JP2015063930A - Process of manufacturing variable wing in vgs type turbocharger and variable wing manufactured by this process - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a new process of manufacturing capable of preventing burrs from being generated when an end surface of a wing part of a variable wing at a VGS type turbocharger is cut.SOLUTION: This invention comprises: a preparing step P1 for raw shape material for getting alloy raw material becoming an original shape of a variable wing 1 having a wing part 11 and a shaft part 12 integrally assembled; and cutting steps P2, P3 for processing the shaft part 12 of a raw shape material W into a desired diameter size and processing the end surface of the wing part 11 into a desired wing width size (h) characterized in that the raw shape material W becoming the original shape of the variable wing 1 is formed with a chamfer C having a specified inclination and a round shape at the wing end edge in advance and the wing end surface is cut under this state. In addition, the raw shape material W can be obtained through casting work and it is preferable that a casting mold for molding the raw shape material W is formed to have a chamfer in advance and the wing end edge of the wing part 11 has already been formed with the chamfer C at the step in which the raw shape material W is taken out of the casting mold.

Description

  The present invention relates to a method for manufacturing a variable wing incorporated in a turbocharger used in an automobile engine or the like, and in particular, a novel method capable of preventing burrs that have occurred during cutting of a blade end face (blade tip). It relates to a simple manufacturing method.

  For example, a turbocharger is known as a turbocharger used as a means for increasing the output and performance of an automobile engine. This turbocharger drives a turbine by engine exhaust energy, and a compressor is driven by the output of the turbine. It is a device that rotates and brings the engine to a supercharged state that exceeds natural aspiration. By the way, in this turbocharger, when the engine rotates at a low speed, the exhaust turbine hardly works due to a decrease in the exhaust flow rate. Then, the time required to blow up all at once, it was inevitable that a so-called turbo lag would occur. In addition, a diesel engine having a low engine speed originally has a drawback that it is difficult to obtain a turbo effect.

  For this reason, a VGS type turbocharger (VGS unit) has been developed that operates efficiently even in the low rotation range, and this one throttles a small exhaust flow rate with variable blades (blades), increasing the exhaust speed, and exhaust turbine. By increasing the amount of work, high output can be achieved even at low speeds. For this reason, in the VGS unit, a variable mechanism of a variable wing is required separately, and peripheral components have to be made more complicated in shape and the like than the conventional one.

For this reason, the present applicant has also earnestly researched and developed the variable wing and its variable mechanism, and has made many patent applications (see, for example, Patent Documents 1 to 3).
In these conventional manufacturing methods, the variable wing is made of an alloy material, and the shaft portion and the wing portion are integrally formed (this becomes the original shape of the variable wing and is referred to as a shape material). The burr generated at the time of cutting is removed to obtain the variable blade 1 as a finished product, and the cutting process and the burr removing process were considered to be inseparable processes.

Specifically, when the variable blade 1 'is a single-shaft type (in the case of the variable blade 1' in which the shaft portion 12 'exists only on one side of the blade portion 11'), as an example, FIG. As shown in FIG. 4, the portion of the blade end (blade end surface) on the axial pear side is cut by an end mill EM. At this time, since the material (end face of the variable blade 1 ′) is cut while rotating the end mill EM, when comparing the left and right blade end edges on which the end mill EM acts, the blade tip that drags the material is compared. Burr B as shown in the figure was generated at the edge.
Further, when the variable blade 1 'is a double shaft type (in the case of the variable blade 1' having shaft portions 12 'on both sides of the blade portion 11'), as an example, as shown in FIG. Since the cutting is performed by applying the cutting tool CT to the blade tip while rotating the variable blade 1 ′, the direction of dragging the material is approximately 180 degrees opposite to the shaft portion 12 ′ as shown in FIG. Position), and burrs B are generated at the site.
Even when the blade tip of the shaft portion 12 'of the single-shaft variable blade 1' is cut, the cutting is performed while rotating the variable blade 1 '. Burr B is generated.
Such burrs B are conventionally removed in a burr removal process such as buffing, shot blasting, or electrolytic polishing, and this process has become common technical knowledge. For this reason, in the manufacturing process of the conventional variable blade 1 ′, as shown in FIG. 7, after the major axis side cutting step (blade tip cutting) and the minor axis side cutting step (blade tip cutting), the measurement is performed. Two deburring steps (for example, buffing) were performed.

  However, the present applicant has fundamentally reviewed such technical common sense and has arrived at the present invention. That is, the present applicant can prevent burrs caused by cutting of the blade tip by devising the shape of the blank before the blade tip cutting, more specifically, by obtaining the blank. The idea has led to the present invention.

JP 2007-23840 A JP 2007-23841 A JP 2012-20318 A

  The present invention has been made in view of such a background, and has been produced in the blade cutting process in the conventional manufacturing process by devising the cross-sectional shape of the shaped material that receives blade cutting. Development of a new variable blade manufacturing method for VGS type turbochargers that prevents the generation of burrs and eliminates the two burr removal processes (for example, buffing process) that have been performed in conjunction with blade cutting. Is an attempt.

First, the manufacturing method of the variable blade in the VGS type turbocharger according to claim 1 is:
It includes a shaft portion serving as a rotation center and a wing portion that substantially adjusts the flow rate of exhaust gas,
A relatively small amount of exhaust gas discharged from the engine is appropriately throttled, the speed of the exhaust gas is amplified, the exhaust turbine is rotated by the energy of the exhaust gas, and air that exceeds natural intake is sent to the engine by a compressor directly connected to this exhaust turbine. In a method of manufacturing variable wings incorporated in a VGS type turbocharger that allows the engine to exhibit high output even at low speed rotation,
The process includes a step of preparing a base material to obtain an alloy material that is the original shape of a variable wing including at least a wing and a shaft.
The shaft portion of the base material is processed to have a desired diameter and thickness, and the end surface of the blade portion is processed to a desired blade width dimension,
The original shape of the variable wing is characterized in that a constant inclination or a rounded chamfer is formed at the wing tip edge and the blade tip surface is cut in this state. is there.

In addition to the requirement of claim 1, the method of manufacturing the variable blade in the VGS type turbocharger according to claim 2
The base material is obtained by casting, and the chamfering process is already performed on the mold into which the base material is cast, and the chamfer is already formed at the blade edge of the wing portion when the base material is removed from the mold. It is characterized by that.

In addition to the requirement described in claim 1 or 2, the method for manufacturing a variable blade in a VGS type turbocharger according to claim 3
The chamfer formed on the blade edge of the shaped member is a constant inclined chamfer, and the angle is an inclined surface of 45 degrees.

In addition to the requirement described in claim 1, 2 or 3, the method for manufacturing the variable blade in the VGS type turbocharger according to claim 4
The variable wing is a double-shaft type having shaft portions on both sides of the wing portion.

The variable wing in the VGS type turbocharger according to claim 5 is:
It includes a shaft portion serving as a rotation center and a wing portion that substantially adjusts the flow rate of exhaust gas,
A relatively small amount of exhaust gas discharged from the engine is appropriately throttled, the speed of the exhaust gas is amplified, the exhaust turbine is rotated by the energy of the exhaust gas, and air that exceeds natural intake is sent to the engine by a compressor directly connected to this exhaust turbine. In a variable wing incorporated in a VGS type turbocharger that allows the engine to exhibit high output even at low speed rotation,
It is manufactured by the manufacturing method according to claim 1, 2, 3 or 4.

The above-described problems can be solved by using the configuration of the invention described in each of the claims.
According to the first or fifth aspect of the present invention, since the blade tip is cut in a state where a constant inclination or an R-shaped chamfer is formed on the blade tip edge of the blade portion of the shaped material, burrs are generated by the cutting. Can be prevented. Conventionally, since chamfering was not particularly performed on the blade edge, a subsequent burr removal process (for example, buffing) was considered inseparable for this type of end face cutting. This makes it possible to eliminate the burrs removal process.
If the chamfer formed on the blade tip edge is a chamfer with a constant inclination, the angle of the inclined surface (chamfer) formed on the blade edge is not changed (constant) depending on the cutting position, and burrs are generated. Can be effectively prevented (the effect of suppressing the generation of burrs is increased), which is desirable. On the other hand, if the chamfering formed on the blade tip edge is an R-shaped chamfer, the angle formed by the cutting surface and the tangential direction of the R surface (chamfering) changes depending on the cutting position, so that burr generation is suppressed. Although the effect may be somewhat reduced, if the cutting position is set appropriately, the same burr suppression effect as that obtained when the above-described constant chamfering is formed can be obtained.

  Further, according to the invention described in claim 2 or 5, since a constant slope or a rounded chamfer is already formed on the blade edge of the wing portion at the stage of removing the shaped material from the mold, after obtaining the shaped material. There is no need for chamfering separately after casting (that is, after casting), and the variable blade can be manufactured efficiently.

  Further, according to the third or fifth aspect of the present invention, the specific configuration of chamfering formed on the blade tip edge of the wing portion is actualized. In addition, since 45 degree chamfering is a very general chamfering, it becomes easy to perform the chamfering process performed on the mold even when the raw material is obtained by casting.

  Further, according to the invention described in claim 4 or 5, since the variable blade is of the double shaft type, the blade cutting on the long axis side and the blade tip cutting on the short shaft side are performed while rotating the variable blade. That is, it becomes the same cutting mode and is easy to perform processing. On the other hand, when the variable blade is a single-shaft type, the blade tip cutting without the shaft portion is a process in which the variable blade is applied to the rotating end mill, and the processing mode is different.

FIG. 4 is a perspective view (a) showing an example of a VGS type turbocharger incorporating variable blades according to the present invention, and an exploded perspective view (b) showing an example of an exhaust guide assembly. It is a front view, a left side view, and a right side view of a variable wing (reference plane ant) according to the present invention. It is the front view of the other variable wing | blade (reference surface pear) which concerns on this invention, and a right view. It is a flowchart which shows the manufacturing process of a variable wing | skeleton skeleton. Blade portion when chamfering with constant slope is formed at the blade tip edge, explanatory diagram (a) showing the state of blade tip cutting in that case, and blade tip cutting when R-shaped chamfering is formed at the blade tip edge It is explanatory drawing (b) which shows the mode of. Cutting of the blade end surface on the axial pear side of a conventional single-shaft type variable blade, an explanatory diagram (a) showing the state of burrs generated at this time, and cutting of the blade end surface of a conventional double-shaft type variable blade It is explanatory drawing (b) which shows a mode that it does, and the mode of the burr | flash which arises in this case. It is a flowchart which shows the manufacturing process of the conventional variable shaft of a double shaft type (when a reference plane is formed in the front-end | tip of a long shaft part) skeleton.

  The mode for carrying out the present invention includes one described in the following embodiments, and further includes various methods that can be improved within the technical idea.

  In the description, while explaining the exhaust guide assembly A of the VGS unit to which the variable blade 1 according to the present invention is applied, the variable blade 1 will be described together, and then the method for manufacturing the variable blade will be described.

  The exhaust guide assembly A adjusts the exhaust gas flow rate by appropriately narrowing the exhaust gas G particularly when the engine is running at a low speed. As shown in FIG. 1, as an example, the exhaust guide assembly A is provided on the outer periphery of the exhaust turbine T and substantially exhausts. A plurality of variable blades 1 for setting the flow rate, a turbine frame 2 for rotatably holding the variable blades 1, and a variable mechanism 3 for rotating the variable blades 1 at a constant angle so as to appropriately set the flow rate of the exhaust gas G. It is made up of. Each component will be described below.

  First, the variable blade 1 will be described. As an example, as shown in FIG. 1, a plurality of these are arranged in an arc shape along the outer periphery of the exhaust turbine T (approximately 10 to 15 with respect to one exhaust guide assembly A). The exhaust gas flow is adjusted by rotating approximately the same degree. The variable wing 1 includes a wing portion 11 and a shaft portion 12, which will be described below.

  First, the blade portion 11 is formed to have a constant width mainly in accordance with the width dimension of the exhaust turbine T. The cross section in the width direction is formed into an airfoil shape so that the exhaust gas G can be effectively exhausted. It is configured to go to the turbine T. Here, as shown in FIG. 1B, the width dimension of the wing part 11 is defined as a wing width h for convenience. Further, as shown in FIG. 2, the thick edge in the airfoil cross section of the wing part 11 is the leading edge 11a, the thin edge is the trailing edge 11b, and the length from the leading edge 11a to the trailing edge 11b is as follows. The chord length is L. Furthermore, the wing portion 11 is formed with a flange portion 13 having a diameter slightly larger than that of the shaft portion 12 at a boundary portion (connection portion) with the shaft portion 12. The bottom surface (seat surface) of the flange portion 13 is formed on substantially the same plane as the end surface of the blade portion 11, and this plane becomes a seat surface when the variable blade 1 is attached to the turbine frame 2. It is responsible for regulating the position in the width direction (direction of the blade width h).

  On the other hand, the shaft portion 12 is formed integrally with the wing portion 11 and serves as a rotation shaft when the wing portion 11 is moved. In the present embodiment, a so-called dual-support type variable wing 1 in which shaft portions 12 are mainly formed on both sides of the wing portion 11 is illustrated, and when these shaft portions 12 are shown separately, Due to the axial length, the major axis portion 12a and the minor axis portion 12b are distinguished for convenience. Incidentally, the variable wing 1 of such a double shaft type is more stable in operation than the so-called single-shaft type (cantilever type) in which the shaft portion 12 is formed on only one of the wing portions 11. This is effective in that (rotational stability), strength, and the like can be improved.

Further, as shown in FIG. 2B, for example, a sliding step 14 having a diameter somewhat larger than the shaft diameter is partially formed on the long shaft portion 12a and the short shaft portion 12b. This is a surface that comes into contact with a bearing portion of the turbine frame 2 (a receiving hole 25 of the turbine frame 2 to be described later) when the variable blade 1 is rotated, thereby sliding when the variable blade 1 is rotated. Resistance (friction resistance) is suppressed, and stable operation (rotation) of the variable blade 1 is achieved. Since the variable blade 1 is repeatedly used in a severe environment of high temperature and exhaust gas atmosphere, the suppression of the sliding resistance by the sliding step 14 further stabilizes the opening / closing operation in such a severe environment. It is.
Further, the sliding step 14 does not necessarily need to be formed in a convex shape having a larger diameter than the shaft portion 12 serving as the base, and from the viewpoint of partial contact with the bearing portion, for example, as shown in FIG. A part of the shaft portion 12 is formed in a concave shape (here, the base of the flange portion 13 in the short shaft portion 12b is formed in a neck shape), and the shaft portion 12 serving as the base portion is configured to be in partial contact with the bearing portion. Such a partial contact portion also becomes a substantial sliding step 14. Incidentally, the sliding step 14 is not necessarily an essential component in the variable wing 1.

Further, a reference surface 15 serving as a reference for the mounting state of the variable wing 1 is formed on the distal end side of the long shaft portion 12a. The reference surface 15 is a part fixed to the variable mechanism 3 to be described later by caulking or the like, and as an example, as shown in FIGS. . However, the reference surface 15 is not necessarily formed as two opposing flat surfaces, but may be formed as four flat surfaces having a rectangular cross section or a square cross section. In short, as long as the posture (mounting posture) of the variable blade 1 can be regulated. Various forms are possible.
Incidentally, such a reference surface 15 is not necessarily an essential component, and may not be formed by the variable structure of the variable blade 1 (see, for example, FIG. 3).

Next, the turbine frame 2 will be described. This is configured as a frame member that rotatably holds a plurality of variable blades 1. As an example, as shown in FIG. 1, the variable blade 1 (blade) is constituted by a frame segment 21 and a holding member 22. Part 11). The frame segment 21 includes a flange portion 23 that receives the long shaft portion 12a of the variable wing 1 and a boss portion 24 that externally fits the variable mechanism 3 described later. With this structure, the same number of receiving holes 25 as the variable blades 1 are formed at equal intervals in the peripheral portion of the flange portion 23.
Further, as shown in FIG. 1, the holding member 22 is formed in a disc shape having a hole in the center portion. In this embodiment, the variable wing 1 is a double-shaft type. A receiving hole 25 for receiving the short shaft portion 12b of the blade 1 is equally arranged.
The dimension between the two members is substantially constant (generally the blade of the variable blade 1 so that the variable blade 1 (wing portion 11) sandwiched between the frame segment 21 and the holding member 22 can be rotated smoothly at all times. As an example, the dimensions between the two members are maintained by caulking pins 26 provided at four locations on the outer peripheral portion of the receiving hole 25. Here, a hole opened in the frame segment 21 and the holding member 22 to receive the caulking pin 26 is referred to as a pin hole 27.

  In this embodiment, the flange portion 23 of the frame segment 21 is composed of two flange portions, that is, a flange portion 23A having substantially the same diameter as the holding member 22 and a flange portion 23B having a diameter somewhat larger than the holding member 22. These are formed with the same member, but when it is difficult to form with the same member, two flange parts with different diameters are formed separately, and later by caulking or brazing, etc. It is also possible to join.

  Next, the variable mechanism 3 will be described. This is provided on the outer peripheral side of the boss portion 24 of the turbine frame 2 and rotates the variable blade 1 in order to adjust the exhaust flow rate. As an example, as shown in FIG. A rotating member 31 that causes the variable blade 1 to rotate and a transmission member 32 that transmits the rotation to the variable blade 1 are provided. As shown in the drawing, the rotating member 31 is formed in a substantially disk shape with a hole in the center portion, and the same number of transmission members 32 as the variable blades 1 are arranged at the peripheral portion thereof. The transmission member 32 includes a drive element 32A that is rotatably attached to the rotating member 31, and a passive element 32B that is fixedly attached to the reference surface 15 of the variable wing 1 by caulking or the like. The rotation is transmitted in the engaged state in which the drive element 32A and the passive element 32B are connected. Specifically, a square piece drive element 32A is rotatably pinned to the rotating member 31, and the reference surface 15 of the variable blade 1 is press-fitted into the passive element 32B and caulked. Here, the passive element 32B is formed in advance with a substantially U-shaped portion that can receive the drive element 32A, and by engaging the square-shaped drive element 32A in this part, The rotating member 31 is attached to the boss portion 24.

In the initial state where a plurality of variable blades 1 are attached, in order to align them in a circumferential shape, each variable blade 1 and the passive element 32B must be attached at a substantially constant angle. Primarily, the reference surface 15 of the variable wing 1 performs this function. Further, if the rotating member 31 is simply fitted into the boss portion 24, there is a concern that when the rotating member 31 is slightly separated from the turbine frame 2, the engagement of the transmission member 32 is released. For this reason, in order to prevent this, the ring 33 etc. are provided so that the rotation member 31 may be pinched | interposed from the opposite side of the turbine frame 2, and the pressing tendency to the turbine frame 2 side is provided with respect to the rotation member 31. .
With such a configuration, when the engine rotates at a low speed, the rotation member 31 of the variable mechanism 3 is appropriately rotated and transmitted to the shaft portion 12 via the transmission member 32. The variable vane 1 is rotated as shown in FIG. 1A, and the exhaust gas G is appropriately throttled to adjust the exhaust gas flow rate.

An example of the exhaust guide assembly A to which the variable vane 1 according to the present invention is applied is configured as described above. Hereinafter, a method for manufacturing the variable vane 1 will be described with reference to FIG.
The variable wing 1 according to the present invention is processed from the raw material W into a final product (variable wing 1) by the following steps (1) to (5).
(1) Preliminary material preparation process P1
(2) Cutting step P2 on the long axis side (including blade cutting on the long axis side)
(3) Short axis side cutting process P3 (including short axis side blade tip cutting)
(4) Two-sided cutting process (reference surface cutting process) P4
(5) Barrel polishing process

(1) Preliminary material preparation process P1
This step is a step of preparing a raw material W (original shape of the variable wing 1) in which the wing portion 11 and the shaft portion 12 are integrally formed of an alloy material. As an example, a precision casting method represented by lost wax is used. Applied. Of course, in this step, casting is performed so that the raw material W has a volume (volume) that can realize the target variable blade 1, but the subsequent cutting process is reduced as much as possible. It is preferable that the raw material W is brought close to the final product state (so-called near net shape state).
In addition, it is preferable that a chamfering C (here, a chamfering C having a constant slope) is formed on the blade tip edge, as shown in FIG. In this case, it is desirable to chamfer the mold for casting the raw material W (the part where the blade tip edge is formed). As a result, chamfering C can be formed at the blade tip edge of the shaped member W simultaneously with casting. For example, it is not necessary to perform chamfering separately after casting, and the variable blade 1 can be manufactured more efficiently.

Incidentally, the chamfering C formed on the blade tip edge of the wing part 11 is not necessarily limited to the chamfering C having a constant inclination (for example, an inclined surface of 45 degrees), and as shown in FIG. 5B. In addition, an R-shaped chamfer C may be formed in a sectional view. Here, “R shape” is described in this specification when rounded chamfering (round shape) is always formed with a constant diameter when the blade edge is rounded. In addition to this, for example, it also includes an elliptical (oval) shape whose diameter dimension gradually changes in a sectional view. Further, as the chamfering C formed on the blade tip edge, for example, one that gradually changes from a certain inclined surface (an inclined straight line in a sectional view) to an R shape, that is, a combination of the C surface and the R surface, etc. It is included.
Moreover, in obtaining the raw material W, it is not necessarily limited to casting (precision casting), but can also be obtained by metal injection molding. In this case as well, the raw material W ( It is preferable to form a chamfer C on the blade edge. Furthermore, as another method for obtaining the raw material W, it is also possible to obtain it by blanking. In this case, for example, a volume capable of realizing the target variable blade 1 from a metal plate having an appropriate thickness is provided. It is possible to form a chamfer C at the blade tip edge by appropriately forging the punched blank material.

(2) Long axis side cutting process P2
This step is mainly a step of cutting the diameter of the long shaft portion 12a to a desired size, but is also a step of cutting the blade tip on the long shaft side. Specifically, while rotating the variable blade 1, the cutting tool CT is moved along the axial direction of the long shaft portion 12a to cut the long shaft portion 12a to a desired diameter. At this time, if the variable blade 1 has the sliding step 14, the sliding step 14 is also formed. Thereafter, the cutting tool CT is moved along the blade tip surface with respect to the rotating variable blade 1, and the blade end surface on the long axis side is cut. In the present invention, when this blade tip cutting is performed, a burr B is not generated at the blade tip edge because a constant slope or an R-shaped chamfer C is already formed at the blade tip edge at the stage of the shaped material W. Is. Therefore, the burr removal process (buffing or the like) conventionally performed after this process can be eliminated.

Incidentally, as the chamfering C formed on the blade tip edge of the wing part 11, the chamfering C having a constant inclination is preferable to the chamfering C having the R shape, and this will be described below.
For example, when a chamfer C having a constant slope is formed at the blade edge of the raw material W, as shown in FIG. 5A as an example, the inclination angle of the chamfer C is changed even if the cutting position (cutting allowance) changes. Since (here, 45 degrees) is constant, burrs B are very unlikely to occur. On the other hand, when the R-shaped chamfer C is formed at the blade edge of the shaped member W, as shown in FIG. 5B, for example, when the cutting position (cutting allowance) is changed, the R surface ( Since the angle formed between the tangential direction and the cutting surface in the R-shaped chamfer C) changes (because it varies), the burr B suppressing effect can be somewhat reduced. However, even when an R-shaped chamfer C is formed at the blade edge, if the cutting position is properly set, the same burr suppressing effect as that obtained when the constant chamfer C is formed can be obtained. It is.

(3) Short axis side cutting process P3
As shown in FIG. 4 as an example, this step is a step of mainly cutting the diameter of the short shaft portion 12b to a desired size, but is also a step of cutting the blade tip on the short shaft side. In this step, the tip of the short shaft portion 12b is also cut to form the short shaft portion 12b in a desired length. Specifically, for example, the tip of the short shaft portion 12b is applied to the rotated end mill EM, the short shaft portion 12b is cut to a desired length, and then the bite CT is rotated while the variable blade 1 is rotated. It moves along the axial direction of 12b, and the short shaft portion 12b is cut to a desired diameter. At this time, if the variable blade 1 has the sliding step 14, the sliding step 14 is also formed. Thereafter, the cutting tool CT is moved along the blade tip surface with respect to the rotating variable blade 1, and the blade tip surface on the short axis side is cut. In the present invention, in this blade cutting as well as the long axis side, a constant slope or an R-shaped chamfer C is already formed on the blade edge at the stage of the shaped material W. Burr B is not generated. Therefore, here again, the burr removing step that has been conventionally performed after this step can be eliminated.

(4) Two-sided cutting process (reference surface cutting process) P4
This step is a step (cutting step) performed when the variable blade 1 includes the reference surface 15 at the tip of the shaft portion 12 (long shaft portion 12a). Here, along with the formation (cutting) of the reference surface 15, the tip of the long shaft portion 12a is also cut, whereby the long shaft portion 12a is formed in a desired length dimension. Incidentally, when the variable blade 1 originally does not have the reference surface 15, the tip of the long shaft portion 12 a is also cut in the long-axis-side cutting step P <b> 2 described above to form the portion to a desired length. .
In addition, here, the reference surface 15 is formed as two opposing flat surfaces in the long axis portion 12a, but the reference surface 15 is not necessarily limited to this as described above. In this case, this process is a four-surface cutting process (the reference surface cutting process is not changed).

(5) Barrel polishing step This step is a step of polishing the entire surface of the variable wing 1 (original material W) that has finished the two-face cutting step P4. For example, the variable wing 1 and an additive called a medium are added. The surface of the variable blade 1 is finished by colliding the variable blade 1 and the medium by putting it in a barrel container and rotating or vibrating the barrel container.

1 Variable blade 2 Turbine frame 3 Variable mechanism

DESCRIPTION OF SYMBOLS 1 Variable wing | blade 11 Blade | wing part 11a Leading edge 11b Trailing edge 12 Shaft part 12a Long shaft part 12b Short shaft part 13 Ridge part 14 Sliding level | step difference 15 Reference surface

2 Turbine frame 21 Frame segment 22 Holding member 23 Flange part 23A Flange part (small)
23B Flange (Large)
24 Boss portion 25 Receiving hole 26 Caulking pin 27 Pin hole

3 Variable Mechanism 31 Rotating Member 32 Transmission Member 32A Drive Element 32B Passive Element 33 Ring

h Blade width A Exhaust guide assembly B Burr (Burn at blade tip cutting)
C Chamfering G Exhaust gas L Chord length T Exhaust turbine W Shape material CT Bit EM End mill

P1 Preliminary material preparation process P2 Long axis side cutting process P3 Short axis side cutting process P4 Two-sided cutting process (reference surface cutting process)

Claims (5)

It includes a shaft portion serving as a rotation center and a wing portion that substantially adjusts the flow rate of exhaust gas,
A relatively small amount of exhaust gas discharged from the engine is appropriately throttled, the speed of the exhaust gas is amplified, the exhaust turbine is rotated by the energy of the exhaust gas, and air that exceeds natural intake is sent to the engine by a compressor directly connected to this exhaust turbine. In a method of manufacturing variable wings incorporated in a VGS type turbocharger that allows the engine to exhibit high output even at low speed rotation,
The process includes a step of preparing a base material to obtain an alloy material that is the original shape of a variable wing including at least a wing and a shaft.
The shaft portion of the base material is processed to have a desired diameter and thickness, and the end surface of the blade portion is processed to a desired blade width dimension,
The base material that is the original shape of the variable wing is formed with a constant slope or a rounded chamfer at the blade tip edge, and the blade tip surface is cut in this state. Manufacturing method of variable wing in type turbocharger.
The base material is obtained by casting, and the chamfering process is already performed on the mold into which the base material is cast, and the chamfer is already formed at the blade edge of the wing portion when the base material is removed from the mold. The method for manufacturing a variable wing in a VGS type turbocharger according to claim 1, wherein the variable wing is manufactured as described above.
3. The variable wing in a VGS type turbocharger according to claim 1, wherein the chamfer formed on the blade tip edge of the shaped member is a chamfer with a constant slope, and the angle thereof is a slope of 45 degrees. Manufacturing method.
4. The method of manufacturing a variable wing in a VGS type turbocharger according to claim 1, wherein the variable wing is of a double shaft type having shaft portions on both sides of the wing portion.
It includes a shaft portion serving as a rotation center and a wing portion that substantially adjusts the flow rate of exhaust gas,
A relatively small amount of exhaust gas discharged from the engine is appropriately throttled, the speed of the exhaust gas is amplified, the exhaust turbine is rotated by the energy of the exhaust gas, and air that exceeds natural intake is sent to the engine by a compressor directly connected to this exhaust turbine. In a variable wing incorporated in a VGS type turbocharger that allows the engine to exhibit high output even at low speed rotation,
A variable wing manufactured by the manufacturing method according to claim 1, 2, 3, or 4.

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