Nozzle for separating a volute

Abstract

An assembly can include an exhaust turbine housing including an inner wall and an outer wall defining a first exhaust passage and a second exhaust passage to a turbine wheel space, wherein the inner wall includes an inner wall end at the turbine wheel space and the outer wall includes an outer wall end at the turbine wheel space; a first flow body disposed adjacent the inner wall end; a second flow body disposed adjacent the outer wall end; and at least one set of adjustable variable geometry nozzle vanes defining a nozzle throat that directs a flow of exhaust from at least one of the exhaust passages to the turbine wheel space, wherein at least one of the first flow body and the second flow body includes a concave aft surface defined in part by a circular arc.

Description

[0001] Related applications This application claims priority and interest in U.S. Provisional Application No. 63 / 151755, filed February 21, 2021, which is incorporated herein by reference. Technical Field

[0002] The topics discussed in this article generally relate to turbochargers. Background Technology

[0003] A turbocharger increases the output of an internal combustion engine. A turbocharger may include an exhaust turbine assembly that receives exhaust gases from the cylinders of the internal combustion engine. The exhaust gases can be directed to the turbine impeller, allowing energy to be extracted, for example, to drive the compressor impeller of a compressor assembly. Attached Figure Description

[0004] A more complete understanding of the various methods, apparatuses, components, systems, arrangements, and their equivalents described herein can be obtained by referring to the following detailed description, in conjunction with the examples shown in the accompanying drawings, wherein: Figure 1 This is an example diagram of a turbocharger, internal combustion engine, and controller; Figure 2A , 2B 2C is a view of examples of turbocharger-related equipment; Figure 3 A series of views that are part of a component; Figure 4 This is a perspective view of an example of a component that includes a variable geometry mechanism; Figure 5 This is a perspective view of a portion of an example of a component that includes a variable geometry mechanism.

[0005] Figure 6A , 6B 6C is a perspective view of the component, a cross-sectional view of it, and a perspective view of a portion of the component including a variable geometry mechanism.

[0006] Figure 7 A cross-sectional view of an example component is shown.

[0007] Figure 8 It shows Figure 7 A cross-sectional view of a portion of a component.

[0008] Figure 9 It shows Figure 7 A cross-sectional view of a portion of a component.

[0009] Figure 10 It shows Figure 7 A cross-sectional view of a portion of a component.

[0010] Figure 11 It shows Figure 7 A cross-sectional view of a portion of a component.

[0011] Figure 12 It shows Figure 7 A perspective view of a portion of a component.

[0012] Figure 13 A perspective view and cross-sectional view of an example of a fluid are shown.

[0013] Figure 14 It shows Figure 9 An enlarged cross-sectional view of a part of the component.

[0014] Figure 15 It shows Figure 10 An enlarged cross-sectional view of a part of the component.

[0015] Figure 16 It shows Figure 11 An enlarged cross-sectional view of a part of the component.

[0016] Figure 17 It shows Figure 7 A cross-sectional view of a portion of a component.

[0017] Figure 18 It shows Figure 7 A cross-sectional view of a component, showing an example of a fluid. Detailed Implementation

[0018] Turbochargers are frequently used to increase the output of internal combustion engines. (Reference) Figure 1 As an example, system 100 may include an internal combustion engine 110 and a turbocharger 120. Figure 1 As shown, system 100 may be part of vehicle 101, wherein system 100 is disposed in the engine compartment and connected to exhaust duct 103, which directs exhaust gas to exhaust outlet 109, for example, located behind passenger compartment 105. Figure 1 In one example, a processing unit 107 may be provided to process exhaust gas (e.g., reduce emissions through catalytic conversion of molecules, etc.).

[0019] like Figure 1 As shown, the internal combustion engine 110 includes an engine block 118 that houses one or more combustion chambers operatively driving a shaft 112 (e.g., via a piston), and an intake port 114 and an exhaust port 116, the intake port 114 providing a flow path for air to the engine block 118 and the exhaust port 116 providing a flow path for exhaust gas from the engine block 118.

[0020] The turbocharger 120 can be used to extract energy from the exhaust and provide energy to the intake air, which can then combine with fuel to form combustion gases. For example... Figure 1 As shown, the turbocharger 120 includes an air inlet 134, a shaft 122, a compressor housing assembly 124 for a compressor impeller 125, a turbine housing assembly 126 for a turbine impeller 127, another housing assembly 128, and an exhaust outlet 136. The housing assembly 128 may be referred to as a central housing assembly because it is disposed between the compressor housing assembly 124 and the turbine housing assembly 126. The shaft 122 may be a shaft assembly comprising various components. The shaft 122 may be rotatably supported by a bearing system (e.g., journal bearings, rolling element bearings, etc.) disposed in the housing assembly 128 (e.g., in a bore defined by one or more bore walls), such that rotation of the turbine impeller 127 causes rotation of the compressor impeller 125 (e.g., rotatably coupled by the shaft 122). As an example, the central housing rotating assembly (CHRA) may include a compressor impeller 125, a turbine impeller 127, a shaft 122, a housing assembly 128, and various other components (e.g., a compressor side plate disposed at an axial position between the compressor impeller 125 and the housing assembly 128).

[0021] exist Figure 1 In the example, the variable geometry component 129 is shown partially disposed between the housing assembly 128 and the housing assembly 126. Such a variable geometry component may include blades or other components to change the geometry of the passageway leading to the turbine impeller space in the turbine housing assembly 126. As an example, a variable geometry compressor assembly may be provided.

[0022] exist Figure 1 In the example, the exhaust bypass valve (or simply exhaust bypass valve) 135 is located near the exhaust inlet of the turbine housing assembly 126. The exhaust bypass valve 135 can be controlled to allow at least some exhaust gas from the exhaust port 116 to bypass the turbine impeller 127. Various exhaust bypass valves, exhaust bypass valve components, etc., can be applied to conventional fixed-nozzle turbines, fixed-blade nozzle turbines, variable-nozzle turbines, twin-scroll turbochargers, etc. As an example, the exhaust bypass valve can be an internal exhaust bypass valve (e.g., at least partially located inside the turbine housing). As an example, the exhaust bypass valve can be an external exhaust bypass valve (e.g., operatively connected to a pipe in fluid communication with the turbine housing).

[0023] exist Figure 1 The example also shows an exhaust gas recirculation (EGR) pipe 115, which may optionally be equipped with one or more valves 117, for example, to allow exhaust gas to flow to a location upstream of the compressor impeller 125.

[0024] Figure 1Example arrangement 150 for exhaust flow to exhaust turbine housing assembly 152 and another example arrangement 170 for exhaust flow to exhaust turbine housing assembly 172 are also shown. In arrangement 150, cylinder head 154 includes internal passage 156 for guiding exhaust from cylinders to turbine housing assembly 152, while in arrangement 170, manifold 176 is used to mount turbine housing assembly 172, for example, without any separate exhaust pipe of intermediate length. In example arrangements 150 and 170, turbine housing assemblies 152 and 172 can be configured for use with exhaust bypass valves, variable geometry assemblies, etc.

[0025] exist Figure 1 In this document, an example of controller 190 is shown including one or more processors 192, memory 194, and one or more interfaces 196. Such a controller may include circuitry such as that of an engine control unit (ECU). As described herein, various methods or techniques may be optionally implemented, for example, with control logic along with the controller. The control logic may depend on one or more engine operating conditions (e.g., turbine speed, engine speed, temperature, load, lubricant, cooling, etc.). For example, sensors may transmit information to controller 190 via one or more interfaces 196. The control logic may rely on such information, and controller 190 may output control signals to control engine operation. Controller 190 may be configured to control lubricant flow, temperature, variable geometry components (e.g., variable geometry compressors or turbines), exhaust bypass valves (e.g., via actuators), electric motors, or one or more other components associated with the engine, turbocharger(s), etc. As an example, turbocharger 120 may include one or more actuators and / or one or more sensors 198, which may be coupled, for example, to one or more interfaces 196 of controller 190. As an example, the exhaust bypass valve 135 may be controlled by a controller that includes an actuator responsive to electrical signals, pressure signals, etc. As an example, the actuator for the exhaust bypass valve may be a mechanical actuator, which can operate without electricity (e.g., consider a mechanical actuator configured to respond to a pressure signal supplied via a pipe).

[0026] Internal combustion engines (such as) Figure 1Engine 110 in a turbocharger can produce exhaust gas with a pulsating flow. In so-called constant-pressure turbocharging (e.g., Stauaufladung), a sufficiently large exhaust manifold acts as a damper for mass flow and pressure pulses, making the flow of exhaust gas to the turbine relatively stable. Another method, called pulse turbocharging (e.g., Stoßaufladung), can aim to utilize the kinetic energy of exhaust gas as it leaves the cylinder exhaust ports. For example, relatively short pipes with small cross-sections can connect each exhaust port to the turbine, thus utilizing most of the kinetic energy associated with the exhaust emissions. As an example, proper grouping of the exhaust ports from different cylinders can organize the exhaust gas pulses so that they are continuous, for example, with minimal overlap. In this way, the instability of the exhaust gas flow can be kept at an acceptable level. As an example, the decision to implement constant-pressure or pulse turbocharging can depend on one or more factors, such as power requirements, efficiency requirements, fuel type, number of cylinders, cylinder / stroke volume, engine size, etc.

[0027] Figure 2A An example of a system 200 including a four-cylinder internal combustion engine with a firing order 201 is shown; for example, consider a firing order of 1-3-4-2. As shown, a manifold 216 (e.g., one or more manifolds) may define an exhaust gas flow path that directs exhaust gas from the internal combustion engine cylinders to a turbine assembly 260, which at least partially houses a turbine impeller 270. Figure 2A As shown, turbine assembly 260 includes a flange 261, an outer wall 262, and an inner wall 264, wherein the outer wall 262 and the inner wall 264 define exhaust volute passages 267 and 269. Path 267 may receive exhaust from flow path 217 communicating with cylinders 1 and 4, and path 269 may receive exhaust from flow path 219 communicating with cylinders 2 and 3.

[0028] Figure 2BAn example of a manifold 216 comprising two flow paths 217 and 219 is shown. As an example, manifold 216 can be considered a partitioned manifold that separates exhaust flows from multiple cylinders whose cycles may interfere with each other (e.g., regarding exhaust pulse energy). For example, in a four-cylinder engine with a firing order of 1-3-4-2, cylinder 1 is finishing its expansion stroke and opening its exhaust valve, while the exhaust valve of cylinder 2 is still open (cylinder 2 is in its overlap period). In an unpartitioned exhaust manifold, the pressure pulse from the exhaust event of cylinder 1 might be more likely to contaminate cylinder 2 with high-pressure exhaust gas, which could affect the performance of cylinder 2 (e.g., its ability to properly intake and exhaust) and reduce the pulse energy that the turbine might better utilize. As an example, appropriate grouping of the aforementioned engine could group complementary cylinders together (e.g., the exhausts of cylinders 1 and 4 as one complementary group, and cylinders 2 and 3 as another complementary group). This method allows for better utilization of exhaust pulse energy and, for example, improves turbine performance (e.g., increases boost pressure more quickly).

[0029] refer to Figure 2C The image shows a turbine assembly 290, which includes volutes 292-1 and 292-2 with partition walls 295 and a turbine impeller 297. The turbine assembly 290 differs from the turbine assembly 260 in that the volutes 292-1 and 292-2 span a common angular range around the turbine impeller 297.

[0030] exist Figure 2A In the figure, walls 262 and 264 may be walls of a double-channel turbine casing, wherein paths 267 and 269 are radially adjacent channels. As shown, paths 267 and 269 extend in a generally helical form with respect to turbine impeller 270.

[0031] As shown in the figure, paths 267 and 269 have different lengths due to their geometric arrangement, and therefore can have different gas volumes. For example, the length of path 269 is greater than the length of path 267.

[0032] Despite Figure 2A The diagram shows an internal combustion engine with four cylinders, but one or more other engine types and / or numbers of cylinders may be used (e.g., inline six-cylinder engine, V8 engine, V6 engine, six-cylinder boxer engine).

[0033] exist Figure 2A In this context, path 217 can be defined by the length of the first manifold exhaust gas path, while path 219 can be defined by the length of the second manifold exhaust gas path. Figure 2A In the example, the length of the first manifold exhaust path 217 is longer than the length of the second exhaust path 219.

[0034] like Figure 2A As shown, the first manifold path 217 is connected to the first path 267, while the second manifold path 219 is connected to the second path 269, allowing the longer exhaust gas path length to connect to the shorter path of the turbine assembly. Such a method may be intended to “balance” the total path length. As an example, a dual-channel (e.g., dual-path) turbine housing with considerably different channels can be “balanced” by manifold geometries with similarly different channels. As an example, a combination of short and long independent paths (e.g., channels) of the turbine housing and manifold can be used to obtain approximately equal total paths.

[0035] Figure 3 An example of a dual-channel turbine housing is shown, which includes an inlet flange 361 and axially adjacent helical channels 367 and 369, defined, for example, by walls 362 and 364.

[0036] For diesel engine applications, variable nozzle turbines (VNTs) can improve turbine energy efficiency, thus making the engine more fuel-efficient. For gasoline engines, especially 4-cylinder engines, they tend to be sensitive to knocking due to back pressure affecting residual gases. Technologies that enable flow separation (such as twin-scroll turbines) can be used to improve scavenging, thereby improving low-end torque. As an example, pulsating flow can be used to increase turbine power.

[0037] The applicability of VNT to gasoline engines may be limited because its inefficient characteristics in the closed position affect the sensitivity to knocking caused by high back pressure. Furthermore, the position of the closed blades can suppress pulse recovery from exhaust gases.

[0038] For example, one approach is to maintain flow separation up to the turbine impeller using a VNT-type method that can be used to improve fuel efficiency.

[0039] As an example, a variable nozzle can be combined with a dual-flow housing. As an example, the mechanism can include one or two blades that can move (e.g., pivot) relative to a wall, which can be a fixed wall. For example, consider one or more blades that can be positioned to act as "extensions" of one or more housing tongues (e.g., continuing flow separation up to a turbine impeller, forming a dual-flow nozzle). As an example, two blades can be used to define two approximately 180-degree segments (e.g., between the two blades) defining a circumferential region of the nozzle, wherein a movable blade can be added to one or both of said segments (e.g., in the VNT method, etc.). As an example, the end of the wall (e.g., a wall end) can be a tongue, and the blades can be used to change the tongue shape, tongue length, tongue continuity, etc.

[0040] As an example, the blade orientation can provide a pulsed volute, while another blade orientation can provide an open volute. In such an example, dual flow may occur in the open volute, which could potentially contribute to higher engine speeds (e.g., consider the Stoß – Stau method).

[0041] As an example, blades applied to axial wheels (e.g., dual-boost variable dual-flow) can be used to combine ultra-low inertia and variable dual-flow.

[0042] As an example, turbine components can be used to address one or more backflow issues. As an example, one or more blades can be actuated to address exhaust gas backflow during operation (e.g., depending on power demand, mass flow rate, volumetric flow rate, etc.).

[0043] Figure 4 An example of a portion of an assembly 860 including a variable geometry mechanism 880 is shown. As shown, assembly 860 includes a body with walls 862 and 864 having defining paths 867 and 869. Wall 862 includes a wall end 863 in the turbine impeller space, while wall 864 includes a wall end 865 in the turbine impeller space. The variable geometry mechanism 880 includes blades 882-1 and 882-2 and blades 884-1 to 884-N. Structures 883-1 and 883-2 are also shown. Structures 883-1 and 883-2 may be fixed or optionally movable. As shown, blades 882-1 and 882-2 may form relatively continuous surfaces with structures 883-1 and 883-2. Pivoting of blades 883-1 and 883-2 can change these surfaces to guide exhaust gas, for example, with respect to paths 867 and 869.

[0044] As in Figure 8 As shown in the example, blade 882-1 can pivot about a fixed wall end 863, while blade 882-2 can pivot about a fixed wall end 865. In such an example, the flow at walls 863 and 865 can be altered via the pivoting of blades 882-1 and 882-2. Such pivoting alters the flow into the turbine impeller space in paths (or channels) 867 and 869. Operating modes can coordinate the pivoting of blades 882-1 and 882-2 with the pivoting of blades 884-1 to 884-N. As an example, blades 884-1 to 884-N can comprise two sets, each corresponding to each of paths 867 and 869. As an example, such sets can be independently adjustable, or, for example, uniformly adjustable. As an example, blades 882-1 and 882-2, and blades 884-1 to 884-N, can be uniformly adjustable. As an example, blades 882-1 and 882-2 are adjustable independently of blades 884-1 to 884-N.

[0045] As an example, the component may include an exhaust gas turbine housing including an inner wall and an outer wall defining a first exhaust gas passage and a second exhaust gas passage leading to a turbine impeller space, wherein the inner wall includes an inner wall end at the turbine impeller space, and the outer wall includes an outer wall end at the turbine impeller space; a first adjustable partition blade disposed adjacent to the inner wall end; a second adjustable partition blade disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle blades defining a nozzle throat for guiding the flow of exhaust gas from at least one of the exhaust gas passages to the turbine impeller space.

[0046] Figure 5 It shows Figure 4 A portion of component 860, specifically the sectional view and partially exploded view. Figure 5 In the examples, various components, features, etc., can be described, for example, with respect to a z-axis that may coincide with the axis of rotation of the turbine impeller. As shown, the z-axis can serve as a reference defining various radial and / or axial dimensions. For example, a blade may include a blade height Δz, and one or more blade columns may be arranged at a radial distance r from the z-axis, which may be referred to as the central axis. As an example, various components may be concentric (e.g., substantially aligned with respect to the z-axis). As an example, during operation, one component may be fixed with respect to the z-axis, while another component rotates about the z-axis. As an example, a blade may rotate about a separate column axis, such as a separate z-column axis. Figure 5 As shown in the example, the marked z-axis can be set at a radial distance r from the z-axis.

[0047] like Figure 5 As shown, the variable geometry mechanism 880 includes a sub-assembly 890, which includes a ring 891, which may be a rotatable ring (e.g., a rotatable uniform ring) wherein the ring 891 is rotatable about the z-axis. Figure 5 In the example, ring 891 includes a socket that receives a corresponding convex end of control link 892, which is operatively coupled to a corresponding blade post 893. For example... Figure 5 As shown in the example, the socket of ring 891 accepts the convex end of a first control link 895, which is operatively connected to a second control link 896, which is operatively connected to a post 897 of blade 882-2. Blade 882-1 is also operatively connected to a component (e.g., another set of first control links 895 and second control links 896, etc.). Ring 891 may be at least partially supported by rollers (e.g., along the inner and / or outer circumference).

[0048] Figure 5The image also shows a nozzle ring 898, shown in cross-sectional view, having a cross-sectional surface spanning a column bore for blades 882-1 and 882-2 (e.g., see column 897). As an example, the nozzle ring 898 may be substantially centered about the z-axis and may be positioned in the assembly such that the nozzle ring 898 is substantially fixed so that it does not rotate about the z-axis. As an example, the nozzle ring 898 may be operatively coupled to one or more biasing mechanisms (e.g., one or more elastic plates, one or more springs, etc.) such that the nozzle ring 898 may undergo some movement along the z-axis. Figure 5 In the example, the nozzle ring 898 includes an upper surface and a lower surface, wherein post holes of blades 882-1, 882-2, and 884-1 to 884-N extend from the lower surface to the upper surface. A post disposed in the post hole can be rotated by rotation of the ring 891 (e.g., about a respective post axis), thereby pivoting the blade to which the post is attached. One or more blade front surfaces may be disposed on one side of the blade; for example, the hub side of each blade opposite the bottom side of each blade may face one or more blade front surfaces, wherein the bottom side faces the upper surface of the nozzle ring 898. In such an example, the nozzle may be defined between the upper surface of the nozzle ring 898 and the blade front surfaces, and between adjacent blades. As an example, the space between two adjacent blades may be referred to as a throat, wherein, for example, the shape of the throat may be adjusted by pivoting one or both of the two adjacent blades. The throat shape can guide exhaust gas in a more tangential or more axial manner with respect to the axis of rotation of the turbine impeller, which is disposed in the turbine impeller space, which can be partially defined by the nozzle ring 898.

[0049] exist Figure 5 In one example, the nozzle ring 898 includes a partial bore capable of receiving a pin extending axially from a first control link 895. As shown, the first control link 895 (e.g., a control arm) includes convex ends, one received by a socket of the ring 891 and the other by a socket of the second control link 896. In such an example, rotation of the ring 891 causes the first control link 895 to pivot about a pin (e.g., a pin axis), which in turn causes the second control link 896 to pivot. As shown, the second control link 896 includes a bore receiving one end of a post 897. In such an example, the post 897 can be fixed about the second control link 896 such that when the second control link 896 pivots, the blade 882-2 pivots.

[0050] Despite Figure 5The diagram shows a ring with a socket and a control linkage with a convex angle, but the blades can be controlled by one or more other types of mechanisms. For example, one or more mechanisms may include multiple rings, a single ring mechanism, and another type of mechanism, etc. As an example, blades 884-1 to 884-N may be adjustable independently of blades 882-1 and 882-2, or the blades may be adjustable in a coordinated manner (e.g., via rotation of the ring mechanism, etc.).

[0051] As an example, the mechanism may be actuated via a mechanical actuator, an electronic actuator, a pneumatic actuator, a hydraulic actuator, etc. (e.g., adjustable, etc.). As an example, the actuator may be a hybrid actuator (e.g., a combination of two or more actuators of the aforementioned types). As an example, the actuator may be operatively coupled to an engine control unit (ECU). As an example, the processor may execute instructions stored in memory to instruct the actuator to actuate one or more mechanisms capable of adjusting blades, a pair of blades, a set of blades, multiple sets of blades, etc. As an example, the actuator may actuate a ring in which the convex end of a control link moves together with the ring, thereby directly and / or indirectly rotating the blades (e.g., via blade columns, etc.).

[0052] Figure 6A A portion of component 860 is shown, which includes another component 1050. Figure 6B A cross-sectional view including a portion of component 860 and a portion of component 1050 is shown, and Figure 6C A portion of component 860 is shown, wherein a first control link 895 and a second control link 896 are mounted and controllable via rotation of ring 891. Figure 6A An example of an insert 1060 is shown, which includes a cylindrical portion 1064, wherein the insert 1060 may include one or more sealing elements 1085, which may be disposed in one or more recesses.

[0053] exist Figure 6A In this embodiment, component 1050 includes an insert 1060, which is operatively coupled to a variable geometry mechanism 880 via a plurality of spacers 1080-1, 1080-2, and 1080-3, noting that fewer or more spacers may be included. For example, in Figure 6C The diagram shows two spacers, 1080-1 and 1080-2. Figure 6A In the example, insert 1060 includes a generally planar base portion 1062 and a cylindrical portion 1064 rising axially from the generally planar base portion 1062. As shown, the cylindrical portion 1064 may include one or more sealing elements 1085. As an example, one or more sealing elements of different types may be included. Figure 6BIn a cross-sectional view, blade 884 is shown disposed between the lower surface of the generally flat base portion 1062 of insert 1060 and the upper surface of nozzle ring 898. As an example, spacers (e.g., 1080-1 and 1080-2 or 1080-1, 1080-2, 1080-3, etc.) may space insert 1060 from nozzle ring 898 by an axial distance to define a nozzle axial height of the nozzle space, wherein pivotable blades disposed in the nozzle space may include blade heights that provide clearance for pivoting in the nozzle space. As an example, insert 1060 may include a shroud surface whose profile is shaped to define clearance with respect to turbine impeller blades. The cylindrical portion 1064 of insert 1060 may be defined by an inner radius that defines a flow path for exhaust gas, such that exhaust gas entering the nozzle space may flow around the turbine impeller and then exit.

[0054] Figure 7 An example of a component 1700 is shown, comprising a compressor assembly 1740, a central housing assembly 1780, and a turbine assembly 1800, wherein the turbine assembly 1800 is coupled to the central housing assembly 1780.

[0055] like Figure 7 As shown in the example, turbine assembly 1800 includes an actuator 1810 with a control arm 1812 for positioning the blades 1900 of turbine assembly 1800. As shown, the blades 1900 are positioned radially outward from turbine impeller 1870, which defines an axis of rotation z. The axis of rotation z can be used to define one or more features of the turbine assembly. For example, various features can be defined in a cylindrical coordinate system having axial (z), radial (r), and azimuth (Θ) coordinates.

[0056] As shown in the figure, the turbine assembly 1800 includes a turbine housing 1860 that partially defines a first exhaust gas passage 1867 and a second exhaust gas passage 1869 via a wall end 1863 of an outer wall 1862 and a wall end 1865 of an inner wall 1864. As explained, the turbine housing may include wall ends that may be part of a volute or spiral wall that supplies exhaust flow to the turbine impeller. Figure 7 In the example, wall ends 1863 and 1865 may be the ends of two volute or spiral walls (e.g., walls 1862 and 1864) that define exhaust passages 1867 and 1869.

[0057] As shown in the figure, the turbine housing 1860 includes an inner wall 1864 and an outer wall 1862, which define a first exhaust gas passage 1867 and a second exhaust gas passage 1869 leading to a turbine impeller space for a turbine impeller 1870, wherein the inner wall 1864 includes an inner wall end 1865 in the turbine impeller space, and the outer wall 1862 includes an outer wall end 1863 in the turbine impeller space. Figure 7 In the example, the first flow body 2000-1 is disposed near the outer wall end 1863, while the second flow body 2000-2 is disposed near the inner wall end 1865. As shown, the turbine assembly 1800 includes multiple sets of adjustable variable geometry nozzle blades 1900 that define nozzle throats that guide the flow of exhaust gas from exhaust gas passages 1867 and 1869 to the turbine impeller space.

[0058] As explained, actuator 1810 can control the position of blade 1900 via control arm 1812, for example, positioning blade 1900 in a closed position and one or more open positions. In such an example, the closed position may define a minimum flow condition. For example, blade-to-blade contact may not exist in the closed position, resulting in a relatively small, narrow channel where a certain flow rate might be present, which can be defined as a minimum amount or minimum flow rate (e.g., for a given pressure). Figure 7 In one example, the turbine assembly may include a cylinder 1880 that carries at least the blades 1900. As an example, fluids 2000-1 and 2000-2 may be fitted onto or otherwise positioned relative to the cylinder 1880, and adjacent to wall ends 1863 and 1865, respectively. As an example, fluids 2000-1 and 2000-2 may be positioned stationary such that they do not move, while the blades 1900 may pivot relative to the stationary fluids 2000-1 and 2000-2.

[0059] Figure 8 It shows Figure 7 A cross-sectional view of component 1800, in which exhaust gas passages 1867 and 1869 are shown in the open position together with turbine housing 1860, turbine impeller 1870 and blades 1900.

[0060] Figure 9 It shows Figure 7 Sectional plan view of component 1800. Figure 9 In the example, the first fluid 2000-1 can be set at an angle of approximately 102 degrees to the horizontal (e.g., 12 degrees to the vertical), while the second fluid 2000-2 can be set at an angle of approximately 292 degrees or -68 degrees to the horizontal (e.g., -22 degrees to the vertical). Figure 9In the example, in the clockwise direction, there are eight blades 1900 between the two blades 1900-1 and 1900-10 associated with the first fluid 2000-1 and the second fluid 2000-2; while in the counterclockwise direction, there are nine blades 1900 between the two blades 1900-1 and 1900-10 associated with the first fluid 2000-1 and the second fluid 2000-2. Figure 9 In the example, the number of blades 1900 is 19. As an example, a turbine assembly may include fewer or more blades, an even number of blades, or an odd number of blades. As an example, a turbine assembly may include at least five blades and fewer than forty blades.

[0061] As explained, the line drawn between the columns of blades 1900-1 and 1900-10 may not intersect the axis of rotation z of the turbine impeller 1870, for example, in Figure 9 In the example, such a line (dashed line) is offset to the right of the rotation axis z.

[0062] Figure 10 It shows Figure 7 A cross-sectional view of component 1800, wherein exhaust gas passages 1867 and 1869 are shown together with turbine housing 1860, turbine impeller 1870, and blades 1900, which are in a more... Figure 9 The example shows the opening position with the smaller opening position.

[0063] Figure 11 It shows Figure 7 A cross-sectional view of component 1800, wherein exhaust gas passages 1867 and 1869 are shown together with turbine housing 1860, turbine impeller 1870, and blades 1900, which are in a more... Figure 10 The example shows the opening position with the smaller opening position.

[0064] Figure 9 , 10 Figures 1 and 11 illustrate how blades 1900 can be controllably moved (e.g., positioned) from a more open position to a more closed position. As blades 1900 become more closed (e.g., less open), they act as barriers impeding the flow of exhaust gas toward turbine impeller 1870 (e.g., toward turbine impeller space). As an example, a fully closed position may involve inter-blade contact of blades 1900. For example, in the case of inter-blade contact of blades 1900, the contact area can be used to further impede the flow of exhaust gas (e.g., sealing the blade surfaces together). Figure 9 , 10 In the view of 11, each blade rotates 190° clockwise, moving from a more open position to a more closed position (e.g., a less open position).

[0065] Figure 12 A perspective view of a portion of component 1800 is shown, in which three blades 1900 are labeled 1900-1, 1900-2, and 1900-3. Figure 12 In the example, portions of exhaust gas passages 1867 and 1869 are shown in general, wherein wall end 1863 and first flow body 2000-1 act as barriers to fluid communication between exhaust gas passages 1867 and 1869.

[0066] As explained, the exhaust gas passage can be supplied by different cylinder banks of an internal combustion engine, where each cylinder includes a piston connected to a rotatable shaft. The pistons operate according to the firing order and the intake and exhaust strokes. Regarding the firing order of a four-cylinder internal combustion engine with pistons labeled 1, 2, 3, and 4, consider an inline four-cylinder engine with a firing order of 1-3-4-2 or 1-2-4-3; and for a horizontal four-cylinder engine, consider pistons labeled R1, R2, L1, and L2, with a firing order of R1-R2-L1-L2. Figure 2A As shown, one exhaust passage may receive exhaust gas from two cylinders (e.g., 1 and 4), while another exhaust passage may receive exhaust gas from two different cylinders (e.g., 2 and 3). As an example, the engine may be in an inline, V-type, or horizontal configuration. As an example, the engine may include multiple manifolds. In such an example, each of the multiple manifolds may provide passage for exhaust gas to a corresponding exhaust gas passage in the turbine assembly. As an example, the engine may include more than one cylinder and less than 20 cylinders (e.g., consider 3, 4, 5, 6, 8, 10, 12, etc.).

[0067] As an example, a manifold may provide exhaust gas recirculation (EGR), for example, to the intake manifold and / or the manifold. In such an example, the exhaust gas flow in the exhaust passages may be different (e.g., one provides EGR while the other does not).

[0068] As explained, pulsation can occur in and / or between the two exhaust gas passages. As an example, the arrangement of features in component 1800 can accommodate pulsation. As an example, in cases where pulsation tends to be intense, the clearance between the blade leading edge and the fluid may increase. In such an approach, pulsation can be slightly dispersed via communication with a larger, freer fluid volume. For example, in… Figure 11In this configuration, blade 1900-1 can be rotated an additional degree clockwise (e.g., in accordance with other blades 1900) to provide an increased clearance relative to the first flow element 2000-1, which allows for increased fluid communication between exhaust passages 1867 and 1869. As an example, the clearance of blade 1900 in the closed position relative to one or more flow elements 2000-1 and 2000-2 can be controlled by the positioning of blade 1900 (e.g., column radius), the position of the blade column, the distance between the blade column and the leading edge, etc. Thus, the closed position clearance can be designed to accommodate considerations related to pulsation (e.g., pulse pressure). In cases of strong pulsation (e.g., pulse pressure), the clearance (one or more) can be increased.

[0069] like Figure 12 As shown in the example, a gap c may exist between the fluid 2000-1 and the wall end 1863. we Such clearances can be adjusted based on one or more criteria. For example, consider fluid connectivity with respect to pulsation, mounting clearance, thermal expansion / contraction clearance, etc. As explained, in cases of strong pulsation, such clearances may be larger to provide increased fluid connectivity between exhaust passages 1867 and 1869.

[0070] Figure 13 An example of the flow body 2000 is shown in perspective and cross-sectional views. As shown, the flow body 2000 may include a concave rear surface 2002 and a front surface 2004, an upper surface 2006 and a lower surface 2008, opposing airfoil surfaces 2010 and 2020, a boss 2040, and a pillar 2060 including a pillar end 2062. As shown, the boss 2040 may be shaped as a truncated cylinder and slightly raised above the upper surface 2006, such that the boss 2040 acts as a spacer, for example, to provide axial clearance between the components of assembly 1800.

[0071] exist Figure 13 In the example, the fluid 2000 may be defined by an axial height h, wherein the boss 2040 and the pillar 2060 may have a greater axial height. As an example, the height of the fluid 2000 at the front surface 2004 may be greater than the height at the rear surface. For example, the height at the front surface 2004 may be selected to substantially match the height of the wall end, while the height at the rear surface 2002 may be selected to substantially match the height of the blade. As an example, the upper surface 2006 may be inclined upward between the boss 2040 and the leading edge 2004.

[0072] For airfoil surfaces 2010 and 2020, they can be defined using one or more radii. For example, Figure 13The figures show radii R1 and R2 that define airfoil surfaces 2010 and 2020, respectively. As shown, the rear surface 2002 can be defined by radius R... ve This radius can be based on the arc of the blade's leading edge. For example, consider radius R. ve The arc R swept by the pivoting motion of the blade's leading edge le Including the clearance amount, this clearance amount can be R. le The percentage (e.g., from 0.1% to 25%). Figure 13 As shown in the example, the rear surface 2002 may include concavity, wherein the concavity is partially defined by an arc. As explained, such a rear surface may be referred to as a concave rear surface. As an example, a concavity test may be to draw a line between two points on the body, wherein if the line passes through a boundary of the body (e.g., a surface of the body), the body may be defined as concave (e.g., including concavity), for example, having a concave surface. As for the front surface 2004, it may be defined by a radius R. se The definition may depend on the shape of the wall ends. As an example, the front surface 2004 may be a concave front surface or a flat front surface. For example, if a line is drawn between the two ends of the front surface 2004, the front surface 2004 is not concave if the line does not pass through the front surface 2004. As explained with respect to the rear surface 2002, if a line is drawn between the ends of the rear surface 2002, the line is at least partially outside the fluid 2000, such that the rear surface 2002 is a concave rear surface. As an example, the rear surface 2002 may be defined as concave by a concave arcuate shape that effectively forms a recessed rear surface 2002 (e.g., recessed into the fluid 2000). As an example, a convex arcuate shape may form a convex surface (e.g., a convex surface). For example, the fluid may include a rear surface that includes a concavity that may be disposed between the ends of the rear surface, one or both ends of which may be rounded and / or chamfered. For the rounded ends, they can be defined as convex. For example, consider a concave portion of the rear surface between the convex rounded ends of the rear surface, such that the rear surface can be defined as a concave rear surface (e.g., a rear surface with a concavity that can accommodate the leading edge of the blade when the blade sweeps across an arc in response to pivoting about a pivot axis).

[0073] exist Figure 13 In the example, the inserted geometry shows circles with radii R1 and R2, which are offset about their centers. As shown, this offset defines a region, a portion of which defines the airfoil surfaces 2010 and 2020 of the fluid 2000. As shown, the thickness of the fluid 2000 can vary along its length. For example, it can be thicker at the trailing surface 2002 of the blade, ΔR... ve However, the surface at 2004 on the front surface can be thinner, △R seIn such an example, the thickness can be selected to accommodate the pivoting range of the blade leading edge and / or to accommodate the wall thickness. When the fluid 2000 is to accommodate a larger arc swept by the blade leading edge (e.g., defined by a pivoting range based on angles, etc.), the fluid 2000 may be thicker at the trailing surface 2002; and when the fluid 2000 is to accommodate a smaller arc swept by the blade leading edge (e.g., defined by a pivoting range based on angles, etc.), the fluid 2000 may be thinner at the trailing surface 2002.

[0074] Figure 14 , 15 16 and 16 respectively show as follows Figure 9 , 10 An enlarged view of a portion of component 1800 shown in Figure 11.

[0075] exist Figure 14 In the example, blade 1900-1 is shown as including a leading edge 1902, a trailing edge 1904, an upper surface 1906, a lower surface 1908 (hidden), a pressure airfoil side 1910, and a suction airfoil side 1920. In such an example, airfoil sides 1910 and 1920 extend between the leading edge 1902 and the trailing edge 1904. Blade 1900-1 is also shown as including a pivot axis z that defines blade 1900-1. v The column 1960. As explained, the blade 1900-1 can rotate around its pivot axis z. v Pivot in either clockwise or counterclockwise direction.

[0076] exist Figure 14 In the example, the pivoting of blade 1900-1 to its leading edge 1902 can create a substantially continuous position between airfoil surfaces 2020 and 1920, although a gap exists between the leading edge 1902 of blade 1900-1 and the trailing surface 2002 of flow body 2000-1. Furthermore, as shown, the airfoil surface 2010 of flow body 2000-1 can provide a throat for blade 1900-2, with the throat extending to the airfoil surface 1910 of blade 1900-1. As for the gap between the leading edge 1902 of blade 1900-1 and the trailing surface 2002 of flow body 2000-1, it can be small enough that a considerable amount of exhaust gas flow will not appear in the gap between the exhaust gas in exhaust gas passages 1867 and 1869.

[0077] exist Figure 14 In the example, blade 1900-1 can be defined as being at a pivot angle of approximately 69 degrees, as if from the pivot axis z v The dashed line extends to the leading edge 1902. As shown, the dashed line may be tangential to or otherwise approach the end of the rear surface 2002 of the fluid 2000-1. As shown, the end may be located between the rear surface 2002 and the airfoil surface 2020.

[0078] like Figure 14 As shown in the examples, blades 1900-1, 1900-2, and 1900-3, etc., have a pivot axis 1960 located between the leading edge 1902 and the trailing edge 1904. In such examples, the distance from the pivot axis 1960 to the leading edge 1902 may be approximately the same as the distance from the pivot axis 1960 to the trailing edge 1904. As an example, such a distance can be defined by a ratio or one or more percentages. For example, in Figure 14 In this case, the distance from the pivot axis 1960 to the trailing edge 1904 is slightly greater than the distance from the pivot axis 1960 to the leading edge 1902. As an example, the distance from the blade's pivot axis to the leading edge can be at least 40% of the distance from the blade's pivot axis to the trailing edge. Figure 14 In the example, the distance from pivot 1960 to leading edge 1902 is greater than approximately 60%, 70%, and 80% of the distance from pivot 1960 to trailing edge 1904. If the blade does not include a leading edge located at a certain distance from the column region of the blade, the leading edge will not sweep across the arc when pivoting about the pivot axis; instead, it will remain confined within the radius of the column region.

[0079] As explained, when blade 1900-1 pivots about its pivot axis 1960, the distance from pivot axis 1960 to leading edge 1902 can define an arc (see dashed circle). In such a method, the radius of this circle can be larger than the radius of the cylindrical region (see dotted circle). As an example, in Figure 14 In this context, the radius of the circle drawn around the leading edge 1902 can be at least three times the radius of the cylindrical region of blade 1900-1. For example, in Figure 14 In the diagram, the radius of the circle (short dashed circle) drawn around the leading edge 1902 and centered on the pivot axis 1960 is approximately 4 to 5 times the radius of the circle (dotted dashed circle) drawn around the cylindrical region of blade 1900-1.

[0080] like Figure 14 As shown, blade 1900-1 has an airfoil shape in which its length is greater than its width. As for the trailing surface 2002 of fluid 2000-1, as explained, it can be defined as partially overlapping the leading edge 1902 of blade 1900-1 within a pivot angle range, and not overlapping at various angles outside this range (see, for example...). Figure 17 ).

[0081] Figure 15 The blade 1900-1 is shown to be in the position of... Figure 14 Examples in different locations. Figure 15 In the example, blade 1900-1 can be defined as being at a pivot angle of approximately 54 degrees, as indicated by the distance from the pivot axis z. vThe dashed line extends to the leading edge 1902. As shown in the figure, the dashed line may be located between the ends of the rear surface 2002 of the fluid 2000-1.

[0082] Figure 16 The blade 1900-1 is shown to be in the position of... Figure 15 Examples in different locations. Figure 16 In the example, blade 1900-1 can be defined as being at a pivot angle of approximately 42 degrees, as indicated by the distance from the pivot axis z. v The leading edge 1902 is defined by a dashed line. As shown, the dashed line may be tangential to or otherwise approach the end of the rear surface 2002 of the fluid 2000-1. As shown, the end may be located between the rear surface 2002 and the airfoil surface 2010.

[0083] exist Figure 14 , 15 In the example of 16, the pivot angle ranges from approximately 69 degrees to approximately 42 degrees, which is an angular pivot span of approximately 27 degrees. As explained, the closed position can be at a further pivot amount, such as to a pivot angle less than 42 degrees, at which, for example, the blades can contact. Figure 14 , 15 Examples 1 and 16 represent the overlap range of the pivoting amount of blade 1900-1, where, for example, the overlap can be defined by a radial line from the blade's column or pivoting axis to the blade's leading edge. In such an example, a first overlap mark can move from open to a smaller open, while a second overlap mark can move from a smaller open to a more closed (e.g., or vice versa). As an example, the overlap range of the pivot angle can be a range smaller than the overall operating range of the pivot angle. As an example, the overlap range of the pivot angle can be closer to the closed end of the pivot angle range than the open end of the pivot angle range. For example, refer to... Figure 14 Counterclockwise pivoting of blade 1900-1 is possible, so that blade 1900-1 does not overlap when in a more open position. In such an example, consider a pivot angle of approximately 90 degrees (e.g., Figure 14 The vertical line in the diagram makes the overlap range of the pivot angle from approximately 69 degrees to approximately 42 degrees closer to the closed position of blade 1900-1 than the fully open position (e.g., approximately 90 degrees) of blade 1900-1. For the fully closed position of blade 1900-1, refer to... Figure 16A pivot angle of approximately 30 degrees could be a position where contact might occur between blades 1900-1 and 1900-2 (e.g., a position where both are pivoted). In such an example, the lower range of an overlap of approximately 42 degrees is within 12 degrees of the closed position, which could be a contact position; however, the upper range of an overlap of approximately 69 degrees is within 21 degrees of the example of a fully open position of 90 degrees, which could be defined by the clearance from the blade trailing edge to the turbine impeller blade (e.g., approximately 1% to 10% of the outer radius of the turbine impeller). As an example, the fully open position of blade 1900-1 could be less than approximately 90 degrees. For example, consider a fully open position corresponding to a pivot angle of approximately 81 degrees. In such an example, the overlap range could be substantially between the fully open and fully closed pivot angles (e.g., approximately 12 degrees from fully open and approximately 12 degrees from fully closed or in contact).

[0084] Figure 17 A portion of component 1800 is shown in plan view, along with a pivot angle range ϕ defined by a fully open position FO and a fully closed position FC, where the fully closed position FC can be the blade-to-blade contact position. As shown, the overlapping pivot angle range ϕ... o It can be within the pivot angle range ϕ. In addition, the overlapping pivot angle range can be some degree from the FO position and some degree from the FC position, wherein, for example, the degree from the FC position can be less than the degree from the FO position.

[0085] exist Figure 17 In the examples, the overlapping pivot angle range can be a percentage of the pivot angle range. For example, consider an overlapping pivot angle range of 40% to 80% of the pivot angle range, or, for example, 50% to 75% of the pivot angle range, or, for example, 55% to 72% of the pivot angle range.

[0086] In various examples, the wall end may be a tongue extension or serve as a tongue extension. Such a wall end may be positioned symmetrically or asymmetrically with respect to the blade (e.g., consider one set of blades comprising 10 blades and another set comprising 9 blades, for a total of 19 blades).

[0087] As explained, the closed position can define minimum flow conditions. For example, blade-to-blade contact may not exist in the closed position, resulting in relatively small, narrow channels where some flow can occur, which can be defined as a minimum amount or minimum flow rate (e.g., for a given pressure). Where contact does occur, some minimum flow rate may occur, for example, in the gaps above and / or below the blades.

[0088] As explained, the flow body may be part of a cylinder assembly (e.g., positioned between the plate portion and the insert portion of the cylinder assembly, where blades may also be positioned). As explained, the blades may pivot about their respective pivot axes, with a relatively small gap between the two blades and the two respective flow bodies. For example, the flow body may include a side closest to the axis of rotation of a turbine impeller (e.g., the central axis of the cylinder assembly), such as in a turbine impeller space, which may be at least partially rounded (e.g., bent) to account for the leading edge of the respective blade, as shown, which, although a leading edge, may not be directly exposed to the incoming flow due to the presence of the flow body. For example, the leading edge of the blade may allow the flow to be “split,” with one portion of the flow flowing along one side of the blade and another portion flowing along the opposite side of the blade. In various examples, the presence of the flow body may partially impede the leading edge, such that the incoming flow on one side of the flow body flows primarily along one side of the respective blade, while the incoming flow on the other side of the flow body flows primarily along the opposite side of the respective blade.

[0089] As an example, the fluid may be made of a material such as steel. As an example, the fluid may be made of the same material as the blade. In various examples, the fluid may be a fixed structure. For example, consider a fixed structure fixed within a cylinder assembly.

[0090] As explained, one side of the fluid (e.g., an airfoil surface) may be at least partially defined by an arc, which may have an arc length defined as a distance and / or degree. In such an example, the pivot axis of the blade may be used to define the arc. For example, consider drawing a circle around the blade, where the circle is centered on the blade axis, and where the side of the fluid is defined by at least a portion of the circumference of the circle. In the closed position of the blade (e.g., the closed position of the cylinder assembly), the blade at the fluid may form a relatively continuous curved surface with one side of the fluid, and, for example, the curved surface may be spaced apart on the opposite side of the fluid and on a portion of the blade. The profile of the fluid is shaped to correspond to the pivotable blade.

[0091] As an example, for at least a portion of the entire stroke of a corresponding blade (e.g., not exceeding the entire stroke), the exhaust gas flow can be substantially separated by the flow body. In such an example, the flow body can be shaped to introduce minimal disturbance (e.g., only as needed regarding the end “arc” side, which can be determined by one or more blade characteristics, such as the length to the pivot side, etc.). Such a method may help separate the flow of two vortices (e.g., a volute), as explained, which may originate from different cylinders of an internal combustion engine.

[0092] As an example, the fluid can be identical, so only one piece needs to be manufactured. For example, consider manufacturing two identical pieces and inserting them into a cylinder assembly during assembly, where the cylinder assembly includes multiple pivotable blades, which can be an odd number of blades or, for example, an even number of blades; note that an odd number of blades may be used, for example, where the flow in one vortex differs from the flow in another vortex of the two vortex assemblies.

[0093] As an example, the fluid can be non-contact because no blades contact the fluid during operation of the variable nozzle tube assembly.

[0094] As an example, a component may include one or more features that can be defined using continuity with respect to curves and / or surfaces. For example, consider a fluid-to-blade system where the blade is pivotable about an axis and, for example, where the fluid is fixed, and / or, for example, consider a tongue-to-fluid-to-blade system where the blade is pivotable about an axis and, for example, where both the tongue and the fluid are fixed.

[0095] As explained, the flow field upstream of turbomachinery blades is often non-uniform. Therefore, it may be desirable to minimize disturbances between portions of the flow that differ in one or more aspects, such as velocity vectors and fluid states.

[0096] Variable position guide vanes can be used to adapt the critical flow characteristics of a turbine stage to different operating conditions of the turbine. As an example, it may be desirable to minimize the interference between two adjacent portions of a flow that must at least partially enter two adjacent variable geometry nozzles, without altering the relative flow distribution between these two portions of the flow at various or all possible positions of the movable vane.

[0097] As explained, the shape of the fluid located upstream of the movable guide vane can be defined in a specific manner. As explained, the rear surface of the fluid can be defined at least partially by a portion of a circle, which can be defined at least partially by the leading edge of the vane. As explained, such a rear surface can be a concave rear surface, wherein the concavity of the rear surface can adapt to the leading edge of the vane when the leading edge sweeps across the arc in response to pivoting about the vane's pivot axis.

[0098] As an example, the center of the circle could be the axis of the movable blade. In such an example, the radius of such a circle could be equal to the extension of the movable blade from the midpoint of its axis to its trailing edge, plus a suitable clearance (e.g., considering a clearance of a few millimeters or less).

[0099] As an example, the sector portion of a circle (e.g., an arc) may be equal to the portion of the circle traversed by the movable blade. As an example, this sector may be shortened at either one or both end positions of the movable blade. In such an example, such shortening (e.g., chamfering, etc.) may be desirable to allow for some mixing of the flow near the two corresponding end positions of the movable blade.

[0100] As an example, the fan shape can be extended at any one or both ends of the movable blade. In such an example, this approach can help, for example, minimize the effect of small movements of the blade on the flow.

[0101] In various situations, vehicles may employ one or more forms of non-wheel braking. For example, in heavy vehicles, the engine is often used to provide additional braking power to relieve stress on the vehicle's conventional braking system and help prevent brake overheating. Consider, for instance, a butterfly valve that stops exhaust flow (which can be called exhaust braking). Another form is compression-release braking, which can be used in large diesel trucks. Such braking is operated by opening the exhaust valve at the top of the compression stroke, so the significant amount of energy stored in the compressed air is not returned to the crankshaft but released into the atmosphere. Normally, during the compression stroke, energy is utilized as the upward-moving piston compresses the air in the cylinder; the compressed air then acts as a compression spring, pushing the piston back down. However, with the jack brake, the compressed air is suddenly released just before the piston begins to move down. This sudden release of compressed air produces audible sound waves, similar to the expanding gas escaping from the muzzle of a firearm. Without the energy stored in the compressed air, there is no "rebound," so the engine must expend more energy to pull the piston back down. Such braking can be effective and generate a large amount of braking power (for example, a 565 hp (421 kW) diesel engine can generate up to 600 hp (450 kW) of braking force at 2100 RPM).

[0102] As an example, a fluid (e.g., an object) can be shaped to help handle one or more of a variety of situations. Ideally, for example, perfect flow separation might be achieved across the entire range of operating conditions. However, situations such as engine-related braking can alter the pulsation. In cases of strong pulsation, the spacing (e.g., gap) between the fluid and the corresponding blades can help reduce the effects of strong pulsation in the closed position of the cylinder assembly, which could otherwise be too strong to overload the blade adjustment mechanism, potentially causing one or more control problems when attempting to maintain a specific blade position (e.g., the closed position, which could be the minimum flow position, etc.). Such an approach helps increase the lifespan of a variable geometry turbocharger. Furthermore, as explained, with the blades open, the fluid can provide even greater flow separation because the open channels formed between the blades allow the flow to the turbine impeller to "release" and / or "even" pulsating pressure.

[0103] Figure 18 An example of a portion of component 1800 is shown, wherein the fluid 2000-1 includes ends 2003 and 2005 of a rear surface 2002, wherein ends 2003 and 2005 are different. For example, with Figure 17 Compared to the example, the end 2003 can be shortened (e.g., chamfered, etc.) to provide an increased amount of clearance.

[0104] As an example, the component may include an exhaust gas turbine housing including an inner wall and an outer wall defining a first exhaust gas passage and a second exhaust gas passage leading to a turbine impeller space, wherein the inner wall includes an inner wall end in the turbine impeller space and the outer wall includes an outer wall end in the turbine impeller space; a first flow body disposed adjacent to the inner wall end; a second flow body disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle blades defining a nozzle throat for guiding the flow of exhaust gas from at least one of the exhaust gas passages to the turbine impeller space, wherein at least one of the first and second flow bodies includes a concave rear surface partially defined by an arc. In such an example, the first and second flow bodies may be fixed.

[0105] As an example, a first tongue may be formed at the inner wall end, wherein a first fluid is adjacent to the first tongue, and a second tongue may be formed at the outer wall end, wherein a second fluid is adjacent to the second tongue.

[0106] As an example, the circle can be centered on the pivot axis of one of multiple blades (e.g., a set of blades), where the fluid includes a concave rear surface partially defined by an arc. For example, the leading edge of the blade can define an arc when the blade pivots (e.g., rotates) about a pivot axis (e.g., the pivot axis of a column, hole, etc.). In such an example, the rear surface can be defined using an arc (e.g., the radius of a circle) plus a clearance distance (e.g., a radial clearance distance) such that the blade can pivot about its pivot axis without the leading edge undesirably contacting the rear surface of the fluid. In such an example, overlap can occur at multiple angles between the rear surface of the fluid and the leading edge of the blade as the blade pivots about its pivot axis. In such an example, the overlap clearance between the leading edge of the blade and the rear surface of the fluid can be small enough to prevent exhaust gas flow from one exhaust passage to another.

[0107] As an example, the circle may be defined by a radius greater than the radius swept by the leading edge of one of the adjustable variable geometry nozzle blades when transitioning from the closed position to the open position (e.g., consider a distance greater than the defined gap, etc.).

[0108] As an example, the first fluid may include a front surface, a rear surface, and a first airfoil surface and a second airfoil surface extending between the front and rear surfaces. In such an example, the front surface may be positioned close to the wall end with a small gap, which may accommodate thermal effects, vibrations, etc. (e.g., to avoid contact with the wall end but impede exhaust flow between the front surface and the wall end). As an example, the rear surface may include a first airfoil surface end adjacent to the first airfoil surface and a second airfoil surface end adjacent to the second airfoil surface. In such an example, the first airfoil surface end and the second airfoil surface end may define an overlapping pivot angle range for the leading edge of a respective one of a plurality of adjustable variable geometry nozzle blades. In such an example, the overlapping pivot angle range may be less than the total pivot angle range of the leading edge of a respective one of the adjustable variable geometry nozzle blades. In such an example, the overlapping pivot angle range may be greater than 50% and less than 80% of the total pivot angle range. As an example, the overlapping pivot angle range may be offset toward a closed position of the total pivot angle range.

[0109] As an example, the second airflow surface end may include a chamfer that defines a bypass gap with respect to the leading edge of a corresponding one of a plurality of adjustable variable geometry nozzle blades. In such an example, the first airflow surface end may define a gap with respect to the leading edge of a corresponding one of the adjustable variable geometry nozzle blades, wherein the bypass gap is larger than this gap. As an example, a bypass gap may be provided to reduce pulsating pressure stress on the actuator of at least one set of adjustable variable geometry nozzle blades.

[0110] As an example, the first fluid and the second fluid may include corresponding heights that are approximately equal to the blade height.

[0111] As an example, the number of adjustable variable geometry nozzle blades in the component may be greater than five. As an example, the number of adjustable variable geometry nozzle blades may be odd (e.g., or even).

[0112] As an example, the component may include an exhaust turbine housing including an inner wall and an outer wall defining a first exhaust gas passage and a second exhaust gas passage leading to a turbine impeller space, wherein the inner wall includes an inner wall end at the turbine impeller space and the outer wall includes an outer wall end at the turbine impeller space; a first flow body disposed adjacent to the inner wall end; a second flow body disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle blades defining a nozzle throat that guides exhaust gas flow from at least one of the exhaust gas passages to the turbine impeller space.

[0113] In such an example, the first and second fluids may be stationary (i.e., immovable during operation). As an example, the first and / or second fluids may move in response to pressure exceeding a predetermined pressure (e.g., as may be caused by significant pulsation, thereby relieving stress on the blades and / or actuators).

[0114] As an example, a first tongue may be formed at the inner wall end, and a first fluid may be adjacent to the first tongue, and a second tongue may be formed at the outer wall end, and a second fluid may be adjacent to the second tongue.

[0115] As an example, the first fluid and / or the second fluid may include a trailing edge partially defined by a circular arc. In such an example, the circle may be centered on the pivot axis of one of the blades. In such an example, the trailing edge may include a chamfer adjacent to the circular arc, wherein the chamfer defines a gap with respect to the leading edge of one of the blades. In such an example, the circular arc may define a gap with respect to the leading edge of one of the blades. In such an example, the gap may be less than about 70% of the interval. In such an example, the gap may reduce pulsating pressure stress on the actuator of at least one set of adjustable variable geometry nozzle blades.

[0116] As an example, the interval can be within the working range of one of the blades, which is located between the midpoint of the open and closed positions and the closed position.

[0117] As an example, the first fluid and / or the second fluid may include a height approximately equal to the blade height.

[0118] As an example, the first fluid and / or the second fluid may be defined using one or more continuity with respect to another component.

[0119] As an example, the number of leaves can be greater than about 5, and can be either odd or even.

[0120] Although some examples of methods, apparatuses, systems, arrangements, etc. have been illustrated in the accompanying drawings and described in the foregoing detailed description, it should be understood that the disclosed exemplary embodiments are not limiting, but are capable of many rearrangements, modifications and substitutions.

Claims

1. A component comprising: An exhaust gas turbine housing includes an inner wall and an outer wall, the inner wall and the outer wall defining a first exhaust gas passage and a second exhaust gas passage leading to a turbine impeller space, wherein the inner wall is contained at an inner wall end in the turbine impeller space and the outer wall is contained at an outer wall end in the turbine impeller space. A first fluid is disposed adjacent to the end of the inner wall; A second fluid body is disposed adjacent to the outer wall end; and At least one set of adjustable, variable geometry nozzle blades defines a nozzle throat that guides the flow of exhaust gas from at least one of the exhaust gas passages to the turbine impeller space. At least one of the first and second fluids includes a concave rear surface partially defined by an arc of a circle, wherein the radius of the circle is greater than the radius swept by the leading edge of one of the adjustable variable geometry nozzle blades during the transition from the closed position to the open position.

2. The component of claim 1, wherein the first fluid and the second fluid are fixed.

3. The component of claim 1, wherein the inner wall end forms a first tongue, and wherein the first fluid is adjacent to the first tongue.

4. The component of claim 1, wherein the outer wall end forms a second tongue, and wherein the second fluid is adjacent to the second tongue.

5. The component of claim 1, wherein the circle is centered on the pivot axis of one of the adjustable variable geometry blades.

6. The component of claim 1, wherein the first fluid and the second fluid comprise a height substantially equal to the blade height.

7. The component of claim 1, wherein the number of adjustable variable geometry nozzle blades is greater than 5.

8. The component of claim 1, wherein the number of adjustable variable geometry nozzle blades is odd.

9. The component of claim 1, wherein the first fluid comprises a front surface, the concave rear surface, and a first airfoil surface and a second airfoil surface extending between the front surface and the concave rear surface.

10. The component of claim 9, wherein the concave rear surface includes a first airfoil end adjacent to the first airfoil surface and a second airfoil end adjacent to the second airfoil surface.

11. The component of claim 10, wherein the first airfoil end and the second airfoil end define an overlapping pivot angle range for the leading edge of a respective one of the adjustable variable geometry nozzle blades.

12. The assembly of claim 11, wherein the overlapping pivot angle range is less than the total pivot angle range of the leading edge of the respective one of the adjustable variable geometry nozzle blades.

13. The component of claim 12, wherein the overlapping pivot angle range is greater than 50% and less than 80% of the total pivot angle range.

14. The component of claim 12, wherein the overlapping pivot angle range is offset toward the closed position of the total pivot angle range.

15. The component of claim 10, wherein the second airfoil surface end includes a chamfer that defines a bypass clearance with respect to the leading edge of a corresponding one of the adjustable variable geometry nozzle blades.

16. The component of claim 15, wherein the first airfoil surface end defines a gap with respect to the leading edge of the respective one of the adjustable variable geometry nozzle blades, wherein the bypass gap is larger than the gap.

17. The component of claim 15, wherein the bypass clearance reduces the pulsating pressure stress on the actuator for at least one set of adjustable variable geometry nozzle blades.

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