JP2001073787A - Exhaust volume adjustment system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide exhaust volume adjustment system that is stable in operation and rich in durability by reducing number of components and simplifying structure. SOLUTION: This exhaust volume adjustment system is provided with plural circular concaves 2c each at equal angle either at inner circumference of mounting base material 2B or outer circumference of nozzle base materials 2A of base material 2 comprising nozzle base material 2A press fitted into inner circumference of mounting base material 2B which is equipped with first flange 2a at one end and second flange 2b at the other. Then, wing part 3A which makes up a movable vane provided with a face crossing at right angles with surface of first flange 2a is arranged on top of first flange 2a, and at same time, a part of operating link 3B arranged on top of second flange 2b connecting through concave part 2c from this wing part 3A is linked with connecting part (concave part 4a) of operating plate 4 whose inner circumference is fitted in free rotation to outer circumference of nozzle base material 2A.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a displacement control mechanism which can reduce the number of parts, simplify the structure, operate stably, and is excellent in durability.

[0002]

2. Description of the Related Art In a diesel engine, purification of exhaust gas, that is, reduction of harmful substances such as nitrogen oxides (NOx) and particulate matters is an environmental problem. On the other hand, in diesel engines, in order to improve dynamic performance such as high torque and high output, a turbine is driven by exhaust gas, and the turbine drives an air compressor to supply a large amount of intake air to the engine. There is a case where a so-called turbocharger is mounted to increase the combustion amount of the fuel cell to improve the output.

[0003] The details of the turbocharger will not be described here because it is a well-known technology. However, as a means for improving the power performance while responding to the above-mentioned demands on a diesel engine, a conventional turbocharger has been used. The charger is equipped with a displacement adjusting mechanism having variable vanes to adjust the displacement from the engine.

As shown in FIG. 7, the above-mentioned displacement adjusting mechanism 51 is provided with a turbine housing 6 of a turbocharger 60 provided in an intake pipe E1 to an engine E and an exhaust pipe E2.
1, it is provided outside a turbine blade 63 provided at one end of the shaft 62. In FIG. 7, reference numeral 64 denotes a compressor impeller provided at the other end of the shaft 62.

[0005] The conventional displacement adjusting mechanism 51 is configured as shown in FIGS. 8 and 9. That is, 52 is a base material formed in a short tubular shape and having the first flange surface 52a formed at an end thereof. The turbine blade 63 described above is coaxially fitted inside the inner diameter of the base material 52.

[0006] On the opposite side of the base material 52 where the first flange surface 52a is formed, a second flange surface 52b is formed.
Are formed. From the first flange surface 52a, the second
Through holes 52c are formed over the flange surface 52b by the number of variable wing members 53 described later. The first flange surface 52a is provided with a cover 52d for protecting a variable wing member 53 described later.

An insertion part 53a is inserted into the through-hole 52c so as to protrude from the first flange surface 52a and is orthogonal to the first flange surface 52a. This is a variable wing member whose inclination angle can be changed from the center of the base material 52 so as to extend radially or along an arc. The insertion portion 53a is formed by expanding a diameter of a portion of the variable wing member 53 opposite to a surface on which the surface is formed by a drill, and caulking in a hole 54a of an operation link 54 described later.

Reference numeral 54 denotes operating links provided on the second flange surface 52b by the number of the variable wing members 53. The variable wing members penetrating the base material 52 extend over the front and back surfaces of the operating link 54. A hole 54 a through which the insertion portion 53 a of the 53 is penetrated is formed, and a surface opposite to the direction in which the variable wing member 53 is located at the other end of the operation link 54 is provided with an engagement hole 55 a of an operation plate 55 described later. A projection 54b to be fitted is formed.

The insertion portion 53a of the variable wing member 53 that has penetrated the hole 54a of the operation link 54 is integrated with the operation link 54 by caulking the penetrated end, whereby the variable wing member 53, the base material 52, Since the operating link 54 is integrated and the penetrating end of the insertion portion 53a is enlarged by a drill and caulked, the angle of the surface of the variable wing member 53 is changed with the operation of the operating link 54. It has become so.

Reference numeral 55 denotes an eccentric long hole-shaped engagement member in which the center of one substantially circular plate is fitted to the end of the base material 52 and the projection 54b of the operation link 54 is fitted on the circular arc. Hole 55
a is formed, and an operating portion 55
b is the working plate formed.

In the displacement adjusting mechanism 51 having the above-described structure, by driving an operation actuator (not shown) connected to the operation portion 55b of the operation plate 55, the operation plate 55 rotates by a predetermined angle. The side of the link 54 on which the protrusion 54b is formed rotates and the operation link 54
The side on which the hole 54a is formed also rotates, whereby the insertion portion 53a rotates axially and the angle of the movable wing member 53 is changed. Then, the displacement adjusting mechanism 5 driven in this manner.
By providing 1, the displacement of the turbocharger 60 is adjusted, and suitable engine performance can be obtained.

[0012]

However, the conventional displacement adjusting mechanism 51 shown in FIG. 8 and FIG.
Since the high-precision through-hole 52c is formed to insert the insertion portion 53a of the variable wing member 53 in the above, it takes time and effort to form the through-hole 52c when manufacturing the displacement adjusting mechanism 51. And the insertion portion 53a are fitted with high precision, so that there is a problem that seizure occurs due to adhesion of dust and the like contained in exhaust gas and durability is poor.

Further, the conventional displacement adjusting mechanism 51 has a structure in which the operating link 54 is provided at the insertion portion 53a in the variable wing member 53.
a (variable wing member 53) and the actuation link 54 require a plurality of parts, so that the number of parts and the number of assembly steps increase,
Further, high processing accuracy is required in the same manner as described above, and it is troublesome to determine the mounting position (angle) between the variable wing member 53 and the operation link 54 with high accuracy.

Further, in the conventional displacement adjusting mechanism 51, there is the same problem as described above between the engagement hole 55a of the operation plate 55 and the projection 54b of the operation link 54.

As described above, the conventional displacement adjusting mechanism 51
Requires a high degree of machining accuracy to withstand the use of the turbocharger in harsh conditions, which increases labor and costs, and in addition, requires a large number of parts and a complicated structure. Therefore, it takes a long time to complete the process, and therefore, the production efficiency is reduced and the cost is increased.

The present invention has been made to solve the above-mentioned problems, and provides a displacement control mechanism which can reduce the number of parts, simplify the structure, operate stably, and have excellent durability. The purpose is to do.

[0017]

In order to achieve the above-mentioned object, the present invention provides an arc-shaped concave portion for a substrate and an operating plate which have been perforated by a conventional displacement adjusting mechanism. In order to reduce the number of parts by integrating the variable wing member and the operating link consisting of multiple parts with the conventional displacement adjustment mechanism, The insertion portion of the variable wing member, which had been made linear by the mechanism, was formed with a small-diameter portion in the middle thereof to reduce the portion requiring shaft machining accuracy. By selectively or all adopting these,
The number of parts can be reduced, the structure can be simplified, and the operation stability and durability can be improved.

[0018]

A displacement adjusting mechanism according to a first aspect of the present invention includes a mounting base material having a short tube having a first flange formed at one end and a second flange formed at the other end. A plurality of arc-shaped concave portions are formed at an equal angle on the inner peripheral side of the mount substrate or on the outer peripheral side of the nozzle substrate, respectively, of the substrate provided with the nozzle substrate pressed into the inner peripheral surface of the mount substrate. A wing portion forming a variable wing vane having a surface orthogonal to the surface of the first flange is arranged on the first flange, and one of the operating links arranged on the second flange by passing a concave portion from the wing portion and passing through a concave portion. The part is rotatably fitted on the outer peripheral part of the nozzle base material with the engaging part of the operation plate whose inner peripheral part is externally fitted.

By doing so, when the nozzle base material is pressed into the mount base material, the open portion of the concave portion is closed,
As a result, the recess functions as a hole. In other words, if the concave portion is formed on the inner peripheral side of the mount substrate or the outer peripheral side of the nozzle substrate, the drilling process becomes unnecessary, and the area for finishing by the reaming process is reduced, thereby simplifying the manufacturing operation. Can be.

Further, according to a second aspect of the present invention, in the above structure, the displacement adjusting mechanism is provided on the first flange and forms a variable vane vane having a surface orthogonal to the surface of the first flange. And a rod-shaped portion formed from the wing portion so as to fit into the concave portion in the direction of the second flange, a connecting portion formed continuously from the rod-shaped portion in a direction parallel to the surface of the second flange, and the connection And an operation link having a projection formed in a direction perpendicular to the surface of the second flange continuously from the portion.

As described above, by integrally forming the wing portion and the operating link, the number of parts can be reduced, and the number of assembling steps involved can be reduced. No need to determine the angle to the link,
Therefore, labor can be further reduced.

According to a third aspect of the present invention, there is provided a displacement adjusting mechanism according to any one of the first to third aspects, wherein a part of the operation link is engaged with an outer peripheral portion extending over the front and back surfaces of the operation plate. And an operating portion is formed in a part of the outer peripheral portion.

By doing so, the strength against thermal distortion can be improved and the workability can be improved as compared with the case where the working plate is perforated.

Further, according to a fourth aspect of the present invention, in the displacement adjusting mechanism according to any one of the above structures, the intermediate portion of the portion of the operating link that is inserted into the concave portion has a small diameter portion.

By doing so, the small diameter portion does not come into contact with the surface of the concave portion, so that precision finishing is not required, the time is shortened by that amount, and the occurrence of image sticking can be prevented. .

[0026]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the displacement adjusting mechanism of the present invention will be described below with reference to FIGS. 1 and 2
1 shows a schematic configuration of a displacement adjusting mechanism of the present invention. FIG.
Shows a substrate portion in the displacement adjusting mechanism of the present invention.
FIG. 4 shows a variable vane operating link portion in the displacement adjusting mechanism of the present invention. 5 and 6 show an operation plate portion in the displacement adjusting mechanism of the present invention.

In FIG. 1 to FIG. 6, reference numeral 1 denotes a displacement adjusting mechanism of the present invention which is mounted on a turbocharger (not shown) and has a variable vane type vane for adjusting the displacement for rotating a turbine blade. , Are configured as follows.

Numeral 2 denotes a short base material. As shown in FIG. 2, the base material 2 includes a nozzle base material 2A constituting an inner peripheral portion, and the nozzle base material 2A And a mounting base material 2B press-fitted into the portion.

The mounting base 2B has a first flange 2a formed at one end thereof and a second flange 2a formed at the other end thereof.
b is formed. Further, in this embodiment, the mount base 2B has a plurality of arc-shaped concave portions 2c formed at an equal angle on an inner peripheral surface extending from the first flange 2a to the second flange 2b. In this mount base 2B, a first flange 2a, a second flange 2b, and a recess 2c are integrally formed.

As shown in FIG. 3, when the nozzle base 2A is pressed into the inner periphery of the mount base 2B, the open side of the recess 2c of the mount base 2B is closed by the outer periphery of the nozzle base 2A. . Therefore, the nozzle substrate 2A and the mount substrate 2
As a result of assembling B, the concave portion 2c functions as a hole. With this configuration,
The perforation step can be omitted.

As shown in FIG. 4, the wing part 3A constituting the variable wing vane is integrally provided on one end with an operating link 3B for changing the surface angle of the wing part 3A on the other end. It is a variable wing vane operating link formed. In the variable vane vane operation link 3, the wing portion 3A forming one end is disposed on the first flange 2a such that its surface is orthogonal to the surface of the first flange 2a, and the angle of this surface is actuated. It is changed by driving the link 3B.

In the variable vane vane operating link 3, the operating link 3B at the other end is connected to the first flange 2a.
A rod-like portion 3a fitted into the recess 2c from the side to the second flange 2b, and a second flange 2b from the end of the rod-like portion 3a.
3b formed in parallel with the second flange 2b, and a projection 3 formed perpendicularly to the second flange 2b from the end of the connection 3b.
c.

A small-diameter portion 3d having a reduced diameter is formed in the middle of the rod-shaped portion 3a, and the small-diameter portion 3d reduces the contact area with the recess 2c to prevent image sticking. This variable vane operating link 3
The wing part 3A, the rod-shaped part 3a in the operation link 3B, the connecting part 3b, and the projection part 3c are integrally formed.

Reference numeral 4 denotes an operating plate whose inner peripheral portion is rotatably fitted to the outer peripheral portion of the nozzle base 2A. For example, the operating plate 4 shown in FIG. 5 is formed by punching an outer peripheral portion extending over the front and back surfaces, and forming an arc-shaped concave portion 4a into which the projection 3c is fitted.
(Engaging portion).

The operating plate 4 shown in FIG. 6 has a concave portion 4a in an arc shape into which the protruding portion 3c is fitted by applying a pressing force from the back surface to make it concave. The operating plate 4 is formed at a part of its outer peripheral portion with an operating portion 4b to which an actuator (not shown) for rotating the operating plate 4 is connected.

In the operating plate 4 shown in FIG. 5, the portion where the operating portion 4b is formed is exceptionally formed with a hole instead of the concave portion 4a. If the position is avoided, all of the recesses 4a
It can be.

5 is a protective cover for the wing 3A (see FIG. 2).
The protective cover 5 is formed in an annular shape, and is provided on the first flange 2a at a spacing slightly larger than the surface width of the wing portion 3A by the coupling member 5a.

In the displacement adjusting mechanism 1 having the above-described structure, in the turbocharger, when the operating portion 4b is rotated by a predetermined angle by an actuator (not shown) based on the assembly, the operating plate 4 rotates by the same angle.

When the operating plate 4 rotates, the projection 3c of the operating link 3B of the variable blade vane operating link 3 fitted in the recess 4a of the operating plate 4 also rotates, and then the connecting portion 3b turns to form a rod-shaped portion. 3a rotates. Then, the angle of the surface of the wing portion 3A in the variable wing vane operating link 3 is changed by the rotation of the shaft of the rod portion 3a, whereby the amount of exhaust flowing into the inner periphery of the nozzle base 2A is adjusted.

Next, the effect of the difference in structure between the conventional displacement adjusting mechanism 51 described with reference to FIGS. 9 and 10 and the displacement adjusting mechanism 1 of the present invention will be described. (1) In the conventional displacement adjusting mechanism 51, the through-hole 52c is formed using a small-diameter drill in order to insert the insertion portion 53a of the variable wing member 53 in the base material 52. Therefore, the conventional displacement adjusting mechanism 51 requires time and effort to perforate the through-holes 52 c by the number of the variable wing members 53.
Since the fitting portion between a and the through-hole 52c is highly accurate, it takes much more time and effort.

On the other hand, the displacement adjusting mechanism 1 of the present invention
Is formed by forming a concave portion 2c on the inner periphery of the mount base 2B of the base material 2B from the first flange 2a to the second flange 2b, press-fitting the nozzle base 2A into the inner periphery of the mount base 2B, The release portion of 2c is closed by the outer periphery of the nozzle base material 2A so as to function as a hole for supporting the rod portion 3a of the variable blade vane operation link 3 by three-point contact.

Accordingly, in the displacement adjusting mechanism 1 of the present invention, the recess 2c can be formed by broaching or cold forging.
The nozzle base 2A is press-fitted into the mount base 2B to form the recess 2c.
Function as a hole to be supported by three-point contact as described above, so that labor required for processing is omitted, and seizure between the hole formed by the concave portion 2c and the nozzle base 2A and the rod-shaped portion 3a is less likely to occur. .

(2) The conventional displacement adjusting mechanism 51 has a structure in which the insertion portion 53a of the variable wing member 53 is formed linearly, and the insertion portion 53a is caulked and attached to the operation link 54. . Therefore, the conventional displacement adjusting mechanism 51 requires a plurality of components for the insertion portion 53a (the variable wing member 53) and the operating link 54,
The increase in the number of parts and the number of assembling man-hours, as well as the need for high shaft machining accuracy, as described above, required labor and cost.

On the other hand, the displacement adjusting mechanism 1 of the present invention
The variable wing vane operating link 3 is formed by forging the wing 3
A, a rod-shaped portion 3a, a connecting portion 3b in the operation link 3B,
And the projection 3c are integrally formed. Therefore, the displacement adjusting mechanism 1 of the present invention can reduce the number of parts and the number of assembling steps accordingly, and further adjust the angle of attachment between the wing portion 3A and the operating link 3B. Is unnecessary, and labor is remarkably reduced.

(3) In the conventional displacement adjusting mechanism 51, the engaging hole 55a of the operating plate 55 is formed as a hole, and the projection 54b of the operating link 54 is inserted into the engaging hole 55a. Therefore, the conventional displacement control mechanism 51 requires time and effort to form the engagement holes 55a by the number of the variable wing members 53, and performs a high-precision finishing process on the contact surface between the projection 54b and the engagement hole 55a. It was more time-consuming because of the necessity.

On the other hand, the displacement adjusting mechanism 1 of the present invention
Forms a recess 4a in the operation plate 4 and
a shows an operating link 3B in the variable vane operating link 3;
Of the projection 3c. Therefore, in the displacement adjusting mechanism 1 of the present invention, since the projection 3c is engaged with the concave portion 4a of the operation plate 4 and is not drilled, the strength against thermal distortion is improved and the workability is improved.

As described above, the displacement adjusting mechanism 1 of the present invention
Can reduce the number of parts, simplify the structure, and can be manufactured in a short time because various high-precision processing is not required. Can be reduced.

The present invention is not limited to the above embodiment,
Various modifications are possible. For example, in the above-described embodiment, an example in which the concave portion 2c is formed on the inner peripheral side of the mount substrate 2B and the nozzle substrate 2A is press-fitted, but the concave portion 2c is formed on the outer peripheral side of the nozzle substrate 2A. Even if the nozzle base material 2A is press-fitted into the mount base material 2B having no concave portion 2c on the inner peripheral side, the same operation and effect as described above can be obtained.

[0049]

As described above, in the displacement adjusting mechanism according to the first aspect of the present invention, a plurality of arc-shaped concave portions are formed at an equal angle on the inner peripheral side of the mount substrate or the outer peripheral side of the nozzle substrate. When the nozzle base material is pressed into the mount base material, the recess functions as a hole, saving the labor of drilling.In addition, the area for precision finishing is reduced and this finishing work is also performed. It is possible to significantly reduce seizure with a part of the operating link engaged with the recess.

Further, in the displacement adjusting mechanism according to claim 2 of the present invention, in the above structure, a wing portion forming a variable wing vane having a surface orthogonal to the surface of the first flange, a rod-shaped portion, a connecting portion, And the operating link having the protrusion are integrally formed, so that the number of parts can be reduced, the number of assembling steps can be reduced, and the angle between the wing portion and the operating link can be adjusted. Can be omitted.

According to a third aspect of the present invention, in the displacement adjusting mechanism according to any one of the above aspects, an arc-shaped concave portion in which a part of the operation link is engaged with an outer peripheral portion extending over the front and back surfaces of the operation plate. Is formed, labor for drilling can be saved, strength against thermal distortion is improved, and workability is improved.

Further, in the displacement adjusting mechanism according to claim 4 of the present invention, in any one of the above structures, the intermediate portion of the portion of the operating link inserted into the concave portion has a small diameter portion. As the contact area decreases, the time required for precision finishing can be shortened, and burn-in can be prevented.

[Brief description of the drawings]

FIG. 1 shows a schematic configuration of a displacement adjusting mechanism of the present invention,
(A) is the figure seen from the working plate side, (b) is the elements on larger scale of the variable wing vane working link.

FIG. 2 shows a schematic configuration of a displacement adjusting mechanism of the present invention, and is a cross-sectional view taken along line BB of FIG. 1 (a).

FIG. 3 shows a substrate in the displacement adjusting mechanism of the present invention,
(A) is a view from the second flange side, (b) shows a situation where the nozzle base material is pressed into the mount base material, and CC of (a) is shown.
It is a line sectional view.

4A and 4B show a variable vane operating link in the displacement adjustment mechanism of the present invention, wherein FIG.
(B) is the figure seen from the side direction of (a).

5A and 5B show an operation plate in the displacement adjusting mechanism of the present invention, wherein FIG. 5A is a view seen from above, and FIG.
FIG. 4 is a sectional view taken along line D.

6A and 6B show another operation plate in the displacement adjusting mechanism of the present invention, wherein FIG. 6A is a view seen from above, and FIG.
FIG. 7 is a sectional view taken along line EE of FIG.

FIG. 7 is a diagram illustrating a place where a displacement adjusting mechanism is disposed in an engine equipped with a turbocharger.

FIG. 8 shows a schematic configuration of a conventional displacement adjusting mechanism,
(A) is the figure seen from the working plate side, (b) is the sectional view on the AA line of (a).

FIG. 9 shows a schematic configuration of a conventional displacement adjusting mechanism;
(A) is a partial enlarged view showing the periphery of the variable wing member and the operation link, and (b) is a diagram omitting a protective cover as viewed from the variable wing member side.

[Explanation of symbols]

 Reference Signs List 1 Displacement adjusting mechanism 2 Base 2A Nozzle base 2B Mount base 2a First flange 2b Second flange 2c Depression 3 Variable wing vane operation link 3A Wing section 3B Operation link 3a Bar-shaped section 3b Connecting section 3c Projection 3d Small diameter section 4 Working plate 4a Recess 4b Working part

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Yoshihiro Ishihara 13 Nishidai, Kitamachida, Tanabe-cho, Tsuzuki-gun, Kyoto (72) Inventor Takashi Mikogami 2-5-1, Marunouchi, Chiyoda-ku, Tokyo 3 F-term (reference) in Hishi Heavy Industries, Ltd. 3G005 EA04 EA15 EA16 FA13 FA41 GA04 GB24 GB86

Claims (4)

[Claims] 1. A displacement adjusting mechanism mounted on a turbocharger and having a variable vane type vane for adjusting a displacement for rotating a turbine blade, wherein a first flange is formed at one end of a short tube. An inner peripheral side of the mount substrate or an outer periphery of the nozzle substrate of a substrate having a mount substrate having a second flange formed at the other end and a nozzle substrate press-fitted into the inner peripheral surface of the mount substrate. A plurality of arcuate concave portions are formed on the side at an equal angle, and a wing portion forming a variable wing vane having a surface orthogonal to the surface of the first flange is arranged on the first flange, and from this wing portion, A part of the operation link inserted on the second recess and arranged on the second flange,
An exhaust volume adjusting mechanism, wherein an inner peripheral portion of the nozzle substrate is rotatably engaged with an engaging portion of an operation plate having an outer peripheral portion fitted to the outer peripheral portion of the nozzle substrate. 2. A wing portion provided on a first flange and forming a variable wing vane having a surface orthogonal to a surface of the first flange, and fitted into a recess from the wing portion in a direction of the second flange. A connecting portion formed in a direction parallel to the surface of the second flange continuously from the bar portion;
2. The displacement adjusting mechanism according to claim 1, wherein an operating link having a projection formed in a direction perpendicular to a surface of the second flange is formed integrally with the connecting portion. 3. An arcuate recess in which a part of an operation link is engaged is formed in an outer peripheral portion extending over the front and back surfaces of the operation plate, and an operation part is formed in a part of the outer peripheral portion. The displacement adjusting mechanism according to claim 1 or 2. 4. The operation link according to claim 1, wherein an intermediate portion of a portion of the operation link inserted into the concave portion has a small diameter portion.
4. The displacement adjusting mechanism according to any one of claims 1 to 3.