Variable power charger
Patent Information
- Authority / Receiving Office
- DE · DE
- Patent Type
- Patents
- Current Assignee / Owner
- IHI CORP
- Filing Date
- 2019-10-23
- Publication Date
- 2026-07-02
AI Technical Summary
Existing variable capacity turbochargers face issues with performance deterioration due to gas flow separation at step-shaped nozzle flow passage walls and increased manufacturing costs due to complex machining required for perpendicular mounting of connecting pins.
A variable capacity turbocharger design featuring inclined inner and outer peripheral side wall surfaces and a parallel intermediate wall surface in the nozzle flow passage, ensuring smooth rotation of nozzle vanes while simplifying the manufacturing process by allowing perpendicular mounting of connecting pins.
Simultaneously suppresses performance deterioration of the turbine and reduces manufacturing costs by ensuring smooth rotation of nozzle vanes and optimizing the assembly process.
Abstract
Description
Technical field
[0001] The present disclosure relates to a variable-power charger (a turbocharger). State of the art
[0002] A conventionally known technology in this field is a variable-power turbocharger, described in the following patent reference 1. In this type of turbocharger, a nozzle blade rotates while sliding on a wall surface of a nozzle flow passage of a turbine. Patent reference 1 discloses that a wall surface of a nozzle flow passage is chamfered to be spaced from a nozzle blade at positions corresponding to the outer and inner circumferential sections of the nozzle blade. It is further proposed that the wall surface of the nozzle flow passage be spaced from the nozzle blade by a stepped shape instead of the chamfered shape. In this way, it is proposed that the shape of the wall surface of the nozzle flow passage ensures the reliability of the nozzle blade sliding and the trouble-free rotation of the nozzle blade. List of citations from patent literature Patent literature 1: Japanese unexamined utility model publication no. S61-37404 Patent literature 2: Japanese unexamined patent publication no. 2009-243375 Patent Literature 3: Japanese Unexamined Patent Publication No. 2008-184971 Summary of the invention; Technical task
[0003] However, if the wall surface of the nozzle flow passage is formed with a stepped shape, as described above, it is likely that gas flow within the nozzle flow passage will separate at the stepped section, potentially leading to a reduction in turbine performance. On the other hand, if the wall surface of the nozzle flow passage is formed with a chamfered shape, gas flow separation is less likely compared to the stepped shape. However, it is difficult to mount a connecting pin that joins the flow passage wall surfaces so that it is perpendicular to the flow passage wall surfaces. More precisely, during the turbocharger manufacturing process, a portion of the chamfered flow passage wall surface must be machined to create a mounting surface for the connecting pin.Accordingly, it cannot be claimed that processability at the time of manufacture is desirable, and this may hinder a reduction in manufacturing costs.
[0004] The present disclosure describes a variable-power turbocharger which, in a structure that ensures trouble-free rotation of a nozzle blade, simultaneously suppresses a deterioration in turbine performance and an increase in manufacturing effort. Solution to the task
[0005] A variable-power turbocharger according to one aspect of the present disclosure is a variable-power turbocharger having the following: a nozzle flow passage in which a gas is able to flow from a screw flow passage towards a turbine impeller; a connecting pin connecting flow passage wall surfaces that form the nozzle flow passage;and nozzle blades arranged in a direction of rotation of the turbine runner, wherein the nozzle blades are configured to set a degree of opening of the nozzle flow passage by rotating in the nozzle flow passage, wherein at least one of the flow passage wall surfaces has the following: an inner circumferential wall surface extending radially inward from a first reference line extending in the direction of rotation as a starting position, wherein the inner circumferential wall surface is inclined to extend away from the nozzle blades in a direction of rotation of the turbine runner when the inner circumferential side wall surface extends radially inward;an outer circumferential wall surface, which is a plane extending radially outward from a second reference line extending in the direction of rotation as a starting position and parallel to a plane perpendicular to an axis of rotation of the nozzle blade, wherein the outer circumferential wall surface is located further away from the nozzle blade than a boundary section of the inner circumferential wall surface, wherein the second reference line is located radially outward from the first reference line, and wherein the boundary section is located on the first reference line;and an intermediate wall surface, which is a plane extending from the first reference line to the second reference line and parallel to the plane extending perpendicular to the axis of rotation of the nozzle blade, wherein the intermediate wall surface intersects the inner circumferential wall surface on the first reference line, wherein the first reference line is located radially outside an inner circumferential contact circle of the nozzle blades at a maximum degree of opening of the nozzle flow passage, and the second reference line is located radially inside an outer circumferential contact circle of the nozzle blades at the maximum degree of opening of the nozzle flow passage, radially outside an inner circumferential contact circle of the nozzle blades at a minimum degree of opening of the nozzle flow passage, and radially inside an inner circumferential contact circle of a mounting seat surface of the connecting pin. Effects of the invention
[0006] According to the variable power turbocharger of the present disclosure, it is possible in a structure that ensures trouble-free rotation of the nozzle blade, while simultaneously suppressing the deterioration of the turbine's performance and the increase in manufacturing effort. List of characters Fig. Figure 1 is a cross-sectional view showing a cross-section including a rotation axis of a variable power turbocharger according to an exemplary embodiment. Fig. Figure 2 is a view showing nozzle blades and an AR plate, viewed from a suction port side of a compressor in an axial direction. Fig. Figure 3 is a cross-sectional view in the vicinity of the nozzle blade, showing a cross-section including a rotation axis of the nozzle blade. Fig. Figure 4 is a view showing the positional relationship of the nozzle blades, a connecting pin, and the AR plate. Fig. 5(a) to Fig. Figure 5(c) shows cross-sectional views in the vicinity of a nozzle blade according to a further embodiment. Description of the exemplary implementations
[0007] A variable-power turbocharger according to one aspect of the present disclosure is a variable-power turbocharger having the following: a nozzle flow passage in which a gas is able to flow from a screw flow passage towards a turbine impeller; a connecting pin connecting flow passage wall surfaces that form the nozzle flow passage;and nozzle blades arranged in a direction of rotation of the turbine runner, wherein the nozzle blades are configured to set a degree of opening of the nozzle flow passage by rotating in the nozzle flow passage, wherein at least one of the flow passage wall surfaces has the following: an inner circumferential wall surface extending radially inward from a first reference line extending in the direction of rotation as a starting position, wherein the inner circumferential wall surface is inclined to extend away from the nozzle blades in a direction of rotation of the turbine runner when the inner circumferential side wall surface extends radially inward;an outer circumferential wall surface, which is a plane extending radially outward from a second reference line extending in the direction of rotation as a starting position and parallel to a plane perpendicular to an axis of rotation of the nozzle blade, wherein the outer circumferential wall surface is located further away from the nozzle blade than a boundary section of the inner circumferential wall surface, wherein the second reference line is located radially outward from the first reference line, and wherein the boundary section is located on the first reference line;and an intermediate wall surface, which is a plane extending from the first reference line to the second reference line and parallel to the plane extending perpendicular to the axis of rotation of the nozzle blade, wherein the intermediate wall surface intersects the inner circumferential wall surface on the first reference line, wherein the first reference line is located radially outside an inner circumferential contact circle of the nozzle blades at a maximum degree of opening of the nozzle flow passage, and the second reference line is located radially inside an outer circumferential contact circle of the nozzle blades at the maximum degree of opening of the nozzle flow passage, radially outside an inner circumferential contact circle of the nozzle blades at a minimum degree of opening of the nozzle flow passage, and radially inside an inner circumferential contact circle of a mounting seat surface of the connecting pin.
[0008] The first reference line can be located radially inward from the circle passing through the axis of rotation of the nozzle blades, and the second reference line can be located radially outward from an outer circumferential contact circle of rotational shafts of the nozzle blades.
[0009] The first reference line can be located radially inwards from the inner circumferential contact circle of the nozzle blades at a minimum degree of opening of the nozzle flow passage, and the second reference line can be located radially outwards from the outer circumferential contact circle of the nozzle blades at a minimum degree of opening of the nozzle flow passage.
[0010] A variable-power turbocharger according to one aspect of the present disclosure is a variable-power turbocharger having the following: a nozzle flow passage in which a gas is able to flow from a screw flow passage towards a turbine impeller; a connecting pin connecting flow passage wall surfaces that form the nozzle flow passage;and nozzle blades arranged in a direction of rotation of the turbine runner, wherein the nozzle blades are configured to set a degree of opening of the nozzle flow passage by rotating in the nozzle flow passage, wherein at least one of the flow passage wall surfaces has the following: an inner circumferential wall surface extending radially inward from a first reference line extending in the direction of rotation as a starting position, wherein the inner circumferential wall surface is inclined to extend away from the nozzle blades in a direction of rotation of the turbine runner when the inner circumferential wall surface extends radially inward;an outer circumferential wall surface, which is a plane extending radially outward from the first reference line extending in the direction of rotation as a starting position and parallel to a plane perpendicular to an axis of rotation of the nozzle blade, wherein the outer circumferential wall surface is located further away from the nozzle blade than a boundary section of the inner circumferential wall surface, and wherein the boundary section is located on the first reference line, and wherein the first reference line is located radially inward from an outer circumferential contact circle of the nozzle blades at the maximum degree of opening of the nozzle flow passage, radially outward from an inner circumferential contact circle of the nozzle blades at a minimum degree of opening of the nozzle flow passage, and radially inward from an inner circumferential contact circle of a mounting seat surface of the connecting pin.
[0011] An embodiment of the present disclosure is described below with reference to the drawings. Fig. Figure 1 is a cross-sectional view showing a cross-section including a rotation axis H of a turbocharger. 1 with variable power output. The turbocharger 1 is applied, for example, to an internal combustion engine of a ship or vehicle.
[0012] As in Fig. As shown in 1, the turbocharger has 1 a turbine 2 and a compressor 3. The turbine 2 It has a turbine housing 4 and a turbine impeller 6 , which is housed in the turbine casing 4. The turbine casing 4 has a screw flow passage. 16 , which extends in a circumferential direction around the turbine impeller 6The compressor 3 has a compressor housing 5 and a compressor impeller 7, which is housed in the compressor housing 5. The compressor housing 5 has a screw flow passage 17, which extends circumferentially around the compressor impeller 7.
[0013] The turbine impeller 6 A turbine housing 4 is located at one end of a rotating shaft 14, and the compressor impeller 7 is located at the other end of the rotating shaft 14. A bearing housing 13 is located between the turbine housing 4 and the compressor housing 5. The turbine housing 4 and the compressor housing 5 are fastened to the bearing housing 13, for example, by screws or the like. The rotating shaft 14 is rotationally supported by the bearing housing 13 by means of a bearing 15, and the rotating shaft 14, the turbine impeller 6 and the compressor impeller 7 rotates as a one-piece rotating body 12 around the axis of rotation H.
[0014] The turbine housing 4 is provided with an exhaust gas inlet (not shown) and an exhaust gas outlet 10. Exhaust gas emitted by an internal combustion engine (not shown) flows through the exhaust gas inlet into the turbine housing 4 and then through the screw flow passage. 16 into the turbine impeller 6 and the turbine impeller 6 rotate. The exhaust gas then flows out of the turbine housing 4 through the exhaust outlet 10.
[0015] The compressor housing 5 is provided with a suction port 9 and a discharge port (not shown). When the turbine impeller 6As described above, the compressor impeller 7 rotates by means of the rotating shaft 14. The rotating compressor impeller 7 draws in external air through the suction port 9. This air passes through the compressor impeller 7 and the screw flow passage 17 to be compressed and is discharged from the discharge port. The compressed air discharged from the discharge port is supplied to the internal combustion engine described above.
[0016] The turbine 2 of the turbocharger 1 This will be described further. In the following description, the "axial direction", the "radial direction", and the "circumferential direction" simply mean the direction of the axis of rotation (the direction of the axis of rotation H), the radial direction of rotation, and the direction of rotation of the turbine impeller, respectively. 6 .
[0017] At the turbine 2 of the turbocharger 1is a movable nozzle blade 21 in a nozzle flow passage 19 provided for, which the screw flow passage 16 and the turbine impeller 6 connects. As in Fig. Figure 2 also shows the multitude of nozzle blades. 21 arranged at equal intervals around the circumference centered on the axis of rotation H. Each of the nozzle blades 21 rotates in a synchronized manner around a rotational axis J , which is parallel to the axis of rotation H. With the plurality of nozzle blades rotating as described above. 21 The gap between the adjacent nozzle blades will be 21 enlarged and reduced, thereby changing the degree of opening of the nozzle flow passage. 19 set.
[0018] To the nozzle vane 21 to drive the turbine as described above 2 a variable nozzle mechanism20 The variable nozzle mechanism 20 is housed in the turbine housing 4 and is arranged and fixed between the turbine housing 4 and the bearing housing 13.
[0019] The variable nozzle mechanism 20 has the multitude of nozzle blades 21 , a nozzle ring 23 and a spacer plate 27 (hereinafter referred to as an “AR plate 27”). The nozzle blade 21 is in the axial direction between the nozzle ring 23 and the AR plate 27 arranged. The nozzle ring 23 and the AR plate 27 Each forms a ring shape centered on the axis of rotation H and is arranged in such a way that it supports the turbine impeller. 6 surrounded in the circumferential direction. The nozzle ring 23 when considering the nozzle blade 21 Located on the side of compressor 3. The AR plate 27when considering the nozzle blade 21 located on the side opposite compressor 3.
[0020] An area that extends in the axial direction between the nozzle ring 23 and the AR plate 27 It is arranged to form the nozzle flow passage. 19 That is, a flow-through wall surface 24 of the nozzle flow passage 19 is through an area of the nozzle ring 23 formed. In addition, the other flow-through wall surface is formed. 28 of the nozzle flow passage 19 through an area of the AR plate 27 formed, which form the flow path wall surface 24 is turned towards.
[0021] As in Fig. 2 and Fig. As shown in section 3, the nozzle blade 21 a blade rotation shaft 21a , which point towards the nozzle ring 23 extends, and a blade end face 22, which of the flow path wall surface 28 the AR plate 27 is facing the blade end surface 22 forms a plane that is perpendicular to the direction of extension of the blade rotation shaft 21a is. As in Fig. As shown in section 3, the nozzle ring has bearing holes. 23a equipped with as many as the nozzle blades. 21 The blade rotation shaft 21a each nozzle blade 21 is through the bearing hole 23a rotatable and the nozzle ring 23 supports each nozzle blade 21 axially, in a cantilevered manner. Each blade rotation shaft 21a penetrates the nozzle ring 23 one. In addition, an end section of each blade rotation shaft 21a with a drive mechanism on the rear surface side of the nozzle ring 23connected. A driving force is transmitted by this drive mechanism from an actuator (not shown) to each blade rotation shaft. 21a transmitted. The driving force causes each nozzle blade to rotate. 21 around the axis of rotation J , which are on the blade rotation shaft 21a is centered.
[0022] The nozzle ring 23 and the AR plate 27 are connected by a large number of connecting pins 29 , which extend in the axial direction, are connected to each other. The connecting pin 29 is equipped with two flange sections 31 and 33 provided which are perpendicular to the axis of the connecting pin 29 are. The flange section 31 comes with the flow-through wall surface 24 in contact and the flange section 33 comes with the flow-through wall surface 28 in contact, so that the nozzle ring 23 and the AR plate27 Each one is positioned. The dimensional accuracy of the nozzle flow path. 19 In the axial direction, this is ensured by the dimensions between the flange sections. 31 and 33 manufactured with high precision. The connecting pin 29 is mounted in a position where the connecting pin prevents the rotation of the nozzle blade. 21 not affected.
[0023] The flow passage wall surface 28 the AR plate 27 is in the radial direction with a first reference line 41 and a second reference line 42 as boundary lines divided into three areas. Both the first reference line 41 as well as the second reference line 42 They form a circle centered on the axis of rotation H. Furthermore, the second reference line... 42 radially outward from the first reference line 41 located.
[0024] The three areas are referred to as one inner circumference area in this order, starting from the inner circumference side. 37 , an intermediate area 38 and an outer perimeter area 39 designated. The inner circumference area 37 is a ring-shaped area from the first reference line 41 up to an inner circumferential edge 27a the AR plate 27 The intermediate area 38 is a ring-shaped area from the first reference line 41 up to the second reference line 42 The outer circumference 39 is a ring-shaped area from the second reference line 42 up to an outer circumferential edge 27b the AR plate 27 . At the flow-through wall surface 28 A section of the inner circumference area will be used. 37 as an interior wall surface 47 designated, a section of the intermediate area 38 is used as an intermediate wall surface 48designated and a section of the outer circumference 39 is considered an outer perimeter wall surface 49 designated.
[0025] The inner perimeter wall surface 47 extends radially inwards from the first reference line 41 as a starting position. Furthermore, the inner perimeter wall surface is 47 an inclined surface which is inclined in such a way that it is separated from the blade end surface 22 the nozzle blade 21 It is spaced away in the axial direction, while it extends inwards in the radial direction. In a Fig. The cross-section shown in section 3 forms the inner perimeter wall surface. 47 a straight line.
[0026] The outer perimeter wall surface 49 extends radially outwards from the second reference line 42 as a starting position. Furthermore, the outer wall surface is 49a plane which is parallel to the plane which is perpendicular to the axis of rotation J the nozzle blade 21 is. The outer perimeter wall surface 49 is positioned such that it is aligned in the axial direction with respect to an edge section 47b on the first reference line 41 the inner perimeter wall surface 47 away from the blade tip 22 is spaced apart.
[0027] The partition wall surface 48 is a plane which is parallel to a plane which is perpendicular to the axis of rotation J is, and cuts through the inner perimeter wall surface 47 on the first reference line 41 The partition wall area 48 is positioned such that it is aligned in the axial direction with respect to the edge section 47b the inner perimeter wall surface 47 on the first reference line 41 to the same distance away from the blade tip 22is spaced apart. Compared to the partition wall area 48 is the outer perimeter wall surface 49 further away from the blade end face in the axial direction 22 spaced apart. Accordingly, a step section exists. 51 between the outer perimeter wall surface 49 and the partition wall surface 48 on the second reference line 42 .
[0028] Referring to Fig. 4. The radial positions of the first reference line are defined. 41 and the second reference line 42 described. Fig. Figure 4 is a view showing the positional relationship of the nozzle blades. 21 , of the connecting pin 29 and the AR plate 27 schematically represented. The first reference line 41 and the second reference line 42 , which in Fig. Figure 4 shows examples, and the radial positions of the first reference line. 41and the second reference line 42 are not on those of Fig. 4 limited.
[0029] A nozzle blade 21S in Fig. Figure 4 shows the nozzle blade 21 , when the nozzle flow passage 19 has a minimum degree of opening. A nozzle blade 21T in Fig. Figure 4 shows the nozzle blade 21 , when the nozzle flow passage 19 has a maximum degree of opening. When the nozzle flow passage 19 The angle that has a minimum opening degree is determined by the longitudinal direction of the nozzle blade. 21 formed with reference to the circumferential direction, is the smallest and the minimum gap (nozzle neck) between the adjacent nozzle blades. 21 is at its narrowest point. When the nozzle flow passage 19 The angle that has a maximum opening degree is determined by the longitudinal direction of the nozzle blade. 21formed with reference to the circumferential direction, is the largest and the minimum gap (nozzle neck) between the adjacent nozzle blades. 21 is the widest. Reference mark 29' in Fig. Figure 4 shows the mounting surface of the connecting pin. 29 , which is among the multitude of connecting pins 29 It is mounted on the innermost side in the radial direction. The flange section 33 of the connecting pin 29 comes with this mounting seat surface 29' in contact.
[0030] A line Q1 in Fig. 4 provides an inner circumferential contact circle of the mounting seat surface 29' on. That is, the line Q1 specifies an inscribed circle centered on the axis of rotation H and passing through the mounting surface 29' is inscribed.
[0031] A line Q2 in Fig. 4 provides an outer circumferential contact circle of the nozzle blade21T on. That is, the line Q2 specifies a circumscribed circle that includes all nozzle blades 21T describes.
[0032] A line Q3 in Fig. 4 provides an inner circumferential contact circle of the nozzle blades 21T on. That is, the line Q3 indicates an inscribed circle that passes through all nozzle blades. 21T is inscribed.
[0033] A line Q4 in Fig. 4 provides an outer circumferential contact circle of the nozzle blade 21S on. That is, the line Q4 specifies a circumscribed circle that includes all nozzle blades 21S describes.
[0034] A line Q5 in Fig. 4 provides an inner circumferential contact circle of the nozzle blades 21S on. That is, the line Q5 indicates an inscribed circle that passes through all nozzle blades. 21S is inscribed.
[0035] A line Q6 in Fig. 4 gives an outer circumferential contact circle of the blade rotation shaft 21a on. That is, the line Q6 specifies a circumscribed circle that encompasses all blade rotation waves 21a describes.
[0036] A line Q7 in Fig. 4 indicates a circle that passes through the axes of rotation. J all nozzle blades 21 passes through it.
[0037] It should be noted that in the example of Fig. 4. Line Q1 is located radially outside of line Q2, however, line Q1 may lie radially inside line Q2. Lines Q1 to Q7 are concentric circles centered on the axis of rotation H. Furthermore, all lines Q1 to Q7 extend in a plane perpendicular to the axis of rotation H.
[0038] Regarding the turbocharger 1 In this embodiment, the radial positions of the first reference line are 41and the second reference line 42 chosen such that all of the following conditions C1 to C4 are met.
[0039] Condition C1: The first reference line 41 is located radially outward from line Q3.
[0040] Condition C2: The second reference line 42 is located radially inwards from line Q2.
[0041] Condition C3: The second reference line 42 is located radially outward from line Q5.
[0042] Condition C4: The second reference line 42 is located radially inwards from line Q1.
[0043] The operation and effects of the turbocharger 1 described above are described.
[0044] When the nozzle flow passage 19 has a maximum degree of opening if condition C1 is met, is a radially inward end section 22a the blade end surface 22 located in a position adjacent to the inner perimeter wall surface 47is turned towards, as in Fig. 3 is shown. Even if the blade end face 22 with the partition wall surface 48 When it comes into contact, an axial gap is created between the end section. 22a and the inner perimeter wall surface 47 formed because the inner perimeter wall surface 47 a sloping surface.
[0045] Similarly, if the nozzle flow passage 19 has a maximum degree of opening if condition C2 is met, is a radially outer end section 22b the blade end surface 22 located in a position adjacent to the outer perimeter wall surface 49 is turned towards, as in Fig. Figure 3 is shown. Since the outer perimeter wall surface 49 is situated such that it is aligned in the axial direction with respect to the edge section 47b from the blade end face 22Because it is spaced apart, a gap is thus created in the axial direction between the end section 22b and the outer wall surface 49 formed, even if the blade end surface 22 with the partition wall surface 48 comes into contact.
[0046] As described above, when the nozzle flow passage 19 It has a maximum degree of opening if conditions C1 and C2 are met; a slight gap will appear between the end sections in the axial direction. 22a and 22b the blade end surface 22 and the flow wall surface 28 formed. Accordingly, the probability of a problem, such as a change in the rotation of the nozzle blade, can be reduced. 21 due to the friction between the end sections 22a as well as 22b the blade end surface 22 and the flow wall surface 28is hindered, and the trouble-free operation of the nozzle blade 21 This can be ensured.
[0047] When the nozzle flow passage 19 has a minimum degree of opening if condition C3 is not met, the end section 22a the blade end surface 22 outside of the step section 51 located. Therefore, the end section gets stuck. 22a the blade end surface 22 at the step section 51 , and the trouble-free rotation function of the nozzle blade 21 is lost. Accordingly, if condition C3 is satisfied, the problem described above is avoided.
[0048] If condition C4 is met, the flange section 33 of the connecting pin 29 on the outer perimeter wall surface 49 mounted. If the outer perimeter wall surface 49a sloping surface similar to the inner perimeter wall surface 47 If necessary, the mounting surface of the connecting pin must be checked. 29 by means of a countersinking process for the outer perimeter wall surface 49 to train in order to train the flange section 33 perpendicular to the axis of the connecting pin 29 to mount. On the other hand, since the outer perimeter wall surface 49 parallel to the plane that is perpendicular to the axis of rotation J is, is it possible to the flange section 33 to the outer perimeter wall surface 49 to assemble without performing the processing described above. Accordingly, there will be an increase in effort at the time of manufacturing the turbocharger. 1 suppressed, and therefore an increase in production costs is suppressed.
[0049] The inner perimeter wall surface 47 and the partition wall area 48are without a step at the first reference line 41 interconnected. Accordingly, the probability of the gas flow separating from the partition surface is increased. 48 to the inner perimeter wall surface 47 compared to a case where there is a step between the inner perimeter wall surface 47 and the partition wall surface 48 exists. On the other hand, since the stage section 51 between the outer perimeter wall surface 49 and the partition wall surface 48 Since the outer wall surface... 49 with reference to the inner perimeter wall surface 47 on the upstream side of the gas and the gas flow velocity is slow, the turbine's performance degradation is 2 relatively small, even when detachment occurs.
[0050] As described above, according to the turbocharger 1 in a structure that allows for trouble-free rotation of the nozzle blade 21 ensures, if possible, the simultaneous deterioration of the turbine's performance. 2 and at the same time suppress the increase in manufacturing costs.
[0051] For example, as in Fig. 5(a) to Fig. The first reference line shown in Figure 5(c) can be considered an embodiment capable of achieving the same operation and effects as described above. 41 and the second reference line 42 agree with each other, and the intermediate area 38 and the partition wall area 48 can be omitted. In the exemplary implementations of the Fig. 5(a) to Fig. 5(c) all of conditions C1 to C4 are satisfied. If conditions C1 to C4 are ordered subject to the condition that the first reference line 41and the second reference line 42 The first and second reference lines that coincide with each other are the corresponding reference lines. 41 and 42 located radially inwards from line Q2, radially outwards from line Q5 and radially inwards from line Q1.
[0052] Fig. 5(a) represents an embodiment in which the first reference line 41 and the second reference line 42 at a position that coincides radially inwards from the blade rotation shaft 21a is located. In this case, the intermediate area exists. 38 and the partition wall area 48 no, and a step section 52 exists between the inner perimeter wall surface 47 and the outer wall surface 49 As in Fig. As shown in 5(b), the first reference line can be 41 and the second reference line 42at a position that is radially outward from the blade rotation shaft 21a is located. As in Fig. 5(c) shows, the first reference line can also be 41 and the second reference line 42 at a position on the blade rotation shaft 21a agree with each other. This also applies to the exemplary embodiments described in Fig. 5(a) to Fig. As shown in 5(c), the same operation and effects as those described above can be achieved.
[0053] Regarding the turbocharger 1 In this embodiment, the following conditions C5 and C6 can still be met.
[0054] Condition C5: the first reference line 41 is located radially inwards from line Q7.
[0055] Condition C6: the second reference line 42 is located radially outwards from line Q6.
[0056] Operation and effects are described if conditions C5 and C6 are also met. If conditions C5 and C6 are met, part of a section in the blade tip surface 22 , which is at least the blade rotation shaft 21a corresponds to the partition wall area 48 facing. Since there is a gap between the blade end surface 22 and the flow wall surface 28 in a section that forms the partition wall area 48 If the gap is small and gas leakage is reduced, the turbine's performance deterioration will be minimized. 2 suppressed.
[0057] The following procedure can be considered an example of how to assemble the variable nozzle mechanism. 20 can be applied. The blade rotation shaft 21a each nozzle blade 21 will be placed in each bearing hole 23a of the nozzle ring 23 inserted, and the nozzle ring23 and the AR plate 27 are through the connecting pin 29 connected to each other. Then, a component of the drive mechanism is attached to the rear surface of the nozzle ring. 23 to the end section of each blade rotation shaft 21a tacked. At this time, if conditions C5 and C6 are met, part of a section is in the blade tip face. 22 , which is at least the blade rotation shaft 21a corresponds to the partition wall area 48 turned towards. Therefore, the caulking process can be carried out while the nozzle blade is in position. 21 is stabilized by connecting the section to the partition wall surface 48 is brought into contact, and the processability is improved. In this way, if the assembly procedure of the variable nozzle mechanism described above is followed, 20When applied, processability can be improved by fulfilling conditions C5 and C6.
[0058] Regarding the turbocharger 1 Furthermore, the following conditions C7 and C8 can be met in this embodiment.
[0059] Condition C7: the first reference line 41 is located radially inwards from line Q5.
[0060] Condition C8: the second reference line 42 is located radially outwards from line Q4.
[0061] If conditions C7 and C8 are met, the entire blade end surface 22 the partition wall surface 48 facing, when the nozzle flow passes 19 It has a minimal opening degree. Therefore, there is a gap between the nozzle blade. 21 and the flow wall surface 28 small, and gas leakage from the gap can be reduced. As a result, the turbine's performance deteriorates.2 at the minimum degree of opening of the nozzle flow passage 19 suppressed. Because the gas flow velocity is high when the nozzle flow passes through. 19 The influence of a gas leakage from the gap between the nozzle blade is minimal, as it has a minimum opening degree. 21 and the flow wall surface 28 on the turbine's performance 2 large. For this reason, it is particularly effective to reduce the gap between the nozzle blade. 21 and the flow wall surface 28 to reduce if the nozzle flow passage 19 has a minimum degree of opening.
[0062] As in Fig. As shown in section 4, if all conditions C1 to C8 are met, the first reference line is 41 located between line Q3 and line Q5 and the second reference line 42is located between line Q4 and one of lines Q1 and line Q2, which is located radially inwards from the other.
[0063] The present disclosure can be implemented in various embodiments with different modifications and improvements, including the embodiment described above, based on the knowledge of a person skilled in the art. Furthermore, a modified example can be constructed using the technical relationships described in the embodiment described above. The configurations of the respective embodiments can be combined and used as appropriate.
[0064] In this embodiment, although the nozzle blade 21 is used, which is inserted through the nozzle ring. 23The present disclosure can be applied even if the nozzle blade is supported in a freestanding manner, which is supported on both sides by the nozzle ring. 23 and the AR plate 27 is supported.
[0065] In this embodiment, the inner circumferential wall surface 47 , the partition wall area 48 and the outer wall surface 49 as described above in the flow passage wall surface 28 formed, however, the inner perimeter wall surface 47 , the partition wall area 48 and the outer wall surface 49 at the flow wall surface 24 be formed. Furthermore, the inner perimeter wall surface can be 47 , the partition wall area 48 and outer wall surface 49 both at the flow wall surface 24as well as at the flow wall surface 28 be trained.
[0066] With this type of turbocharger 1 can the nozzle blade 21 due to the pressure equilibrium between the nozzle blade 19 and the rear surface of the nozzle ring 23 in the direction of the flow wall surface 28 be pressed. In the case of such a pressure equilibrium, since the blade end surface 22 in the direction of the flow wall surface 28 When pressed, the friction between the blade end surface tends to increase. 22 and the flow wall surface 28 This can be a problem. Therefore, in the case of the pressure equilibrium described above, the inner circumferential wall surface exists. 47 , the partition wall area 48 and the outer wall surface 49 preferably at the flow passage wall surface 28On the other hand, in the case of pressure equilibrium, where the nozzle blade 21 in the direction of the flow wall surface 24 When pressed, the inner perimeter wall surface exists for the same reason. 47 , the partition wall area 48 and the outer wall surface 49 preferably at the flow passage wall surface 24 .
[0067] In this embodiment, the nozzle blades 21 arranged at equal intervals (equal spaces) in the circumferential direction, however the nozzle blades can 21 be arranged with unequal spacing. Furthermore, the connecting pin 29 of the exemplary embodiment the flange sections 31 and 33 However, the flange section can be omitted. In this case, the connecting pin 29a large-diameter column section located between the flow-through wall surfaces 24 and 28 in the axial direction, and small-diameter column sections, each extending axially from both end faces of the large-diameter column section. The small-diameter column sections are then each inserted into the nozzle ring. 23 and the AR plate 27 inserted. Then comes a circumferential edge section of an end face of the large-diameter column section of the connecting pin. 29 with the mounting seat surface 29' the flow passage wall surface 28 in contact. Reference symbol list 1: Variable power turbocharger, 2: Turbine, 6: Turbine impeller, 16: Snail flow passage, 19: Nozzle flow passage, 21: Nozzle blade, 21S: Nozzle blade (nozzle blade at minimum opening degree of the nozzle flow passage), 21T: Nozzle blade (nozzle blade at maximum opening degree of the nozzle flow passage), 24: Flow passage wall area, 28: Flow passage wall area, 29: Connecting pin, 29': Mounting seat surface, 41: first reference line, 42: second reference line, 47: inner perimeter wall surface, 47b: Marginal section, 48: Partition wall area, 49: outer perimeter wall surface, J: Axis of rotation, Q1: Line (inner circumferential contact circle of the mounting seat surface of the connecting pin), Q2: Line (outer circumferential contact circle of the nozzle blade at maximum opening degree of the nozzle flow passage), Q3: Line (inner circumferential contact circle of the nozzle blade at maximum opening degree of the nozzle flow passage), Q4: Line (outer circumferential contact circle of the nozzle blade at minimum opening degree of the nozzle flow passage), Q5: Line (inner circumferential contact circle of the nozzle blade at minimum opening degree of the nozzle flow passage), Q6: Line (outer circumferential contact circle of the blade rotation shaft), Q7: Line (circle passing through the axis of rotation of the nozzle blade) QUOTES INCLUDED IN THE DESCRIPTION
[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature
[0000] JP S6137404
[0002] JP 2009243375
[0002] JP 2008184971
[0002]
Claims
[1] Variable power turbocharger with: a nozzle flow passage in which a gas is able to flow from a screw flow passage towards a turbine impeller; a connecting pin that joins flow passage wall surfaces forming the nozzle flow passage; and Nozzle blades arranged in a direction of rotation of the turbine impeller, wherein the nozzle blades are configured to adjust a degree of opening of the nozzle flow passage by rotating within the nozzle flow passage, where at least one of the flow-through wall surfaces has the following: an inner circumferential wall surface extending radially inwards from a first reference line extending in the direction of rotation as a starting position, wherein the inner circumferential wall surface is inclined to extend away from the nozzle blades in a rotational axis direction of the turbine impeller when the inner circumferential wall surface extends radially inwards; an outer circumferential wall surface, which is a plane extending radially outward from a second reference line extending in the direction of rotation as a starting position and parallel to a plane perpendicular to an axis of rotation of the nozzle blade, wherein the outer circumferential wall surface is located further from the nozzle blade than a boundary section of the inner circumferential wall surface, wherein the second reference line is located radially outward from the first reference line and the boundary section is located on the first reference line; and an intermediate wall surface which is a plane extending from the first reference line to the second reference line and is parallel to the plane extending perpendicular to the axis of rotation of the nozzle blade, wherein the intermediate wall surface intersects the inner circumferential wall surface on the first reference line, wherein the first reference line is located radially outward from an inner circumferential contact circle of the nozzle blades at a maximum degree of opening of the nozzle flow passage, and wherein the second reference line is located radially inward from an outer circumferential contact circle of the nozzle blades at the maximum degree of opening of the nozzle flow passage, radially outward from an inner circumferential contact circle of the nozzle blades at a minimum degree of opening of the nozzle flow passage, and radially inward from an inner circumferential contact circle of a mounting seat surface of the connecting pin. [2] Variable power turbocharger according to claim 1, wherein the first reference line is located radially inwards from a circle passing through the axis of rotation of the nozzle blades, and wherein the second reference line is located radially outwards from an outer circumferential contact circle of the rotating shafts of the nozzle blades. [3] Variable power turbocharger according to claim 2, wherein the first reference line is located radially inwards from the inner circumferential contact circle of the nozzle blades at the minimum degree of opening of the nozzle flow passage, and wherein the second reference line is located radially outwards from an outer circumferential contact circle of the nozzle blades at the minimum degree of opening of the nozzle flow passage. [4] Variable power turbochargers with: a nozzle flow passage in which a gas is able to flow from a screw flow passage towards a turbine impeller; a connecting pin that joins the flow passage wall surfaces that form the nozzle flow passage; and Nozzle blades arranged in a direction of rotation of the turbine impeller, wherein the nozzle blades are configured to adjust a degree of opening of the nozzle flow passage by rotating within the nozzle flow passage, where at least one of the flow-through wall surfaces has the following: an inner circumferential wall surface extending radially inwards from a first reference line extending in the direction of rotation as a starting position, wherein the inner circumferential wall surface is inclined to extend away from the nozzle blades in a rotational axis direction of the turbine impeller when the inner circumferential wall surface extends radially inwards; an outer circumferential wall surface, which is a plane extending radially outward from the first reference line extending in the direction of rotation as a starting position and parallel to a plane perpendicular to an axis of rotation of the nozzle blade, wherein the outer circumferential wall surface is located further from the nozzle blade than a boundary section of the inner circumferential wall surface, and the boundary section is located on the first reference line, and wherein the first reference line is located radially inward from an outer circumferential contact circle of the nozzle blades at the maximum degree of opening of the nozzle flow passage, radially outward from an inner circumferential contact circle of the nozzle blades at a minimum degree of opening of the nozzle flow passage, and radially inward from an inner circumferential contact circle of a mounting seat surface of the connecting pin.