers. The method according to claim 1 or 2,
When pressing the axial part before molding in the axial direction, one end of the axial part before molding is fixed to the axial molding die in the axial direction, and the pusher movable in the axial direction is not fixed in the axial direction. When pressing the said pre-molding shaft part on the other end side which is not the other end, and pressing the said pre-molding wing part in the direction orthogonal to the wing surface, the said wing part in the direction substantially orthogonal to the said wing surface when one end of the said pre-molding wing part is pressed. The manufacturing method of the nozzle vane which fixes to the shaping | molding die, and presses the pusher which is movable in the direction orthogonal to the said wing surface, to the said pre-molding wing part of the other end side which is not fixed in the direction orthogonal to the said wing surface. .

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