Inlet passage system including split volute turbocharger

Abstract

The present application relates to an inlet passage system comprising: a split volute turbocharger comprising a turbine housing, a first volute, a second volute, a turbine housing outlet, and a wall; and a vane ring coupled to the turbine housing and disposed in the turbine housing interior between the first volute and the second volute and surrounding the turbine wheel, where the vane ring includes a vane dividing wall further separating the first volute from the second volute, the vane dividing wall having a vane dividing surface facing the first wall surface, the vane dividing wall having a vane dividing surface facing the second wall surface, and the vane dividing wall having a vane dividing surface facing the second wall surface. The guide vane ring comprises a plurality of guide vanes coupled to the guide vane partition wall; wherein a first wall surface of the wall and a vane separation surface of the vane separation wall define between each other a confinement path with respect to the turbine housing axis, at least a portion of the confinement path being non-parallel to the turbine housing axis, exhaust leakage from one of the first volute and the second volute to the other of the first volute and the second volute is reduced.

Description

[0001] Cross-references to related applications

[0002] This application claims priority to U.S. Provisional Patent Application No. 63 / 644,172, filed May 8, 2024, the contents of which are incorporated herein by reference in their entirety. Background Technology 1. Technical Field

[0003] The present invention generally relates to an inlet channel system comprising a split-type volute turbocharger having a variable turbine geometry.

[0004] 2. Relevant Technical Specifications

[0005] A turbocharger receives exhaust gas from an internal combustion engine and delivers compressed air to it. Turbochargers increase the power output of the internal combustion engine, reduce its fuel consumption, and / or decrease its emissions. Delivering compressed air to the internal combustion engine via a turbocharger allows for a smaller engine while still producing the same or similar horsepower as a larger naturally aspirated engine. Using a smaller internal combustion engine in a vehicle reduces its mass and aerodynamic frontal area, which helps reduce fuel consumption and improve fuel economy.

[0006] Some turbochargers include turbines with separate volute turbine housings; these turbochargers are therefore sometimes referred to as separate volute turbochargers, including twin-volute turbochargers, twin-scroll turbochargers, etc. The volutes of a separate volute turbine housing are generally isolated from each other, such that exhaust mixing does not occur until exhaust gases have passed through one or more tongues of the respective volute. The separate volute turbine housing includes a turbine inlet, a turbine outlet, and an internal volume. The turbine inlet is configured to attach to an internal combustion engine (e.g., to an exhaust manifold or cylinder head of the internal combustion engine) and includes multiple inlet ports configured to be in fluid communication with the exhaust path of the internal combustion engine upon attachment. The internal volume of the turbine housing defines at least two separate volutes in fluid communication with their respective inlet ports for delivering exhaust gases from the internal combustion engine to a turbine impeller disposed within the internal volume. After extracting energy from the exhaust gas through the turbine impeller, the exhaust gas exits the turbine housing via the turbine outlet. These volutes guide the exhaust gas from the engine's exhaust manifold into an arc flow to distribute the exhaust gas around the circumference of the turbine impeller, thus rotating the turbine impeller.

[0007] The turbocharger also includes a compressor. The compressor includes a compressor impeller connected to a turbine impeller via a shaft. The compressor is powered by the rotation of the turbine impeller, which in turn drives the compressor impeller within the compressor housing.

[0008] In a multi-cylinder engine, cylinders are fired in a specific sequence. For example, in an inline four-cylinder engine with cylinder numbers 1 through 4, the firing order could be 1-3-4-2. The sets of cylinders can be grouped into 'groups'. In the example above, the first group of cylinders would include cylinders 1 and 4, and the second group would include cylinders 2 and 3. In the case of a "V" type engine, cylinder groups can be separated across the engine, and multiple cylinders can be fired simultaneously. In the case of an inline engine, a cylinder group can simply be front-to-rear cylinders, or an alternative set of cylinders as described above. The exhaust flow is not a smooth flow because exhaust leaves each cylinder based on the engine's firing sequence, resulting in intermittent exhaust pulses. Exhaust from each group is directed to the turbine housing in a corresponding manifold. These manifolds can be ducts and / or pipes attached to the internal combustion engine, or they can be integral with the internal combustion engine (e.g., manifold pipes cast into the engine's cylinder head). By separating the exhaust flow, the pressure “pulse” that occurs when exhaust is released from the cylinder can be sustained through the volute, allowing the pressure pulse to strike the turbine impeller. This pulse sustaining is typically desirable because the pressure pulse imparts momentum to the turbine impeller, accelerating it more quickly and reducing turbine lag. Effective airflow separation also reduces instantaneous back pressure in the “unignited” volute. The term “ignited” volute refers to the volute through which the pressure pulse passes. This pulse separation begins at the exhaust of each cylinder and is maintained in the exhaust manifold up to the turbine inlet (sometimes referred to as the turbine inlet vortex). In the areas where exhaust is allowed into the turbine housing, separation walls between the respective volutes help maintain separation between the exhaust from each cylinder or cylinder bank, and thus sustain the pressure pulse. However, exhaust leakage often still occurs between the respective volutes, leading to reduced turbocharger performance and efficiency.

[0009] To help guide and control the exhaust flow from the volute or split volute to reach the turbine impeller evenly, a guide vane ring (sometimes called a nozzle ring or guide vane nozzle stator) with multiple guide vanes can be arranged inside the turbine housing on an annular disk between the volute and the turbine impeller. These guide vanes can be fixed to the annular disk (sometimes called a fixed nozzle ring or fixed guide vane nozzle stator) or rotatably coupled to the annular disk (sometimes called a variable nozzle ring or variable guide vane nozzle stator) to produce a variable turbine geometry (VTG).

[0010] Typically, these rotatable guide vanes on the guide vane ring are equidistant from each other and each is positioned at the same radial distance relative to the axis of rotation of the turbine impeller. Furthermore, these rotatable guide vanes are typically at equal angles to radial lines drawn from the axis of rotation. Typically, the number of rotatable guide vanes arranged on the guide vane ring is odd, for example, a prime number, which here provides asymmetry along the guide vane ring associated with the odd number of equidistant guide vanes.

[0011] Therefore, it is still necessary to reduce the amount of exhaust gas leaking from one of these volutes into the other. Summary of the Invention

[0012] An inlet channel system includes a split-type volute turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine. The internal combustion engine includes a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke. The split-type volute turbocharger includes a turbine housing including a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades. The turbine housing extends along a turbine housing axis. The split-type volute turbocharger also includes a first volute and a second volute, the first volute being adapted to be in fluid communication with the internal combustion engine and the turbine housing interior for delivering exhaust gas from the first group of cylinders to the turbine housing interior, and the second volute being adapted to be in fluid communication with the internal combustion engine and the turbine housing interior for delivering exhaust gas from the second group of cylinders to the turbine housing interior independently of the first volute. The split-casing turbocharger further includes a turbine housing outlet in fluid communication with the interior of the turbine housing, and a wall separating the first and second volutes. The wall has a first wall surface facing the turbine housing axis. The inlet passage system includes a guide vane ring coupled to and disposed within the turbine housing, between the first and second volutes, and surrounding the turbine impeller. The guide vane ring includes a guide vane partition wall further separating the first and second volutes. The guide vane partition wall has a guide vane partition surface facing the first wall surface. The guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall. The first wall surface of the wall and the guide vane partition surface of the guide vane partition wall define a limiting path between each other relative to the turbine housing axis. At least a portion of the limiting path is not parallel to the turbine housing axis, thereby reducing exhaust leakage from one of the first and second volutes to the other.

[0013] In another embodiment, an inlet channel system includes a split-type volute turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine. The internal combustion engine includes a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke. The split-type volute turbocharger includes a turbine housing including a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades. The turbine housing extends along a turbine housing axis. The split-type volute turbocharger also includes a first volute and a second volute, the first volute being adapted to be in fluid communication with the internal combustion engine and the turbine housing interior for delivering exhaust gas from the first group of cylinders to the turbine housing interior, and the second volute being adapted to be in fluid communication with the internal combustion engine and the turbine housing interior for delivering exhaust gas from the second group of cylinders to the turbine housing interior independently of the first volute. The split-type volute turbocharger further includes a turbine housing outlet in fluid communication with the interior of the turbine housing, and a wall separating the first and second volutes. The wall has a first wall surface facing the turbine housing axis. The inlet passage system includes a guide vane ring coupled to and disposed within the turbine housing, between the first and second volutes, and surrounding the turbine impeller. The guide vane ring includes a guide vane partition wall further separating the first and second volutes. The guide vane partition wall has a guide vane partition surface facing the first wall surface. The guide vane ring includes a plurality of guide vanes coupled to and fixed to the guide vane partition wall. The inlet passage system also includes a pin coupled to the guide vane ring and the turbine housing to prevent rotation of the guide vane ring relative to the turbine housing.

[0014] In another embodiment, an inlet channel system includes a split-type volute turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine. The internal combustion engine includes a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke. The split-type volute turbocharger includes a turbine housing including a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades. The turbine housing extends along a turbine housing axis. The split-type volute turbocharger also includes a first volute and a second volute, the first volute being adapted to be in fluid communication with the internal combustion engine and the turbine housing interior for delivering exhaust gas from the first group of cylinders to the turbine housing interior, and the second volute being adapted to be in fluid communication with the internal combustion engine and the turbine housing interior for delivering exhaust gas from the second group of cylinders to the turbine housing interior independently of the first volute. The split-type volute turbocharger further includes a turbine housing outlet in fluid communication with the interior of the turbine housing, and a wall separating the first volute and the second volute. The wall has a first wall surface facing the turbine housing axis. The inlet passage system includes a guide vane ring coupled to the turbine housing and disposed within the turbine housing, between the first and second volutes, and surrounding the turbine impeller. The guide vane ring includes a guide vane partition wall further separating the first and second volutes. The guide vane partition wall has a guide vane partition surface facing the first wall surface. The guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall. The inlet passage system further includes a pin coupled to the guide vane ring and the turbine housing to prevent the guide vane ring from rotating relative to the turbine housing. The wall includes a tongue forming the first wall surface. The pin is adjacent to the first wall surface such that the pin is configured as the leading edge of one of the guide vanes. Attached Figure Description

[0015] Other advantages of this disclosure will be readily apparent, as they will become more readily understood when considered in conjunction with the accompanying drawings and with reference to the following detailed description.

[0016] Figure 1 It is a cross-sectional side view of the inlet passage system of a split-type volute turbocharger, the split-type volute turbocharger including a turbine housing adapted to receive a turbine impeller, the turbine housing extending along the turbine housing axis, and the split-type volute turbocharger also including a first volute, a second volute, a turbine housing outlet, and a wall, and the inlet passage system further including guide vane rings connected to and disposed within the turbine housing.

[0017] Figure 2It is a cross-sectional side view of the inlet passage system, the wall having a first wall surface facing the turbine housing axis, the guide vane ring including a guide vane partition wall having a guide vane partition surface facing the first wall surface, the first wall surface and the guide vane partition surface defining a limiting path between each other relative to the turbine housing axis, and at least a portion of the limiting path is not parallel to the turbine housing axis, such that exhaust leakage from one of the first volute and the second volute to the other of the first volute and the second volute is reduced.

[0018] Figure 3 This is a top view of the inlet passage system, which includes a pin connected to a guide vane ring and a turbine housing to prevent the guide vane ring from rotating relative to the turbine housing. The turbine housing wall has a tongue, one of the plurality of guide vanes has a leading edge, and the pin is adjacent to a first wall surface such that the pin is configured to be the leading edge of one of the guide vanes.

[0019] Figure 4 This is a cross-sectional side view of the inlet passage system. The turbine casing defines the turbine casing slot, the guide vane partition wall defines the partition slot, and pins are arranged in the turbine casing slot and the partition slot.

[0020] Figure 5 This is a cross-sectional side view of the inlet channel system, where the outer circumference defines the outer annular groove, and pins are arranged in the outer annular groove and the turbine housing groove.

[0021] Figure 6 yes Figure 5 A close-up cross-sectional side view of the entrance channel system.

[0022] Figure 7 It is a cross-sectional side view of the inlet passage system, the pin is further defined as a first pin, and further includes a second pin, the first pin being connected to the guide vane partition wall and the turbine housing, the second pin being connected to the outer circumferential ring and the turbine housing, the first pin being arranged in the partition slot and the first turbine housing slot, and the second pin being arranged in the second turbine housing slot and the outer guide vane ring slot.

[0023] Figure 8 This is an exploded view of the inlet channel system, where the guide vane ring and outer circumferential ring are separate components, and the inlet channel system further includes a spring.

[0024] Figure 9 This is a cross-sectional side view of the inlet channel system, with springs connected to the guide vane rings to preload them against the turbine housing in order to reduce vibration during operation of the split-type volute turbocharger.

[0025] Figure 10It is a perspective view of the inlet channel system. The turbine housing has a first turbine housing surface facing a first direction, and an outer circumferential ring has a second surface facing a second direction opposite to the first direction. The first turbine housing surface and the second turbine surface are at an angle relative to the turbine housing axis. Detailed Implementation

[0026] Referring to the accompanying drawings, where the same reference numerals indicate the same parts throughout these views, Figure 1 The inlet passage system 30 is shown in general. The inlet passage system 30 includes a split-type volute turbocharger 32, which receives exhaust gas from the internal combustion engine and delivers compressed air to the internal combustion engine. The internal combustion engine includes a first group of cylinders and a second group of cylinders, and the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke.

[0027] Continue to refer to Figure 1 The split-type volute turbocharger 32 includes a turbine housing 34, which includes a turbine housing interior 36 adapted to receive a turbine impeller 38 having a plurality of turbine blades 40. The turbine housing 34 extends along the turbine housing axis THA.

[0028] The split-type volute turbocharger 32 may include a turbocharger shaft 41 rotatably coupled to a turbine impeller 38, and may include a compressor impeller 43 rotatably coupled to the turbocharger shaft 41. The split-type volute turbocharger 32 also includes a first volute 42 and a second volute 44, the first volute being adapted to be in fluid communication with the internal combustion engine and the turbine housing interior 36 for delivering exhaust gas from a first group of cylinders into the turbine housing interior 36, and the second volute being adapted to be in fluid communication with the internal combustion engine and the turbine housing interior 36 for delivering exhaust gas from a second group of cylinders into the turbine housing interior 36 independently of the first volute 42.

[0029] The split-type volute turbocharger 32 further includes a turbine housing outlet 46 in fluid communication with the turbine housing interior 36, and a wall 48 separating the first volute 42 from the second volute 44. (See reference) Figure 2 Wall 48 has a first wall surface facing the turbine housing axis THA.

[0030] Continue to refer to Figure 2The inlet passage system 30 also includes a guide vane ring 52, which is coupled to the turbine housing 34 and disposed within the turbine housing interior 36, between the first volute 42 and the second volute 44, and surrounding the turbine impeller 38. The guide vane ring 52 includes a guide vane partition wall 54 that further separates the first volute 42 and the second volute 44. In other words, the guide vane partition wall 54 is operatively aligned with the wall 48 of the turbine housing 34 to further extend the wall 48 of the turbine housing 34 toward the turbine impeller 38, thereby further separating the first volute 42 and the second volute 44. The guide vane partition wall 54 has a guide vane partition surface 56 facing the first wall surface 50, and the guide vane ring 52 includes a plurality of guide vanes 58 coupled to the guide vane partition wall 54. Although not required, the plurality of guide vanes 58 can be further defined as a first plurality of guide vanes 60 protruding from the guide vane partition wall 54 into the first volute 42, and a second plurality of guide vanes 62 protruding from the guide vane partition wall 54 into the second volute 44. Typically, the plurality of guide vanes 58 are fixed to the guide vane partition wall 54. In other words, each of the plurality of guide vanes 58 is immovable relative to the guide vane partition wall 54. In such embodiments, the guide vane ring 52 may be referred to as a fixed guide vane ring. Depending on the application of the inlet channel system 30, the guide vane ring 52 can be optimized, for example, by adjusting the various dimensions of the guide vane ring 52 and / or the angles of the plurality of guide vanes 58. As described above, the inlet channel system 30 with the guide vane ring 52 improves the efficiency of the inlet channel system 30 / split volute turbocharger 32, for example, by 1%-3%.

[0031] The first wall surface 50 of wall 48 and the guide vane partition surface 56 of guide vane partition wall 54 define a limiting path 64 between them relative to the turbine housing axis THA. At least a portion of the limiting path 64 is not parallel to the turbine housing axis THA, thereby reducing exhaust leakage from one of the first volute 42 and the second volute 44 to the other. It should be understood that the limiting path 64 includes embodiments in which the first wall surface 50 and the guide vane partition surface 56 are engaged with each other, and embodiments in which the first wall surface 50 and the guide vane partition surface are spaced apart from each other to accommodate thermal deformation of the turbine housing 34. In either of these embodiments, exhaust leakage between the first volute 42 and the second volute 44 is reduced. When exhaust leakage between the first volute 42 and the second volute 44 is reduced, the exhaust flow to the turbine impeller 38 is increased, which promotes better performance and efficiency of the split volute turbocharger 32. Improving the performance and efficiency of the split-type volute turbocharger 32 also enhances the fuel economy of the internal combustion engine (which allows vehicle manufacturers to meet current and future emission regulations) and braking thermal efficiency, and improves the durability of the inlet channel system 30.

[0032] It should be understood that, throughout this disclosure, references to the turbine housing axis THA can also include the relationships between different components and other axes such as the guide vane ring axis, the turbocharger shaft axis, and the rotor axis. For example, the first wall surface 50 of wall 48 and the guide vane partition surface 56 of guide vane partition wall 54 may define a limiting path 64 between them relative to the guide vane ring axis. As another example, the first wall surface 50 of wall 48 and the guide vane partition surface 56 of guide vane partition wall 54 may define a limiting path 64 between them relative to the turbocharger shaft axis. As another example, the first wall surface 50 of wall 48 and the guide vane partition surface 56 of guide vane partition wall 54 may define a limiting path 64 between them relative to the rotor axis. The turbine housing axis THA, the guide vane ring axis, the turbocharger shaft axis, and the rotor axis may be concentric with each other. Alternatively, the turbine housing axis, the guide vane ring axis, the turbocharger shaft axis, and the rotor axis may be non-concentric with each other, or some of these axes may be concentric with each other while others are non-concentric. It should be understood that it is envisioned that all other references to the turbine housing axis THA throughout this disclosure may equally apply to other axes of the inlet passage system 30, such as the guide vane ring axis, the turbocharger shaft axis, the rotor axis, etc.

[0033] The limiting path 64 can be any path defined between the guide vane partition surface 56 and the first wall surface 50, at least a portion of which is not parallel to the turbine housing axis THA. For example, the limiting path 64 can have a zigzag configuration relative to the turbine housing axis THA. As another example, the limiting path 64 can have a meandering configuration relative to the turbine housing axis THA. As another example, the limiting path 64 can have a curved configuration relative to the turbine housing axis THA. As another example, the limiting path 64 can be angled relative to the turbine housing axis THA. As another example, the limiting path 64 can have a stepped configuration.

[0034] As another example, Figure 2As shown, the limiting path 64 may have a first limiting path 66 extending adjacent to the first volute 42 and parallel to the turbine housing axis THA, a second limiting path 68 extending adjacent to the second volute 44 and parallel to the turbine housing axis THA, and a third limiting path 70 extending from the first limiting path 66 to the second limiting path 68. In such embodiments, the third limiting path 70 may define a first angle θ1 with the first limiting path 66 and a second angle θ2 with the second limiting path 68. The first angle θ1 and the second angle θ2 may form acute angles relative to the turbine housing axis THA. When the first angle θ1 and the second angle θ2 form acute angles relative to the turbine housing axis THA, the first angle θ1 may be between 45 and 90 degrees, and the second angle θ2 may be between 45 and 90 degrees. Alternatively, the first angle θ1 and the second angle θ2 may form obtuse angles relative to the turbine housing axis THA. When the first angle θ1 and the second angle θ2 are obtuse angles relative to the turbine housing axis THA, the first angle θ1 can be between 90 and 135 degrees, and the second angle θ2 can also be between 90 and 135 degrees. As another example, the third limiting path 70 can be orthogonal to the turbine housing axis THA and at least one of the first limiting path 66 and the second limiting path 68. The limiting path 64 can have a Z-shaped configuration relative to the turbine housing axis THA. In an embodiment where the limiting path 64 has a Z-shaped configuration, the limiting path 64 can have a first limiting path 66, a second limiting path 68, and a third limiting path 70, which define the Z-shaped configuration.

[0035] Making at least a portion of the limiting path 64 non-parallel to the turbine housing axis reduces exhaust leakage from one of the first volute 42 and the second volute 44 to the other. Although not required and not explicitly shown in the figures, to further reduce exhaust leakage from one of the first volute 42 and the second volute 44 to the other, an abrasive coating may be applied to at least one of the first wall surface 50 and the guide vane partition surface 56. Alternatively, a seal may be applied between the first wall surface 50 and the guide vane partition surface 56. Alternatively, a metal foam may be applied between the first wall surface 50 and the guide vane partition surface 56. Alternatively, para-aramid synthetic fibers (such as...) may be applied between the first wall surface 50 and the guide vane partition surface 56. ).

[0036] The first plurality of guide vanes 60, the second plurality of guide vanes 62, and the guide vane partition wall 54 can be integrated with each other, such as Figure 1 , Figure 2 , Figures 4 to 7 as well as Figure 9 As shown. Figures 1 to 9 As shown, the guide vane ring 52 may include an outer circumferential ring 72 coupled to the partition wall 48. It should be understood that the outer circumferential ring 72 may be further referred to as a backplate. The plurality of guide vanes 58 (which may include a first plurality of guide vanes 60 and a second plurality of guide vanes 62), the guide vane partition wall 54, and the outer circumferential ring 72 may be integrally formed with each other (i.e., one piece). Alternatively, the outer circumferential ring 72 and the guide vane ring 52 may be separate components, such as... Figure 8 As shown.

[0037] refer to Figure 1 and Figures 3 to 8 The inlet passage system 30 may further include a pin 74 connected to the guide vane ring 52 and the turbine housing 34 to prevent rotation of the guide vane ring 52 relative to the turbine housing 34. The circumferential forces exerted by the exhaust on the plurality of guide vanes 58, as well as the thermal deformation of the turbine housing 34, may cause rotation and wear of the guide vane ring 52 and other components of the inlet passage system 30; however, the inlet passage system 30, including the pin 74 connected to the guide vane ring 52 and the turbine housing 34, prevents rotation of the guide vane ring 52 relative to the turbine housing 34, and thus reduces wear on the guide vane ring 52 compared to an inlet passage system that allows rotation of the guide vane ring relative to the turbine housing.

[0038] In one embodiment, such as Figure 1 and Figures 3 to 7 As shown, pin 74 is coupled to guide vane partition wall 54. In another embodiment, pin 74 is coupled to at least one of guide vane partition wall 54 and outer circumferential ring 72 of guide vane ring 52 and turbine housing 34 to prevent rotation of guide vane ring 52 relative to turbine housing 34. Pin 74 may extend parallel to turbine housing axis THA, or alternatively, pin 74 may extend perpendicular to turbine housing axis THA.

[0039] To secure the pin 74, the turbine housing 34 may define a turbine housing slot 76 in which the pin 74 is disposed. Alternatively or additionally, the guide vane partition wall 54 may define a partition slot 78 in which the pin 74 is disposed.

[0040] In an embodiment where the guide vane ring 52 includes an outer circumferential ring 72, the outer circumferential ring 72 may define an outer annular groove 80, in which a pin 74 is arranged.

[0041] refer to Figure 3The wall 48 may include a tongue 82 that forms a first wall surface 50. In such embodiments, a pin 74 may be adjacent to the first wall surface 50 such that the pin 74 is configured as the leading edge 83 of one of the plurality of guide vanes 58. This configuration of the pin 74 as the leading edge 83 of one of the plurality of guide vanes 58 allows the pin 74 to guide the exhaust flow. The pin 74 may advantageously be configured to guide the exhaust flow through the plurality of guide vanes 58, for example, by having a curved leading edge, an angled leading edge, or otherwise configured to guide the exhaust flow through the plurality of guide vanes 58. Additionally, the leading edge 83 of the pin 74 may be located below the tongue 82, which mitigates or even eliminates any interruption of the exhaust flow due to the wake of the tongue 82 and / or any lateral leakage around the pin when the exhaust flow passes through the guide vane ring 52.

[0042] It should be understood that pin 74 can be further defined as a first pin 84, and the inlet passage system 30 can include a second pin 86. In such embodiments, the first pin 84 can be coupled to the guide vane partition wall 54 and the turbine housing 34, and the second pin 86 can be coupled to the outer circumferential ring 72 and the turbine housing 34. The first pin 84 can be arranged in the partition slot 78 and the turbine housing slot 76, such as... Figure 7 As shown. The outer circumferential ring 72 can define the outer guide vane ring groove 88, and the turbine housing 34 can define the second turbine housing groove 90, with the second pin 86 arranged in the outer guide vane ring groove 88 and the second turbine housing groove 90.

[0043] like Figure 8 and Figure 9 As shown, the inlet passage system 30 may include a spring 91 coupled to the guide vane ring 52 for preloading the guide vane ring 52 against the turbine housing 34 to reduce vibration during operation of the split-casing turbocharger 32 and also to reduce any end-face leakage of the guide vane ring 52. In one embodiment, the spring 91 may be further defined as a cup spring, wave spring, helical spring, clover spring, Belville washer spring, etc. The spring 91 may also preload the guide vane ring 52 during installation. The inlet passage system 30 may include a heat shield 92 coupled to the guide vane ring 52 and the spring 91 and disposed between the guide vane ring and the spring relative to the turbine housing axis. The inlet passage system 30 may include an adapter 94 coupled to the heat shield 92 and the guide vane ring 52 and disposed between the heat shield and the guide vane ring.

[0044] refer to Figure 2 and Figure 10The turbine housing 34 may have a first turbine housing surface 96 that engages with the guide vane ring 52 and faces a first direction relative to the turbine housing axis THA, and the outer circumferential ring 72 may have a second surface 98 that faces a second direction opposite to the first direction relative to the turbine housing axis THA. At least one of the first turbine housing surface 96 and the second surface 98 of the outer circumferential ring 72 is angled relative to the turbine housing axis THA. In one embodiment, the first turbine housing surface 96 is angled relative to the turbine housing axis THA, and additionally or alternatively, the second surface 98 of the outer circumferential ring 72 is angled relative to the turbine housing axis THA. Angles the second surface 98 and the first turbine housing surface relative to the turbine housing axis THA create a conical configuration, which can facilitate the alignment and preloading of the guide vane ring 52 during the assembly of the inlet passage system 30.

[0045] refer to Figure 2 and Figure 5 The guide vane partition wall 54 may have an inner partition wall tip 100 extending toward the turbine impeller 38, and the inner partition wall tip 100 may be chamfered. The inner partition wall tip 100 may have a tip radius TR defined between itself and the turbine housing axis THA, and the turbine impeller 38 may have a turbine impeller radius TWR, the tip radius TR being optionally 1.05-1.25 times or 1.15-1.25 times the turbine impeller radius TWR.

[0046] It should be understood that the split-type volute turbocharger 32 can be further defined as a twin-scroll turbocharger (commonly referred to as a twin-scroll turbocharger, wherein the first and second volutes are parallel to each other 360 degrees around the turbine impeller inlet), a twin-scroll turbocharger, etc.

[0047] In another embodiment, the inlet channel system 30 includes a split-type volute turbocharger 32 for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine. The internal combustion engine includes a first group of cylinders and a second group of cylinders, the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders being generally equal for each exhaust stroke. The split-type volute turbocharger 32 includes a turbine housing 34, which includes a turbine housing interior 36 adapted to receive a turbine impeller 38 having a plurality of turbine blades 40. The turbine housing 34 extends along a turbine housing axis THA. The split-type volute turbocharger 32 also includes a first volute 42 and a second volute 44. The first volute is adapted to be in fluid communication with the internal combustion engine and turbine housing interior 36 for delivering exhaust gas from a first group of cylinders to the turbine housing interior 36. The second volute is adapted to be in fluid communication with the internal combustion engine and turbine housing interior 36 for delivering exhaust gas from a second group of cylinders to the turbine housing interior 36 independently of the first volute 42. The split-type volute turbocharger 32 further includes a turbine housing outlet 46 in fluid communication with the turbine housing interior 36, and a wall 48 separating the first volute 42 and the second volute 44. (Reference) Figure 2 Wall 48 has a first wall surface facing the turbine housing axis THA. (Continue to reference) Figure 2 The inlet passage system 30 also includes a guide vane ring 52, which is coupled to the turbine housing 34 and disposed within the turbine housing interior 36, between the first volute 42 and the second volute 44, and surrounding the turbine impeller 38. The guide vane ring 52 includes a guide vane partition wall 54 that further separates the first volute 42 from the second volute 44. The guide vane partition wall 54 has a guide vane partition surface 56 facing the first wall surface 50, and the guide vane ring 52 includes a plurality of guide vanes 58 coupled to the guide vane partition wall 54. The inlet passage system 30 further includes a pin coupled to the guide vane ring 52 and the turbine housing 34 to prevent rotation of the guide vane ring 52 relative to the turbine housing 34. The wall 48 includes a tongue 82 that forms the first wall surface 50. The pin 74 is adjacent to the first wall surface 50 such that the pin 74 is configured as the leading edge 83 of one of the plurality of guide vanes 58. The pin 74 is configured such that the leading edge 83 of one of the plurality of guide vanes 58 allows the pin 74 to guide the exhaust flow through. The pin 74 can advantageously be configured to guide the exhaust flow through the plurality of guide vanes 58, for example, by having a curved leading edge, an angled leading edge, or otherwise configured to guide the exhaust flow through the plurality of guide vanes 58. Additionally, the leading edge 83 of the pin 74 can be located below the tongue 82, which mitigates or even eliminates any interruption of the exhaust flow due to the wake in the tongue 82 and / or any lateral leakage around the pin when the exhaust flow passes through the guide vane ring 52.

[0048] Although the present invention has been described above, it should be understood that the present invention can also be defined according to the following embodiments:

[0049] Example 1: An entrance passage system, comprising:

[0050] A split-type volute turbocharger, wherein the split-type volute turbocharger is used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke, the split-type volute turbocharger comprising:

[0051] A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis.

[0052] A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing.

[0053] A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute.

[0054] The turbine casing outlet is in fluid communication with the interior of the turbine casing.

[0055] A wall separating the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing; and

[0056] A guide vane ring, the guide vane ring being coupled to and disposed within the turbine housing, between the first volute and the second volute and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, and wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall;

[0057] The first wall surface of the wall and the guide vane partition surface of the guide vane partition wall define a limiting path between each other relative to the turbine housing axis, and at least a portion of the limiting path is not parallel to the turbine housing axis, thereby reducing exhaust leakage from one of the first volute and the second volute to the other of the first volute and the second volute.

[0058] Example 2: The inlet channel system as described in Example 1, wherein the limiting path has a tortuous configuration relative to the turbine housing axis.

[0059] Example 3: An inlet channel system as described in any of the preceding examples, wherein the limiting path has a curved configuration relative to the turbine housing axis.

[0060] Example 4: An inlet passage system as described in any of the preceding embodiments, wherein the limiting path defined between the guide vane separating surface and the first wall surface of the wall has a first limiting path extending adjacent to the first volute and parallel to the turbine housing axis, a second limiting path extending adjacent to the second volute and parallel to the turbine housing axis, and a third limiting path extending from the first limiting path to the second limiting path.

[0061] Example 5: The inlet channel system as described in Example 4, wherein the third limiting path defines a first angle with the first limiting path and a second angle with the second limiting path, and wherein the first angle and the second angle are acute angles relative to the turbine housing axis.

[0062] Example 6: The entrance channel system as described in Example 5, wherein the first angle is between 45 and 90 degrees, and the second angle is between 45 and 90 degrees.

[0063] Example 7: The inlet channel system as described in Example 4, wherein the third limiting path defines a first angle with the first limiting path and a second angle with the second limiting path, and wherein the first angle and the second angle are obtuse angles relative to the turbine housing axis.

[0064] Example 8: The entrance passage system as described in Example 7, wherein the first angle is between 90 and 135 degrees, and the second angle is between 90 and 135 degrees.

[0065] Example 9: The inlet channel system as described in Example 4, wherein the third limiting path is orthogonal to the turbine housing axis and to at least one of the first limiting path and the second limiting path.

[0066] Example 10: The inlet channel system as described in Example 1, wherein the limiting path is angled relative to the turbine housing axis.

[0067] Example 11: An inlet channel system as described in any of the preceding examples, wherein the limiting path has a Z-shaped configuration relative to the turbine housing axis.

[0068] Example 12: An inlet channel system as described in any of the preceding examples, wherein the limiting path is defined as 360 degrees around the turbine housing axis.

[0069] Example 13: An inlet channel system as described in any of the preceding embodiments, wherein an abrasive coating is disposed on at least one of the first wall surface and the guide vane partition surface.

[0070] Example 14: An inlet channel system as described in any one of Examples 1-12, wherein a seal is arranged between the first wall surface and the guide vane separating surface.

[0071] Example 15: An inlet channel system as described in any one of Examples 1-12, wherein a metal foam is disposed between the first wall surface and the guide vane separating surface.

[0072] Example 16: An inlet channel system as described in any one of Examples 1-12, wherein para-aramid synthetic fibers are arranged between the first wall surface and the guide vane partition surface.

[0073] Example 17: An inlet channel system as described in any of the preceding examples, wherein the guide vane ring further includes an outer circumferential ring connected to the guide vane partition wall.

[0074] Example 18: An inlet channel system as described in any of the preceding embodiments, wherein the plurality of guide vanes are further defined as a first plurality of guide vanes protruding from the guide vane partition wall into the first volute, and a second plurality of guide vanes protruding from the guide vane partition wall into the second volute.

[0075] Example 19: The entrance channel system as described in Example 18, wherein the first plurality of guide vanes, the second plurality of guide vanes, and the guide vane partition wall are integrally formed with each other.

[0076] Example 20: An inlet channel system as described in any one of Examples 17-19, wherein the plurality of guide vanes, the guide vane partition wall, and the outer circumferential ring are integrally formed with each other.

[0077] Example 21: The inlet channel system as described in any of the preceding embodiments further includes a pin connected to the guide vane ring and the turbine housing to prevent the guide vane ring from rotating relative to the turbine housing.

[0078] Example 22: The inlet channel system as described in Example 21, wherein the pin is connected to the guide vane partition wall.

[0079] Example 23: An inlet channel system as described in any one of Examples 21 and 22, wherein the pin is connected to at least one of the guide vane partition wall and the outer circumferential ring of the guide vane ring and the turbine housing to prevent the guide vane ring from rotating relative to the turbine housing.

[0080] Example 24: An inlet channel system as described in any one of Examples 21-23, wherein the pin extends parallel to the axis of the turbine housing.

[0081] Example 25: An inlet channel system as described in Examples 21-23, wherein the pin extends perpendicularly to the turbine housing axis.

[0082] Example 26: An inlet channel system as described in any one of Examples 21-25, wherein the turbine housing defines a turbine housing slot, and wherein the pin is arranged in the turbine housing slot.

[0083] Example 27: An inlet channel system as described in any one of Examples 21-26, wherein the guide vane partition wall defines a partition slot, and wherein the pin is arranged in the partition slot.

[0084] Example 28: An entrance channel system as described in any one of Examples 21-27, wherein the outer circumferential ring defines an outer annular groove, and wherein the pin is arranged in the outer annular groove.

[0085] Example 29: An inlet channel system as described in any of the preceding embodiments, wherein the wall includes a tongue that forms the first wall surface, and wherein the pin is adjacent to the first wall surface such that the pin is configured as the leading edge of one of the guide vanes.

[0086] Example 30: The inlet channel system as described in Example 21, wherein the pin is further defined as a first pin and further includes a second pin, wherein the first pin is coupled to the guide vane partition wall and the turbine housing, and wherein the second pin is coupled to the outer circumferential ring and the turbine housing.

[0087] Example 31: An inlet channel system as described in Example 30, wherein the guide vane partition wall defines a partition slot and the turbine housing defines a first turbine housing slot, and wherein the first pin is disposed in the partition slot and the first turbine housing slot.

[0088] Example 32: The inlet channel system as described in Example 31, wherein the outer circumferential ring defines an outer guide vane ring slot and the turbine housing defines a second turbine housing slot, and wherein the second pin is arranged in the outer guide vane ring slot and the second turbine housing slot.

[0089] Example 33: The inlet channel system as described in any of the preceding embodiments further includes a spring connected to the guide vane ring for preloading the guide vane ring against the turbine housing to reduce vibration during operation of the split-type volute turbocharger.

[0090] Example 34: An entrance channel system as described in Example 33, wherein the spring is further defined as one of a cup spring, a wave spring, a helical spring, a cloverleaf spring, and a Belleville washer spring.

[0091] Example 35: The inlet channel system as described in any one of Examples 33 and 34 further includes a heat shield connected to the guide vane ring and the spring and arranged between the guide vane ring and the spring relative to the turbine housing axis.

[0092] Example 36: An inlet channel system as described in any of the preceding embodiments, wherein the turbine housing has a first turbine housing surface that engages with the guide vane ring and faces a first direction relative to the turbine housing axis, wherein the outer circumferential ring has a second surface that faces a second direction opposite to the first direction relative to the turbine housing axis, and wherein at least one of the first turbine housing surface and the second surface of the outer circumferential ring is angled relative to the turbine housing axis.

[0093] Example 37: The inlet channel system as described in Example 36, wherein the surface of the first turbine housing is at an angle relative to the axis of the turbine housing.

[0094] Example 38: An inlet channel system as described in any one of Examples 36 and 37, wherein the second surface of the outer circumferential ring is angled relative to the turbine housing axis.

[0095] Example 39: An inlet channel system as described in any of the preceding embodiments, wherein the guide vane partition wall has an inner partition wall tip extending toward the turbine impeller, and wherein the inner partition wall tip is chamfered.

[0096] Example 40: An inlet channel system as described in Example 39, wherein the tip of the inner partition wall has a tip radius defined between itself and the axis of the turbine housing, wherein the turbine impeller has a turbine impeller radius, and wherein the tip radius is 1.05-1.25 times the turbine impeller radius.

[0097] Example 41: An inlet channel system as described in any of the preceding examples, wherein the plurality of guide vanes are fixed to the guide vane partition wall.

[0098] Example 42: An inlet channel system as described in any of the preceding examples, wherein the split-type volute turbocharger is further defined as a dual-volute turbocharger.

[0099] Example 43: An entrance passage system, comprising:

[0100] A split-type volute turbocharger, wherein the split-type volute turbocharger is used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke, the split-type volute turbocharger comprising:

[0101] A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis.

[0102] A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing.

[0103] A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute.

[0104] The turbine casing outlet is in fluid communication with the interior of the turbine casing.

[0105] A wall separating the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing; and

[0106] A guide vane ring, coupled to and disposed within the turbine housing, between a first volute and a second volute, and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall, and wherein the plurality of guide vanes are fixed to the guide vane partition wall; and

[0107] A pin, which is connected to the guide vane ring and the turbine housing, is used to prevent the guide vane ring from rotating relative to the turbine housing.

[0108] Example 44: The inlet channel system as described in Example 43, wherein the pin is connected to the guide vane partition wall.

[0109] Example 45: An inlet passage system as described in any one of Examples 43 and 44, wherein the guide vane ring further includes an outer circumferential ring coupled to the guide vane partition wall, and wherein the pin is coupled to at least one of the guide vane partition wall and the outer circumferential ring of the guide vane ring and the turbine housing to prevent the guide vane ring from rotating relative to the turbine housing.

[0110] Example 46: An inlet channel system as described in any one of Examples 43-45, wherein the pin extends parallel to the axis of the turbine housing.

[0111] Example 47: An inlet channel system as described in Examples 43-46, wherein the pin extends perpendicularly to the turbine housing axis.

[0112] Example 48: An inlet channel system as described in any one of Examples 43-47, wherein the turbine housing defines a turbine housing slot, and wherein the pin is arranged in the turbine housing slot.

[0113] Example 49: An inlet channel system as described in any one of Examples 43-48, wherein the guide vane partition wall defines a partition slot, and wherein the pin is arranged in the partition slot.

[0114] Example 50: An entrance channel system as described in any one of Examples 43-49, wherein the outer circumferential ring defines an outer annular groove, and wherein the pin is arranged in the outer annular groove.

[0115] Example 51: An inlet channel system as described in any one of Examples 43 to 50, wherein the wall includes a tongue that forms the first wall surface, and wherein the pin is adjacent to the first wall surface such that the pin is configured as the leading edge of one of the guide vanes.

[0116] Example 52: The inlet channel system as described in Example 43, wherein the pin is further defined as a first pin and further includes a second pin, wherein the first pin is coupled to the guide vane partition wall and the turbine housing, and wherein the second pin is coupled to the outer circumferential ring and the turbine housing.

[0117] Example 53: An inlet channel system as described in Example 52, wherein the guide vane partition wall defines a partition slot and the turbine housing defines a first turbine housing slot, and wherein the first pin is disposed in the partition slot and the first turbine housing slot.

[0118] Example 54: The inlet channel system as described in Example 53, wherein the outer circumferential ring defines an outer guide vane ring slot and the turbine housing defines a second turbine housing slot, and wherein the second pin is disposed in the outer guide vane ring slot and the second turbine housing slot.

[0119] Example 55: An entrance channel system as described in any one of Examples 45-54, wherein the inner circumferential ring and the outer circumferential ring are integral with each other.

[0120] Example 56: An entrance channel system as described in any one of Examples 45-54, wherein the inner circumferential ring and the outer circumferential ring are separated from each other.

[0121] Example 57: The inlet channel system as described in any one of Examples 45-56, wherein the split-type volute turbocharger is further defined as a dual-volute turbocharger.

[0122] Example 58: An entrance access system, comprising:

[0123] A split-type volute turbocharger, wherein the split-type volute turbocharger is used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke, the split-type volute turbocharger comprising:

[0124] A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis.

[0125] A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing.

[0126] A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute.

[0127] The turbine casing outlet is in fluid communication with the interior of the turbine casing.

[0128] A wall separating the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing; and

[0129] A guide vane ring, the guide vane ring being coupled to the turbine housing and disposed inside the turbine housing, between the first volute and the second volute and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall, wherein the plurality of guide vanes are fixed to the guide vane partition wall, and wherein the guide vane ring further includes an outer circumferential ring coupled to the guide vane partition wall;

[0130] The outer circumferential ring and the guide vane partition wall are separate components.

[0131] Example 59: An inlet channel system as described in Example 58, wherein the plurality of guide vanes are further defined as a first plurality of guide vanes protruding from the guide vane partition wall into the first volute, and a second plurality of guide vanes protruding from the guide vane partition wall into the second volute.

[0132] Example 60: The inlet channel system as described in Example 59, wherein the first plurality of guide vanes, the second plurality of guide vanes, and the guide vane partition wall are integrally formed with each other.

[0133] Example 61: An entrance passage system, comprising:

[0134] A split-type volute turbocharger, wherein the split-type volute turbocharger is used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke, the split-type volute turbocharger comprising:

[0135] A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis.

[0136] A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing.

[0137] A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute.

[0138] The turbine casing outlet is in fluid communication with the interior of the turbine casing.

[0139] A wall separating the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing; and

[0140] A guide vane ring, the guide vane ring being coupled to the turbine housing and disposed inside the turbine housing, between the first volute and the second volute and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall, wherein the plurality of guide vanes are fixed to the guide vane partition wall, and wherein the guide vane ring further includes an outer circumferential ring coupled to the guide vane partition wall;

[0141] The outer circumferential ring and the guide vane partition wall are integrally formed.

[0142] Example 62: The inlet channel system as described in Example 61, wherein the plurality of guide vanes are further defined as a first plurality of guide vanes protruding from the guide vane partition wall into the first volute, and a second plurality of guide vanes protruding from the guide vane partition wall into the second volute.

[0143] Example 63: The inlet channel system as described in Example 62, wherein the plurality of guide vanes, the guide vane partition wall, and the outer circumferential ring are integrally formed with each other.

[0144] Example 64: An entrance passage system, comprising:

[0145] A split-type volute turbocharger, wherein the split-type volute turbocharger is used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke, the split-type volute turbocharger comprising:

[0146] A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis.

[0147] A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing.

[0148] A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute.

[0149] The turbine casing outlet is in fluid communication with the interior of the turbine casing.

[0150] A wall separating the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing; and

[0151] A guide vane ring, the guide vane ring being coupled to the turbine housing and disposed inside the turbine housing, between the first volute and the second volute and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall, wherein the plurality of guide vanes are fixed to the guide vane partition wall, and wherein the guide vane ring further includes an outer circumferential ring coupled to the guide vane partition wall;

[0152] The turbine housing has a first turbine housing surface that engages with the inner circumferential ring and faces a first direction relative to the turbine housing axis. The outer circumferential ring has a second surface that faces a second direction opposite to the first direction relative to the turbine housing axis. At least one of the first turbine housing surface and the second surface of the outer circumferential ring is angled relative to the turbine housing axis.

[0153] Example 65: The inlet channel system as described in Example 64, wherein the surface of the first turbine housing is at an angle relative to the axis of the turbine housing.

[0154] Example 66: An inlet channel system as described in any one of Examples 64 and 65, wherein the second surface of the outer circumferential ring is angled relative to the turbine housing axis.

[0155] Example 67: An entrance passage system, comprising:

[0156] A split-type volute turbocharger, wherein the split-type volute turbocharger is used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, wherein the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders are generally equal for each exhaust stroke, the split-type volute turbocharger comprising:

[0157] A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis.

[0158] A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing.

[0159] A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute.

[0160] The turbine casing outlet is in fluid communication with the interior of the turbine casing.

[0161] A wall that separates the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing;

[0162] A guide vane ring, coupled to and disposed within the turbine housing, between a first volute and a second volute, and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, and wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall; and

[0163] A pin, which is connected to the guide vane ring and the turbine housing, is used to prevent the guide vane ring from rotating relative to the turbine housing;

[0164] The wall includes a tongue that forms the first wall surface, and the pin is adjacent to the first wall surface such that the pin is configured as the leading edge of one of the guide vanes.

[0165] Example 68: An inlet channel system as described in Example 67, wherein the pin extends parallel to the axis of the turbine housing.

[0166] Example 69: An inlet channel system as described in any one of Examples 67 and 68, wherein the guide vane ring further includes an outer circumferential ring connected to the guide vane partition wall.

[0167] Example 70: An inlet channel system as described in any one of Examples 67-69, wherein the plurality of guide vanes are further defined as a first plurality of guide vanes protruding from the guide vane partition wall into the first volute, and a second plurality of guide vanes protruding from the guide vane partition wall into the second volute.

[0168] Example 71: The inlet channel system as described in Example 70, wherein the first plurality of guide vanes, the second plurality of guide vanes, and the guide vane partition wall are integrally formed with each other.

[0169] Example 72: An inlet channel system as described in any one of Examples 69-71, wherein the plurality of guide vanes, the guide vane partition wall, and the outer circumferential ring are integrally formed with each other.

[0170] Example 73: An inlet channel system as described in any one of Examples 67-72, wherein the pin is connected to the guide vane partition wall.

[0171] Example 74: An inlet channel system as described in Example 73, wherein the pin is connected to at least one of the guide vane partition wall and the outer circumferential ring of the guide vane ring and the turbine housing to prevent the guide vane ring from rotating relative to the turbine housing.

[0172] Example 75: An inlet channel system as described in any one of Examples 67-74, wherein the turbine housing defines a turbine housing slot, and wherein the pin is arranged in the turbine housing slot.

[0173] Example 76: An inlet channel system as described in any one of Examples 67-75, wherein the guide vane partition wall defines a partition slot, and wherein the pin is arranged in the partition slot.

[0174] Example 77: An entrance channel system as described in any one of Examples 67-76, wherein the outer circumferential ring defines an outer annular groove, and wherein the pin is arranged in the outer annular groove.

[0175] Example 78: An inlet channel system as described in any one of Examples 67-77, wherein the pin is further defined as a first pin and further includes a second pin, wherein the first pin is coupled to the guide vane partition wall and the turbine housing, and wherein the second pin is coupled to the outer circumferential ring and the turbine housing.

[0176] Example 79: An inlet channel system as described in Example 78, wherein the outer circumferential ring defines an outer guide vane ring slot and the turbine housing defines a second turbine housing slot, and wherein the second pin is disposed in the outer guide vane ring slot and the second turbine housing slot.

[0177] Example 80: An inlet channel system as described in any one of Examples 69-79, wherein the outer circumferential ring and the guide vane partition wall are integral with each other.

[0178] Example 81: The inlet channel system as described in Example 80, wherein the plurality of guide vanes, the guide vane partition wall, and the outer circumferential ring are integrally formed with each other.

[0179] Example 82: An inlet channel system as described in any one of Examples 69-79, wherein the outer circumferential ring and the guide vane partition wall are separate components.

Claims

1. An entrance access system, the entrance access system comprising: A split-type volute turbocharger, the split-type volute turbocharger being used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders being approximately equal for each exhaust stroke, the split-type volute turbocharger comprising: A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis. A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing. A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute. The turbine casing outlet is in fluid communication with the interior of the turbine casing. A wall separating the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing; and A guide vane ring, the guide vane ring being coupled to and disposed within the turbine housing, between the first volute and the second volute and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, and wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall; The first wall surface of the wall and the guide vane partition surface of the guide vane partition wall define a limiting path between each other relative to the turbine housing axis, and at least a portion of the limiting path is not parallel to the turbine housing axis, thereby reducing exhaust leakage from one of the first volute and the second volute to the other of the first volute and the second volute.

2. The entrance passage system according to claim 1, wherein, The limiting path has a tortuous configuration relative to the turbine housing axis.

3. The entrance access system as described in any one of claims 1 and 2, wherein, The limiting path has a curved configuration relative to the turbine housing axis.

4. The entrance access system as described in any one of claims 1 and 2, wherein, The limiting path defined between the guide vane partition surface and the first wall surface of the wall has a first limiting path that extends adjacent to the first volute and parallel to the turbine housing axis, a second limiting path that extends adjacent to the second volute and parallel to the turbine housing axis, and a third limiting path that extends from the first limiting path to the second limiting path.

5. The entrance access system according to claim 4, wherein, The third limiting path defines a first angle with the first limiting path and a second angle with the second limiting path, wherein the first angle and the second angle are acute angles relative to the turbine housing axis.

6. The entrance access system as described in any one of claims 1 and 2, wherein, The restricted path is defined as a 360-degree loop around the turbine housing axis.

7. The entrance access system as described in any one of claims 1 and 2, wherein, The guide vane ring further includes an outer circumferential ring connected to the guide vane partition wall, wherein the outer circumferential ring and the guide vane partition wall are integral with each other.

8. The entrance access system as described in any one of claims 1 and 2, wherein, The guide vane ring further includes an outer circumferential ring connected to the guide vane partition wall, wherein the outer circumferential ring and the guide vane partition wall are separate components.

9. The entrance access system as described in any one of claims 1 and 2, wherein, The plurality of guide vanes are further defined as a first plurality of guide vanes protruding from the guide vane partition wall into the first volute, and a second plurality of guide vanes protruding from the guide vane partition wall into the second volute.

10. The entrance access system according to claim 9, wherein, The first plurality of guide vanes, the second plurality of guide vanes, and the guide vane partition wall are integrally formed with each other.

11. The entrance access system according to claim 9, wherein, The plurality of guide vanes, the guide vane partition wall, and the outer circumferential ring are integrally formed.

12. The inlet passage system of any one of claims 1 and 2, further comprising a pin coupled to the guide vane ring and the turbine housing for preventing the guide vane ring from rotating relative to the turbine housing.

13. The entrance access system according to claim 12, wherein, The pin is connected to the guide vane partition wall.

14. The entrance access system according to claim 12, wherein, The pin is connected to at least one of the guide vane partition wall and the outer circumferential ring of the guide vane ring and the turbine housing to prevent the guide vane ring from rotating relative to the turbine housing.

15. The entrance access system according to claim 12, wherein, The wall includes a tongue that forms the first wall surface, and wherein the pin is adjacent to the first wall surface such that the pin is configured as the leading edge of one of the guide vanes.

16. The entrance access system as claimed in any one of claims 1 and 2, wherein, The turbine housing has a first turbine housing surface that engages with the guide vane ring and faces a first direction relative to the turbine housing axis, wherein the outer circumferential ring has a second surface that faces a second direction opposite to the first direction relative to the turbine housing axis, and wherein at least one of the first turbine housing surface and the second surface of the outer circumferential ring is angled relative to the turbine housing axis.

17. An entrance access system, the entrance access system comprising: A split-type volute turbocharger, the split-type volute turbocharger being used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders being approximately equal for each exhaust stroke, the split-type volute turbocharger comprising: A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis. A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing. A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute. The turbine casing outlet is in fluid communication with the interior of the turbine casing. A wall separating the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing; and A guide vane ring, coupled to and disposed within the turbine housing, between a first volute and a second volute, and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall, and wherein the plurality of guide vanes are fixed to the guide vane partition wall; and A pin, which is connected to the guide vane ring and the turbine housing, is used to prevent the guide vane ring from rotating relative to the turbine housing.

18. The entrance access system according to claim 17, wherein, The wall includes a tongue that forms the first wall surface, and wherein the pin is adjacent to the first wall surface such that the pin is configured as the leading edge of one of the guide vanes.

19. An entrance access system, the entrance access system comprising: A split-type volute turbocharger, the split-type volute turbocharger being used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, the relative pulses of exhaust gas delivered from the first group of cylinders and the second group of cylinders being approximately equal for each exhaust stroke, the split-type volute turbocharger comprising: A turbine housing, comprising a turbine housing interior adapted to receive a turbine impeller having a plurality of turbine blades, the turbine housing extending along a turbine housing axis. A first volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the first set of cylinders into the turbine housing. A second volute, adapted to be in fluid communication with the interior of the internal combustion engine and the turbine housing, is used to deliver exhaust gas from the second set of cylinders into the turbine housing independently of the first volute. The turbine casing outlet is in fluid communication with the interior of the turbine casing. A wall that separates the first volute from the second volute, wherein the wall has a first wall surface facing the axis of the turbine housing; A guide vane ring, coupled to and disposed within the turbine housing, between a first volute and a second volute, and surrounding the turbine impeller, wherein the guide vane ring includes a guide vane partition wall further separating the first volute and the second volute, wherein the guide vane partition wall has a guide vane partition surface facing the first wall surface, and wherein the guide vane ring includes a plurality of guide vanes coupled to the guide vane partition wall; and A pin, which is connected to the guide vane ring and the turbine housing, is used to prevent the guide vane ring from rotating relative to the turbine housing; The wall includes a tongue that forms the first wall surface, and the pin is adjacent to the first wall surface such that the pin is configured as the leading edge of one of the guide vanes.

20. The entrance access system according to claim 19, wherein, The pin extends parallel to the axis of the turbine housing.

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