Nozzle assembly of a turbocharger

Abstract

Nozzle assembly of a turbocharger, the assembly comprising: a nozzle (202) having flow passages (210; 400, 402) extending through the nozzle (202) and configured to direct air received from a spiral casing (108) of the turbocharger (100) through the nozzle (202) to turbine blades (106) of the turbocharger (100); and an annular body (204) coupled to the nozzle (202) and arranged to be rotatable about the nozzle (202), wherein the annular body (204) includes barrier segments (218) that block the flow of air and openings (209) between the barrier segments (218) that allow the air to flow through the annular body (204), wherein the annular body (204) is arranged to be rotatable relative to the nozzle (202) in order to change how many of the flow passages (210;400, 402) in the nozzle (202) are blocked by the blocking segments (218) of the annular body (204), characterized in that the nozzle (202) has an inner surface (214) and an opposing outer surface (212) on which the annular body (204) rotates relative to the nozzle (202), wherein the flow passages (400, 402) are oriented at different angles with respect to the outer surface (212) of the nozzle (202).

Description

AREA

[0001] The item described herein concerns turbochargers. BACKGROUND

[0002] Variable geometry turbochargers contain turbines that move to modify the turbocharger's output. These movable turbines accommodate the turbocharger's power requirements during part-load operation. For example, if the load applied to the engine (or power unit), which is partially driven by the turbocharger, changes, each of the turbocharger's turbines, or impeller blades, can move to alter the turbocharger's rotational speed. This change in rotational speed affects how much air is forced into the engine, thereby altering the amount of power produced.

[0003] This turbine design eliminates the need for boost pressure control valves and can improve engine efficiency by reducing pumping losses associated with undersized turbines in air handling systems. However, variable geometry turbochargers are expensive and less reliable than other turbochargers due to the large number of moving parts. SHORT DESCRIPTION

[0004] In one aspect, a turbocharger nozzle assembly comprises a nozzle and an annular body. The nozzle has flow passages extending through it, designed to direct air received from a volute casing of the turbocharger through the nozzle to the turbine blades of the turbocharger. The annular body is coupled to the nozzle and is designed to rotate around it. The annular body contains barrier segments that restrict the flow of air and openings between the barrier segments that allow air to flow through the annular body. The annular body is designed to rotate relative to the nozzle to change how many of the flow passages in the nozzle are restricted by the barrier segments of the annular body.

[0005] In the previously mentioned nozzle arrangement, the annular body can be arranged to be rotated relative to the nozzle in order to change through which of the flow passages in the nozzle the air flows to the turbine blades.

[0006] In some embodiments of any of the aforementioned nozzle device, the annular body may contain a first and an opposing second ring spaced apart from each other along a central axis of the annular body, wherein the locking segments of the annular body may extend from the first ring to the second ring in directions parallel to the central axis of the annular body.

[0007] In addition, all of the openings of the ring-shaped body are arranged between the first and second rings and various pairs of the locking segments of the ring-shaped body and are framed by them.

[0008] In any of the aforementioned nozzle arrangements, the nozzle can have an inner surface and an opposing outer surface on which the annular body rotates relative to the nozzle.

[0009] Alternatively, the nozzle can have an outer surface and an opposing inner surface on which the ring-shaped body rotates relative to the nozzle.

[0010] In some embodiments of any of the aforementioned nozzle devices, the flow passages through the nozzle can be centered on non-radial, non-tangential directions relative to an outer surface of the nozzle and elongated along this surface.

[0011] In some embodiments of any of the aforementioned nozzle arrangements, the nozzle may have an inner and an opposing outer surface, wherein the flow passages in the nozzle extend from the outer surface to the inner surface, wherein the flow passages may include at least a first and a second set of flow passages through which the air flows through the nozzle, wherein the flow passages in the first set extend from the outer surface to the inner surface along first non-radial, non-tangential directions and may be centered around them, wherein the flow passages in the second set extend from the outer surface to the inner surface along second non-radial, non-tangential directions, which are oriented transversely with respect to the first non-radial, non-tangential directions, and may be centered around them.

[0012] In other preferred embodiments of any of the aforementioned nozzle arrangements, the flow passages through the nozzle can comprise a first and a second set of flow passages, wherein the flow passages in the first set extend along first directions oriented at a first angle with respect to an outer surface of the nozzle and are centered on these, and the flow passages in the second set extend along other, second directions oriented at another, second angle with respect to the outer surface of the nozzle and are centered on these.

[0013] In the last-mentioned preferred embodiments, the blocking segments and the openings of the annular body can be positioned to prevent the air from flowing through the flow passages in the first set of the nozzle, and to allow the air to flow through the flow passages in the second set of the nozzle when the annular body is in a first position relative to the nozzle, and the blocking segments and the openings of the annular body can be positioned to prevent the air from flowing through the flow passages in the second set of the nozzle, and to allow the air to flow through the flow passages in the first set of the nozzle when the annular body is in another, second position relative to the nozzle.

[0014] Any of the aforementioned nozzle arrangements may further comprise an actuating device configured to be coupled to the annular body and configured to move the annular body around the nozzle.

[0015] In another aspect, a turbocharger's airflow restrictor comprises a first ring, a second ring, and restrictor segments. The first ring is configured to be coupled to a turbocharger nozzle. The second ring is also configured to be coupled to the turbocharger nozzle and is spaced from the first ring in a direction parallel to a central axis of the turbocharger nozzle. The restrictor segments extend from the first ring to the second ring and are spaced apart by openings. The first and second rings and the restrictor segments are configured to rotate around the turbocharger nozzle to modify which of the nozzle's flow passages—through which air flows from a turbocharger volute to the turbocharger's impeller blades—are open and which are closed.

[0016] In the aforementioned airflow limiting body, the blocking segments can extend from the first ring to the second ring in directions parallel to the central axis of the nozzle.

[0017] Additionally or as an alternative, each of the openings between the first and second rings and different pairs of locking segments can be arranged and framed by them.

[0018] In preferred embodiments of any of the aforementioned airflow limiting bodies, the first and second rings and the locking segments may be arranged to rotate on an outer surface of the nozzle.

[0019] Alternatively, the first and second rings and the locking segments can be arranged to rotate on an inner surface of the nozzle.

[0020] In a further aspect, a method includes determining a load applied to one or more of an engine and a turbocharger operationally coupled to the engine, and rotating an annular body around a turbocharger nozzle based on the determined load. The annular body has blocking segments that obstruct at least some of the nozzle's flow passages through which air flows from a turbocharger's spiral casing to its impeller blades, and openings that allow air to flow from the turbocharger's spiral casing to the impeller blades. Rotating the annular body prevents air from flowing through at least some of the nozzle's flow passages by means of the blocking segments.

[0021] The aforementioned method may further include a rotation of the annular body to move the locking segments away from the nozzle flow passages in response to an increase in load applied to one or more of the engine or turbocharger.

[0022] In some embodiments of any of the foregoing methods, the rotation of the annular body may include a rotation of the barrier segments to prevent the air from flowing through the flow passages oriented at a first angle with respect to an outer surface of the nozzle, and to allow the air to flow through the flow passages oriented at another, second angle with respect to the outer surface of the nozzle.

[0023] In some embodiments of any of the aforementioned methods, the rotation of the annular body may include rotating the annular body to prevent air from flowing through a set of fewer than all flow passages in response to a decrease in the load applied to one or more of the motor and turbocharger, and rotating the annular body to cease preventing air from flowing through any of the flow passages in response to an increase in the load applied to one or more of the motor and turbocharger. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The present subject matter according to the invention will be better understood by reading the following description of non-limiting embodiments with reference to the accompanying drawings, which are shown below:

[0025] Fig. 1 a cut-out view of a fixed-geometry turbocharger according to one embodiment;

[0026] Fig. 2 an embodiment of a nozzle device for a turbocharger;

[0027] Fig. 3 the in Fig. 2 illustrated nozzle assembly in a different position relative to a nozzle that is also in Fig. 2 is illustrated;

[0028] Fig. 4 a cross-sectional view of an embodiment of the in the Fig. 2 and Fig. 3 illustrated nozzle assembly;

[0029] Fig. 5 a first perspective view of an embodiment of an actuating device;

[0030] Fig. 6 another, second perspective view of the in Fig. 5 illustrated operating device; and

[0031] Fig. 7 a flow diagram of an embodiment of a method for controlling an air flow through a nozzle of a turbocharger. DETAILED DESCRIPTION

[0032] The invention described herein provides a nozzle assembly for a turbocharger, comprising an annular body that can rotate around a turbocharger nozzle to cover one or more flow passages of the nozzle. This can reduce the number and complexity of the moving parts in the turbocharger compared to some known variable geometry turbochargers, while still offering the flexibility to change the amount of air flowing through the nozzle based on the load applied to the engine receiving air from the turbocharger.The nozzle assembly can be used in fixed-geometry turbochargers or turbochargers with blades or turbines that are fixed in relative positions to each other, to allow fixed-geometry turbochargers to change the airflow through the nozzles in the turbochargers in response to a change in loads applied to the engines connected to the turbochargers.

[0033] Fig. Figure 1 illustrates a cropped view of a turbocharger 100 with a fixed geometry according to one embodiment. The turbocharger 100 contains a turbine impeller 102 , which rotates in response to the detection of an airflow. The turbine impeller 102 is equipped with a compressor impeller 104 connected via a shaft (not illustrated). The turbine impeller 102 contains turbines or rotor blades 106 , which the turbine impeller 102 , the compressor impeller104 and cause the shaft to rotate. A section of a spiral casing 108 is in Fig. 1 illustrated. The spiral casing 108 or the spiral extends along the circumference around at least part of the turbine impeller 102 around. A nozzle 110 is between the spiral casing 108 and the turbine impeller 102 arranged concentrically. The nozzle 110 contains flow passages 112 , through the air from a room 114 out, which is through the spiral casing 108 and the turbine impeller 102 Once defined, it flows. The turbocharger 100 Therefore, a turbocharger can 100 with a fixed geometry than the turbine blades 106 They do not rotate or move individually in relation to each other. Instead, all the turbine blades are 106 They are fixed in a position relative to each other and rotate together.

[0034] Fig. Figure 2 illustrates an embodiment of a nozzle device. 200 for a turbocharger. The nozzle assembly 200 can be used instead of the nozzle 110 in which Fig. 1 illustrated turbocharger 100 can be used. The nozzle assembly 200 contains a nozzle 202 with flow passages 210 , which pass through the nozzle 202 extend through it. The nozzle 202 has a ring shape with an outer and an opposing inner surface 212 , 214 up. The nozzle 202 and the surfaces 212 , 214 extend around or surround a central axis 215 the nozzle 202 and the nozzle assembly 200 The central axis 215 can be connected to the (not illustrated) central axis of the turbine impeller 102 in the (in Fig. 1 illustrated) turbocharger 100 be identical.

[0035] The flow passages 210 are openings or channels that extend through the nozzle 202 through from the outer surface 212 to the inner surface 214 extend to allow and direct air through the nozzle 202 from the (in Fig. 1 illustrated) space 114 , which is through the (in Fig. 1 illustrated) spiral case 108 is defined, to the (in Fig. 1 illustrated) turbines 106 of (in Fig. 1 illustrated) turbine runner 102 to flow.

[0036] A ring-shaped body 204 is with the nozzle 202 coupled. The ring-shaped body 204 can be used with the nozzle 202 connected and able to move along the outer surface 212 the nozzle 202 to move. For example, the ring-shaped body can 204 along and around the outer surface 212 the nozzle 202extend around and be able to access the outer surface 212 the nozzle 202 around the central axis 216 to glide. Similar to the nozzle. 202 the ring-shaped body extends 204 around the central axis 216 around and surrounds them.

[0037] The ring-shaped body 204 contains a first and a second ring 206 , 208 , in directions parallel to the central axis 216 The rings run parallel to each other and are axially spaced apart. 206 , 208 can have the same shape as the outer surface 212 the nozzle 202 have, but slightly larger along radial directions from the central axis 216 as the outer surface 212 the nozzle 202 to be in order to resemble the ring-shaped body 204 to allow it to move outside the nozzle, for example by moving along the outer surface 212 the nozzle 202along one or more circumferential directions 220 , 222 leads to the outer perimeter or circumferential edge of the outer surface 212 the nozzle 202 run parallel.

[0038] The ring-shaped body 204 contains locking segments 218 , which are located between the rings 206 , 208 of the ring-shaped body 204 extend. For example, the locking segments can 218 from solid bodies or extensions of the rings 206 , 208 be formed, which are formed by a ring 206 or 208 to the other ring 208 or 206 extend along axial directions that are parallel to the central axis 216 The blocking segments run. 218 They also extend partially in transverse directions (e.g., vertical directions), such as directions parallel to the circumferential directions. 220 , 222 get lost.

[0039] The locking segments 218 are separated by gaps along the circumferential directions 220 , 222 separated from each other to create open segments or openings 209 in the ring-shaped body 204 to define. As in Fig. As illustrated in Figure 2, the rings extend 206 , 208 and the locking segments 218 around the openings 209 of the ring-shaped body 204 around or frame them. In the illustrated embodiment, the locking segments form 218 and the openings 209 an alternating sequence along the circumferential directions 220 , 222 in the ring-shaped body 204 .

[0040] The ring-shaped body 204 can in relation to the nozzle 202 be moved to move one or more of the locking segments 218 above the flow passages 210 in the nozzle 202 to position. The locking segments 218, which are above the flow passages 210 Positioned, they block the airflow into these flow passages. 210 into and through the nozzle 202 through to the (in Fig. 1 illustrated) turbines 106 of the turbocharger 100 The ring-shaped body 204 defined openings 209 , which are above the flow passages 210 the nozzle 202 are positioned to allow air to pass through the openings. 209 through and into the flow passages 210 into the turbines 106 of the turbocharger 100 to flow.

[0041] Fig. 3 illustrates the in Fig. 2 nozzle assembly shown 200 in a different position relative to the one in Fig. 2 illustrated nozzles 202 The ring-shaped body 204 can be done around the nozzle 202 to be rotated to determine the positions of the locking segments218 and the openings 209 in the ring-shaped body 204 relative to the flow passages 210 in the nozzle 202 to change. As a result, the amount of air coming out of the (in) Fig. 1 illustrated) space 114 , which is through the (in Fig. 1 illustrated) spiral case 108 and that (in Fig. 1 illustrated) turbine impeller 102 of (in Fig. 1 illustrated) turbocharger 100 is defined by the flow passages 210 in the nozzle 202 through and to the (in Fig. 1 illustrated) turbines 106 of (in Fig. 1 illustrated) turbine charger 100 flows, at least partially, through a movement of the ring-shaped body 204 in relation to the nozzle 202 can be controlled.

[0042] For example, the locking segments 218 of the ring-shaped body 204in the state or position of the ring-shaped body 204 in Fig. 2 (relative to the nozzle) 202 ) between the flow passages 210 in the nozzle 202 positioned, and the openings 209 in the ring-shaped body 204 are above the flow passages 210 arranged. The locking segments 218 in the ring-shaped body 204 In these positions, the air does not obstruct its flow into the flow passages. 210 in the nozzle 202 to flow in and through them. As a result, more air can pass through the turbocharger. 100 and the one with the turbocharger 100 flow to the connected motor.

[0043] However, a twisting of the ring-shaped body causes 204 from the in Fig. 2 illustrated position to the one in Fig. Position 3 illustrated that the locking segments 218 in the ring-shaped body 204over a part (e.g. half or another fraction) of the flow passages 210 in the nozzle 202 be positioned. The openings 209 in the ring-shaped body 204 are above some, but not all, of the flow passages 210 arranged. The locking segments 218 in the ring-shaped body 204 In these positions, at least some of the air is prevented from entering the flow passages. 210 in the nozzle 202 to flow into and through them. For example, the ring-shaped body 204 In this position, half of the air passes through the nozzle. 202 in the Fig. The flow in position 2, which is illustrated, prevents it from passing through the nozzle. 202 to flow. As a result, less air can pass through the turbocharger. 100 and the one with the turbocharger 100 flow to the connected motor.

[0044] In the illustrated embodiment, the locking segments 218 the same size as every other one, and the openings 209 They are the same size as any other. Alternatively, two or more locking segments can be used. 218 have different sizes, and / or two or more of the openings 209 They can have different sizes. This can result in the locking segments... 218 less or more of one or more of the flow passages 210 in the nozzle 202 block. Furthermore, the ring-shaped body 204 in the illustrated embodiment on the outer surface 212 the nozzle 202 arranged and moves along this path. Alternatively, the ring-shaped body 204 on the inner surface 214 the nozzle 202 to be arranged and move along these lines. A placement of the body. 204 on the inner surface 214can reduce entry losses.

[0045] The one that passes through the nozzle 202 extending flow passages 210 can be the same size (or nearly the same size, such as when size differences are within manufacturing tolerances of the nozzle). 202 have (lying). The flow passages 210 can turn and go in directions 300 (the in Fig. 3 are illustrated) centered and along the directions 300 be elongated, perpendicular to the radial directions of the central axis 216 (e.g. in non-radial directions) and which lead to the outer or inner surface 212 , 214 the nozzle 202 do not run tangentially. Furthermore, the flow paths can be aerodynamically designed to reduce flow losses through the passage by applying rounded leading edges and / or curvature to the cross-sectional area. A flow path210 is in one direction 300 centered when the inner surface of the nozzle 202 to control the flow 210 (the surface of the nozzle 202 , which determine the shape and size of the flow passage 210 defined) has opposite sides that lead to the direction 300 are equidistant, or has all sides that differ from the direction 300 are equidistant.

[0046] In one embodiment, the directions 300 , along which the flow passages 210 are centered and extend at the same angle with respect to the outer surface 212 the nozzle 202 aligned and / or at the same angle with respect to the inner surface 214 the nozzle 202 aligned. For example, all flow passages can be 210 Guide air along paths that have the same orientation relative to the nozzle. 202exhibit.

[0047] Fig. Figure 4 illustrates a cross-sectional view of an embodiment of the [unclear text] Fig. 2 and Fig. 3 illustrated nozzle assembly 200 This view of the nozzle assembly 200 shows the shape of the flow passages 210 through the nozzle 202 As in Fig. As illustrated in section 4, the flow paths include 210 Flow passages 400 , 402 , which are viewed at different angles with respect to the outer surface 212 the nozzle 202 are aligned. The flow passages 400 , 402 are viewed from different angles with respect to the outer and / or inner surface 212 , 214 the nozzle 202 aligned.

[0048] For example, the flow passages 400 on first directions or axes 404centered and elongated along these first directions, and the flow passages 402 are directed towards other, second directions or axes 406 centered and elongated along this line. The first directions 404 the flow passages 400 are at obtuse angles 408 in relation to the outdoor area 212 the nozzle 202 aligned, and the second directions 406 the flow passages 402 are at obtuse angles 410 in relation to the outdoor area 212 the nozzle 202 aligned. As in Fig. As illustrated in 4, the angles are 408 , among which the directions 404 , into which the flow passages 400 in relation to the outdoor area 212 the nozzle 202 are aligned greater than the angles 410 , among which the directions 406 , into which the flow passages 402in relation to the outdoor area 212 the nozzle 202 are aligned.

[0049] In the illustrated embodiment, the flow paths alternate. 400 , 402 each other around the circumference of the nozzle 202 such that each flow passage 400 a flow passage 402 on each side of the flow passage 400 exhibits and each flow passage 402 a flow passage 400 on each side of the flow passage 402 exhibits. Alternatively, a larger number of flow passages can be used. 400 and / or 402 between pairs of flow passages 402 and / or 400 be arranged.

[0050] The flow passages 400 , 402 Different orientations allow for different sets of flow paths. 210 represent the flow paths. 400can in one set of flow passages 210 be included, and the flow passages 402 can in another, second set of flow passages 210 be included. The (in Fig. 2 illustrated) blocking segments 218 and / or the (in Fig. 2 illustrated openings 209 of (in Fig. 2 illustrated) ring-shaped body 204 can be positioned to block the locking segments 218 to cause some or all of the flow passages 210 to block in one sentence, while the flow passages 210 in the other sentence not be blocked if the ring-shaped body 204 in a first position or at a first place relative to the nozzle 202 is located, and the locking segments 218 and / or the openings 209 of the ring-shaped body 204 can be positioned to block the locking segments218 to cause some or all of the flow passages 210 to block in another, different set, while the flow passages 210 in another sentence not be blocked if the ring-shaped body 204 in a different, second position or orientation relative to the nozzle 202 is located.

[0051] For example, the ring-shaped body 204 in relation to the nozzle 202 to be rotated to a first position to ensure that none of the locking segments 218 the airflow through any flow passages 210 (or 400 , 402 ) blocked. The ring-shaped body 204 can be rotated to a different, second position to engage the locking segments 218 to cause the airflow through the flow passages 210 in the first sentence (e.g. the flow passages) 400) to block, while the airflow through the flow passages 210 in the second sentence (e.g. the flow passages) 402 ) is not blocked. The ring-shaped body 204 can be rotated to another, third position to lock the segments 218 to cause the airflow through the flow passages 210 in the second sentence (e.g. the flow passages) 402 ) to block, while the airflow through the flow passages 210 in the first sentence (e.g. flow passages) 400 ) is not blocked.

[0052] This allows the ring-shaped body 204 , to be used to control the airflow through the nozzle 202 based on the position of the ring-shaped body 204 in relation to the nozzle 202 to control it. In the first position described above, more air flows through the nozzle. 202less air flows through the nozzle than in the second or third position. In the second position described above, less air flows through the nozzle. 202 than in the first position, however, with more air passing through the nozzle 202 Less air flows through the nozzle in the third position, as described above. 202 than in the first or second position. More air can pass through the nozzle. 202 flow when the ring-shaped body 204 the flow passages 400 blocked, or in other words, the obtuse angle 410 is smaller than the obtuse angle 408 Optionally, the cross-sectional area of ​​the flow passages can be adjusted. 400 , 402 to differentiate, in order to allow different amounts of air to pass through the nozzle 200 flow. For example, the flow passages can 400 be wider than the flow passages 402(or vice versa) to allow more air to pass through the passages 400 as through the passages 402 flows.

[0053] Fig. Figure 5 illustrates a first perspective view of an embodiment of an actuating device. 500 . Fig. Figure 6 illustrates a different, second perspective view of the in Fig. 5 illustrated operating devices 500 The operating device 500 can be used to create the ring-shaped body 204 relative to the nozzle 202 in which Fig. 1 illustrated turbocharger 100 to move. The operating device 500 moves the ring-shaped body 204 in relation to the nozzle 202 , in order to change which, if any, the (in the Fig. 2 to Fig. 4 illustrated) flow passages 210 through the (in Fig. 2 illustrated) blocking segments 218of the ring-shaped body 204 be blocked.

[0054] The operating device 500 contains connecting elements 502 , which has a ring-shaped body 204 are coupled at one or more points. The connecting links 502 are made with elongated rods 504 coupled, which in turn are connected to swivel plates 506 are connected. The swivel plates 506 are connected to a fixed body, such as part of the turbocharger housing 100 , which is not relative to the nozzle 202 movable, pivotably connected. The swivel plates 506 contained (in Fig. 6 illustrated pivot points 600 , which are connected to the stationary body of the turbocharger 100 are connected, and guided tours 508 , which move along corresponding slots in the stationary body, as in Fig. 5 illustrates. The guided tours 508and / or other parts of the swivel plates 506 can be connected to a motor or other device capable of rotating the pivot points 600 to move. For example, a motor can move the guides. 508 move along the slots in the stationary body to the swivel plates 506 to cause the pivot points 600 to swivel around.

[0055] This pivoting of the swivel plates 506 is caused by the poles 504 and the connecting links 502 in a rotational movement of the ring-shaped body 204 at the nozzle 202 implemented or converted. The operating device 500 can the ring-shaped body 204 to move in this way in order to change which flow paths 210 , if at all, be blocked to prevent airflow through them.

[0056] Fig.Figure 7 illustrates a flowchart of an embodiment of a process. 700 for controlling the airflow through a nozzle of a turbocharger. At 702 A load applied to an engine (or power unit) (and / or turbocharger) is determined. This load can represent an amount of torque, power, or other force to be delivered by the engine. The load can be determined based on a throttle or pedal position of a vehicle or an operating stage on a locomotive, a change in the number of devices driven by a generator or alternator connected to the engine, or based on sensor data. 704A determination is made as to whether the airflow through the turbocharger nozzle to the engine should be modified. For example, if the load applied to the engine has decreased (e.g., by at least a defined non-zero amount, such as a drop of 20%, 40%, 50%, or more), less airflow through the turbocharger to the engine may be required compared to when the load remains the same, increases, or decreases by a smaller amount. Conversely, if the load applied to the engine has increased (e.g., by at least a defined non-zero amount, such as an increase of 20%, 40%, 50%, or more), a greater airflow through the turbocharger to the engine may be required compared to when the load remains the same, decreases, or increases by a smaller amount.

[0057] If the airflow is to be changed in response to a change in load, the sequence of the procedure can be 700 to 706 progress. Otherwise, if the airflow is not to be changed in response to a change in load, the procedure may not proceed. 700 to 708 progress. At 706A change is made regarding which flow passages through a turbocharger nozzle are open and / or closed. For example, if the load has decreased, several flow passages can be blocked, and / or a different set of flow passages can be blocked to reduce the air flowing through the nozzle to the turbine and engine. Conversely, if the load has increased, fewer or different flow passages can be blocked, or no flow passages can be blocked at all, to increase the air flowing through the nozzle to the turbine and engine.

[0058] The change in which flow passages are blocked or open can be made by rotating the annular body relative to the nozzle, as described above.

[0059] At 708Air is directed through the turbocharger to the engine via the open flow passages. For example, if no flow passages are blocked by the annular body's restrictor segments, air can flow through many or all of the nozzle's flow passages from the spiral to the turbines and then to the engine. If some flow passages are blocked by the restrictor segments, air can flow through the remaining, unblocked flow passages from the spiral to the turbines and then to the engine. The process unfolds as follows: 700 can lead to 702 return or may end.

[0060] In the sense used herein, an element or step specified in the singular and preceded by the word "a" or "an" should be understood as not excluding several such elements or steps, unless such exclusion is explicitly stated. Furthermore, references to "an embodiment" of the subject matter described herein should not be interpreted as excluding the existence of other embodiments that also include the specified features. Moreover, unless explicitly stated otherwise, embodiments that "have" or "feature" an element or elements with a particular property may include additional such elements that do not have that property.

[0061] It should be understood that the foregoing description is intended to be illustrative and not limiting. For example, the embodiments described above (and / or aspects thereof) can be used in combination with one another. Furthermore, many modifications can be made to adapt a particular situation or material to the teachings of the subject matter explained herein without deviating from its scope. While the dimensions and types of materials described herein are intended to define the parameters of the disclosed subject matter, they are in no way limiting and represent exemplary embodiments. Many further embodiments will become apparent to those skilled in the art upon review of the foregoing description.The scope of protection of the subject matter described herein should therefore be determined by reference to the accompanying claims together with the full scope of equivalents to which such claims are entitled. In the accompanying claims, the expressions "contain" and "in the" are used as linguistic equivalents of the respective expressions "exhibit" and "in which." Furthermore, in the following claims, the terms "first," "second," and "third," etc., are used merely as designations and are not intended to impose any numerical requirements on their objects. Additionally, the features of the following claims are not written in the means-plus-function format and are not intended to be interpreted on the basis of 35 USC § 112(f), unless and until such claim features expressly use the phrase "means to," followed by a statement of a function without any further structure.

[0062] This written description uses examples to disclose various embodiments of the subject matter set forth herein, including the best embodiment, and also to enable a person skilled in the field to carry out the embodiments of the disclosed subject matter, including the creation and use of the devices or systems and the performance of the methods. The patentable scope of the subject matter described herein is defined by the claims and may include further examples that would occur to a person skilled in the field. Such further examples shall be within the scope of protection of the claims if they have structural elements that do not differ from the literal meaning of the claims or if they contain equivalent structural elements with insignificant differences from the literal meaning of the claims.

[0063] A nozzle assembly 200 a turbocharger100 contains a nozzle 202 and a ring-shaped body 204 The nozzle 202 exhibits flow passages 210 ; 400 , 402 on, which protrudes through the nozzle 202 extend through and are designed to be housed in a spiral casing 108 of the turbocharger 100 air received through the nozzle 202 through to turbine blades 106 of the turbocharger 100 to conduct. The ring-shaped body 204 is with the nozzle 202 coupled and is set up to move around the nozzle 202 to rotate the ring-shaped body 204 contains locking segments 218 , which block the flow of air, and openings 209 between the locking segments 218 , which allow the air to pass through the ring-shaped body 204 to flow. The ring-shaped body 204 is set up to be in relation to the nozzle 202to be twisted in order to change how many of the flow passages 210 ; 400 , 402 in the nozzle 202 through the locking segments 218 of the ring-shaped body 204 be blocked.

Claims

[1] Nozzle assembly of a turbocharger, wherein the assembly comprises: a nozzle ( 202 ), the flow passages ( 210 ; 400 , 402 ) exhibits, which extends through the nozzle ( 202 ) extend through and are designed to be accessed from a spiral casing ( 108 ) of the turbocharger ( 100 ) air received through the nozzle ( 202 ) to turbine rotor blades ( 106 ) of the turbocharger ( 100 ) to lead; and a ring-shaped body ( 204 ), which is connected to the nozzle ( 202 ) coupled and around the nozzle ( 202 ) is arranged to be rotatable, wherein the ring-shaped body ( 204 ) Blocking segments ( 218 ), which block the flow of air, and openings ( 209 ) between the blocking segments ( 218 ) contains, which allow the air to pass through the ring-shaped body ( 204 ) to flow, whereby the ring-shaped body ( 204 ) relative to the nozzle ( 202) is rotatable to change how many of the flow passages ( 210 ; 400 , 402 ) in the nozzle ( 202 ) through the blocking segments ( 218 ) of the ring-shaped body ( 204 ) be blocked. [2] Nozzle device claim 1, wherein the annular body ( 204 ) is set up to be relative to the nozzle ( 202 ) to be twisted in order to change which of the flow passages ( 210 ; 400 , 402 ) in the nozzle ( 202 ) the air to the turbine blades ( 106 ) flows. [3] Nozzle device according to claim 1 or 2, wherein the annular body ( 204 ) a first and an opposing second ring ( 206 , 208 ) contains which are along a central axis ( 216 ) of the ring-shaped body ( 204 ) are spaced apart from each other, with the blocking segments ( 218 ) of the ring-shaped body (204 ) from the first ring ( 206 ) to the second ring ( 208 ) extend in directions parallel to the central axis ( 216 ) of the ring-shaped body ( 204 ) get lost. [4] Nozzle device according to claim 3, wherein all of the openings ( 209 ) of the ring-shaped body ( 204 ) between the first and the second ring ( 206 , 208 ) and different pairs of the blocking segments ( 218 ) of the ring-shaped body ( 204 ) arranged and framed by this. [5] Nozzle assembly according to any one of the preceding claims, wherein the nozzle ( 202 ) an interior surface ( 214 ) and an opposite outer surface ( 212 ) exhibits, on which the ring-shaped body ( 204 ) relative to the nozzle ( 202 ) rotates; or wherein the nozzle has an outer surface ( 212 ) and an opposite inner surface ( 214) exhibits, on which the ring-shaped body ( 204 ) relative to the nozzle ( 202 ) turns. [6] Nozzle device according to any one of the preceding claims, wherein the flow passages ( 210 ; 400 , 402 ) through the nozzle ( 202 ) in radial, non-tangential directions ( 300 ; 404 , 406 ) relative to an outer surface ( 212 ) the nozzle ( 202 ) centered and along the non-radial, non-tangential directions ( 300 ; 400 , 404 , 406 ) are elongated. [7] Nozzle assembly according to any one of the preceding claims, wherein the nozzle ( 202 ) an inner surface and an opposite outer surface ( 214 , 212 ) exhibits, whereby the flow passages ( 210 ) in the nozzle ( 202 ) from the outer surface ( 214 ) to the inner surface ( 212) extend, with the flow passages ( 400 , 402 ) at least a first and a second set of flow passes ( 400 , 402 ) contained, through which the air passes through the nozzle ( 202 ) flows, whereby the flow passages ( 400 ) in the first sentence about the first non-radial, non-tangential directions ( 404 ) are centered and extend from the outer surface ( 214 ) to the inner surface ( 212 ) along the first non-radial, non-tangential directions ( 404 ) extend, with the flow passages ( 402 ) in the second sentence about second non-radial, non-tangential directions ( 406 ) are centered and extend from the outer surface ( 214 ) to the inner surface ( 212 ) along the second non-radial, non-tangential directions ( 406 ) extend in relation to the first non-radial, non-tangential directions ( 404are aligned horizontally. [8] Nozzle device according to any one of the preceding claims, wherein the flow passages ( 400 , 402 ) through the nozzle ( 202 ) a first and a second set of flow passes ( 400 , 402 ) containing the flow passages ( 400 ) in the first sentence on first directions ( 404 ) are centered and extend along the first directions ( 404 ) extend at a first angle ( 408 ) in relation to an exterior surface ( 214 ) the nozzle ( 202 ) are aligned, and the flow passages ( 402 ) in the second sentence to other, second directions ( 406 ) are centered and extend along the other, second directions ( 406 ) extend at a different, second angle ( 410 ) in relation to the outer surface ( 214 ) the nozzle ( 202 are aligned. [9] Nozzle assembly according to any one of the preceding claims, further comprising an actuating device ( 500 ) has which is set up to interact with the ring-shaped body ( 204 ) to be coupled, and is set up to form the ring-shaped body ( 204 ) around the nozzle ( 202 ) to move. [10] Air flow limiting body of a turbocharger, wherein the air flow limiting body comprises: a first ring ( 206 ), which is set up to use a nozzle ( 200 ) of the turbocharger ( 100 ) to be coupled; a second ring ( 208 ), which is set up to work with the nozzle ( 202 ) of the turbocharger ( 100 ) to be coupled, with the second ring ( 208 ) in a direction parallel to a central axis ( 216 ) the nozzle ( 202 ) of the turbocharger ( 100 ) runs from the first ring ( 206 ) is spaced apart; and Blocking segments ( 218 ), which differ from the first ring ( 206 ) to the second ring ( 208 ) extend and through openings ( 209 ) are spaced apart from each other, with the first and second rings ( 206 , 208 ) and the locking segments ( 218 ) around the nozzle ( 202 ) of the turbocharger ( 100 ) are rotatably set up to change which flow passages ( 210 ; 400 , 402 ) the nozzle ( 202 ), through the air from a spiral casing ( 108 ) of the turbocharger ( 100 ) to running vanes ( 106 ) of the turbocharger ( 100 ) flows, are open and which of the flow passages ( 210 ; 400 , 402 ) are closed.

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