A turbocharger turbine assembly

Abstract

A turbine housing assembly can include a turbine housing defining an axis of rotation of a turbine wheel; and a cartridge receivable by the turbine housing, wherein the cartridge includes a nozzle wall member having an upper nozzle surface and a plate member having a lower nozzle surface, wherein the upper nozzle surface and the lower nozzle surface define a nozzle space, and a guide vane positioned in the nozzle space, wherein the guide vane is pivotable between a closed guide vane position of 0% open and a fully open guide vane position of 100% open, and wherein for guide vane positions of at least 50% open and less than 75% open, an axial dimension of the nozzle space increases with respect to a decreasing radius as measured from the axis of rotation.

Description

Technical Field

[0001] The topics discussed in this article generally relate to turbochargers used in internal combustion engines. Background Technology

[0002] An exhaust-driven turbocharger comprises a rotating assembly including a turbine impeller and a compressor impeller connected to each other by a shaft. The shaft is typically rotatably supported within a central housing by one or more bearings. During operation, exhaust gases from the internal combustion engine drive the turbocharger's turbine impeller, which in turn drives the compressor impeller to boost the intake air to the internal combustion engine. Attached Figure Description

[0003] When viewed in conjunction with the examples shown in the accompanying drawings, a more complete understanding of the various methods, devices, components, systems, arrangements, etc., and their equivalents described herein can be obtained by referring to the following detailed description, in which: Figure 1 It is a diagram of a turbocharger, an internal combustion engine, and a controller; Figure 2 This is a cross-sectional view of an example turbocharger; Figures 3A and 3B are perspective views of an example of a turbocharger barrel; Figure 4 These are cross-sectional plan views of the cylinder shown in Figures 3A and 3B; Figure 5 These are a series of views of a portion of the cylinder shown in Figures 3A and 3B; Figure 6 This is a perspective view of an example of a guide vane and an example of a nozzle surface; Figure 7 These are a series of views of a portion of the cylinder shown in Figures 3A and 3B, in which an increased gap exists between the guide vane and the nozzle surface; Figure 8 This is a schematic diagram of an example of a guide vane relative to a nozzle and turbine impeller blades; Figure 9 This is a schematic diagram of an example of a guide vane relative to a nozzle and turbine impeller blades; Figure 10 This is a cross-sectional view of a portion of an example of a component; Figure 11 This is a cross-sectional view of a component example and a graph of the material's coefficient of thermal expansion versus temperature. Figure 12 yes Figure 10 A cross-sectional view of a portion of an example component; Figure 13 yes Figure 10 A cross-sectional view of a portion of an example component; Figure 14 yes Figure 10 A cross-sectional view of an example component; Figure 15 Here is an example curve of the experimental data; and Figure 16 This is an example curve graph of the experimental data. Detailed Implementation

[0004] Below, we describe an example of a turbocharged engine system, followed by various examples of parts, components, methods, etc.

[0005] Turbochargers are frequently used to increase the output of internal combustion engines. (Reference) Figure 1 As an example, system 100 may include an internal combustion engine 110 and a turbocharger 120. Figure 1 As shown, system 100 may be part of vehicle 101, wherein system 100 is located in the engine compartment and connected to exhaust pipe 103, which directs exhaust gas to exhaust outlet 109, for example, located behind passenger compartment 105. Figure 1 In one example, a processing unit 107 may be provided to process exhaust gas (e.g., reduce emissions via catalytic conversion of molecules, etc.).

[0006] like Figure 1 As shown, the internal combustion engine 110 includes: an engine block 118 that houses one or more combustion chambers that operatively drive a shaft 112 (e.g., via a piston); an intake port 114 that provides a flow path for air flowing to the engine block 118; and an exhaust port 116 that provides a flow path for exhaust from the engine block 118.

[0007] The turbocharger 120 can be used to extract energy from the exhaust and provide energy to the intake air, which can then combine with fuel to form combustion gases. For example... Figure 1 As shown, the turbocharger 120 includes an air inlet 134, a shaft 122, a compressor housing assembly 124 for a compressor impeller 125, a turbine housing assembly 126 for a turbine impeller 127, another housing assembly 128, and an exhaust outlet 136. The housing assembly 128 may be referred to as the central housing assembly because it is disposed between the compressor housing assembly 124 and the turbine housing assembly 126.

[0008] exist Figure 1In this configuration, shaft 122 may be a shaft assembly comprising various components (e.g., consider a shaft and impeller assembly (SWA) to which turbine impeller 127 is welded). As an example, shaft 122 may be rotatably supported by a bearing system (e.g., journal bearings, rolling element bearings, etc.) disposed in housing assembly 128 (e.g., in holes defined by one or more bore walls), such that rotation of turbine impeller 127 causes rotation of compressor impeller 125 (e.g., as rotatably coupled by shaft 122). As an example, central housing rotating assembly (CHRA) may include compressor impeller 125, turbine impeller 127, shaft 122, housing assembly 128, and various other components (e.g., compressor side plates disposed at an axial position between compressor impeller 125 and housing assembly 128).

[0009] exist Figure 1 In the example, variable geometry component 129 is shown partially disposed between housing assembly 128 and housing assembly 126. Such variable geometry components may include guide vanes or other components to change the geometry of the passageway leading to the turbine impeller space in the turbine housing assembly 126. As an example, a compressor assembly with variable geometry may be provided.

[0010] exist Figure 1 In the example, the exhaust valve (or simply exhaust valve) 135 is positioned near the exhaust inlet of the turbine housing assembly 126. The exhaust valve 135 can be controlled to allow at least some exhaust gas from the exhaust port 116 to bypass the turbine impeller 127. Various exhaust valves, exhaust valve assemblies, etc., can be applied to conventional fixed-nozzle turbines, fixed-blade nozzle turbines, variable-nozzle turbines, twin-scroll turbochargers, etc. As an example, the exhaust valve can be an internal exhaust valve (e.g., at least partially inside the turbine housing). As an example, the exhaust valve can be an external exhaust valve (e.g., operatively connected to a conduit in fluid communication with the turbine housing).

[0011] exist Figure 1 The example also shows an exhaust gas recirculation (EGR) line 115, which may optionally be equipped with one or more valves 117, for example to allow exhaust gas to flow to a location upstream of the compressor impeller 125.

[0012] Figure 1Example arrangement 150 for exhaust flow to exhaust turbine housing assembly 152 and another example arrangement 170 for exhaust flow to exhaust turbine housing assembly 172 are also shown. In arrangement 150, cylinder head 154 includes internal passages 156 to guide exhaust from cylinders to turbine housing assembly 152, while in arrangement 170, manifold 176 provides mounting for turbine housing assembly 172, for example, without any separate, intermediate-length exhaust pipe. In example arrangements 150 and 170, turbine housing assemblies 152 and 172 can be configured for use with wastegates, variable geometry components, etc.

[0013] exist Figure 1 In this document, an example of controller 190 is shown including one or more processors 192, memory 194, and one or more interfaces 196. Such a controller may include circuitry of circuitry such as that of an engine control unit (ECU). As described herein, various methods or techniques may optionally be implemented, for example, by combining the controller with 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, sensors may send information to controller 190 via one or more interfaces 196. The control logic may rely on such information, and thus, controller 190 may output control signals to control engine operation. Controller 190 may be configured to control lubricant flow, temperature, variable geometry components (e.g., variable geometry compressors or turbines), exhaust valves (e.g., via actuators), electric motors, or one or more other components associated with the engine, turbocharger (or multiple turbochargers), etc. As an example, turbocharger 120 may include one or more actuators and / or one or more sensors 198, which may be coupled, for example, to one or more interfaces 196 of controller 190. As an example, the exhaust valve 135 may be controlled by a controller that includes an actuator responsive to electrical signals, pressure signals, etc. As an example, the actuator of the exhaust valve may be, for example, a mechanical actuator that can operate without electricity (e.g., consider a mechanical actuator configured to respond to a pressure signal provided via a conduit).

[0014] Figure 2 An example of a turbocharger assembly 200 is shown, which includes a shaft 220 supported by bearings 230 (e.g., journal bearings, bearing assemblies, such as rolling element bearings with outer races, etc.) disposed in a bore (e.g., a through-hole defined by one or more bore walls) of a housing 280 between a compressor assembly 240 defining a compressor side (left) and a turbine assembly 260 defining a turbine side (right). The compressor assembly 240 includes a compressor housing 242 that defines a volute 246 and houses a compressor impeller 244. Figure 2As shown, turbine assembly 260 includes turbine housing 262 that defines a volute 266 and houses turbine impeller 264. Turbine impeller 264 may be, for example, welded or otherwise attached to shaft 220 to form a shaft and impeller assembly (SWA), wherein the free end of shaft 220 allows attachment of compressor impeller 244.

[0015] As an example, an impeller, whether a turbine impeller or a compressor impeller, can include an inlet section and an outlet section, for example, partly defined by the inlet section radius (r). i ) and exit section radius (r e Characterization. As an example, a single blade may include an inlet section edge (e.g., leading edge) and an outlet section edge (e.g., trailing edge). The impeller may be partially defined by a trim value that characterizes the relationship between the inlet section and the outlet section.

[0016] For compressor impellers, the inlet section can be characterized by a "small" diameter; while for turbine impellers, the inlet section can be characterized by a "large" diameter. During operation, the inlet flow to the compressor impeller or turbine impeller occurs with respect to its inlet section, while the outlet flow from the compressor impeller or turbine impeller occurs with respect to its outlet section.

[0017] Regarding airflow, during operation of the turbocharger 200, as the compressor impeller 244 rotates, air can be guided from the compressor impeller 244 to the volute 246 via a diffuser portion partially defined by the compressor housing 242 and the compressor side plate 270, and drawn into the air passage 248 via inlet 249, both of which can be defined by the compressor housing 242. For example... Figure 2 As shown, during the operation of the turbocharger 200, the compressor impeller 244 is used to boost the air pressure, such that the air pressure in the volute 246 (P) cv The air pressure in channel 248 is greater than the air pressure (P). co The rotation of the compressor impeller 244 generates a negative pressure that is used to "draw" air into the compressor assembly 240 and guide such air to the volute 246 via the diffuser section. As an example, in the case of exhaust gas recirculation (EGR), ambient air can be mixed with exhaust gas (e.g., upstream and / or downstream of the compressor impeller 244).

[0018] exist Figure 2In the example, the axial locating pin 285 is received in an opening in the bearing 230, which may be a transverse bore of the bearing 230. As an example, a turbocharger may include one or more other types of axial locating mechanisms for limiting the axial movement of the bearing (e.g., and / or movement in one or more other directions). As an example, the locating pin may allow radial movement of the bearing, which may allow for the effective operation of one or more lubricant films disposed around the bearing surface.

[0019] exist Figure 2 In the example, shaft 220 includes a step (e.g., a shoulder) forming an axial annular surface. Figure 2 In such examples, the thrust collar 275 (e.g., a collar) includes a surface disposed against the axially annular surface of the shaft 220. In such examples, the lock nut 221 may include threads that mate with the threads of the end of the shaft 220, such that tightening the lock nut 221 relative to the shaft 220 loads the compressor impeller 244 and the thrust collar 275 against the axially annular surface of the shaft 220, which can tension the shaft 220 (e.g., from the step to its end). In such examples, the shaft 220, the compressor impeller 244, and the lock nut 221 can rotate as a unit (e.g., in response to exhaust from the driving turbine impeller 264). Figure 2 As shown in the example, the compressor side plate 270 may include a hole (e.g., an opening) where at least a portion of the thrust collar 275 is positioned at a location where the thrust collar 275 (and / or the compressor side plate 270) may include one or more recesses that may accommodate one or more sealing elements (e.g., O-rings, piston rings, etc.).

[0020] exist Figure 2 In the example, turbine assembly 260 includes a variable geometry assembly 250, which may be referred to as a "cylinder" (e.g., cylinder 250). This "cylinder" is positioned using a plate member 251, which may be referred to as a flange of cylinder 250 (e.g., optionally formed as a stepped annular disc or annular plate). Cylinder 250 is clamped between housing 280 and turbine housing 262, for example, using bolts 293-1 to 293-N and a heat shield 290 (e.g., optionally formed as a stepped annular disc). The heat shield 290 is disposed between cylinder 250 and housing 280 and may be resilient, as it can apply a biasing force. Figure 2 As shown in the example, the cylinder 250 includes a nozzle wall component 300 and a plate component 251. As an example, one or more mounting members or spacers 254 may be disposed between the nozzle wall component 300 and the plate component 251 (e.g., or an annular plate component), for example, to axially space the nozzle wall component 300 and the plate component 251 (e.g., to form a nozzle space).

[0021] As an example, a vane 400 may be positioned between a nozzle wall component 300 and a plate component 251, for example, where a control mechanism may cause the vane 400 to pivot. As an example, the vane 400 may include a blade post 420 that extends axially to be operatively coupled to a control mechanism, for example, for pivoting the vane 400 about a pivot axis defined by the blade post 420.

[0022] Regarding the exhaust flow, during operation of the turbocharger 200, high-pressure exhaust gas in the volute 266 passes through a passage in the cylinder 250 (e.g., one or more nozzles, one or more throats, etc.) to reach the turbine impeller 264, which is disposed in a turbine impeller space defined at least partially by the cylinder 250 and at least partially by the turbine housing 262. After passing through the turbine impeller space, the exhaust gas travels axially outward along a passage 268 defined by the wall of the turbine housing 262, which also defines an opening 269 (e.g., an exhaust outlet). As indicated, during operation of the turbocharger 200, the exhaust pressure (P) in the volute 266 is... tv The pressure is greater than the exhaust pressure (P) in channel 268. to ).

[0023] As an example, the exhaust pressure in turbine assembly 260 may depend on the position or orientation of guide vanes 400. For instance, the closing and / or opening of guide vanes 400 (e.g., a narrowing or widening throat) can affect the exhaust pressure at one or more locations.

[0024] Although Figure 2 The general direction of gravity (G, Earth's gravity) is shown, but the orientation of the turbocharger 200 can be an orientation in the engine compartment, which is suitable for operation given the details of lubricant feeding, flow, and discharge.

[0025] As an example, the turbine assembly of an exhaust turbocharger may include guide vanes as part of a variable geometry turbine (VGT) or a variable nozzle turbine (VNT). The guide vanes may be at least partially disposed within a cylinder, which is positioned between the turbine housing and the center housing of the turbocharger.

[0026] As an example, the cylinder may include nozzle wall components and plate components axially spaced apart by mounting members (e.g., spacers), wherein guide vanes are accommodated to control exhaust flow from the volute to the turbine impeller space. As an example, the guide vanes may include a trailing edge and a leading edge, wherein pressure-side airfoil components and suction-side airfoil components intersect at the trailing and leading edges. Such guide vanes may have a flat upper surface and a flat lower surface, wherein a gap exists between the flat upper surface and the nozzle wall component (e.g., between the lower flat surfaces of the annular portion of the nozzle wall component) and / or wherein a gap exists between the flat lower surface and the plate component (e.g., between the upper flat surfaces of the annular portion of the plate component).

[0027] As an example, each guide vane may include an axis about which the guide vane can pivot (e.g., a pivot axis). As an example, each guide vane may include a post (e.g., or axle) defining the pivot axis. As an example, the post may be integral with the guide vane (e.g., cast as a single piece of metal, alloy, etc.), or the post may be a separate component operatively coupled to the guide vane.

[0028] As an example, the movement of the guide vane (e.g., arcing) can be closer to or farther from the pivot axis. For instance, the trailing or leading edge can be positioned at a distance from the pivot axis such that, as the guide vane pivots, the leading and / or trailing edges sweep across the maximum arc of the guide vane to achieve the desired amount of pivoting. If the gap between the upper surface of the guide vane and the lower surface of the nozzle wall component decreases, the guide vane may jam (e.g., stick), where the risk can increase with the arc length as the interaction area can increase relative to the arc length. In such examples, deformation of the nozzle wall component can cause one or more guide vanes to jam during pivoting or even in a stationary position. Jamming (e.g., sticking) can lead to loss of control, stress on the control mechanism, wear, etc.

[0029] As an example, forces acting on the guide vanes and / or the posts of the guide vanes can cause one or more guide vanes to jam during pivoting or even when stationary. Jamming can lead to loss of control, stress on the control mechanism, wear, etc.

[0030] Regarding pressure differentials and temperatures in variable geometry turbine assemblies, as an example, exhaust gas in the volute can have pressures ranging from about 120 kPa to about 400 kPa and possible peak pressures up to about 650 kPa (absolute), as well as temperatures ranging from about 150 degrees Celsius to about 980 degrees Celsius; while at a location axially downstream of the turbine impeller, exhaust gas can have pressures and temperatures in a lower range. Exhaust temperatures in gasoline-powered internal combustion engines can exceed those in diesel-powered internal combustion engines. When variable geometry turbine assemblies are used with gasoline-powered internal combustion engines, the environment can be more severe in terms of temperature compared to diesel-powered internal combustion engines.

[0031] As an example, one or more components of a variable geometry turbine assembly (e.g., a VGT assembly or a variable nozzle turbine (VNT) assembly) may include at least a portion made of a material capable of withstanding the pressures and temperatures described above. For example, the material could be INCONEL 718 alloy (Specialty Materials Corporation, New Hartford, NY). Some other examples of materials include INCONEL 625, C263 (aluminum-titanium age-hardening nickel), René41 (nickel-based alloy), WASPALOY alloy (age-hardening austenitic nickel-based alloy, United Technologies Corporation, Hartford, CT), etc.

[0032] As an example, the cylinder may include guide vanes at least partially disposed between two components. As an example, at least a portion of the guide vanes may be made of a material such as HK30, a chromium-nickel-iron stainless steel alloy comprising approximately 30% chromium and 20% nickel, with the remainder being primarily iron (by mass percentage). As an example, at least a portion of the guide vanes may be made of an HK series stainless steel alloy comprising approximately 18-22% by mass nickel. Such alloys may be fully austenitic. As an example, one or more components of the cylinder may be made of a material such as PL23 alloy or 310SS alloy.

[0033] As an example, an exhaust variable geometry turbine assembly may include a plurality of pivotable guide vanes that at least partially define a throat within an exhaust nozzle, wherein each of the pivotable guide vanes includes a corresponding post.

[0034] Figures 3A and 3B show Figure 2 A perspective view of an example cylinder 250. In Figures 3A and 3B, the nozzle wall component 300 includes a lower surface of the nozzle upper surface 302, which may be an annular plate portion 310. As an example, the nozzle wall component 300 may include a cylindrical tube portion 350. When the nozzle wall component 300 includes a cylindrical tube portion 350, the overall shape of the nozzle wall component 300 may be referred to as cap-shaped. As shown, the annular plate portion 310 includes an outer perimeter defined by an outer surface 312. The outer surface 312 intersects with opposing annular surfaces 314 and 316, wherein the annular surface 316 includes a shroud portion 318 as a shroud for a turbine impeller space, wherein there is a gap between the shroud portion 318 and a suitable turbine impeller disposed in the turbine impeller space.

[0035] As shown, the nozzle wall component 300 includes a plurality of holes 320-1, 320-2, and 320-3 (e.g., spacer holes) that receive a plurality of spacers 254-1, 254-2, and 254-3, which axially space the nozzle wall component 300 relative to the plate component 251. As shown, the plate component 251 includes an upper surface that may be a nozzle lower surface 252, wherein the nozzle is defined by the nozzle upper surface 302 and the nozzle lower surface 252. Orifices 320-1, 320-2, and 320-3 are shown as cylindrical and extend between opposing surfaces 314 and 316 of nozzle wall component 300. Each orifice 320-1, 320-2, and 320-3 has a diameter and an axial length along its axis, which is located at the radius of an axis defined by the turbine impeller space (e.g., defined by the shroud portion 318), which may be referred to as the axis of rotation (e.g., the intended axis of rotation of the turbine impeller disposed in the turbine impeller space). In the examples of Figures 3A and 3B, cylinder 250 can be mounted in a turbocharger, which can then be mounted in the engine compartment of an internal combustion engine. Nozzle wall component 300 can be subjected to various conditions (e.g., force, temperature, pressure, etc.) that can affect nozzle wall component 300 (e.g., regarding integrity, shape, etc.).

[0036] Regarding the cylindrical tube portion 350, it includes an inner surface 352, an outer surface 354, and an end surface 356. The cylindrical tube portion 350 may be defined at least partially by an inner diameter, an outer diameter, and an axial length, such as that measured along the axis of rotation. In the illustrated example, the outer surface 354 includes one or more grooves 355 that may receive one or more sealing elements (e.g., sealing components such as or similar to piston rings). In the illustrated example, surfaces 314 and 354 intersect and form a shoulder with an angle of approximately 90 degrees. Regarding surfaces 316 and 352, they intersect at corresponding ends of the shroud portion 318. For example, surface 316 may be substantially flat, intersecting the profiled shroud portion 318 and then intersecting surface 352, which extends axially to the end surface 356. As shown, the end surface 356 is an annular surface that intersects with the inner surface 352 and the outer surface 354.

[0037] The perspective view shows one or more sealing rings 261, multiple spacers 254-1, 254-2 and 254-3 disposed in one or more recesses 355 of the nozzle wall component 300, multiple guide vanes 400 (e.g., 400-1 to 400-N) and corresponding blade posts 420-1 to 420-N, multiple guide vane control arms 256, coordinating ring 257, multiple pins 258-1, 258-2 and 258-3, and multiple guides 259-1, 259-2 and 259-3.

[0038] In the examples of Figures 3A and 3B, the coordinating ring 257 is rotatable about a central axis (e.g., substantially aligned with the axis of rotation of the turbine impeller) to allow multiple guide vane control arms 256 to rotate about the respective column axes of the individual blade columns 420 of the multiple guide vanes 400. Multiple pins 258-1, 258-2, and 258-3, and multiple guides 259-1, 259-2, and 259-3 help align the coordinating ring 257 relative to the other components of the cylinder 250.

[0039] In the examples of Figures 3A and 3B, one or more ends of spacers 254-1, 254-2, and 254-3 may be fixed (e.g., riveted, capped, etc.). For example, the ends of the spacers may be flattened to a radius larger than the opening radius of the hole through which the spacers extend, preventing axial movement of the spacers into the hole. As shown, each of spacers 254-1, 254-2, and 254-3 includes a nozzle portion having a radius and / or diameter larger than the corresponding end of the opposite ends received by the respective spacer holes of the nozzle wall member 300 and the plate member 251. For example, the spacers may be defined by one or more radii and / or one or more diameters and one or more axial dimensions (such as the axial dimension of the nozzle portion).

[0040] The nozzle portion of each of spacers 254-1, 254-2, and 254-3 may include opposing shoulders, one of which abuts the nozzle wall component 300 and the other abuts the plate component 251 to define a nozzle axial dimension that may be slightly larger than the guide vane axial dimension to allow the guide vane to pivot in the nozzle, wherein the gap may be defined at least in part based on one or more thermal considerations (e.g., thermal expansion, thermal contraction, etc.).

[0041] In the examples of Figures 3A and 3B, the cylinder 250 can be fastened into a cylinder unit via the riveted ends of spacers 254-1, 254-2, and 254-3, which fix the axial distance between the nozzle wall component 300 and the plate component 251 at a given temperature (e.g., the ambient temperature during assembly). This riveting process can introduce a certain amount of stress at the channels (e.g., holes) through which the spacers 254-1, 254-2, and 254-3 pass through the nozzle wall component 300 and / or the plate component 251.

[0042] Figure 4 A plan view of a portion of a cylinder 250 including multiple guide vanes 400 is shown. The guide vanes 400 are... Figure 4The diagram uses solid and dashed lines, where solid lines indicate the open position of guide vanes 400 and dashed lines indicate the closed position. Arrows with hollow heads are shown to roughly illustrate the direction of exhaust flow between adjacent pairs of guide vanes 400 when in the open position. In the closed position, guide vanes 400 act as obstructions to the exhaust flow, allowing for higher pressure in the radially outward region of guide vanes 400 compared to the radially inward region. In such examples, the gaps between guide vanes 400 and the upper nozzle surface 302 and lower nozzle surface 252 are minimal, minimizing bypass of exhaust within these gaps. Exhaust flow that does occur can be termed exhaust leakage. However, as explained, the gaps are sufficient to reduce the risk of jamming, where guide vanes jamming against nozzle surfaces 302 and 252 would disrupt controllability. In cases where the risk of jamming exists, the actuator may require more power, which could mean larger size, higher cost, increased energy consumption, etc. Therefore, the design of cylinder 250 typically involves balancing the risk of jamming (e.g., sticking) in the closed position with venting leakage.

[0043] exist Figure 4 In the example, in the open position, the trailing edge of the guide vane 400 may define a circle as shown by the thick dashed line, and in the closed position, the trailing edge of the guide vane 400 may define another circle, which may be approximately the same as the circle defining the pivot axis of the guide vane 400 (e.g., the blade post 420). Therefore, as the guide vane 400 moves from the closed position to the open position, a circle with a decreasing radius (e.g., diameter) may be defined by the trailing edge of the guide vane 400. Furthermore, as shown, the leading edge of the guide vane 400 may define a circle with an increasing radius (e.g., diameter).

[0044] As an example, the angular range of a set of guide vanes can be defined using a closed position and a fully open position. In such an example, the closed position can be defined as one that restricts pivoting due to one or more reasons. For example, one reason for restricting pivoting is guide vane contact between adjacent guide vanes (e.g., guide vane-to-guide vane contact). Another reason might be due to one or more stops built into the actuator or other control linkage. Regarding the fully open position, one or more references can be used to define it. For example, the outer radius of the turbine impeller can be used, where, in the fully open position, the trailing edge of a set of guide vanes is in the range of approximately 3% to approximately 10% of the outer radius of the turbine impeller. Within such a range, the trailing edge can be spaced sufficiently from the turbine impeller blades such that the leading edge of the blades does not contact the trailing edge of the guide vane when the set of guide vanes is in the fully open position. For the purpose of appropriate performance, such a distance can be adjusted to be not too large, and to avoid contact between the turbine impeller and the guide vanes (e.g., given vibration, thrust on the turbine impeller, thermal effects, etc.), such a distance can be adjusted to be not too small. The angle range can have a minimum angle and a maximum angle, where the intermediate angle can be defined as a 50% opening angle. As explained, one or more features of a set of guide vanes (e.g., leading and / or trailing edges) can be used to define one or more radii (e.g., one or more diameters), which can be used to define one or more features of the component.

[0045] Figure 5 Plan and sectional views of a portion of cylinder 250 are shown, indicating various angles, including a 0-degree closed angle with respect to the corresponding circle, a 41-degree open angle with respect to the corresponding circle, a 68-degree angle with respect to the corresponding circle, and an 82-degree fully open angle with respect to the corresponding circle.

[0046] like Figure 5 As shown in the example, the guide vane 400 includes a trailing edge 401 and a leading edge 402, wherein the pressure-side airfoil and the suction-side airfoil intersect at the trailing edge 401 and the leading edge 402. As shown, the guide vane 400 may have a flat upper surface 403 and a flat lower surface 405, wherein there is a gap between the flat upper surface 403 and the upper nozzle surface 302 of the wall member 300, and / or there is a gap between the flat lower surface 405 and the lower nozzle surface 252 of the plate member 251.

[0047] exist Figure 5In the example, the trailing edge 401 or the leading edge 402 can be positioned at a distance from the pivot axis 407 of the guide vane 400 such that, as the guide vane 400 pivots, the leading edge 402 and / or the trailing edge 401 sweep across the maximum arc of the guide vane 400 to achieve the desired amount of pivoting. As explained, if the gap between the upper surface 403 of the guide vane 400 and the upper nozzle surface 302 decreases, the guide vane 400 may jam (e.g., stick), where the risk can increase with the interaction area relative to the arc length. In such examples, deformation of the nozzle wall component 300 can cause the guide vane 400 to jam during pivoting or even in a stationary position. Jamming (e.g., sticking) can lead to loss of control, stress on the control mechanism, wear, etc.

[0048] As an example, a turbine assembly may include a non-uniform or variable clearance between the upper surface of the guide vane and the upper nozzle surface. For example, the clearance may increase relative to a decrease in the radius of the upper nozzle surface. In such examples, the clearance may be small enough in the closed position of the guide vane to reduce exhaust leakage, while in the open position of the guide vane, the clearance may be larger to reduce jamming and / or reduce resistance to exhaust flow. For example, the clearance may be increased for a guide vane opening position greater than or equal to 50% of the fully open position. In such examples, the guide vane opening position with increased clearance can be defined using angles, diameters, etc., for example, as per [reference to...]. Figure 4 The example illustrates this.

[0049] Figure 6 A perspective view of the guide vane 400 is shown, in which the pressure-side airflow surface 404 and the suction-side airflow surface 408 are indicated by corresponding labels. Furthermore, the outline of the upper nozzle surface 302 is shown existing above the guide vane 400, as would be present in an assembled turbine assembly, wherein the nozzle surface 302 may be a relatively constant region intersecting with a first transition point 304, which intersects with a variable region 306, which intersects with a second transition point 307, which intersects with a rise region 308.

[0050] exist Figure 6 The examples show various dimensions, including the guide vane height z. v Nozzle height z n (For example, between nozzle surfaces 302 and 252), gap z c (For example, between surfaces 403 and 302), variable gap z c (r) and the enlarged gap In such an example, the first transition point 304 may correspond to the 50% opening position of the trailing edge 401 of the guide vane 400.

[0051] As an example, a guide vane can be defined in part by one or more airfoil items (e.g., dimensions, etc.). For instance, guide vane 400 can be defined in part by one or more of the following: the mid-curvature, chord length, thickness, upper radii, lower radii, pivot axis, etc., of an intermediate surface between surfaces 404 and 408. Figure 6 In the example, the guide vane 400 is shown as relatively slender, with a thickness less than the chord length. For example... Figure 5 As shown, the guide vane 400 can have its pivot axis 407 located approximately midway between the leading edge 402 and the trailing edge 401; note that the length of the guide vane 400 from the pivot axis 407 to the trailing edge 401 is greater than the length from the pivot axis 407 to the leading edge 402, such that if the guide vane 400 rotates 360 degrees about its pivot axis 407 (e.g., as a single guide vane without interference from other guide vanes), the leading edge 402 will form a circle centered on the pivot axis 407 with a radius smaller than the circle centered on the pivot axis 407 of the trailing edge 401.

[0052] Figure 7 Show Figure 5 The example plan and sectional views, however, show different gap profiles between the guide vane 400 and the upper nozzle surface 302, as indicated by at least a first transition point 304, a variable surface region 306, and a second transition point 307, which can transition to a shroud profile 308, which can transition to a relatively vertical surface 309. Figure 5 Compared to the example, due to the increased clearance area, the guide vane 400 has a reduced risk of jamming at an opening angle greater than approximately 41 degrees (which may be a half-open angle) compared to an 82-degree full opening angle (e.g., fully open).

[0053] Figure 8 A schematic diagram showing the guide vane 400 and the turbine impeller blade 600 is provided. As shown, the guide vane height z can be used... v Define the increased gap area. For example, consider the nozzle height z. n It can increase the nozzle height z to less than 50% of the open guide vane position. n 1.05 to 1.5 times.

[0054] As explained, the blade 600 may have a leading edge, which may be located at a radius r from the axis of rotation z of the impeller having the blade 600. w At this location, and the trailing edge of the guide vane 400 can be located at a radius r. te At that location, the radius r teThis depends on the angle of the guide vane 400. As the guide vane 400 becomes more open, its trailing edge becomes closer to the leading edge of the blade 600. As an example, the blade could be a radial blade of a radial turbine impeller or a mixed-flow blade of a mixed-flow turbine impeller. Figure 8 In the example, blade 600 can be a runoff blade because the leading edge of blade 600 is at a constant radius r along its height. w .

[0055] exist Figure 8 In the example, the nozzle height z n Considered to be approximately 9.07 mm, where the increased nozzle height z th (For example, throat height) is approximately 11 mm. In such examples, the radius of the 50% open position can be approximately 46.5 mm from the turbine impeller's axis of rotation, and the radius of the 60% open position can be approximately 42.4 mm from the turbine impeller's axis of rotation. For example, the increase can be approximately 0.5 mm to 2 mm or more. In such examples, the exhaust flow can exhibit improved development before passing the leading edge of the turbine impeller blades.

[0056] As an example, a spacer can define the nozzle height. For instance, consider a spacer that defines the nozzle height as 9.07 mm, where the gap between the upper surface of the guide vane and the upper surface of the nozzle is approximately 0.15 mm. In such examples, the gap can be increased to at least 0.5 mm. For example, consider an increased gap of approximately 2 mm (e.g., from 9.07 mm to 11 mm in terms of nozzle height). As an example, the increased gap can provide increased flow bypass passage, defined by a percentage of the guide vane height (e.g., 5% to 30% or optionally greater).

[0057] like Figure 8 As shown in the example, the increase can be inclined, stepped, etc. For example, the inclined area can be provided with one or more slopes and / or the stepped area can be provided with steps of approximately 90°. As explained, one or more combinations of shapes can be used to increase the gap.

[0058] Figure 9 A schematic diagram of the guide vane 400 and an example of the turbine impeller blade 600 are shown. Figure 9 In the example, blade 600 can be a mixed-flow blade because the leading edge of blade 600 is not at a constant radius, making the radius r w The height can vary along the leading edge of the blade at 600° (e.g., to define the cone angle). As an example, Figure 8 The methods and / or Figure 9 The method described can be used with either radial flow turbine impellers or mixed flow turbine impellers.

[0059] like Figure 9 As shown in the example, the guide vane height z can be used. v This defines the increased gap area. For example, consider the nozzle height z. n It can increase the nozzle height z to less than 50% of the open guide vane position. n 1.05 to 1.5 times. In Figure 9 In the example, the increase in gap may be due to the shape of the lower nozzle surface (e.g., surface 252, etc.) and / or the upper nozzle surface (e.g., surface 302, etc.).

[0060] Whether increasing the gap on the upper nozzle surface and / or the lower nozzle surface, the gap can be increased using one or more of the shape combinations.

[0061] Figure 10 A cross-sectional view of a portion of assembly 1000 is shown, which includes guide vanes 400, components 700 and 760, and a turbine housing 800. As shown, component 700 and turbine housing 800 can be assembled using one or more sealing members 900 (e.g., piston rings, etc.). As an example, component 700 can float and be downwardly biased by pressure during operation, or it can be biased by spring force, or it can be fitted to one or more spacers.

[0062] Figure 10 An illustration is also shown where the guide vane 400 is shown by dashed lines because its position depends on the pivot angle. In the example in the illustration, the guide vane can be in a fully open position (e.g., maximum open pivot angle). As shown, the turbine impeller 264 can be composed of a turbine impeller radius r. w Defined, and the trailing edge of the guide vane 400 can be determined by the trailing edge radius r te Defined, as in the fully open position. As explained, in the fully open position, the radius r of the trailing edge of the guide vane 400. te It can be compared to the radius r of the turbine impeller w (For example, the maximum outer radius) is approximately 3% to approximately 10%. As explained, when the guide vane 400 is in the closed position (e.g., guide vane in contact with guide vane, etc.), the trailing edge r te The radius will be larger than the radius in the fully open position. The range of guide vane angles from closed to fully open can be defined by such a radius, where the open position (such as 50%) can be defined as the middle between the closed and fully open positions.

[0063] exist Figure 10In the example, component 700 may be a substantially annular component that defines a clearance relative to the upper surface 403 of guide vane 400. For example, consider the upper nozzle surface 702 intersecting with a first transition point 704, which intersects with a variable surface region 706, which intersects with a second transition point 707. As shown, the second transition point 707 may be located at the innermost end of component 700, where one or more sealing members 900 provide a seal with respect to exhaust movement from volute 866 to nozzle or vice versa.

[0064] exist Figure 10 In the example, the turbine housing 800 includes a lower surface 802 that transitions into a shroud surface 808. The turbine housing 800 may also include various annular recess features that can accommodate components 700. For example, consider cylindrical surfaces 812 and 816, which can be separated by an annular groove 814 that can provide for positioning and stabilizing one or more sealing members 900. As shown, the cylindrical surface 816 may extend to an axial face 820, which can then transition into a surface 826 that partially defines a volute 866.

[0065] exist Figure 10 In the example, a region with a constant gap of approximately 0.12 mm can be increased to a region with a gap of at least approximately 0.175 mm via a ramp (e.g., a cone). Figure 10 In this example, the gap between the upper surface 403 of the guide vane 400 and the surface 802 of the turbine housing 800 can be approximately 0.8 mm. In such examples, the increased gap can partially extend across the component 700 and partially across the turbine housing 800. In such examples, the exhaust flow can utilize the additional space (e.g., increased nozzle space, etc.) to extend and / or develop before encountering the turbine impeller. In such methods, a certain amount of efficiency can be achieved through the increased space.

[0066] exist Figure 10 In the example, component 760 may include a lower nozzle surface 762 intersecting a first transition point 764, which intersects a variable surface region 766, which intersects a second transition point 767. As shown, the second transition point 767 may be at the innermost end of component 760. As shown, components 700 and 760 may be shaped differently, although providing increased clearance for a range of guide vane open positions. As an example, component 1000 may include features with respect to the upper nozzle surface and / or features with respect to the lower nozzle surface to provide increased clearance for one or more ranges of guide vane open positions.

[0067] As an example, the cylinder and turbine housing can be shaped such that no contact occurs between the guide vane and the turbine housing when the cylinder is installed in the turbine housing. For example, the edges may contact each other before contact can occur between the guide vane and the turbine housing. In such examples, the risk of the upper surface 403 of the guide vane 400 contacting the surface 802 of the turbine housing 800 can be reduced. As an example, the axial height of the component 700 may allow the component 700 to contact the surface 820 before contact can occur between the surface 802 and the upper surface 403 of the guide vane 400.

[0068] As explained, the cylinder is axially movable within the turbocharger via one or more spring-like mechanisms. Where the shroud surface is positioned on the turbine housing rather than on a component such as component 700, the clearance between the turbine impeller and the shroud surface may be more defined during operation.

[0069] In example component 1000, when compared with, for example Figure 2 Compared to component 300, component 700 can be smaller, which can provide less thermal effect, stress, etc. Furthermore, in assembly 1000, the shroud profile for the turbine impeller is on the turbine housing, not on component 700. Additionally, by making the inner end of component 700 thinner than its outer end, some thermal effects (e.g., considering thermal expansion and contraction due to volume) can be reduced.

[0070] Figure 11 An approximate cross-sectional view of a portion of component 1102 during a temperature transient is shown, wherein component 1102 includes a plate component 251, a spacer 254 and an annular plate portion 310 of a nozzle wall component 300, along with a curve 1104 of the coefficient of thermal expansion (CTE) with respect to temperature.

[0071] Curve 1104 roughly illustrates the guide vane material region and the nozzle wall material region. For example, the guide vane may be made of a material with a higher CTE than the nozzle wall (e.g., the upper and / or lower portion). Since the guide vane is typically made of a material with a higher CTE and is smaller (smaller in volume) than the nozzle wall, the guide vane will respond to temperature changes faster than the nozzle wall (e.g., plate component 251, annular plate portion 310, etc.). Due to the smaller mass of the guide vane, it has a smaller heat capacity, and therefore heats and cools faster than the nozzle wall, even if the materials used have the same CTE. Therefore, the gap can be modified, including reduced. For example, consider a cold gap of approximately 0.16 mm (e.g., at ambient temperature) and a hot gap of approximately 0.06 mm. During transient operation where the guide vane can move, a reduced gap can lead to control problems (e.g., sticking, jamming, etc.); however, in a thermally stable state, the gap can be appropriately designed as if the component were in a stable temperature distribution. As an example, as explained, one or more increased clearances can be provided to prevent dynamic operation under dynamic thermal conditions from causing control problems (e.g., sticking, jamming, etc.). During dynamic thermal conditions, temperature transients can be non-uniformly defined around the axis of rotation, causing individual guide vanes in a set of guide vanes to experience different temperatures. Given such spatially non-uniform transient conditions, one or more guide vanes may be more likely to stick (e.g., jam) than one or more other guide vanes, which can also lead to uneven (e.g., non-uniform) wear in turbine components. As explained, by providing one or more increased clearances, the risk of one or more individual guide vanes sticking (e.g., jamming) can be reduced; note that control problems may arise from the sticking (e.g., jamming) of a single guide vane in a set of guide vanes.

[0072] As shown in part of component 1102, the nozzle space defined by components 251 and 300 can become V-shaped due to the thermal gradient between the outer and inner radii of components 251 and 300, the spacer 254 which creates some limitation, and the support from a spring-like structure from the heat shield 290 pressed at and / or near the inner radius of component 251. Figure 11 The example shows the axial height z at radius "b". rb z at radius "a" ra During temperature transients, z rb Greater than z raThis results in a V-shape in the cross-section. Given the tendency for V-shape formation under conditions such as high temperatures, utilizing one or more components that increase the gap between the nozzle wall and the guide vanes can reduce the risk of guide vane sticking (e.g., jamming). For example, increasing the gap between the guide vanes and one or more nozzle surfaces (e.g., greater than at or near the outer periphery) near the inner periphery of one or more components can help restore the CTE-related gaps consumed during transient heating and cooling, as well as gaps that may be consumed by one or more other phenomena (e.g., coking). Therefore, by providing gaps, performance (e.g., controllability, lifespan, etc.) can be improved.

[0073] Examples of materials used for constructing guide vanes include NI-RESIST (high-nickel alloy cast iron), NITRONIC 60 (Alloy 218, e.g., Cr 17, Mn 8, Ni 8.5, Si 4, N 0.13, C 0.10, Fe balance), 310 stainless steel (SS), etc. Examples of materials used for constructing components defining the nozzle space include INCONEL 718, SiMoCr, etc. As described above, components defining the nozzle space (e.g., components forming the nozzle wall) may be formed with one or more features (e.g., steps, ramps, etc.) to provide an increased clearance relative to the set of guide vanes when the set of guide vanes is in the open position (e.g., 50% open or greater, etc.).

[0074] Figure 12 Show Figure 10 Another cross-sectional view of example component 1000, without guide vanes 400 and without one or more sealing members 900. (See example...) Figure 12 As shown, component 700 may include an upper nozzle surface 702 as a substantially horizontal portion defining a constant nozzle height, wherein surface 702 intersects a first transition point 704 that intersects a variable surface region 706 that increases the nozzle height with respect to a decreasing radius, the decreasing radius intersects a second transition point 707 that intersects a cylindrical surface 708 that may define the inner periphery of component 700. As shown, turbine housing 800 may include surface 802 positioned at a greater axial height than the second transition point 707. Turbine housing 800 may also include a surface 809 intersecting the shroud surface 808, wherein this surface may define the minimum diameter of turbine housing 800.

[0075] As an example, component 700 can be formed via one or more processes to provide variations in nozzle height. For example, consider machining, where such machining can grind the beveled area into a normal non-beveled surface (e.g., see surface 702). As an example, one or more bevels can be given to form one or more angles, transitions, etc.

[0076] Figure 13 Show Figure 10 Another sectional view of example component 1000. Figure 13 In the example, the guide vane 400, particularly in relation to components 700 and 760 and housing 800, can be seen, with a significant portion of the guide vane 400 having increased clearance in its open position, as shown in the figure. As explained, this approach can reduce the risk of jamming and / or decrease resistance to exhaust flow when the guide vane is in an open position of 50% or more.

[0077] Figure 14 A cross-sectional view of an exemplary assembly 1000 having a turbine housing 800 and components 700 is shown. As an example, Figure 2 One or more features of the cylinder 250 of 3A and 3B may be included in such components.

[0078] As an example, a turbine assembly with an increased guide vane-to-nozzle clearance of 50% or more for the guide vane open position can provide an expansion flow path to reduce the impact intensity at high pressure ratios (PR), can provide performance map width extension to increase flow without changing the guide vane height, can maintain the same performance when the guide vane position is less than 50% closed, can reduce guide vane aerodynamic torque (e.g., by providing a guide vane height smaller than the endwall height), and can reduce the risk of guide vane / nozzle wall friction due to thermal expansion, thermal deformation, or combustion residue deposits.

[0079] Figure 15 Example curves 1500 show test results for two different components at a given pressure ratio (PR), where one component includes an increased clearance (e.g., an enlarged gap) for at least 50% of the guide vane opening position, and the other component includes a constant clearance. As shown, the component with the increased clearance can provide higher efficiency at a higher corrected mass flow rate (kg / s) compared to the component with constant clearance. Furthermore, at lower corrected mass flow rates (e.g., less than about 0.06 kg / s), the two components exhibit the same or similar performance. In such examples, the difference can be defined with respect to the maximum efficiency (e.g., the corrected mass flow rate corresponding to the peak efficiency at a particular guide vane position).

[0080] Figure 16 Example curves 1600 show test results for two different components at a given pressure ratio (PR), where one component includes an increased clearance (e.g., an increased gap) of at least 50% of the guide vane opening position, and the other component includes a constant clearance. As shown, the component with the increased clearance can provide higher efficiency at a higher corrected mass flow rate (kg / s) compared to the component with constant clearance. Furthermore, at lower corrected mass flow rates (e.g., less than about 0.135 g / s), both components exhibit the same or similar performance. In such examples, the difference can be defined relative to the maximum efficiency (e.g., the corrected mass flow rate corresponding to the peak efficiency at a particular guide vane position).

[0081] exist Figure 16 In the examples, the increased clearance demonstrates improved efficiency after the guide vanes are in a 50% open position. In such examples, high-end performance is improved, while low-end performance shows no difference. High-cycle fatigue (HCF) loads (e.g., early flow expansion before the impeller leading edge) can be reduced in such examples. As an example, in the fully open position of the guide vanes, an annular clearance can exist between the guide vane trailing edge and the turbine impeller, where such an annular clearance can be defined by the radius of the turbine impeller. For example, such a clearance can be between approximately 3% and 10% of the turbine impeller radius.

[0082] Given the data in curves 1500 and 1600, turbocharger turbine assemblies can be manufactured with guide vanes having a smaller guide vane height while still achieving suitable performance at high mass flow rates. By using guide vanes with a smaller guide vane height, guide vane loads can be reduced, which can provide a reduction in actuation force and thus allow for smaller actuators (e.g., actuators with a smaller maximum force). As explained, the reduced risk of sticking (e.g., jamming) can also provide a reduction in actuation force and thus allow for smaller actuators (e.g., actuators with a smaller maximum force).

[0083] As an example, one approach could include determining the guide vane position to achieve maximum efficiency with respect to the corrected mass flow rate. In such an example, the guide vane position could be translated into a radius or diameter with respect to the trailing edge of the guide vane. In such an example, one or more components of the cylinder could be machined to provide increased clearance (e.g., exhaust passage) for guide vane positions equal to or greater than the guide vane position corresponding to maximum efficiency.

[0084] As explained, the top and / or bottom clearance of the guide vanes in the nozzle can adversely affect VNT class performance. Typically, such clearances are kept as small as possible along the entire guide vane opening range, which increases the risk of guide vane jamming (e.g., sticking) and / or guide vane friction with the nozzle / pipe. Therefore, to increase the flow range of the VNT class, a larger guide vane height is required, which in turn increases the guide vane load. With increased load, a larger actuator is needed to pivot the guide vanes.

[0085] As explained, a component may include an increased gap region for exhaust passage above and / or below each guide vane in the nozzle, which can improve high-end performance, reduce HCF excitation, and reduce the risk of guide vanes rubbing or sticking to the nozzle wall. By providing an increased gap at / near the inner periphery of the nozzle ring as a bypass channel, the performance flow range can be increased while using a smaller guide vane height to achieve lower drive force.

[0086] As an example, one approach may include machining a common annular component (e.g., as a cap-shaped component or a flat component) and / or selecting guide vanes with a smaller height.

[0087] As an example, a turbine housing assembly may include a turbine housing defining the axis of rotation of a turbine impeller; a cylinder receivable by the turbine housing, wherein the cylinder includes a nozzle wall member having an upper nozzle surface and a plate member having a lower nozzle surface, wherein the upper and lower nozzle surfaces define a nozzle space; and guide vanes positioned in the nozzle space, wherein the guide vanes are pivotable between a 0% open closed guide vane position and a 100% open fully open guide vane position, and for a guide vane position that is at least 50% open and less than 75% open, the axial dimension of the nozzle space increases with respect to a decreasing radius as measured from the axis of rotation. In such examples, for guide vane positions that are less than 50% open, the axial dimension of the nozzle space may be constant.

[0088] As an example, the axial dimension of the nozzle space can be increased with respect to a radius that decreases at the transition radius, where the transition radius is defined by the trailing edge of the guide vane for a guide vane position that is at least 50% open and less than 75% open. In such examples, the guide vane position can correspond to the maximum efficiency with respect to the corrected mass flow rate.

[0089] As an example, for the fully open guide vane position, there may be an annular gap relative to the trailing edge of the turbine impeller and the guide vane, wherein the annular gap may be at least 3% and less than 10% of the turbine impeller radius.

[0090] As an example, in the closed guide vane position, there may be contact between adjacent guide vanes. In such examples, the contact point can be used to limit the rotation of the guide vanes (e.g., pivoting). As an example, a cylinder, control linkage, etc., may include one or more features that act as physical stops that can define the closed guide vane position. In such examples, the guide vanes may be in near contact at a very small throat defined between adjacent guide vanes, such that the guide vanes act as a barrier to the exhaust flow from the volute to the turbine impeller space. In such examples, near contact can be defined by a guide vane-to-guide vane clearance (e.g., throat width) of less than about 3 mm. The closed guide vane position can define the minimum exhaust flow state of the turbine housing assembly, while the fully open position can define the maximum exhaust flow state of the turbine housing assembly.

[0091] As an example, in a turbine housing assembly, the axial dimension of the nozzle space can be increased to a constant axial dimension. As an example, the axial dimension of the nozzle space can be increased based on ramps and / or steps.

[0092] As an example, in a turbine housing assembly, each of a plurality of guide vanes (e.g., a set of guide vanes) can have a constant axial guide vane height between its respective trailing edge and its respective leading edge. For example, consider a slight chamfer at the leading edge and a slight chamfer at the trailing edge, where the axial guide vane height is constant over approximately 90% or more of the guide vane length.

[0093] As an example, a turbine housing assembly may include a component defining a nozzle space, wherein the surface of the component provides an inclined upper nozzle surface, and / or may include a component defining a nozzle space, wherein the surface of the component provides an inclined lower nozzle surface.

[0094] As an example, a turbine housing assembly may include a component defining a nozzle space, wherein the surface of the component provides a stepped upper nozzle surface, and / or may include a component defining a nozzle space, wherein the surface of the component provides a stepped lower nozzle surface.

[0095] As an example, a turbine housing assembly may include a component defining a nozzle space, wherein the surface of the component provides an inclined and / or stepped upper nozzle surface and / or may include a component defining a nozzle space, wherein the surface of the component provides an inclined and / or stepped lower nozzle surface.

[0096] As an example, a turbine housing assembly may include a turbine housing that includes a shroud surface. In such an example, the shroud surface may partially define a turbine impeller space for the turbine impeller.

[0097] As an example, a turbine housing assembly may include a nozzle wall component that includes a shroud surface. In such an example, the shroud surface may partially define a turbine impeller space for the turbine impeller.

[0098] As an example, a method may include operating a turbine housing assembly including a turbine housing defining a rotational axis for a turbine impeller; and a cylinder receivable by the turbine housing, wherein the cylinder includes a nozzle wall member having an upper nozzle surface and a plate member having a lower nozzle surface, wherein the upper and lower nozzle surfaces define a nozzle space; and guide vanes positioned in the nozzle space, wherein the guide vanes are pivotable between a 0% open closed guide vane position and a 100% open fully open guide vane position, and for a guide vane position at least 50% open and less than 75% open, the axial dimension of the nozzle space increases with respect to a decreasing radius as measured from the rotational axis; exhaust flows in a gap between the guide vanes and the upper nozzle surface; and, in response to pivoting the guide vanes from a guide vane position less than 50% open to a guide vane position greater than 75% open, exhaust flows in the increased gap between the guide vanes and the upper nozzle surface. In such examples, the increased clearance can reduce the risk of the guide vanes getting stuck in the nozzle space and / or the increased clearance can facilitate the development of the exhaust flow before the turbine impeller space (e.g., in a region adjacent to the turbine impeller space, where the increased clearance is included).

[0099] Although some examples of methods, apparatus, systems, arrangements, etc. have been shown in the accompanying drawings and described in the foregoing detailed description, it should be understood that the disclosed exemplary embodiments are not limiting, but are capable of numerous rearrangements, modifications and substitutions.

Claims

1. A turbine housing assembly, comprising: Turbine casing, which defines the axis of rotation of the turbine impeller; as well as A cylinder that can be received by the turbine housing, wherein the cylinder includes a nozzle wall member having an upper nozzle surface and a plate member having a lower nozzle surface, wherein the upper nozzle surface and the lower nozzle surface define a nozzle space, and a guide vane positioned in the nozzle space, wherein the guide vane is pivotable between a 0% open (closed) guide vane position and a 100% open (fully open) guide vane position. Specifically, for guide vane positions where the nozzle is at least 50% open and less than 75% open, the axial dimension of the nozzle space increases with respect to a decreasing radius measured from the axis of rotation, and the guide vane positions correspond to the maximum efficiency with respect to corrected mass flow rate, thereby increasing the efficiency with respect to corrected mass flow rate compared to a constant axial dimension of the nozzle space. The axial dimension of the nozzle space increases with respect to a radius that decreases at the transition radius, wherein, for a guide vane position that is at least 50% open and less than 75% open, the transition radius is defined by the trailing edge of the guide vane. Wherein, for the fully opened guide vane position, there is an annular gap relative to the turbine impeller and the trailing edge of the guide vane, wherein the annular gap is at least 3% of the turbine impeller radius and less than 10% of the turbine impeller radius.

2. The turbine housing assembly according to claim 1, wherein, For guide vane positions where less than 50% is open, the axial dimension of the nozzle space is constant.

3. The turbine housing assembly according to claim 1, wherein, For the closed guide vane position, there is contact between adjacent guide vanes.

4. The turbine housing assembly according to claim 1, wherein, The axial dimension of the nozzle space is increased to a constant axial dimension.

5. The turbine housing assembly according to claim 1, wherein, The axial dimension of the nozzle space increases according to the inclined plane.

6. The turbine housing assembly according to claim 1, wherein, Each of the guide vanes includes a constant axial guide vane height between its respective trailing edge and its respective leading edge.

7. The turbine housing assembly according to claim 1, wherein, The surface of the upper nozzle is inclined.

8. The turbine housing assembly according to claim 1, wherein, The surface of the lower nozzle is inclined.

9. The turbine housing assembly according to claim 1, wherein, The upper nozzle surface is inclined, and the lower nozzle surface is also inclined.

10. The turbine housing assembly of claim 1, wherein, The turbine housing includes a protective cover surface.

11. The turbine housing assembly of claim 1, wherein, The nozzle wall component includes a protective cover surface.

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