Nozzle for partitioned volute

Abstract

An assembly may include an exhaust gas turbine housing including an inner wall and an outer wall defining first and second exhaust gas passages leading to a turbine wheel space, where 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 fluid disposed adjacent to the inner wall end; a second fluid disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle vanes defining a nozzle throat that directs exhaust gas from at least one of the exhaust gas passages to the turbine wheel space, where at least one of the first fluid and the second fluid includes a concave aft surface defined in part by an extension of the airfoil surface.

Description

Related Applications

[0001] This application claims priority to and the benefit of U.S. Provisional Application Serial No. 63 / 399,667, filed on August 20, 2022, which is incorporated herein by reference. This application incorporates by reference U.S. Provisional Application Serial No. 63 / 151,755, filed on February 21, 2021, and U.S. Non-Provisional Application Serial No. 17 / 556,758, filed on December 20, 2021 (issued as U.S. Patent No. 11,530,618B2 on December 30, 2022), which claims priority to and the benefit of U.S. Provisional Application Serial No. 63 / 151,755, filed on February 21, 2021. Technical Field

[0002] The subject matter disclosed herein relates generally to turbochargers. Background Art

[0003] A turbocharger can increase the output of an internal combustion engine. A turbocharger can include an exhaust turbine assembly that can receive exhaust gas from cylinders of the internal combustion engine. The exhaust gas can be directed to a turbine wheel so that energy can be extracted, for example, to drive a compressor wheel of a compressor assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0004] The various methods, devices, components, systems, arrangements, etc. described herein, and their equivalents, may be more fully understood by reference to the following detailed description when taken in conjunction with the examples shown in the accompanying drawings, in which:

[0005] Figure 1 is a diagram of an example of a turbocharger, an internal combustion engine, and a controller;

[0006] Figure 2A , Figure 2B and Figure 2C is a diagrammatic representation of an example of turbocharger related equipment;

[0007] Figure 3 A series of views of examples that are part of an assembly;

[0008] Figure 4 is a perspective view of an example of a portion of an assembly including a variable geometry mechanism;

[0009] Figure 5 is a perspective view of a portion of an example of an assembly including a variable geometry mechanism;

[0010] Fig. 6A , Figure 6B and Figure 6Care a perspective view of an assembly, a cross-sectional view of an assembly, and a perspective view of a portion of an assembly including a variable geometry mechanism;

[0011] Figure 7 A cross-sectional view showing an example of an assembly;

[0012] Figure 8 Shows Figure 7 a cross-sectional view of a portion of an assembly;

[0013] Fig. 9 Shows Figure 7 a cross-sectional view of a portion of an assembly;

[0014] Fig.10 Shows Figure 7 a cross-sectional view of a portion of an assembly;

[0015] Fig.11 Shows Figure 7 a cross-sectional view of a portion of an assembly;

[0016] Fig.12 Shows Figure 7 a perspective view of a portion of an assembly;

[0017] Fig.13 A perspective view and a cross-sectional view of an example of a flow body are shown.

[0018] Fig.14 Shows Fig. 9 an enlarged cross-sectional view of a portion of an assembly;

[0019] Fig.15 Shows Fig.10 an enlarged cross-sectional view of a portion of an assembly;

[0020] Fig.16 Shows Fig.11 an enlarged cross-sectional view of a portion of an assembly;

[0021] Fig.17 Shows Figure 7 a cross-sectional view of a portion of an assembly;

[0022] Fig.18 Shows Figure 7 A cross-sectional view of a portion of an assembly of with an example of a flow body;

[0023] Fig.19 Shows Fig.11 an enlarged cross-sectional view of a portion of an assembly of with an example of a flow body including an extension;

[0024] Fig. 20 Shows Fig.11an enlarged cross-sectional view of a portion of an assembly of with an example of a flow body including an extension and / or a spacer;

[0025] Fig.21 An example of a computational fluid dynamics simulation diagram showing an example of an assembly;

[0026] Fig. 22 A series of views showing an example of a flow body;

[0027] Fig.23 A series of views showing an example of a flow body;

[0028] Fig.24 A cross-sectional view showing a portion of an example of an assembly;

[0029] Fig.25 A view showing a portion of an example of an assembly;

[0030] Fig.26 A view showing a portion of an example of an assembly;

[0031] Fig. 27 A perspective view showing an example of a flow body;

[0032] Fig.28 A series of views showing an example of a flow body;

[0033] Fig.29 A view showing a portion of an example of an assembly;

[0034] Fig.30 A view showing a portion of an example of an assembly;

[0035] Fig.31 A view showing a portion of an example of a flow body;

[0036] Fig.32 A view showing a portion of an example of an assembly;

[0037] Fig.33 A view showing a portion of an example of an assembly;

[0038] Fig.34 A view of a portion of an example of an assembly is shown. DETAILED DESCRIPTION

[0039] Turbochargers are often used to increase the output of internal combustion engines. Figure 1 As an example, the system 100 may include an internal combustion engine 110 and a turbocharger 120. Figure 1As shown, the system 100 may be part of a vehicle 101, wherein the system 100 is disposed within an engine compartment and connected to an exhaust duct 103 that directs exhaust gas to an exhaust outlet 109, such as located behind a passenger compartment 105. Figure 1 In the example of FIG. 1 , a processing unit 107 may be provided to process the exhaust gas (eg, reduce emissions via catalytic conversion of molecules, etc.).

[0040] like Figure 1 As shown, the internal combustion engine 110 includes: an engine block 118, which houses one or more combustion chambers that can operably drive a shaft 112 (for example, via a piston); an intake port 114, which provides a flow path for air to the engine block 118; and an exhaust port 116, which provides a flow path for exhaust gas from the engine block 118.

[0041] The turbocharger 120 may be used to extract energy from the exhaust gas and provide energy to intake air, which may be combined with fuel to form combustion gases. 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 center 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 including various components. The shaft 122 may be rotatably supported by a bearing system (e.g., (one or more) journal bearings, (one or more) rolling element bearings, etc.) disposed in the housing assembly 128 (e.g., in a hole defined by one or more bore walls), so that the rotation of the turbine impeller 127 causes the rotation of the compressor impeller 125 (e.g., rotatably coupled via the shaft 122). For example, a center housing rotating assembly (CHRA) may include a compressor wheel 125 , a turbine wheel 127 , a shaft 122 , a housing assembly 128 , and various other components (eg, a compressor side plate disposed at an axial position between the compressor wheel 125 and the housing assembly 128 ).

[0042] exist Figure 1 In the example of FIG. 1 , a variable geometry assembly 129 is shown as being partially disposed between the casing assembly 128 and the casing assembly 126. Such a variable geometry assembly may include vanes or other components to change the geometry of the passage to the turbine wheel space in the turbine casing assembly 126. For example, a variable geometry compressor assembly may be provided.

[0043] exist Figure 1In the example of , a wastegate (or simply a wastegate) 135 is located near the exhaust inlet of the turbine housing assembly 126. The wastegate 135 can be controlled to allow at least some exhaust gas from the exhaust port 116 to bypass the turbine impeller 127. Various wastegates, wastegate components, etc. can be applied to conventional fixed nozzle turbines, fixed vane nozzle turbines, variable nozzle turbines, twin scroll (twin scroll) turbochargers, etc. For example, the wastegate can be an internal wastegate (e.g., at least partially located in the turbine housing). For example, the wastegate can be an external wastegate (e.g., operably connected to a conduit in fluid communication with the turbine housing).

[0044] exist Figure 1 In the example of FIG. 1 , an exhaust gas recirculation (EGR) conduit 115 is also shown, which may optionally be provided with one or more valves 117 , for example, to allow exhaust gas to flow to a location upstream of the compressor impeller 125 .

[0045] Figure 1 Also shown are an example arrangement 150 for exhaust gas flow to an exhaust turbine housing assembly 152 and another example arrangement 170 for exhaust gas flow to an exhaust turbine housing assembly 172. In arrangement 150, cylinder head 154 includes passages 156 therein for directing exhaust gas from the cylinders to turbine housing assembly 152, while in arrangement 170, manifold 176 provides for mounting of turbine housing assembly 172, e.g., without requiring any separate intermediate lengths of exhaust conduit. In example arrangements 150 and 170, turbine housing assemblies 152 and 172 may be configured for use with a wastegate, a variable geometry assembly, and the like.

[0046] exist Figure 1In the example of controller 190, one or more processors 192, memory 194 and one or more interfaces 196 are shown. Such a controller may include circuits, such as circuits of an engine control unit (ECU). As described herein, various methods or techniques may be optionally implemented in conjunction with the controller, such as by control logic. 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, a sensor may transmit information to the controller 190 via one or more interfaces 196. The control logic may rely on such information, and the controller 190 may in turn output a control signal to control the engine operation. The controller 190 may be configured to control lubricant flow, temperature, variable geometry components (e.g., variable geometry compressors or turbines), wastegates (e.g., via actuators), motors, or one or more other components associated with an engine, a turbocharger (or multiple turbochargers), etc. For example, the turbocharger 120 may include one or more actuators and / or one or more sensors 198, which may be, for example, coupled to one or more interfaces 196 of the controller 190. For example, the wastegate 135 may be controlled by a controller that includes an actuator responsive to an electrical signal, a pressure signal, etc. For example, the actuator for the wastegate may be a mechanical actuator, e.g., which may operate without the need for electrical power (e.g., consider a mechanical actuator configured to respond to a pressure signal provided via a conduit).

[0047] Internal combustion engines, such as Figure 1 The engine 110 can produce exhaust gas with a pulsating flow. In so-called constant pressure turbocharging (e.g., Stoβaufladung), a sufficiently large exhaust manifold can play a role in suppressing mass flow and pressure pulses, so that the exhaust gas flow to the turbine is relatively stable. Another method, called pulse turbocharging (e.g., Stoβaufladung), can aim to utilize the kinetic energy of the exhaust gas when it leaves the cylinder exhaust port. For example, a relatively short, small cross-sectional conduit can connect each exhaust port to the turbine, so that most of the kinetic energy associated with the exhaust blowby (exhaust pressure relief) can be utilized. For example, appropriate grouping of different cylinder exhaust ports can organize exhaust pulses so that they are continuous (sequential), for example with minimal overlap. In this way, the instability of the exhaust gas flow can be kept at an acceptable level. For example, the decision on implementing constant pressure or pulse turbocharging may depend on one or more factors, such as power requirements, efficiency requirements, fuel type, number of cylinders, cylinder / stroke volume, engine size, etc.

[0048] Figure 2AAn example of a system 200 is shown, which includes a four-cylinder internal combustion engine with a firing order 201, for example, consider a firing order of 1-3-4-2. As shown, a manifold 216 (e.g., or multiple manifolds) may define an exhaust gas flow path that may direct exhaust gas from the cylinders of the internal combustion engine to a turbine assembly 260, which may at least partially house a turbine wheel 270. Figure 2A As shown, turbine assembly 260 includes flange 261, outer wall 262 and inner wall 264, wherein outer wall 262 and inner wall 264 define exhaust volute flow paths 267 and 269. Path 267 can receive exhaust from flow path 217 communicating with cylinders 1 and 4, and path 269 can receive exhaust from flow path 219 communicating with cylinders 2 and 3.

[0049] Figure 2B An example of a manifold 216 is shown that includes two flow paths 217 and 219. For example, manifold 216 can be considered a split manifold that separates exhaust flow from cylinders whose cycles may interfere with each other (e.g., in terms of exhaust pulse energy). For example, on a four-cylinder engine with a firing order of 1-3-4-2, cylinder #1 ends its expansion stroke and opens its exhaust valve while the exhaust valve of cylinder #2 remains open (cylinder #2 is in an overlap period). In an unsplit exhaust manifold, the pressure pulse from the exhaust blowdown event of cylinder #1 may more easily contaminate cylinder #2 with high-pressure exhaust gas, which may affect the performance of cylinder #2 (e.g., the ability to breathe properly) and reduce the pulse energy that may be better utilized in the turbine. For example, appropriate grouping of the above engine can group complementary cylinders together (e.g., the exhaust of cylinders #1 and #4 as one complementary group, and the exhaust of cylinders #2 and #3 as another complementary group). This approach can better utilize the exhaust pulse energy, for example, to improve turbine performance (e.g., increase boost pressure more quickly).

[0050] refer to Figure 2C , the turbine assembly 290 shown includes volutes 292-1 and 292-2 with a dividing wall 295 and a turbine wheel 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 wheel 297.

[0051] exist Figure 2A In the embodiment, walls 262 and 264 may be walls of a dual-channel turbine housing, wherein paths 267 and 269 are radially adjacent channels. As shown, paths 267 and 269 extend in a substantially spiral form relative to turbine wheel 270.

[0052] As shown, due to their geometric arrangements, paths 267 and 269 are of different lengths and therefore may have different gas volumes, for example, the length of path 269 is greater than the length of path 267 .

[0053] Although Figure 2A A four-cylinder internal combustion engine is shown, but one or more other engine types and / or numbers of cylinders (eg, an inline six-cylinder engine, a V8 engine, a V6 engine, a six-cylinder horizontally opposed engine) may also be used.

[0054] exist Figure 2A In, path 217 may be defined by the first manifold exhaust path length and path 219 may be defined by the second manifold exhaust path length. Figure 2A In the example of FIG. 1 , the length of the first manifold exhaust path 217 is longer than the length of the second exhaust path 219 .

[0055] like Figure 2A As shown, the first manifold path 217 is in communication with the first path 267, and the second manifold path 219 is in communication with the second path 269, so that a longer exhaust gas path length can be connected to a shorter path of the turbine assembly. This approach can be intended to "equalize" the overall path length. For example, a dual-channel (e.g., dual-path) turbine housing with significantly different channels can be "equalized" via a manifold geometry with similarly different channels. For example, a combination of short individual paths and long individual paths (e.g., channels) and manifolds of a turbine housing can be used to obtain approximately equal total paths.

[0056] Figure 3 An example of a dual channel turbine housing is shown, the housing comprising an inlet flange 361 , axially adjacent spiral channels 367 and 369 , for example defined by walls 362 and 364 .

[0057] For diesel applications, variable nozzle turbines (VNT) can improve the energy use of the turbine, making the engine more fuel efficient. For gasoline engines, especially four-cylinder engines, they tend to be sensitive to knock due to back pressure impacting the residual gas. Technologies such as twin scrolls (twin swirls) allow flow separation, which can be used to improve scavenging and thus reduce end torque. For example, pulsating flow can be used to increase turbine power.

[0058] The applicability of the VNT to gasoline engines may be limited due to its inefficiency in the closed position, which affects the knock sensitivity generated by high backpressure. In addition, the closed vane position can be used to suppress the pulse recovery of the exhaust gas.

[0059] For example, a method may be used to maintain flow separation for a turbine wheel via a VNT type approach that may be used to improve fuel efficiency.

[0060] For example, a variable nozzle can be used in conjunction with a dual-flow housing. For example, the mechanism can include one or two blades, for example, the blades can move relative to the wall (e.g., pivot), and the wall can be a fixed wall. For example, consider one or more blades that can be positioned to serve as an "extension" of a housing tongue or multiple housing tongues (e.g., to continue flow separation until a turbine impeller of a dual-flow nozzle is produced). For example, two blades can be used to define two approximately 180-degree sections of the nozzle peripheral area (e.g., between two blades), where movable blades can be added to one or both sections (e.g., in a VNT method, etc.). For example, an end portion of a wall (e.g., a wall end) can be a tongue, and the blades can act to change the shape of the tongue, the length of the tongue, the continuity of the tongue, etc.

[0061] For example, one orientation of the vanes may provide an impulse volute, while another orientation of the vanes may provide an open volute. In such an example, dual flow may occur in the open volute, which may help increase engine speed (e.g., consider the Stoβ-Stau method).

[0062] For example, blades applied to axial impellers (eg, twin boost variable dual flow) can act to combine ultra-low inertia and variable dual flow.

[0063] For example, a turbine assembly may be employed to address one or more backflow issues. For example, one or more vanes may be actuated to address backflow of exhaust gas during operation (eg, depending on power demand, mass flow, volume flow, etc.).

[0064] 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 having a wall 862 and a wall 864 defining paths 867 and 869. Wall 862 includes a wall end 863 at the turbine wheel space, and wall 864 includes a wall end 865 at the turbine wheel space. 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 can be fixed or optionally movable. As shown, blades 882-1 and 882-2 can form relatively continuous surfaces with structures 883-1 and 883-2. Pivoting of blades 883-1 and 883-2 can change these surfaces, for example, to guide exhaust gas relative to paths 867 and 869.

[0065] like Figure 8As shown in the example of, blade 882-1 can be pivotable relative to fixed wall end 863, and blade 882-2 can be pivotable relative to fixed wall end 865. In such an example, the flow at wall ends 863 and 865 can be changed via the pivoting of blades 882-1 and 882-2. Such pivoting can change the flow in paths (or channels) 867 and 869 leading to the turbine wheel space. One operating mode can coordinate the pivoting of blades 882-1 and 882-2 with the pivoting of blades 884-1 to 884-N. For example, blades 884-1 to 884-N can include two groups, one group corresponding to each of paths 867 and 869. For example, these groups can be independently adjustable, or, for example, they are fully adjustable in unison. For example, blades 882-1 and 882-2 and blades 884-1 to 884-N can be fully adjustable in unison. For example, blades 882-1 and 882-2 may be adjusted independently of blades 884-1 through 884-N.

[0066] For example, a component may include: an exhaust gas turbine housing, the exhaust gas turbine housing including an inner wall and an outer wall, which define a first exhaust gas passage and a second exhaust gas passage leading 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 adjustable divider blade, which is arranged adjacent to the inner wall end; a second adjustable divider blade, which is arranged adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle blades, which define a nozzle throat that directs the exhaust gas flow from at least one of the exhaust gas passages to the turbine wheel space.

[0067] Figure 5 Shows Figure 4 A portion of the assembly 860, particularly a cross-sectional view and a partially exploded view. Figure 5 In the example of , various components, features, etc. may be described, for example, with respect to a z-axis that can coincide with the axis of rotation of the turbine wheel. As shown, the z-axis can be used as a reference for 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 disposed at a radial distance r from the z-axis (which may be referred to as a center axis). For example, various components may be concentric (e.g., substantially aligned relative to the z-axis). For example, during operation, one component may be fixed relative to the z-axis while another component rotates about the z-axis. For example, the blades may rotate about a single column axis, such as a single z column axis. As Figure 5 As shown in the example of , the marked z-column axis can be set at a radial distance r from the z-axis.

[0068] like Figure 5As shown, the variable geometry mechanism 880 includes a subassembly 890, which includes a ring 891, which can be a rotatable ring (e.g., a rotatable synchronizing ring), wherein the ring 891 can be rotatable about the z-axis. Figure 5 In the example of FIG. 8 , the ring 891 includes a socket that can receive a corresponding lobed end of a control link 892 that is operably coupled to a corresponding blade post 893. Figure 5 As shown in the example of , the socket of the ring 891 can receive the convex end of the first control link 895, which in turn can be operably connected to the second control link 896, which can be operably connected to the post 897 of the blade 882-2. The blade 882-1 can also be operably connected to these components (e.g., another set of first control links 895 and second control links 896, etc.). The ring 891 can be at least partially supported by rollers (e.g., along the inner periphery and / or the outer periphery).

[0069] Figure 5 Also shown in the drawings is a nozzle ring 898, which is presented in cross-sectional view with a cross-sectional surface spanning the post holes of the posts (e.g., see post 897) for blades 882-1 and 882-2. For example, the nozzle ring 898 can be substantially centered on the z-axis and can be arranged in the assembly so that the nozzle ring 898 is substantially fixed so that it does not rotate about the z-axis. For example, the nozzle ring 898 can be operably connected to one or more biasing mechanisms (e.g., a resilient plate or multiple resilient plates, a spring or multiple springs, etc.) so that some movement of the nozzle ring 898 can occur along the z-axis. Figure 5 In an example of the nozzle ring 898, the nozzle ring 898 includes an upper surface and a lower surface, wherein post holes for blades 882-1, 882-2, and 884-1 to 884-N extend from the lower surface to the upper surface. The posts disposed in the post holes can be rotated via rotation of the ring 891 (e.g., rotation around the corresponding post axis), thereby pivoting the blade to which the post is attached. One or more blade front surfaces can be disposed on one side of the blade, for example, the hub side of each blade, which is opposite to the base side of each blade, and can face the one or more blade front surfaces, wherein the base side faces the upper surface of the nozzle ring 898. In such an example, the nozzle can be defined between the upper surface of the nozzle ring 898 and the one or more blade front surfaces and between adjacent blades. For example, the space between two adjacent blades can be referred to as a throat, wherein, for example, the shape of the throat can be adjustable via pivoting of one or both of the two adjacent blades. The shape of the throat may direct the exhaust gases, for example, in a more tangential or axial manner relative to the axis of rotation of a turbine wheel disposed in a turbine wheel space, which may be defined in part via a nozzle ring 898 .

[0070] exist Figure 5 In an example of a nozzle ring 898, the nozzle ring 898 includes a partial hole that can accommodate a peg extending axially from the first control link 895. As shown, the first control link 895 (e.g., a control arm) includes a lobed end, one lobed end is received by the socket of the ring 891 and one lobed end is received by the 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 the peg (e.g., the peg axis), which in turn causes the second control link 896 to pivot. As shown, the second control link 896 includes an orifice that accommodates the end of the post 897. In such an example, the post 897 can be fixed relative to the second control link 896 so that when the second control link 896 pivots, the blade 882-2 pivots.

[0071] Although Figure 5 , a ring with a socket and a control link with a cam are shown, but the blades can also be controllable by one or more other types of mechanisms. For example, the one or more mechanisms can include multiple rings, a ring mechanism and another type of mechanism, etc. For example, blades 884-1 to 884-N can be adjustable independently of blades 882-1 and 882-2, or the blades can be adjustable in a coordinated manner (e.g., via rotation of a ring mechanism, etc.).

[0072] For example, the mechanism can be actuatable (e.g., adjustable, etc.) via a mechanical actuator, an electronic actuator, a pneumatic actuator, a hydraulic actuator, etc. For example, the actuator can be a hybrid actuator (e.g., a combination of two or more of the above types of actuators). For example, the actuator can be operably coupled to an engine control unit (ECU). For example, the processor can execute instructions stored in a memory to instruct the actuator to actuate one or more mechanisms that can adjust a blade, a pair of blades, a set of blades, multiple sets of blades, etc. For example, the actuator can actuate a ring, wherein the cam end of the control link moves with the ring, thereby directly and / or indirectly rotating the blade (e.g., via a blade post, etc.).

[0073] Fig. 6A A portion of assembly 860 is shown, which includes another assembly 1050, Figure 6B shows a cross-sectional view including a portion of assembly 860 and a portion of assembly 1050, Figure 6C A portion of the assembly 860 is shown, at which a first control link 895 and a second control link 896 are mounted and can be controlled via rotation of the ring 891 . Fig. 6AAn example of an insert 1060 is shown that 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 grooves.

[0074] exist Fig. 6A , assembly 1050 includes insert 1060 operably coupled to 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. Figure 6C In FIG. 1 , two spacers 1080 - 1 and 1080 - 2 are shown. Fig. 6A In the example of FIG. 1 , the insert 1060 includes a substantially flat base portion 1062 and a cylindrical portion 1064 axially rising from the substantially flat base portion 1062. As shown, the cylindrical portion 1064 may include one or more sealing elements 1085. For example, one or more sealing elements of different types may be included. Figure 6B , the vanes 884 are shown as being disposed between a lower surface of a substantially flat base portion 1062 of the insert 1060 and an upper surface of the nozzle ring 898. For example, the spacers (e.g., 1080-1 and 1080-2 or 1080-1, 1080-2, 1080-3, etc.) can space the insert 1060 from the nozzle ring 898 an axial distance to define a nozzle axial height of the nozzle space, wherein the pivotable vanes disposed in the nozzle space can include a vane height that provides clearance for pivoting within the nozzle space. For example, the insert 1060 can include a shroud surface that is contoured in a manner that defines clearance relative to an airfoil of a turbine wheel. The cylindrical portion 1064 of the insert 1060 can be defined by an inner radius that defines a flow path for exhaust gas so that exhaust gas entering the nozzle space can flow around the turbine wheel and then exit.

[0075] Figure 7 An example of an assembly 1700 is shown that includes a compressor assembly 1740 , a center housing assembly 1780 , and a turbine assembly 1800 , where the turbine assembly 1800 is coupled to the center housing assembly 1780 .

[0076] like Figure 7 As shown in the example of , turbine assembly 1800 includes an actuator 1810 having a control arm 1812 to position blades 1900 of turbine assembly 1800. As shown, blades 1900 are positioned radially outward from turbine wheel 1870, which defines a rotation axis z that 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 azimuthal (θ) coordinates.

[0077] As shown, the turbine assembly 1800 includes a turbine housing 1860, which defines a first exhaust gas passage 1867 and a second exhaust gas passage 1869 in part via a wall end 1863 of an outer wall 1862 and a wall end 1865 of an inner wall 1864. As previously described, the turbine housing may include a wall end, which may be a portion of a volute (vortex) or a volute wall, providing exhaust flow to the turbine impeller. Figure 7 In the example of FIG. 1 , wall ends 1863 and 1865 may be the ends of two vortex or volute walls (eg, walls 1862 and 1864 ) that define exhaust gas passages 1867 and 1869 .

[0078] As shown, turbine housing 1860 includes inner wall 1864 and outer wall 1862, which define first exhaust gas passage 1867 and second exhaust gas passage 1869 leading to turbine wheel space for turbine wheel 1870, wherein inner wall 1864 includes inner wall end 1865 at the turbine wheel space, and outer wall 1862 includes outer wall end 1863 at the turbine wheel space. Figure 7 In the example of FIG. 1 , the first flow body 2000-1 is disposed adjacent to the outer wall end 1863 and the second flow body 2000-2 is disposed adjacent to the inner wall end 1865. As shown, the turbine assembly 1800 includes a plurality of sets of adjustable variable geometry nozzle vanes 1900 that define a nozzle throat that directs exhaust gas from the exhaust gas passages 1867 and 1869 to the turbine wheel space.

[0079] As previously described, actuator 1810 can control the position of blades 1900 via control arm 1812, for example, positioning blades 1900 in a closed position and one or more open positions. In such an example, the closed position can define a minimum flow condition. For example, there may be no blade-to-blade contact in the closed position, so that there is a relatively small, narrow passageway in which there may be a certain amount of flow, which can be defined as a minimum or lowest flow (e.g., for a given pressure, etc.). Figure 7 In an example, the turbine assembly may include a cylinder 1880 that carries at least blades 1900. For example, flow bodies 2000-1 and 2000-2 may be mounted to or otherwise positioned relative to cylinder 1880 and adjacent to wall ends 1863 and 1865, respectively. For example, flow bodies 2000-1 and 2000-2 may be statically positioned so that they do not move, while blades 1900 may be pivotally movable relative to static flow bodies 2000-1 and 2000-2.

[0080] Figure 8 Shows Figure 718 is a cross-sectional view of assembly 1800 where exhaust gas passages 1867 and 1869 are shown along with turbine housing 1860, turbine 1870, and blades 1900 in an open position.

[0081] Fig. 9 Shows Figure 7 A cross-sectional plan view of the assembly 1800. Fig. 9 In the example of , the first flow body 2000-1 can be arranged at an angle of about 102 degrees to the horizontal plane (e.g., at an angle of about 12 degrees to the vertical plane), and the second flow body 2000-2 can be arranged at an angle of about 292 degrees or -68 degrees to the horizontal plane (e.g., at an angle of -22 degrees to the vertical plane). Fig. 9 In the example of FIG. 1 , there are eight blades 1900 between the two blades 1900-1 and 1900-10 associated with the first flow body 2000-1 and the second flow body 2000-2 in the clockwise direction, and there are nine blades 1900 between the two blades 1900-1 and 1900-10 associated with the first flow body 2000-1 and the second flow body 2000-2 in the counterclockwise direction. Fig. 9 In the example of FIG. 1 , the number of blades 1900 is nineteen. For example, the turbine assembly may include fewer or more blades, an even number of blades or an odd number of blades, etc. For example, the turbine assembly may include at least five blades and less than forty blades.

[0082] As previously mentioned, a line drawn between the columns of blades 1900-1 and 1900-10 may not intersect the axis of rotation z of turbine wheel 1870, e.g. Fig. 9 In the example of , such a line (dashed line) is offset to the right of the rotation axis z.

[0083] Fig.10 Shows Figure 7 1800, wherein exhaust gas passages 1867 and 1869 are shown together with turbine housing 1860, turbine 1870 and blades 1900, with blades 1900 in an open position, as shown in FIG. Fig. 9 The example has fewer open positions.

[0084] Fig.11 Shows Figure 7 1800, wherein exhaust gas passages 1867 and 1869 are shown together with turbine housing 1860, turbine 1870 and blades 1900, with blades 1900 in an open position, as shown in FIG. Fig.10 The example has fewer open positions.

[0085] Fig. 9 , Fig.10 and Fig.111 and 2. It is shown 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 an obstruction to the flow of exhaust gases to turbine wheel 1870 (e.g., to the turbine wheel space). For example, the fully closed position can involve blade-to-blade contact of blades 1900. For example, in the event that blades 1900 are in blade-to-blade contact, the contact area can be used to further obstruct the flow of exhaust gases (e.g., seal blade surfaces against each other). Fig. 9 , Fig.10 and Fig.11 In the view of FIG. 1 , each blade 1900 rotates clockwise, moving from a more open position to a more closed position (eg, a less open position).

[0086] Fig.12 A perspective view of a portion of assembly 1800 is shown, wherein three blades 1900 are labeled 1900-1, 1900-2, and 1900-3. Fig.12 In the example of FIG. 1 , portions of the exhaust gas channels 1867 and 1869 are generally shown, wherein the wall end 1863 and the first flow body 2000 - 1 act as a barrier to fluid communication between the exhaust gas channels 1867 and 1869 .

[0087] As mentioned previously, the exhaust gas passages may be fed by different cylinder groups of an internal combustion engine, wherein the cylinders include pistons coupled to a rotatable shaft. The pistons may be operated according to a firing order and an intake stroke and an exhaust stroke. For a firing order of a four-cylinder internal combustion engine with pistons labeled 1, 2, 3, and 4, an inline four-cylinder engine may be considered to have a firing order of 1-3-4-2 or 1-2-4-3; for a horizontal (opposed) four-cylinder engine, pistons labeled R1, R2, L1, and L2 are considered, and the firing order is R1-R2-L1-L2. Figure 2A As shown, one exhaust gas passage may receive exhaust from two cylinders (e.g., 1 and 4), while another exhaust gas passage may receive exhaust from different cylinders (e.g., 2 and 3). For example, the engine may be in an in-line configuration, a V-shaped configuration, or a horizontally opposed configuration. For example, the engine may include multiple manifolds. In such an example, each of the multiple manifolds may provide a passage for exhaust gas to a corresponding exhaust gas passage of a turbine assembly. For example, the engine may include more than one and less than twenty cylinders (e.g., considering 3, 4, 5, 6, 8, 10, 12, etc.).

[0088] For example, the manifold may provide exhaust gas recirculation (EGR), for example, to the intake duct and / or the manifold. In such an example, the exhaust gas flows in the exhaust gas passages may be different (for example, one provides EGR and the other does not provide EGR).

[0089] As previously described, pulsation may occur in and / or between the two exhaust gas passages. For example, the arrangement of features of assembly 1800 may account for pulsation. For example, where pulsation tends to be strong, the gap between the leading edge of the blade and the flow body may be increased. In this approach, pulsation may be dispersed to some extent via freer fluid communication with a larger volume. For example, in Fig.11 , blade 1900-1 can be rotated an additional angle in a clockwise direction (e.g., in line with other blades 1900) to provide a larger gap relative to the first flow body 2000-1, which can increase the fluid communication between the exhaust gas channels 1867 and 1869. For example, the gap of blade 1900 relative to one or more of the flow bodies 2000-1 and 2000-2 in the closed position can be controlled by the positioning of blade 1900 (e.g., the radius of the column), the position of the blade column, the distance between the blade column and the leading edge, etc. Therefore, the closed position gap can be designed to accommodate considerations related to pulsation (e.g., pulse pressure, etc.). When the pulsation (e.g., pulse pressure) may be strong, the (multiple) gaps may increase.

[0090] like Fig.12 As shown in the example, there may be a gap c between the flow body 2000-1 and the wall end 1863. we . This gap can be customized according to one or more criteria. For example, considering pulsating fluid communication, installation clearance, thermal expansion / contraction clearance, etc. As mentioned above, in the case of strong pulsation, this gap can be larger to increase the fluid communication between the exhaust gas channels 1867 and 1869.

[0091] Fig.13 An example of a 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 post 2060, the post 2060 including a post end 2062. As shown, the boss 2040 may be shaped as a truncated cylinder and slightly higher than the upper surface 2006, so that the boss 2040 acts as a spacer, for example, to provide an axial gap between the components of the assembly 1800.

[0092] exist Fig.13In the example of FIG. 2 , the flow body 2000 can be defined by an axial height h, wherein the boss 2040 and the column 2060 can have a greater axial height. For example, the height of the flow body 2000 at the front surface 2004 can be greater than the height at the rear surface. For example, the height at the front surface 2004 can be selected to substantially match the height of the wall end, while the height at the rear surface 2002 can be selected to substantially match the height of the blade. For example, the upper surface 2006 can be inclined upward between the boss 2040 and the leading edge 2004.

[0093] For airfoil surfaces 2010 and 2020, one or more radii may be used to define them. For example, Fig.13 Radius R1 and radius R2 are shown, which can define airfoil surfaces 2010 and 2020, respectively. As shown, rear surface 2002 can be formed by radius R ve Limit, radius R ve The radius R can be based on the arc of the leading edge of the blade. ve Considered as the arc R swept by the pivoting motion of the leading edge of the blade le With the gap definition, the gap can be R le percentage (e.g., from 0.1% to 25%). Fig.13 As shown in the example of , the rear surface 2002 may include a concave portion, wherein the concave portion is partially defined by an arc. As previously described, such a rear surface may be referred to as a concave rear surface. For example, a test for a concave portion may be to draw a line between two points in the object, and if this line passes through the boundary of the object (e.g., the surface of the object), then the object may be defined as concave (e.g., including a concave portion), such as having a concave (into) surface. As for the front surface 2004, it may be defined by a radius R se To limit the radius R seIt may depend on the shape of the well end. For example, the front surface 2004 may be a convex front surface or a flat front surface. For example, if a line is drawn between the ends of the front surface 2004, if the line does not intersect the front surface 2004, the front surface 2004 is non-concave. 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 located outside the flow body 2000, so that the rear surface 2002 is a concave rear surface. For example, the rear surface 2002 can be defined as a concave shape via a concave arc shape, which effectively forms a concave (serrated) rear surface 2002 (e.g., recessed into the flow body 2000). For example, a convex arc shape can form a raised surface (e.g., a convex surface). For example, the flow body may include a rear surface, the rear surface including a recess, the recess may be arranged between the ends of the rear surface, wherein one or both ends may be rounded and / or chamfered. For the rounded end, it may be defined as a convex shape. For example, consider a concave portion of the rear surface disposed between the convexly rounded ends of the rear surface such that the rear surface can be defined as a concave rear surface (e.g., a rear surface having a concave portion that can accommodate the leading edge of the blade as the blade sweeps an arc in response to pivoting about a pivot axis).

[0094] exist Fig.13 In the example of FIG. 1 , the embedded geometric diagram shows two circles of radius R1 and R2 that are offset about their centers. As shown, by the offset, a region can be defined, a portion of which can define airfoil surfaces 2010 and 2020 of the flow body 2000. As shown, the thickness of the flow body 2000 can be different over its length. For example, it can be thicker at the rear surface 2002 of the blade, with a ΔR ve , while the front surface 2004 may be thinner, with ΔR se In such an example, the thickness may be selected to accommodate the pivot range of the leading edge of the blade and / or to accommodate the wall end thickness. Where the flow body 2000 is to accommodate a larger arc swept by the leading edge of the blade (e.g., in terms of angles defined by the pivot range, etc.), the flow body 2000 may be thicker at the rear surface 2002; and where the flow body 2000 is to accommodate a smaller arc swept by the leading edge of the blade (e.g., in terms of angles defined by the pivot range, etc.), the flow body 2000 may be thinner at the rear surface 2002.

[0095] Fig.14 , Fig.15 and Fig.16 They are shown respectively Fig. 9 , Fig.10 and Fig.11 An enlarged view of a portion of assembly 1800 is shown.

[0096] exist Fig.14In the example of FIG. 1 , blade 1900-1 is shown to include 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 leading edge 1902 and trailing edge 1904. Blade 1900-1 is also shown to include a post 1960 that defines a pivot axis z of blade 1900-1. v As previously described, blade 1900-1 may be pivoted about its pivot axis z v Pivotable in a clockwise or counterclockwise direction.

[0097] exist Fig.14 In the example of FIG. 1 , the blade 1900-1 is pivoted to a position in which the leading edge 1902 can form a substantially continuous (connected) connection between the airfoil surfaces 2020 and 1920, although there is a gap between the leading edge 1902 of the blade 1900-1 and the rear surface 2002 of the flow body 2000-1. In addition, as shown, the airfoil surface 2010 of the flow body 2000-1 can provide a throat relative to the blade 1900-2, wherein the throat extends to the airfoil surface 1910 of the blade 1900-1. As for the gap between the leading edge 1902 of the blade 1900-1 and the rear surface 2002 of the flow body 2000-1, it can be small enough so that a large amount of exhaust gas flow does not occur in the gap between the exhaust gas of the exhaust gas passages 1867 and 1869.

[0098] exist Fig.14 In the example of FIG. 1 , blade 1900 - 1 may be defined as being at a pivot angle of approximately 69 degrees, such as from the pivot axis z v The dashed line to the leading edge 1902 is defined. As shown in the figure, the dashed line can be tangent to or otherwise close to the end of the rear surface 2002 of the flow body 2000-1. As shown in the figure, the end can be between the rear surface 2002 and the airfoil surface 2020.

[0099] like Fig.14 As shown in the example of , blades 1900-1, 1900-2, 1900-3, etc. have a pivot axis 1960 located between a leading edge 1902 and a trailing edge 1904. In such an example, the distance from the pivot axis 1960 to the leading edge 1902 can be approximately the same as the distance from the pivot axis 1960 to the trailing edge 1904. For example, such a distance can be defined by a ratio or one or more percentages. For example, in Fig.14 In the embodiment, 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. For example, the distance from the pivot axis of the blade to the leading edge may be at least 40% of the distance from the pivot axis of the blade to the trailing edge. Fig.14In the example of FIG. 1 , the distance from the pivot axis 1960 to the leading edge 1902 is greater than about 60%, about 70%, and about 80% of the distance from the pivot axis 1960 to the trailing edge 1904. If the blade does not include a leading edge disposed a distance from the post region of the blade, the leading edge will not sweep out an arc when pivoting about the pivot axis; instead, it will remain constrained within the radius of the post region.

[0100] As previously described, 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 this approach, the radius of the circle can be greater than the radius of the column area (see dashed circle). For example, Fig.14 , the radius of the circle drawn around the leading edge 1902 may be at least three times the radius of the column region of the blade 1900-1. Fig.14 , the radius of a circle drawn around leading edge 1902 centered on pivot axis 1960 (dashed circle) is approximately 4 to 5 times the radius of a circle drawn around the cylindrical region of blade 1900 - 1 (dashed circle).

[0101] like Fig.14 As shown, the blade 1900-1 has an airfoil shape, wherein the air length is greater than its width. As previously described, the rear surface 2002 of the flow body 2000-1 can be defined to overlap with the leading edge 1902 of the blade 1900-1 for a portion of the pivot angle range, and not overlap at various angles outside of the range (e.g., see Fig.17 ).

[0102] Fig.15 The position of blade 1900-1 is shown with Fig.14 The example is different. Fig.15 In the example of FIG. 1 , blade 1900 - 1 may be defined as being at a pivot angle of approximately 54 degrees, such as from the pivot axis z v The dashed line to the leading edge 1902 is defined. As shown, the dashed line can be located between the ends of the rear surface 2002 of the flow body 2000-1.

[0103] Fig.16 The position of blade 1900-1 is shown with Fig.15 The example is different. Fig.16 In the example of FIG. 1 , blade 1900 - 1 may be defined as being at a pivot angle of approximately 42 degrees, such as from the pivot axis z v The dashed line to the leading edge 1902 is defined. As shown in the figure, the dashed line can be tangent to or otherwise close to the end of the rear surface 2002 of the flow body 2000-1. As shown in the figure, the end can be between the rear surface 2002 and the airfoil surface 2010.

[0104] exist Fig.14, Fig.15 and Fig.16 In the example of , the pivot angle ranges from about 69 degrees to about 42 degrees, which is an angle pivot span of about 27 degrees. As previously mentioned, the closed position can be at a further pivot amount, for example, a pivot angle less than 42 degrees, for example, the blades may touch at this angle. Fig.14 , Fig.15 and Fig.16 An example of represents an overlapping range of pivot amounts of blade 1900-1, for example, the overlap can be defined by a radial line from a column or pivot axis of the blade to a leading edge of the blade. In such an example, a first overlap marker can move from open to less open and a second overlap marker can move from less open to more closed (e.g., or vice versa). For example, the overlapping range of pivot angles can be a range that is less than the overall operating range of the pivot angle. For example, the overlapping range of pivot angles can be closer to a closed end of the pivot angle range than an open end of the pivot angle range. For example, referring to Fig.14 , counterclockwise pivoting of blade 1900-1 is possible so that no overlap occurs when blade 1900-1 is in a more open position. In this example, consider a pivot angle of approximately 90 degrees (e.g., Fig.14 1900-1 ), such that the overlap range of the pivot angle of about 69 degrees to about 42 degrees is closer to the closed position of blade 1900-1 (e.g., about 90 degrees) than the fully open position of blade 1900-1. Fig.16 , a pivot angle of approximately 30 degrees may be a position at which contact may occur between blade 1900-1 and blade 1900-2 (e.g., where both are pivoted). In such an example, the lower range of overlap is approximately 42 degrees, which is within 12 degrees of the closed position, which may be a contact position; however, the upper range of overlap is approximately 69 degrees, which is within 21 degrees of the 90 degree example of a fully open position, which may be defined by the blade trailing edge to the turbine impeller blade clearance (e.g., approximately 1% to 10% of the outer radius of the turbine impeller). For example, the fully open position of blade 1900-1 may 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 may be substantially between the fully open pivot angle and the fully closed pivot angle (e.g., approximately 12 degrees from fully open and approximately 12 degrees from fully closed or contact).

[0105] Fig.17A plan view of a portion of the assembly 1800 is shown, along with a pivot angle range Φ defined by a fully open position FO and a fully closed position FC, which may be a blade-to-blade contact position. As shown, the overlapping pivot axis angle range Φ o The pivot angle range Φ may be within Φ. Furthermore, the overlapping pivot angle range may be degrees from the FO position and may be degrees from the FC position, wherein, for example, the degrees from the FC position may be smaller than the degrees from the FO position.

[0106] exist Fig.17 In the example of , the overlapping pivot angle range can be a percentage of the pivot angle range. For example, the overlapping pivot angle range is considered to be 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.

[0107] In various examples, the wall end may be or act as a tongue extension.Such a wall end may be symmetrically or asymmetrically positioned relative to the blades (e.g., consider a set of blades comprising 10 blades and another set of blades comprising 9 blades, for a total of 19 blades).

[0108] As previously discussed, the closed position may define a minimum flow condition. For example, in the closed position there may be no blade-to-blade contact, such that there is a relatively small, narrow passageway in which there may be a certain amount of flow, which may be defined as a minimum or lowest flow (e.g., for a given pressure, etc.). Where contact does occur, some minimum flow may occur, such as in the gaps above and / or below the blades.

[0109] As previously mentioned, the flow body can be part of the barrel assembly (e.g., disposed between the plate portion and the insert portion of the barrel assembly, and the blade can also be positioned at the insert portion). As previously mentioned, the blade can be pivotable around its respective pivot axis, wherein there is a relatively small gap between the two blades and the two corresponding flow bodies. For example, in the turbine wheel space (e.g., the central axis of the barrel assembly), the flow body can include a side closest to the turbine impeller rotation axis, which side can be at least partially rounded (e.g., curved) to take into account the leading edge of the corresponding blade, as shown in the figure, although it is the leading edge of the blade, it 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 can allow the flow to be "divided", wherein a portion of the flow flows along one side of the blade, and another portion of the flow flows along the opposite other side of the blade. In various examples, the presence of the flow body can block the leading edge to a certain extent, so that the incoming flow on one side of the flow body flows mainly along one side of the corresponding blade, and the incoming flow on the other side of the flow body flows mainly along the opposite other side of the corresponding blade.

[0110] For example, the flow body can be made of a material such as steel. For example, the flow body can be made of the same material as the blade material. In various examples, the flow body can be a fixed structure. For example, consider a fixed structure fixed in a barrel assembly.

[0111] As previously mentioned, the side of the flow body (e.g., the airfoil surface) can be at least partially defined by an arc, and the arc length of the arc can be defined as a distance and / or degree. In such an example, the arc can be defined using the pivot axis of the blade. For example, consider drawing a circle around the blade, the circle being centered on the blade axis, and the side of the flow body being 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 barrel assembly), the blade located at the flow body can form a relatively continuous curved surface with one side of the flow body, for example, the curved surface can be defined with a gap on the opposite side of the flow body and a portion of the blade. The profile of the flow body can be determined in a manner corresponding to the pivotable blade.

[0112] For example, the exhaust gas flow may be substantially separated by the flow body over at least a portion of the entire stroke of the corresponding blade, e.g., no more than the entire stroke. In such an example, the flow body may be shaped in a manner that introduces minimal disturbance (e.g., only where an end "arc" side may be required, which may be determined by one or more blade characteristics, such as the length to one side of the pivot axis, etc.). This approach may be helpful in separating the flow of two vortices (e.g., volutes), which, as previously described, may be from different cylinders of an internal combustion engine.

[0113] For example, the flow bodies may be identical so that only a single piece needs to be manufactured. For example, consider manufacturing two identical pieces and inserting the two identical pieces into a cartridge assembly during assembly of a cartridge assembly, wherein the cartridge assembly includes a plurality of pivotable vanes, which may be an odd number of vanes, or, for example, an even number of vanes; noting that an odd number of vanes may be used in situations where, for example, the flow in one vortex is different from the flow in the other vortex of a two vortex assembly.

[0114] For example, the flow body may be non-contacting in that no vanes contact the flow body during operation of the variable nozzle cartridge assembly.

[0115] For example, an assembly may include one or more features that may be defined using the continuity of curves and / or surfaces. For example, consider a flow body to a blade, where the blade is pivotable about an axis, e.g., where the flow body is fixed, and / or for example, consider a tongue to a flow body to a blade, where the blade may be pivotable about an axis, e.g., where both the tongue and the flow body are fixed.

[0116] As previously mentioned, the flow field upstream of the blades of a turbine machine is generally not uniform (homogeneous). Therefore, it may be desirable to minimize the disturbance (interference) between one or more parts of the flow that differ in, for example, velocity vectors and fluid states.

[0117] Variable position guide vanes can be used to adapt the swallowing characteristics (throughput characteristics) of a turbine stage to different operating conditions of the turbine. For example, it may be desirable to minimize the interference between two adjacent parts of a flow that necessarily at least partially enter two adjacent variable geometry nozzles at various or all possible positions of the movable vanes without changing the relative flow distribution between the two parts of the flow.

[0118] As previously mentioned, the shape of the flow body upstream of the movable guide vane may be defined in a particular manner. As previously mentioned, the rear surface of the flow body may be at least partially defined by a cross-section of a circle, which cross-section may be at least partially defined by the leading edge of the blade. As previously mentioned, such a rear surface may be a concave rear surface, wherein the concave portion of the rear surface may receive the leading edge of the blade as the leading edge sweeps an arc in response to pivoting about the pivot axis of the blade.

[0119] For example, the center of the circle can be the axis of the movable blade. In such an example, the radius of such a circle can 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., consider a few millimeters or less).

[0120] For example, a sector of a circle (e.g., an arc) may be equal to a portion of the circle traveled by the movable blade. For example, such a sector may be shortened at either or both end positions of the movable blade. In such an example, such a shortening (e.g., a chamfer, etc.) may be necessary to allow some flow mixing near the two respective end positions of the movable blade.

[0121] For example, the fan can be extended at either or both end positions of the movable blade. In such an example, this approach can help minimize the impact of small movements of the blade on the flow.

[0122] In various situations, a vehicle may be braked using one or more forms of non-wheel brakes. For example, in heavy vehicles, the engine is often used to provide additional braking power to relieve stress on the vehicle's conventional brake system and help avoid overheating of the brakes. For example, consider a butterfly valve that stops the exhaust flow, which may be called an "exhaust brake." Another form is compression release braking, which may be used on large diesel trucks. This braking operation is achieved by opening the exhaust valve at the top of the compression stroke (top dead center), so that a large amount of energy stored in the compressed air is not returned to the crankshaft, but is released to the atmosphere. Normally, energy is used during the compression stroke when the upward moving piston compresses the air in the cylinder; the compressed air then acts as a compressed spring (acts like a compressed spring) to push the piston back down. However, in the case of a jack brake operation, the compressed air is suddenly released just before the piston begins to move downward. This sudden release of compressed air is similar to the expanding gas escaping from the muzzle of a gun, which produces an audible sound wave. Having lost the energy stored in the compressed air, there is no "rebound", so the engine must expend more energy to pull the piston back down again. This braking can be effective and produce a lot of braking force (for example, a 565 hp (421 kW) diesel engine can produce up to 600 hp (450 kW) braking power at 2100 rpm).

[0123] For example, a flow body (e.g., an object) can be shaped to help address one or more of a variety of conditions. For example, it may be ideal to achieve perfect flow separation over a full range of operating conditions. However, conditions such as engine-related braking can change the pulsation. In the case of strong pulsations, a gap (e.g., a clearance) between the flow body and the corresponding blades can help reduce the effects of strong pulsations in the closed position of the barrel assembly, which may otherwise be strong enough to overload the blade adjustment mechanism, thereby potentially causing one or more control problems when attempting to maintain a particular position of the blades (e.g., a closed position, which may be a minimum flow position, etc.). This approach can help extend the useful life of a variable geometry turbocharger. Moreover, as previously described, the flow body can provide more flow separation when the blades are open because the open channels formed between the blades can allow the flow to the turbine impeller to "release" and / or "flatten" the pulsating pressure.

[0124] Fig.18 An example of a portion of assembly 1800 is shown, where flow body 2000-1 includes ends 2003 and 2005 of rear surface 2002, where end 2003 is different from end 2005. For example, Fig.17 Compared to the example of , end 2003 can be truncated (e.g., chamfered, etc.) to provide a larger amount of clearance.

[0125] Fig.19 It shows that Fig. 9 , Fig.10 and Fig.11 An enlarged view of a portion of assembly 1800 is shown, but with flow body 3000-1 included. Fig.19 In the example of FIG. 1 , blade 1900 - 1 is pivoted to a position where leading edge 1902 can form a substantially continuous transition between airfoil surfaces 3010 and 1910 , despite a gap between leading edge 1902 of blade 1900 - 1 and rear surface 3002 of flow body 3000 - 1 .

[0126] exist Fig.19 In the example of FIG. 1 , flow body 3000-1 is shown with labels similar to the labels used to describe various features of flow body 2000 (e.g., flow body 2000-1). However, flow body 3000-1 also includes an extension 3070 at a rear surface 3002 (e.g., a rear end), the extension including a tip 3072. As shown, extension 3070 can be an extension of airfoil surface 3020 of flow body 3000-1. Flow body 3000-1 can limit the pivoting of blade 1900-1 via extension 3070, such as limiting the pivoting of a group of blades to which the blades are mechanically coupled. When blade 1900-1 is in Fig.19 , leading edge 1902 will generally sit in a pocket formed by rear surface 3002 and a surface of extension 3070, wherein an opposing surface of extension 3070 may form a substantially continuous transition between airfoil surface 1920 of blade 1900-1 and airfoil surface 3020. Blade 1900-1 may be limited in its angular range of rotation (e.g., pivoting) in a clockwise and / or counterclockwise direction.

[0127] Fig. 20 It shows that Fig. 9 , Fig.10 and Fig.11 An enlarged view of a portion of assembly 1800 is shown, but with flow body 4000-1 included. Fig. 20 In the example of FIG. 1 , blade 1900 - 1 is pivoted to a position where leading edge 1902 can form a substantially continuous transition between airfoil surfaces 4010 and 1910 despite a gap between leading edge 1902 of blade 1900 - 1 and rear surface 4000 of flow body 4002 - 1 .

[0128] exist Fig. 20In the example of FIG. 4 , flow body 4000-1 is shown with labels similar to the labels used to describe various features of flow body 2000 (e.g., flow body 2000-1). However, flow body 4000-1 also includes an extension 4070 at a rear surface 4002 (e.g., a rear end), the extension including a tip 4072. As shown, extension 4070 can be an extension of airfoil surface 4020 of flow body 4000-1. Flow body 4000-1 can limit the pivoting of blade 1900-1 and, for example, limit the pivoting of a group of blades to which the blades are mechanically coupled via extension 4070. When blade 1900-1 is Fig. 20 , leading edge 1902 will generally sit in a pocket formed by rear surface 4002 and a surface of extension 4070, wherein an opposing surface of extension 4070 may form a substantially continuous transition between airfoil surface 1920 of blade 1900-1 and airfoil surface 4020. Blade 1900-1 may be limited in the angular range over which it may rotate (e.g., pivot) in a clockwise and / or counterclockwise direction.

[0129] exist Fig. 20 In the example of , the flow body 4000 also includes discrete spacers 4090 that do not extend to the rear surface 4002. Fig. 20 In an example of, spacer 4090 can be shaped and / or sized to provide a desired flow transition from tongue 1863 to the blade space. For example, spacer 4090 can be stepped or formed in an axial direction, which is the direction of the axis of rotation of turbine wheel 1870. For example, spacer 4090 can have an axial span, and tongue 1863 can have an axial span, wherein the axial span can be selected to provide a desired flow transition from tongue 1863 to the blade space. For example, spacer 4090 can be used as an extension of tongue 1863, and the extension of tongue 1863 extends a distance into the blade space to provide a more optimal flow in the blade space.

[0130] Fig.21A graph (curve) 21100 of pressure for a portion of an assembly including a flow body with an extension is shown. In graph 21100, the physical components are shown in solid black, while the pressure contours are shown using cross-hatching and solid white. As shown, the extension can be provided to customize the pressure of the flow entering the blade space, where a twin scroll is used. Although graph 21100 shows a single flow body at a single tongue, the assembly can include an additional flow body at another tongue; note that where more than two scrolls are used, a corresponding number of flow bodies can be provided for a corresponding number of tongues. As shown in graph 21100, the pressure on the flow side of the extension may be higher, where the flow can be driven into a throat defined by adjacent blades. For example, the extension of the flow body can help smooth the flow entering the throat, which is defined by a blade, the blade including a leading edge seated in a recess of the flow body and another adjacent blade, the leading edge of the blade being located in the free flow flow flowing out of the inlet flow side of the tongue. This approach can help shape the flow, for example, by effectively providing a barrier to flow extension through a flow body extension tongue, wherein the flow body includes an extension whose radius may be within the outermost radius defined by the blade leading edge. For example, the flow body with the extension may have a flow body thickness and an extension thickness as shown in graph 21100, wherein the extension thickness is less than the flow body thickness (e.g., 50% less, 40% less, 30% less, 20% less, etc.).

[0131] For example, a relatively thin extension of the flow body can provide shaped flow without introducing a significant amount of mass into the flow body, while the relatively thin extension can be thick enough to provide structural integrity, e.g., to withstand flow, high temperatures, possible blade contact, etc. As shown in graph 21100, if blade contact does occur between the leading edges of the blades in the flow body pocket, the blades may contact the extension at or near the junction between the flow body and the extension, which can provide sufficient integrity. For example, the extension of the flow body can have a substantially constant thickness, or can become thinner as it moves from the junction to the tip of the extension.

[0132] Fig. 22 An example of a flow body 3000 is shown in perspective and plan view, and a plan view of a portion of the flow body 3000 is enlarged; note that the cross-sectional view may include Fig.133000; however, note that flow body 3000 includes extension 3070. As shown, flow body 3000 can include concave rear surface 3002 and front surface 3004, upper surface 3006 and lower surface 3008, opposing airfoil surfaces 3010 and 3020, boss 3040, and post 3060, post 3060 including post end 3062 and another boss 3042 and another post 3066, post 3066 including post end 3068. As shown, boss 3040 and / or boss 3042 can be shaped as a truncated cylinder and slightly raised above upper surface 3006, so that boss 3040 acts as a spacer, for example, to provide axial clearance between components of assembly 1800.

[0133] exist Fig. 22 In the example of FIG. 30 , the flow body 3000 may be defined by an axial height h, wherein the extension 3070 may have a smaller axial height h2, which may match the blade height (eg, the blade height may be approximately equal to the extension height).

[0134] As shown, various spans s0, s1, s2, s3, s4, and s5 can be used to define the flow body 3000. For example, the total span or arc length of the flow body 3000 can be defined by the sum of s0 and s2, the latter corresponding to the span of the extension 3070. As shown, the span s3 can correspond to the span of the front surface 3004. As for the extension 3070, it can be partially defined by the span s2 and the span s5 and one or more radii. For example, consider the radius r at the tip 3072 of the extension 3070. 尖端 , which can provide streamlined flow when transitioning from the extension 3070 to the blade. As previously described, the extension 3070 can form a recess with the surface 3002, wherein, for example, the recess can have a radius at least partially defined by the radius r 凹穴 As previously described, the surface 3020 may be defined by one or more radii, wherein, for example, the extension 3070 along the span s2 may be at least partially defined by the radius r ext limited.

[0135] For example, span s4 may be greater than span s5, for example, span s2 may be at least 50% of span s4 and a fraction of span s1. 尖端 The thickness of the extension 3070 can be limited because s5 is greater than r 尖端 , and the extension 3070 tapers from s5 to the tip 3072. For example, s5 may be greater than r 尖端 twice as much.

[0136] For example, the various spans, radii, etc. may be specified using suitable units, such as millimeters. For example, the outermost diameter of the turbine impeller may be in the range of 30 mm to 150 mm. For example, the size of the flow body may be determined in proportion to the turbine impeller, as may the blades. As shown in the various figures, the length of the blades may be less than the outermost diameter of the turbine impeller. Similarly, the length of the flow body may be less than the outermost diameter of the turbine impeller. For example, the length of the flow body may be comparable to the length of the blades. For example, consider a flow body having a length in the range of 0.5 to 2 times the length of the blade, or, for example, in the range of 0.6 to 1.5 times the length of the blade. For example, where the flow body includes an extension, the flow body may be longer than a flow body without the extension, such that the length of the flow body may be a larger portion of the length of the blade, or, for example, greater than the length of the blade, however, typically less than 2 times the length of the blade. As described with reference to Fig.21 As explained, the flow bodies and blades may be customized to obtain a desired flow profile (eg, pressure profile, etc.).

[0137] For example, the height of the flow body 3000 at the front surface 3004 may be greater than the height at the rear surface 3002. For example, the height at the front surface 3004 may be selected to substantially match the height of the wall end.

[0138] As for the airfoil surfaces 3010 and 3020, they may be defined using one or more radii, or, for example, spans (e.g., arc lengths, etc.). Fig.13 Radius R1 and radius R2 are shown, which can define airfoil surfaces 2010 and 2020, respectively. Similar parameters can be used to define airfoil surfaces 3010 and 3020. The rear surface 3002 of the flow body 3000 can be partially defined by radius R1. ve Define, the radius R ve It can be based on the arc of the leading edge of the blade. For example, the radius R ve Considered as the arc R swept by the pivoting motion of the leading edge of the blade le With the gap definition, the gap can be R le As previously mentioned, in the presence of an extension, the recess may be partially defined by the radius (see, for example, r 凹穴 ) or another geometric shape metric (e.g., corners, etc.).

[0139] like Fig. 22As shown in the example of , the rear surface 3002 may include a recess, wherein the recess may be partially defined by an arc. As previously described, such a rear surface may be referred to as a concave rear surface, wherein, for example, a recess at the leading edge of the blade may be formed in combination with an extension 3070 extending to the tip 3072. For example, a recess test may be to draw a line between two points in an object, wherein if this line passes through a boundary of the object (e.g., the surface of the object), then the object may be defined as concave (e.g., including a recess), such as having a concave surface. As for the front surface 3004, it may be defined by a radius R se To limit the radius R se It may depend on the shape of the well end. For example, the front surface 3004 may be a convex front surface or a flat front surface. For example, if a line is drawn between the ends of the front surface 3004, if the line does not intersect the front surface 3004, the front surface 3004 is non-concave. As explained with respect to the rear surface 3002, if a line is drawn between the ends of the rear surface 3002 (e.g., which may include the ends at the tip 3072), the line is at least partially located outside the flow body 3000, so that the rear surface 3002 is a concave rear surface. For example, the rear surface 3002 may be defined as a concave shape via a concave arc shape, which effectively forms a concave (serrated) rear surface 3002 (e.g., recessed into the flow body 3000). For example, a convex arc shape may form a raised surface (e.g., a convex surface). For example, the flow body may include a rear surface, the rear surface including a recess, the recess may be disposed between the ends of the rear surface, wherein one or both ends may be rounded and / or chamfered. For example, the tip 3072 may be rounded (eg, defined by a radius of curvature; see, e.g., 尖端 For rounded ends, they may be defined as convex. For example, consider a concave portion of the rear surface disposed between the convex rounded ends of the rear surface, such that the rear surface may be defined as a concave rear surface (e.g., a rear surface having a concave portion that may receive the leading edge of the blade as the blade sweeps an arc in response to pivoting about the pivot axis).

[0140] For example, the extension 3070 of the flow body 3000 can have a desired length (e.g., see span s2) and can be a constant or variable height (e.g., see height h2). As for the length, it can be long enough to overlap a portion of the blade, thereby forming, for example, a labyrinth-type arrangement, which can help to hinder the flow. For example, the length of the extension can be within a range less than or equal to the distance between the leading edge of the blade and the pivot axis of the blade. As previously described, the extension can form a recess that can receive a portion of the blade, wherein the extension can define a limit to the angular rotation of the blade, and the blade can contact or not contact the extension. The extension of the flow body can overlap with a portion of the blade to form a labyrinth-type seal that hinders the flow and form a relatively continuous airfoil surface with the flow body. For example, used in combination, both of these aspects can help to properly guide the exhaust flow to the turbine impeller (e.g., reduce unwanted leakage, improve the transition from flow along the flow body to flow along the blade). For example, the extension of the flow body can improve the throat fluid dynamics of a throat partially defined between two blades, one of which can be partially covered by the extension.

[0141] For example, an overlap between the extension of the flow body and a portion of the blade may be defined relative to an expected exhaust gas flow direction. For example, the exhaust gas may flow over a surface of the flow body and transition to flow over a portion of the blade where the extension of the flow body overlies another portion of the blade, including a leading edge of the blade. In such an example, the blade may be pivotable about a pivot axis, and pivoting may move the leading edge of the blade away from the extension (see Fig.19 and Fig.24 ). In various examples, the extension of the flow body can direct the flow in such a way that the flow is directed to the airfoil surface of the blade rather than the leading edge of the blade. In various examples, the flow body includes an extension on one side of one of its opposing airfoil surfaces, noting that the flow body can include multiple extensions as an example.

[0142] For example, for the end of the extension, it can be vertical in the direction of the axis of rotation of the turbine wheel. For example, the end of the extension can be inclined, curved, etc. For example, consider a scalloped shape, where the extension is longer at the top and bottom and bends to a shorter length between the two, or, for example, the extension can be longer at a position between the bottom and the top. For example, the end of the extension can be customized (e.g., including the length relative to the height) to achieve a desired flow transition between the flow body and the blade and / or to achieve a desired flow obstruction, such as by forming a labyrinth-type arrangement.

[0143] exist Fig. 22In the example of FIG. 1 , the dashed line labeled s1 represents the dividing line between the height of the flow body 3000 at the extension 3070 (e.g., see height h2) and the height not at the extension 3070; note that the extension 3070 can have the same height as the flow body 3000 and / or a different height than the flow body 3000. In various examples, the height of the extension 3070 can be approximately equal to the height of the blade. For example, the height of the extension 3070 at the tip 3072 can be approximately equal to the height of the blade, or can be greater than or less than the blade height. Fig.21 As shown in the graph in , pressure can be tailored as flow varies by matching the height of the blade extension to the height of the blade; note that as explained with respect to flow body 4000, spacer 4090 or spacer portion can be tailored to achieve the desired pressure and flow. Fig. 22 In the example of FIG. 3000 , the dashed line can demarcate a spacer portion of the flow body 3000 , the height of which can be greater than the height of the blade. Such a spacer portion can be used to space apart components of the assembly, such as in the blade space.

[0144] Fig.23 Various views of the flow body 3000 are shown, which can be described relative to one or more coordinate systems. In the various views, the extension 3070 can be easily identified as an extension extending outward from the rear surface 3002 of the flow body 3000. In the top view, the extension 3070 is shown as having a height less than the height of the rear surface 3002, wherein the extension 3070 forms a portion of the airfoil surface 3020. For example, the airfoil surface 3020 can be defined from the surface 3004 to the tip 3072 using arcs, splines, etc., which optionally have a desired type of continuity. For example, consider parametric curve continuity (e.g., C0, C1, etc.).

[0145] For example, one or more surfaces may be described in terms of continuity, such as: G0 geometric continuity, where two curve segments join together; G1 geometric continuity, where the directions of the tangent vectors of the two segments are equal at the join point; C0 continuity, where the curves share the same point where they join; C1 continuity, where the tangent vectors of the two segments are equal in magnitude and direction (share the same parametric derivative); C2 continuity, where the curves share the same parametric second derivative at their join. Such descriptions may be used in relation to a flow body; a blade; a flow body and a blade; a flow body and a tongue; a flow body, a blade, and a tongue, etc.

[0146] Fig.24 An example of a portion of an assembly is shown, wherein the blade 1900 is shown at different pivot angles relative to the flow body 3000 including the extension 3070. Fig.24In the example of , a gap can be defined between the leading edge of the blade 1900 and the rear surface 3002 of the flow body 3000 and optionally between the leading edge of the blade and the extension 3070 of the flow body 3000, the latter of which can be a non-contact gap, for example, mechanically defined via a set of blade control mechanisms. As previously described, the blade can be rotated relative to the flow body through a range of angles, wherein the airfoil surface of the flow body and the airfoil surface of the blade can have a relatively "smooth" transition, for example, which can be defined using one or more continuity descriptions. This transition can be used to reduce losses (e.g., pressure losses, energy losses, etc.) and / or can be used to customize (adjust) pressure, velocity, flow rate, etc.

[0147] Fig.25 A portion of an assembly is shown having a set of blades 1900 - 1 and 1900 - 2 and a flow body 3000 including an extension 3070 . Fig.25 1 is viewed from the control side, where control links 892-1 and 892-2 are shown coupled to the post of blade 1900-1 and the post of blade 1900-2, respectively. Figure 5 As explained, such a control linkage may be part of a mechanism that causes the blades to rotate in unison about their respective axes that are aligned or defined by their respective blade posts. Fig.25 , blade 1900-1 is shown with its leading edge 1902 received in a recess of flow body 3000 defined by rear surface 3002 and extension 3070. As previously described, if there is contact between blade 1900-1 and extension 3070, the contact can limit the rotation beyond blade 1900-1. For example, because the blades can be connected to a common rotation mechanism, limiting the rotation of one blade can limit the rotation of all blades. For example, where an assembly includes multiple flow bodies, such as multiple flow bodies 3000, each flow body can limit the rotation of multiple blades. When there are multiple groups of blades in a component, there can be a one-to-one correspondence between each group of blades and each flow body, so that each group of blades is limited by the corresponding flow body.

[0148] Fig.26 Shown as Fig.25 A portion of the assembly shown has a set of blades, wherein the flow column axis is aligned with the axis of one of the control components. Fig.25 and Fig.26 As shown, the height of the extended portion of the flow body can be approximately equal to the blade height.

[0149] Fig. 27An example of flow body 4000 is shown in perspective view; note that one or more cutting planes may be used to generate a cross-sectional view. For example, one or more dimensions shown relative to flow body 3000 may be used to describe one or more features of flow body 4000. For example, extension 4070 of flow body 4000 may be defined using various dimensions that may define extension 3070 of flow body 3000.

[0150] like Fig. 27 As shown, flow body 4000 may include a concave rear surface 4002 and a front surface 4004, an upper surface 4006 and a lower surface 4008 (e.g., wherein the upper surface and the lower surface are defined relative to the perspective view), opposing airfoil surfaces 4010 and 4020, holes 4065, and spacers 4090, wherein spacers 4090 are at an end (e.g., a front surface end) of flow body 4000 including front surface 4004. Fig. 27 As shown in the example of the embodiment of the present invention, the spacer 4090 does not extend to the rear surface 4002. The spacer 4090 (e.g., the spacer portion) can, for example, provide an axial gap between the components of the assembly 1800. The various features, dimensions, etc. described with respect to the example flow body 3000 can be used to describe the various features, dimensions, etc. of the flow body 4000 (e.g., taking into account the shape, size, etc. of the extension).

[0151] exist Fig. 27 In the example of FIG. 4 , the flow body 4000 may be defined by an axial height h2, wherein the spacer 4090 may have a greater axial height h; note that the axial height h2 may match the blade height (eg, the blade height may be approximately equal to the extension height). Fig. 27 As shown in the example of FIG. 4 , the height of the flow body 4000 at the front surface 4004 is greater than the height at the rear surface 4002. For example, the height at the front surface 4004 can be selected to substantially match the height of the wall end. In such an example, the height of the flow body 4000 at the spacer 4090 can be approximately equal to the height at the tongue (e.g., the end of the tongue serves as the end of the wall).

[0152] For airfoil surfaces 4010 and 4020, one or more radii may be used to define one or both of them. For example, Fig.13 Radius R1 and radius R2 are shown, which may define airfoil surfaces 2010 and 2020, respectively. Similar parameters may be used to define airfoil surfaces 4010 and / or 4020. Back surface 4002 may be defined by radius R ve Partially defined, radius R ve It can be based on the arc of the leading edge of the blade. For example, the radius R ve Considered as the arc R swept by the pivoting motion of the leading edge of the blade le With the gap definition, the gap can be Rle percentage (e.g., from 0.1% to 25%). Fig. 27 In the example of , the spacer 4090 can be defined by a span s, which can be a single arc length, multiple arc lengths, a single arc length and a straight line length, etc.

[0153] like Fig. 27 As shown in the example of , the back surface 4002 may include a concave portion, wherein the concave portion may be partially defined by an arc. As previously described, such a back surface may be referred to as a concave back surface. For example, a concave test may be to draw a line between two points in an object, and if this line passes through the boundary of the object (e.g., the surface of the object), then the object may be defined as concave (e.g., including a concave portion), such as having a concave surface. As for the front surface 4004, it may be defined by a radius R se To limit the radius R se It may depend on the shape of the well end. For example, the front surface 4004 may be a convex front surface or a flat front surface. For example, if a line is drawn between the ends of the front surface 4004, if the line does not intersect the front surface 4004, the front surface 4004 is non-concave. As explained with respect to the rear surface 4002, if a line is drawn between the ends of the rear surface 4002 (e.g., which may include the ends at the tip 4072), the line is at least partially located outside the flow body 4000, so that the rear surface 4002 is a concave rear surface. For example, the rear surface 4002 may be defined as a concave shape via a concave arc shape, which effectively forms a concave (serrated) rear surface 4002 (e.g., recessed into the flow body 4000). For example, a convex arc shape may form a raised surface (e.g., a convex surface). For example, the flow body may include a rear surface, the rear surface including a recess, the recess may be disposed between the ends of the rear surface, wherein one or both ends may be rounded and / or chamfered. For example, the tip 4072 can be rounded. For the rounded end, it can be defined as a convex shape. For example, consider a concave portion of the rear surface disposed between the convex rounded ends of the rear surface, so that the rear surface can be defined as a concave rear surface (e.g., a rear surface with a concave portion that can accommodate the leading edge of the blade as the leading edge of the blade sweeps an arc in response to pivoting about the pivot axis).

[0154] For example, the extension 4070 of the flow body 4000 can have a desired length and can have a constant or variable height. Fig. 27In the example of FIG. 4 , the dashed line represents the dividing line between the height of the flow body 4000 at the extension 4070 and the height of the spacer 4090; note that the extension 4070 can have the same height as the flow body 4000 and / or a different height than the height of the flow body 4000. In various examples, the height of the extension 4070 can be approximately equal to the height of the blade. For example, the height of the extension 4070 at the tip 4072 can be approximately equal to the height of the blade, or can be greater than or less than the blade height. Fig.21 As shown in the graph of , the pressure can be adjusted (customized) as the flow rate changes, so that the height of the extension matches the height of the blade. As explained with respect to flow body 4000, spacer 4090 or spacer portion can be customized to achieve the desired pressure and flow. Fig. 27 In the example of FIG. 4 , the dashed line can demarcate a spacer portion of the flow body 4000, the height of which can be greater than the height of the blade. Such a spacer portion can be used to space apart components of an assembly, such as at the blade space.

[0155] Fig.28 Various views of an example of flow body 4000 are shown. In several views, hole 4087 is shown as well as hole 4065. For example, hole 4065 may be a through hole, while hole 4087 may be a through hole or a partial hole that does not extend through flow body 4000. Fig.28 As shown, surface 4007 can be the rear surface of spacer 4090, which can extend in a stepped manner from surface 4006. For example, surfaces 4006, 4007, and 4009 can define a step portion, wherein surfaces 4006 and 4009 can be substantially planar and parallel to surface 4007, thereby defining a transition therebetween. Fig.28 As shown, the flow body 4000 may include spacers 4090 having a specific shape and / or size, which can be used to space apart components and to adjust (customize) pressure, flow, etc.

[0156] exist Fig.28 In the example of FIG. 4000 , surface 4020 is shown as being curved, while surface 4010 is shown as being less curved or substantially straight. As previously described, surface 4020 can be a surface that can be positioned near the surface of the tongue so that flow adjacent to the tongue continues to flow smoothly when transitioning to being adjacent to flow body 4000. As previously described, extension 4070 can be an extension of surface 4020 and can overlap a portion of the airfoil surface of the blade so that the transition of flow from adjacent extension 4070 to adjacent exposed (non-overlapping) portions of the blade occurs relatively smoothly (e.g., efficiently).

[0157] Fig.29 A portion of an example assembly showing the positioning of a blade 1900 relative to a flow body 4000 is shown. Fig.29 In the example of FIG. 4 , the flow body 4000 includes a hole 4088 located between the hole 4065 and the rear surface 4002. The hole 4088 can be a through hole and extends to the opposite side of the flow body 4000 (for example, see Fig.28 For example, depending on the orientation in the assembly, the flow body may have multiple holes, which may include one or more through holes and / or one or more partial holes. These holes may provide support, positioning, etc. Fig.29 In the example of FIG. 4 , flow adjacent to the tongue will transition to flow adjacent to the surface 4020 of the flow body 4000, and then will transition to flow adjacent to the blade 1900. As previously described, a labyrinth-like passage can be formed by the extension 4070 and the blade 1900 such that flow is impeded as flow transitions from along the surface 4020 to along the blade 1900 (e.g., toward the trailing edge of the blade 1900). Such a labyrinth-like passage can impede flow therethrough even when the blade 1900 is not in a fully open position (e.g., a position where the leading edge 1902 of the blade 1900 would be closest to or in contact with the extension 4070). Similarly, as described above, in an assembly configured for contact, such contact can define a rotational limit of more than one blade such that a maximum opening angle of a set of blades is defined by the shape and / or position of the flow body.

[0158] Fig.30 Shows Fig.29 4089 is received in hole 4088. For example, such a component may be part of a blade control assembly, a positioning assembly, etc. For example, such a component can help ensure that the flow body 4000 remains in a specific position relative to the tongue of the wall and / or one or more other components of the assembly.

[0159] Fig.31 Shown as Fig.29 A cross-sectional view of a portion of a flow body 4000 is shown, wherein a post 4060 is received in a hole 4065 of the flow body 4000. As shown, the post 4060 can include a lower portion and an upper portion 4066 having an end 4068, which can include a connection feature (e.g., threads, etc.). For example, the opposite end of the post 4060 can also include a connection feature. As shown, the post can include a flange that is substantially aligned with a surface of the flow body 4000, wherein there can be an internal gap between a portion of the hole 4065 and a portion of the post 4060.

[0160] As previously described, a flow passage or throat may be defined between a blade and the flow body, wherein the blade is adjacent to the blade interacting with the flow body (eg, a blade having a leading edge may seat within an end recess of the flow body depending on the pivot angle of the blade).

[0161] Fig.32 A cutaway view of a portion of an example assembly is shown, wherein the blade 1900 and the flow body 4000 and the post 4060 are shown in cross section. As described above, the flow body 4000 may include holes 4065 and 4087 or 4088, wherein the hole 4065 may be used to mount and position the flow body 4000, and wherein the hole 4087 or 4088 may be used to position a component, which may be a control component of the blade or blade assembly.

[0162] Fig.33 A cross-sectional view of one example of an assembly is shown, which includes two instances of a vane 1900 and flow bodies 4000 - 1 and 4000 - 2 positioned adjacent two tongues 1863 and 1865 associated with two vortices 1867 and 1869 . Fig.33 The various features in the reference Fig. 9 The example components are described in detail. Fig. 9 As shown, the blade 1900 is in the open position; however, in Fig.33 In the embodiment of the present invention, the open position can be defined by one or both of the flow bodies 4000-1 and 4000-2. As previously described, the contact between the blades and the extension of the flow body can define the open position of a set of blades, and the open position can correspond to the maximum throat size between adjacent blades. For example, when the blades include two sets, each set can be adjusted independently of the other set. In such an example, one flow body can define one limit for one set and another flow body can define another limit for the other set.

[0163] As described above, the first vortex may be associated with a first number of cylinders and the second vortex may be associated with a second number of cylinders. For example, the two vortices may have different A / R values ​​(see Figure 3 ).For example, Fig.33 The vortices in a vortex can be customized so that the A / R value is different due to one or more factors that can be related to the flow rate of each vortex. For example, due to an exhaust gas recirculation (EGR) port being upstream of one vortex and not upstream of the other vortex, one vortex may experience less flow when EGR is engaged. For example, consider Figure 8 A cross-sectional view of a vortex passage in which a port may be located within an inlet portion of the vortex passage, the inlet portion of the vortex passage may be located at a portion leading to a position where A is defined (see, e.g. Figure 3 ). For example, refer to Figure 2A and Figure 2B , an EGR port can be provided for conduit 217 or conduit 219. As previously described, Figure 1 An example of a wastegate 135 is shown, which may be positioned upstream of the turbine. Figure 1An example of EGR downstream of the turbine housing outlet is shown, but as previously mentioned, EGR and / or other types of exhaust ports may be located upstream, which may affect a single or multiple turbines.

[0164] Fig.34 A cross-sectional view of an example of an assembly including a blade 1900 and two flow bodies 4000-1 and 4000-2, each flow body including an extension, is shown. Fig.34 In the embodiment, the blades 1900 are not in the fully open position, so the throat defined between adjacent blades has a size ratio of Fig.33 The size of the throat in the example is small. As for the most closed (closed most) position, it can be defined by contact between the blades (e.g., blade-to-blade contact) and / or by one or more other mechanisms.

[0165] As previously described, at different positions of the blade, the blade can be positioned relative to the flow body to form a labyrinth-like passage that impedes flow therethrough. As previously described, the extension of the flow body can provide one or more functions. For example, consider one or more restriction functions that limit the fully open position of the blade, a labyrinth function that impedes flow, a transition function that smoothly transitions from the tongue to the airflow surface of the blade (e.g., with a bypass to the leading edge of the blade), a spacing function that spaces two or more components of the assembly apart, etc. As previously described, other functions can be to support one or more components, for example, by receiving a peg or post in a hole, etc.

[0166] As previously described, under partial intake operating conditions, the alternating air loads on the variable vanes may be relatively high for a segmented VNT turbine housing. For example, a segmented VNT turbine assembly may include one or more flow bodies with extensions, which may be referred to as "cap flaps." For example, by using a cap flap on a fixed flow body at a tongue (e.g., a wall) that separates a turbine nozzle sector (nozzle segment) adjacent to the variable vanes, the cap flap may adjust the air force position distance from the swing vane pivot point, thereby reducing the air torque applied to the swing vanes.

[0167] For example, a portion of the swing blade profile can be covered with a bonnet (e.g., a flow body) to change the exhaust gas flow and pressure distribution so that the aerodynamic action position relative to the blade axis is offset (e.g., compared to a fixed flow body without an extension). For example, consider covering the leading edge of the blade by positioning the leading edge of the blade in a recess in the flow body. As previously discussed, the extension of the flow body may result in a reduction in the blade torque load. By reducing the blade torque load, the controllability of the swing blade can be improved and wear can be reduced. In various cases, the determined size of the actuator can be reduced when the blade torque load is reduced.

[0168] For example, the extension of the fixed flow body (e.g., the cap flap) can also form a labyrinth-like structure, which can help seal the gap between the fixed flow body (e.g., the tongue extension) and the swinging blade. In this way, the pressure separation between the active volute (vortex) and the non-active volute (vortex) can be improved; or the pressure separation between the more active volute and the less active volute can be improved.

[0169] The use of extensions on the flow body can be applied to segmented turbines with variable nozzle geometry (e.g. VNG or VNT) and can also be used for exhaust gas pressure pulses to reduce alternating air loads at partial admission and to reduce the phenomenon of synchronous flutter of the blade arms, thereby reducing high wear levels and the risk of potential fatigue failure at the joint between the blade shaft and the blade arm.

[0170] For example, positioning of the fixed flow body may be provided by openings (eg, holes, slots, etc.) in an insert ring of the nozzle assembly. As previously mentioned, one or more posts may be used to mount the fixed flow body.

[0171] By applying additional aerodynamic profiles on top of the base profile, the fixed flow body can be shape modified.Manufacturing may include one or more of machining, casting, forging or MIM.

[0172] As previously mentioned, the exhaust gas flow through the vane grid at the variable nozzle can be restricted by spacers that define the vane height channel. For example, the spacers can be adjacent to the swinging vanes and affect the turbine stage efficiency and the blade aerodynamic load by changing the airflow incidence angle (airflow angle of attack) at the leading edge of the vanes.

[0173] For example, one approach may use a pre-blade body (e.g., flow body) with a defined aerodynamic profile, which may include spacers and leave gaps to shield exhaust gas flow and heat transfer. Exhaust gas streamlines may be optimized with a specific pre-blade flow body profile to minimize negative effects on efficiency.

[0174] For example, a flow body including a spacer or spacer portion may be introduced into the nozzle assembly and secured to the ring assembly. For example, the aerodynamic profile may be optimized via computational fluid dynamics (CFD) to avoid undesirable losses and flow restrictions.

[0175] For example, the spacer (piece) can be shaped and sized in a manner that can reduce thermal effects. For example, consider a flow body with a spacer that can reduce high stress concentrations at a fixed flow body shaft radius (e.g., a column radius). For example, the flow body can be used to separate various functions and reduce thermal deformation loads transmitted to the flow body. For example, a reduction in surface contact area can be used to reduce heat transfer. As described above, the flow body can include a gap relative to the tongue (e.g., a separator wall, etc.). As previously mentioned, the blade can be a moving component to be controlled using an actuator, and in various cases, thermal effects can affect controllability, wear, etc. For example, the flow body can be shaped, sized, positioned, etc. to reduce thermal effects.

[0176] For example, the assembly can include the use of one or more spacers at one or more locations of the nozzle assembly while providing flexibility for dynamically loaded components, such as maintaining an acceptable balance between the rod and the rivet head. For example, the flow body can be a tongue extension, wherein the flow body can include a spacer portion. In such an example, the flow body may or may not include an extension at the rear end (e.g., rear surface). For example, a flow body with a spacer portion can provide separation of sections, wherein the flow body can be connected using a post and hole arrangement (e.g., pins and openings, etc.).

[0177] As mentioned previously, a multi-scroll arrangement can be used for a multi-cylinder engine, where each scroll corresponds to a plurality of cylinders of the multi-cylinder engine. For example, consider a six-cylinder internal combustion engine with two separate exhaust manifold branches, using exhaust gas recirculation (EGR) fed from only one branch, which can provide different airflow feeds to the turbine housing inlet. Since the blade incidence angles of the two sectors (sections) may be the same in the case of using a common variable diffuser vane grid for both volutes, the flow capacity of the turbine housing needs to be adjusted accordingly.

[0178] For example, an assembly may use different A / Rs and different sizes for each volute design (e.g., each vortex design), which are differently targeted to achieve approximately equal exhaust gas velocity angles at each volute outlet even for different exhaust gas mass flows traveling through each volute. For example, a multi-vortex assembly may include different vortex characteristics that may depend on factors such as EGR, which may affect the exhaust flow of the vortex. For example, a method may include performing a CFD simulation, optionally taking into account thermal effects, to provide a design for each turbine housing vortex. In such an example, the flow capacity of the vortex may be unequal.

[0179] A vortex is a generally spiral passage that may be defined by a housing, which may be referred to as a "vortex housing (volute)". A vortex may direct the exhaust gas flow from a single passage, such as a duct, to an annular passage, which may be referred to as an "annular nozzle". For example, a vortex may direct exhaust gas from a manifold to the periphery of a turbine wheel via an annular nozzle.

[0180] The vortex can be characterized by the area to radius ratio (A / R) (see e.g. Figure 3 ). A / R is defined as the inlet (or discharge in the case of a compressor housing) cross-sectional area divided by the radius from the turbine centerline to the centroid of that area. As the scroll spirals radially inward from its inlet to its annular nozzle, its cross-sectional flow area decreases, and both the area and radius change. The A / R can be selected based on a variety of factors to help ensure that when the internal combustion engine produces exhaust gases flowing through the turbine housing, it is able to propel the turbine wheel in an efficient manner. Selecting the right A / R can help optimize performance. For example, an A / R that is too small can hinder exhaust gases and loose power, especially in the upper region of the RPM power band; however, an A / R that is too large can make the turbine slower to respond to changes in exhaust gas flow.

[0181] For a twin scroll housing, generally, A / R may be defined as the sum of the inlet areas of the two scrolls divided by the radius at the inlet. For example, for a twin scroll housing, A / R may be defined on a per-scroll basis or on an overall basis.

[0182] As previously described, a method may include determining the A / R on a per-vortex basis, wherein the flow capacities of the vortices may be unequal. For example, a twin-vortex assembly may include two vortices, each with its own A / R, wherein the A / Rs are different and result in unequal flow capacities of the two vortices.

[0183] For example, an assembly 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 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 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 vanes defining a nozzle throat that directs exhaust gas from at least one exhaust gas passage to the turbine wheel space, wherein at least one of the first flow body and the second flow body includes a concave rear surface defined in part by a circular arc. In such an example, the first flow body and the second flow body may be fixed.

[0184] For example, the inner wall end may form a first tongue portion, wherein the first flow body is adjacent to the first tongue portion, and the outer wall end may form a second tongue portion, wherein the second flow body is adjacent to the second tongue portion.

[0185] For example, a circle can be centered on the pivot axis of one of a plurality of blades (e.g., a group of blades), wherein the flow body includes a concave rear surface defined in part by an arc. For example, when the blade pivots (e.g., rotates) about a pivot axis (e.g., a post, a hole, etc.), the leading edge of the blade can define an arc. In such an example, an arc (e.g., a radius of a circle) plus a gap distance (e.g., a radial gap distance) can be used to define the rear surface so that the blade can pivot about its pivot axis without the leading edge undesirably contacting the rear surface of the flow body. In such an example, overlap may occur between the rear surface of the flow body and the leading edge of the blade for multiple angles at which the blade pivots about its pivot axis. In such an example, the overlapping gap between the leading edge of the blade and the rear surface of the flow body can be small enough to hinder exhaust gas from flowing from one exhaust gas passage to another exhaust gas passage.

[0186] For example, the circle may be defined by a radius that is greater than the radius swept by the leading edge of one of the adjustable variable geometry nozzle vanes when transitioning from the closed position to the open position (eg, to account for a distance greater than a defined gap, etc.).

[0187] For example, the first flow body may include a front surface, a rear surface, and a first airfoil surface and a second airfoil surface extending between the front surface and the rear surface. In such an example, the front surface may be positioned close to the wall end, for example, with a small gap that can accommodate thermal effects, vibrations, etc. (e.g., to avoid contact with the wall end but hinder the exhaust flow between the front surface and the wall end). For 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 corresponding blade in 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 of the leading edge of a corresponding one of the adjustable variable geometry nozzle blades. In such an example, the overlapping pivot angle range may be greater than 50% of the total pivot angle range and less than 80% of the total pivot angle range. For example, the overlapping pivot angle range may be offset to the closed position of the total pivot angle range.

[0188] For example, the second airflow surface end may include a chamfered portion that defines a bypass gap relative to a leading edge of a corresponding one of the plurality of adjustable variable geometry nozzle vanes. In such an example, the first airflow surface end may define a gap relative to a leading edge of a corresponding one of the adjustable variable geometry nozzle vanes, wherein the bypass gap is greater than the gap. For example, the bypass gap may be provided to reduce pulsating pressure stress on an actuator for at least one set of adjustable variable geometry nozzle vanes.

[0189] For example, the first flow body and the second flow body may comprise respective heights approximately equal to the height of the blades.

[0190] For example, the number of adjustable variable geometry nozzle vanes of an assembly may be greater than 5. For example, the number of adjustable variable geometry nozzle vanes may be an odd number (eg, or an even number).

[0191] For example, a component may include: an exhaust gas turbine housing, the exhaust gas turbine housing including an inner wall and an outer wall, which define a first exhaust gas channel and a second exhaust gas channel leading 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, which is arranged adjacent to the inner wall end; a second flow body, which is arranged adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle blades, which define a nozzle throat that guides exhaust gas from at least one exhaust gas channel to the turbine wheel space.

[0192] In such an example, the first flow body and the second flow body can be fixed (i.e., not movable during operation). For example, the first flow body and / or the second flow body can move in response to a pressure exceeding a predetermined pressure (e.g., which may be caused by significant pulsation, thereby relieving stress on the blade and / or actuator).

[0193] For example, the inner wall end may form a first tongue and the first flow body may be adjacent to the first tongue, while the outer wall end may form a second tongue and the second flow body may be adjacent to the second tongue.

[0194] For example, the first flow body and / or the second flow body may include a trailing edge that is 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 arc, wherein the chamfer defines a gap relative to the leading edge of one of the blades. In such an example, the arc may define a gap relative to the leading edge of one of the blades. In such an example, the gap may be less than about 70% of the gap. In such an example, the gap may reduce pulsating pressure stresses on an actuator for at least one set of adjustable variable geometry nozzle blades.

[0195] For example, the gap may be within the operating range of one of the blades between a midpoint between the open and closed positions and the closed position.

[0196] For example, the first flow body and / or the second flow body may comprise a height approximately equal to the height of the blades.

[0197] For example, one or more continua may be used to define the first flow volume and / or the second flow volume relative to another component.

[0198] For example, the number of blades may be greater than about 5, and may be an odd or even number.

[0199] The assembly may include: an exhaust gas turbine housing, the exhaust gas turbine housing including an inner wall and an outer wall, which define a first exhaust gas passage and a second exhaust gas passage leading 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, which is arranged adjacent to the inner wall end; a second flow body, which is arranged adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle vanes, which define a nozzle throat, which guides exhaust gas from at least one passage in the exhaust gas passage to the turbine wheel space, wherein at least one of the first flow body and the second flow body includes a concave rear surface defined in part by an extension of an airfoil surface.

[0200] For example, the first flow body and the second flow body can be fixed. For example, the inner wall end can form a first tongue, wherein the first flow body is adjacent to the first tongue. For example, the outer wall end can form a second tongue, wherein the second flow body is adjacent to the second tongue.

[0201] For example, the extension may define a pocket that receives a leading edge of one of the adjustable variable geometry nozzle vanes.

[0202] For example, the extension may limit rotation of one of the adjustable variable geometry nozzle vanes in one of two rotational directions.

[0203] For example, at least one of the first flow body and the second flow body may include a spacer. In such an example, the spacer may be disposed at a front surface of at least one of the first flow body and the second flow body. For example, the spacer may be disposed at a front surface of at least one of the first flow body and the second flow body without extending to a column of the at least one of the first flow body and the second flow body.

[0204] For example, the first flow body may include a front surface, a concave rear surface, and a first airfoil surface and a second airfoil surface extending between the front surface and the concave rear surface, wherein, for example, one of the first airfoil surface and the second airfoil surface is partially formed by an extension. In such an example, one of the first airfoil surface and the second airfoil surface may include a varying height. For example, the varying height may include a smaller height at the extension.

[0205] For example, the extension may include a height approximately equal to the blade height, which may be constant along the length of the extension, or may be non-constant. For example, the maximum flow body height may exceed the blade height. For example, consider a flow body including a spacer (e.g., a spacer portion) that exceeds the blade height.

[0206] For example, the first exhaust gas passage and the second exhaust gas passage may have different A / R values. For example, the A / R values ​​may be different due to an exhaust gas recirculation port associated with a conduit to one of the first exhaust gas passage and the second exhaust gas passage. For example, the different A / R values ​​may be explained by the unequal exhaust flow capacity of the first exhaust gas passage and the second exhaust gas passage.

[0207] Although some examples of methods, devices, systems, arrangements, etc. have been shown in the drawings and described in the foregoing detailed description, it should be understood that the disclosed example embodiments are not restrictive but are capable of various rearrangements, modifications, and substitutions.

Claims

1. A component comprising: 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 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, the first flow body being 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 vanes defining a nozzle throat that directs exhaust gas from at least one of the exhaust gas passages to the turbine wheel space, Wherein at least one of the first flow body and the second flow body includes a concave rear surface.

2. The assembly according to claim 1, characterized in that The first fluid body and the second fluid body are stationary.

3. The assembly according to claim 1, characterized in that The inner wall end forms a first tongue portion, wherein the first flow body is adjacent to the first tongue portion.

4. The assembly according to claim 1, characterized in that The outer wall end forms a second tongue portion, wherein the second flow body is adjacent to the second tongue portion.

5. The assembly according to claim 1, characterized in that The extension defines a pocket that receives a leading edge of one of the adjustable variable geometry nozzle vanes.

6. The assembly according to claim 1, characterized in that The extension limits rotation of one of the adjustable variable geometry nozzle vanes in one of two rotational directions.

7. The assembly according to claim 1, characterized in that At least one of the first flow body and the second flow body includes a spacer.

8. The assembly according to claim 7, characterized in that The spacer is provided at a front surface of at least one of the first flow body and the second flow body.

9. The assembly according to claim 7, characterized in that The spacer is disposed at a front surface of at least one of the first and second flow bodies without extending to a column of the at least one of the first and second flow bodies.

10. The assembly according to claim 1, characterized in that The first flow body includes a front surface, the concave rear surface, and first and second airfoil surfaces extending between the front surface and the concave rear surface.

11. The assembly according to claim 10, characterized in that One of the first airfoil surface and the second airfoil surface is partially formed by the extension.

12. The assembly according to claim 11, characterized in that One of the first airfoil surface and the second airfoil surface comprises a varying height, optionally wherein the varying height comprises a smaller height at the extension.

13. The assembly according to claim 1, characterized in that The extension comprises a height approximately equal to the height of the blade.

14. The assembly according to claim 13, characterized in that The maximum flow body height exceeds the blade height.

15. The assembly according to claim 1, characterized in that The first exhaust gas passage and the second exhaust gas passage include different A / R values.

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