ENTRY SYSTEM THAT INCLUDES A SPLIT SPIRAL TURBOCHARGER

Abstract

An inlet system comprises a split-spiral turbocharger, including a turbine housing, a first spiral, a second spiral, a turbine housing outlet, and a wall separating the first spiral from the second spiral. The wall has a first wall surface. The inlet system further includes a blade ring. The blade ring includes a blade partition that further separates the first spiral from the second spiral. The blade partition has a blade parting surface that faces the first wall surface. The blade ring includes several blades coupled to the blade partition. The first wall surface and the blade parting surface define a confinement path between each other. At least one segment of the confinement path is non-parallel, so that exhaust gas leakage from the first or second spiral to the other—the first or the second—is reduced.

Description

CROSS-REFERENCE TO RELATED REGISTRATIONS

[0001] The present application claims priority over the preliminary US patent application No. 63 / 644,172 filed on May 8, 2024, and the application in its entirety is hereby incorporated by reference. BACKGROUND OF REVELATION 1. Territory of Revelation

[0002] This invention relates generally to an inlet system comprising a turbocharger with a segmented spiral and variable turbine geometry. 2. Description of the related technology

[0003] Turbochargers draw exhaust gas from an internal combustion engine and supply it with compressed air. Turbochargers increase the engine's power output, reduce its fuel consumption, and / or lower its emissions. The turbocharger's supply of compressed air allows the engine to be smaller while still delivering the same or similar power as larger naturally aspirated engines. Using a smaller engine in a vehicle reduces its mass and frontal area, which contributes to lower fuel consumption and improved fuel economy.

[0004] Some turbochargers incorporate a turbine with a segmented spiral housing, and these turbochargers are alternatively referred to as segmented spiral turbochargers, which includes twin-spiral turbochargers, dual-outlet turbochargers, and the like. The spirals of a segmented spiral turbine housing are generally isolated from one another, so that no exhaust gas mixing occurs until the exhaust gas has passed a tongue or tongues of the respective spirals. The segmented spiral turbine housing includes a turbine inlet, a turbine outlet, and an internal volume. The turbine inlet is configured for attachment to an internal combustion engine (e.g., to an exhaust manifold or cylinder head of an internal combustion engine) and includes multiple inlet channels configured to flow into the exhaust paths of the internal combustion engine after attachment.The internal volume of the turbine housing defines at least two segmented spirals, which are connected to the respective inlet channels for supplying exhaust gas from the combustion engine to a turbine wheel located within the internal volume. After the energy has been extracted from the exhaust gas by the turbine wheel, the exhaust gas exits the turbine housing via the turbine outlet. The spirals guide the exhaust gas from the engine's exhaust manifold into an arc-shaped flow, distributing it around the circumference of the turbine wheel to rotate it.

[0005] Turbochargers also include a compressor. The compressor comprises a compressor wheel that is coupled to the turbine wheel via a shaft. The compressor is driven by the rotation of the turbine wheel, which in turn drives a compressor wheel within the compressor housing.

[0006] In multi-cylinder engines, cylinders fire in a specific sequence. For example, in a four-cylinder inline engine, where the cylinders are numbered 1 through 4, the firing order might be 1-3-4-2. A group of cylinders can be grouped into a "bank." In the example above, the first cylinder bank comprises cylinders 1 and 4, and the second cylinder bank comprises cylinders 2 and 3. In a "V" engine, the cylinder banks may be separated across the engine, and multiple cylinders may fire simultaneously. In the case of an inline engine, the cylinder banks could simply be the front cylinders and the rear cylinders, or an alternative cylinder grouping as described above. Exhaust flow is not a uniform flow, as exhaust gases exit each cylinder based on the engine's firing order, resulting in intermittent exhaust pulses. The exhaust gas from each bank is routed to the turbine housing in respective manifolds.The manifolds can be pipes and / or piping attached to the internal combustion engine or can be integral to the engine (e.g., manifold piping cast into the engine's cylinder head). By separating the exhaust gas flows, the pressure pulses that occur when exhaust gas is released from the cylinder can be retained through the spirals so that they impart their force to the turbine wheel. Retaining these pulses is generally desirable because the pressure pulses transfer torque to the turbine wheel, causing it to accelerate faster and reducing turbocharger response time. Effectively separating the gas flows also reduces the immediate back pressure in the "unignited" spiral. The term "ignited" spiral refers to the spiral through which the pressure pulses pass.This separation of the pressure pulses begins at the exhaust of each cylinder and is maintained in the exhaust manifold up to the turbine inlet (sometimes alternatively referred to as a turbine inlet spiral housing). In the area where the exhaust gases are admitted to the turbine housing, a partition between the individual spirals can help maintain the separation of exhaust gases from each cylinder or cylinder group, thus preserving the pressure pulses. However, exhaust gas leakage between individual spirals often still occurs, leading to reduced performance and efficiency of the turbocharger.

[0007] To aid in the uniform guidance and control of the exhaust gas flow from the spiral or segmented spirals to the turbine wheel, a multi-blade guide vane ring (sometimes alternatively referred to as a nozzle ring or stationary nozzle guide vane) can be arranged on an annular disk inside the turbine casing between the spirals and the turbine wheel. These blades can be fixed to the annular disk (sometimes alternatively referred to as a fixed nozzle ring or fixed stationary nozzle guide vane) or can be rotatably coupled to the annular disk (sometimes alternatively referred to as a variable nozzle ring or variable stationary nozzle guide vane) to create a variable turbine geometry (VTG).

[0008] Typically, the rotating blades on the blade ring are evenly spaced and positioned at the same radial distance from the turbine wheel's axis of rotation. Furthermore, these rotating blades are usually at the same angle to a radial line drawn from the axis of rotation. The number of rotating blades on the blade ring is generally odd, such as a prime number, thus creating a degree of asymmetry along the blade ring that corresponds to the odd number of evenly spaced blades.

[0009] Therefore, there remains a need to reduce exhaust gas leakage from one of the spirals to the other. BRIEF SUMMARY OF THE INVENTION

[0010] An intake system comprises a split-coil turbocharger for receiving exhaust gas from an internal combustion engine and supplying compressed air to the engine. The internal combustion engine comprises a first set of cylinders and a second set of cylinders, with the relative momentum of the exhaust gas supplied by the first and second sets of cylinders being generally the same for each exhaust stroke. The split-coil turbocharger comprises a turbine housing, which includes a turbine housing interior designed to accommodate a turbine wheel with multiple turbine blades. The turbine housing extends along a turbine housing axis.The split-coil turbocharger also comprises a first coil, which is designed to connect to the combustion engine and the turbine housing interior for supplying exhaust gas from the first set of cylinders to the turbine housing interior, and a second coil, which is designed to connect to the combustion engine and the turbine housing interior for supplying exhaust gas from the second set of cylinders to the turbine housing interior independently of the first coil. The split-coil turbocharger further comprises a turbine housing outlet in flow connection with the turbine housing interior and a wall that separates the first coil from the second coil. The wall has a first wall surface that faces the turbine housing axis. The inlet system comprises a blade ring that is coupled to the turbine housing and arranged inside the turbine housing between the first and second coils and around the turbine wheel.The blade ring includes a blade partition that further separates the first spiral from the second spiral. The blade partition has a blade parting surface that faces the first wall surface. The blade ring comprises several blades coupled to the blade partition. The first wall surface of the partition and the blade parting surface of the blade partition define a confinement path between each other with respect to the turbine casing axis. At least one section of the confinement path is not parallel to the turbine casing axis, thus reducing exhaust gas leakage from the first or second spiral to the other spiral. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Further advantages of the present disclosure will become readily apparent with a better understanding of the invention by reference to the following detailed description when viewed in conjunction with the accompanying drawings. Fig. Figure 1 is a cross-sectional side view of an inlet system comprising a segmented spiral turbocharger, wherein the segmented spiral turbocharger comprises a turbine housing configured to receive a turbine wheel, the turbine housing extending along a turbine housing axis, and wherein the segmented spiral turbocharger also comprises a first spiral, a second spiral, a turbine housing outlet and a wall, and wherein the inlet system further comprises a blade ring coupled to the turbine housing and arranged inside the turbine housing. Fig. Figure 2 is a cross-sectional side view of the inlet system, wherein the wall has a first wall surface pointing towards the turbine casing axis, wherein the blade ring comprises a blade partition wall with a blade parting surface pointing towards the first wall surface, wherein the first wall surface and the blade parting surface define a constraint path between each other with respect to the turbine casing axis, and wherein at least one section of the constraint path is not parallel to the turbine casing axis, such that exhaust gas leakage from the first or the second spiral to the other spiral - the first or the second - is reduced. Fig. Figure 3 is a top view of the inlet system, wherein the inlet system comprises a pin coupled to the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing, wherein the wall of the turbine housing has a tongue, wherein one blade of the multiple blades has a leading edge, and wherein the pin is adjacent to the first wall surface such that the pin is configured to be a leading edge of one of the blades. Fig. Figure 4 is a cross-sectional side view of the inlet system, wherein the turbine casing defines a turbine casing slot, wherein the blade partition defines a separating slot, and wherein the pin is positioned in the turbine casing slot and the separating slot. Fig. Figure 5 is a cross-sectional side view of the inlet system, wherein the outer circumferential ring defines an outer annular slot and wherein the pin is arranged in the outer annular slot and the turbine housing slot. Fig. Figure 6 is a cross-sectional close-up view of the entry system of Fig. 5. Fig. Figure 7 is a cross-sectional side view of the inlet system, wherein the pin is further defined as a first pin and further comprising a second pin, wherein the first pin is coupled to the blade partition and the turbine housing, wherein the second pin is coupled to the outer circumferential ring and the turbine housing, wherein the first pin is arranged in the partition slot and a first turbine housing slot, and wherein the second pin is arranged in a second turbine housing slot and the outer blade ring slot. Fig. Figure 8 is an expanded view of the inlet system, wherein the blade ring and the outer circumferential ring are separate components and wherein the inlet system further comprises a spring. Fig. Figure 9 is a cross-sectional side view of the inlet system, wherein the spring is coupled to the blade ring for pre-tensioning the blade ring to the turbine housing to reduce vibrations during operation of the segmented spiral turbocharger. Fig. Figure 10 is a perspective view of the inlet system, wherein the turbine casing has a first turbine casing surface pointing in a first direction, wherein the outer circumferential ring has a second surface pointing in a second direction opposite to the first direction, and wherein the first turbine casing surface and the second turbine surface are angled with respect to the turbine casing axis. DETAILED DESCRIPTION OF THE INVENTION

[0012] Referring to the figures in which the same numbers indicate the same parts in all of the several views, it is stated in Fig. Figure 1 shows an inlet system 30 in general terms. The inlet system 30 comprises a turbocharger 32 with a segmented spiral for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine. The internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein the relative momentum of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke.

[0013] With continued reference to Fig. 1 The turbocharger 32 with segmented spiral comprises a turbine housing 34, which includes a turbine housing interior 36 designed to accommodate a turbine wheel 38 with multiple turbine blades 40. The turbine housing 34 extends along a turbine housing axis THA.

[0014] The turbocharger 32 with a segmented spiral can comprise a turbocharger shaft 41 rotatably coupled to the turbine wheel 38, and can comprise a compressor wheel 43 rotatably coupled to the turbocharger shaft 41. The turbocharger 32 with a segmented spiral also comprises a first spiral 42, which is configured for flow connection with the internal combustion engine and the turbine housing interior 36 for supplying exhaust gas from the first set of cylinders to the turbine housing interior 36, and a second spiral 44, which is configured for flow connection with the internal combustion engine and the turbine housing interior 36 for supplying exhaust gas from the second set of cylinders to the turbine housing interior 36 independently of the first spiral 42.

[0015] The turbocharger 32 with segmented spiral further comprises a turbine housing outlet 46 in flow communication with the turbine housing interior 36 and a wall 48 that separates the first spiral 42 from the second spiral 44. With reference to Fig. 2 The wall 48 has a first wall surface that points towards the turbine housing axis THA.

[0016] With continued reference to Fig. The inlet system 30 also includes a blade ring 52, which is coupled to the turbine housing 34 and arranged inside the turbine housing 36 between the first and second spirals 42, 44 and around the turbine wheel 38. The blade ring 52 includes a blade partition 54, which further separates the first spiral 42 from the second spiral 44. In other words, the blade partition 54 is functionally aligned with the wall 48 of the turbine housing 34 to extend the wall 48 of the turbine housing 34 further towards the turbine wheel 38, thus further separating the first spiral 42 from the second spiral 44. The blade partition 54 has a blade parting surface 56 that faces the first wall surface 50, and the blade ring 52 includes several blades 58 that are coupled to the blade partition 54.Although not necessary, the multiple blades 58 can further be defined as multiple first blades 60 projecting from the blade partition 54 and into the first spiral 42, and multiple second blades 62 projecting from the blade partition 54 and into the second spiral 44. Typically, the multiple blades 58 are fixed to the blade partition 54. In other words, all blades of the multiple blades 58 are immovable with respect to the blade partition 54. In such embodiments, the blade ring 52 can be referred to as a fixed blade ring. Depending on the application of the inlet system 30, the blade ring 52 can be optimized, for example, by... B. Adjusting different dimensions of the blade ring 52 and / or the angle of the multiple blades 58. As mentioned above, the inlet system 30 with the blade ring 52 increases the efficiency of the inlet system 30 / the turbocharger 32 with segmented spiral, such asan increase in efficiency of 1-3%.

[0017] The first wall surface 50 of the wall 48 and the blade parting surface 56 of the blade partition 54 define a constraint path 64 between them with respect to the turbine casing axis THA. At least one section of the constraint path 64 is not parallel to the turbine casing axis THA, so that exhaust gas leakage from the first or the second spiral 42, 44 to the other spiral—the first or the second 42, 44—is reduced. It is understood that the constraint path 64 includes embodiments in which the first wall surface 50 and the blade parting surface 56 are in engagement with each other, and in which the first wall surface 50 and the blade parting surface are spaced apart to accommodate thermal deformation of the turbine casing 34. In either of these two embodiments, exhaust gas leakage between the first spiral 42 and the second spiral 44 is reduced.When exhaust gas leakage between the first spiral 42 and the second spiral 44 is reduced, the flow of exhaust gas to the turbine wheel 38 is improved, thereby promoting better performance and efficiency of the split-spiral turbocharger 32. By improving the performance and efficiency of the split-spiral turbocharger 32, fuel economy (enabling vehicle manufacturers to meet current and future emissions regulations) and the thermal efficiency of the internal combustion engine are also improved, as is the durability of the intake system 30.

[0018] It is understood that throughout this disclosure, references to the turbine casing axis THA may also include relationships of various components to other axes, such as a blade ring axis, turbocharger shaft axis, rotor axis, etc. For example, the first wall surface 50 of the wall 48 and the blade parting surface 56 of the blade partition 54 may define the constraint path 64 between them with respect to the blade ring axis. As another example, the first wall surface 50 of the wall 48 and the blade parting surface 56 of the blade partition 54 may define the constraint path 64 between them with respect to the turbocharger shaft axis. As yet another example, the first wall surface 50 of the wall 48 and the blade parting surface 56 of the blade partition 54 may define the constraint path 64 between them with respect to a rotor axis.The turbine housing axis THA, the blade ring axis, the turbocharger shaft axis, and a rotor axis may be concentric with each other. Alternatively, the turbine housing axis, the blade ring axis, the turbocharger shaft axis, and the rotor axis may not be concentric with each other, or some of the axes may be concentric with each other while other axes are not concentric with each other. It is understood that all other references to the turbine housing axis THA throughout this disclosure are intended to apply equally to other axes of the inlet system 30, such as the blade ring axis, turbocharger shaft axis, rotor axis, and the like.

[0019] The constraint path 64 can be any path defined between the blade parting line 56 and the first wall surface 50, where at least one section of the path is not parallel with respect to the turbine casing axis THA. For example, the constraint path 64 can have a helical configuration with respect to the turbine casing axis THA. As another example, the constraint path 64 can have a serpentine configuration with respect to the turbine casing axis THA. As another example, the constraint path 64 can have a curved configuration with respect to the turbine casing axis THA. As another example, the constraint path 64 can be angled with respect to the turbine casing axis THA. As another example, the constraint path 64 can have a stepped configuration.

[0020] As another example according to the representation in Fig. 2. The constraint path 64 can comprise a first constraint path 66, which adjoins the first spiral 42 and extends parallel to the turbine housing axis THA, a second constraint path 68, which adjoins the second spiral 44 and extends parallel to the turbine housing axis THA, and a third constraint path 70, which extends from the first constraint path 66 to the second constraint path 68. In such embodiments, the third constraint path 70 can define a first angle θ1 with respect to the first constraint path 66 and can define a second angle θ2 with respect to the second constraint path 68. The first and second angles θ1, θ2 can be acute with respect to the turbine housing axis THA. If the first and second angles θ1, θ2 with respect to the turbine casing axis THA are acute, the first angle θ1 can be between 45-90 degrees and the second angle θ2 can be between 45-90 degrees.Alternatively, the first and second angles θ1, θ2 with respect to the turbine casing axis THA can be obtuse. If the first and second angles θ1, θ2 with respect to the turbine casing axis THA are obtuse, 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 constraint path 70 with respect to the turbine casing axis THA and / or the first and second constraint paths 66, 68 can be orthogonal. Constraint path 64 can have a Z-configuration with respect to the turbine casing axis THA. In embodiments where the constraint path 64 has a Z configuration, the constraint path 64 can have the first constraint path 66, the second constraint path 68 and the third constraint path 70, wherein the first, the second and the third constraint paths 66, 68, 70 define the Z configuration.

[0021] Because at least one section of the constraint path 64 is not parallel to the turbine casing axis THA, exhaust gas leakage from the first or second spiral 42, 44 to the other spiral – the first or the second 42, 44 – is reduced. Although not required and although not explicitly shown in the figures, a friction lining can be arranged on the first wall surface 50 and / or the blade parting surface 56 to further reduce exhaust gas leakage from the first or second spiral 42, 44 to the other spiral – the first or the second 42, 44. Alternatively, a seal can be arranged between the first wall surface 50 and the blade parting surface 56. Alternatively, a metallic foam can be arranged between the first wall surface 50 and the blade parting surface 56. Alternatively, a para-aramid synthetic fiber, such as...Kevlar® is positioned between the first wall surface 50 and the blade parting surface 56.

[0022] The multiple first blades 60, the multiple second blades 62 and the blade partition 54 can be integral to each other, as in Fig. 1, 2, 4-7 and 9 are shown. As in Fig. As shown in Figures 1-9, the blade ring 52 can include an outer circumferential ring 72 coupled to the partition 48. It is understood that the outer circumferential ring 72 can further be referred to as a support plate. The multiple blades 58, which can include the multiple first blades 60 and the multiple second blades 62, the blade partition 54, and the outer circumferential ring 72 can be integral (i.e., one piece) to each other. Alternatively, the outer circumferential ring 72 and the blade ring 52 can be separate components, as shown in Figure 1-9. Fig. 8 is shown.

[0023] With reference to Fig. In the case of 1 and 3-8, the inlet system 30 may further comprise a pin 74, which is coupled to the blade ring 52 and the turbine housing 34, to prevent rotation of the blade ring 52 relative to the turbine housing 34. A circumferential force of exhaust gas on the multiple blades 58, as well as thermal deformation of the turbine housing 34, can lead to rotation and wear of the blade ring 52 and other components of the inlet system 30; however, in the inlet system 30, which comprises the pin 74 coupled to the blade ring 52 and the turbine housing 34, rotation of the blade ring 52 relative to the turbine housing 34 is prevented, and thus wear on the blade ring 52 is reduced compared to inlet systems that allow rotation of the blade ring relative to the turbine housing.

[0024] In an embodiment according to the illustration in Fig. In figures 1 and 3-7, the pin 74 is coupled to the blade partition 54. In a further embodiment, the pin 74 is coupled to the blade partition 54 and / or the outer circumferential ring 72 of the blade ring 52 and the turbine housing 34 to prevent rotation of the blade ring 52 relative to the turbine housing 34. The pin 74 can extend parallel to the turbine housing axis THA, or alternatively, the pin 74 can extend perpendicular to the turbine housing axis THA.

[0025] To secure the pin 74, the turbine housing 34 can define a turbine housing slot 76, wherein the pin 74 is arranged in the turbine housing slot 76. Alternatively or additionally, the blade partition 54 can define a partition slot 78, wherein the pin 74 is arranged in the partition slot 78.

[0026] In embodiments in which the paddle ring 52 comprises the outer circumferential ring 72, the outer circumferential ring 72 can define an outer ring slot 80, wherein the pin 74 is arranged in the outer ring slot 80.

[0027] With reference to Fig. 3. The wall 48 can include a tongue 82, wherein the tongue 82 represents the first wall surface 50. In such embodiments, the pin 74 can adjoin the first wall surface 50, such that the pin 74 is configured to be a leading edge 83 of one of the blades of the multiple blades 58. By configuring the pin 74 as the leading edge 83 of one of the blades of the multiple blades 58, it is permitted for the pin 74 to conduct exhaust gas flow. The pin 74 can advantageously be configured to conduct the exhaust gas flow through the multiple blades 58 such that the leading edge is curved, angled, or otherwise configured to conduct the exhaust gas flow through the multiple blades 58.Furthermore, the leading edge 83 of the pin 74 can be located below the tongue 82, thereby mitigating or even eliminating any interruption of the exhaust flow and / or any side-to-side leakage around the pin when exhaust gas flows through the blade ring 52, as it follows the tongue 82.

[0028] It is understood that the pin 74 can further be defined as a first pin 84 and that the inlet system 30 can comprise a second pin 86. In such embodiments, the first pin 84 can be coupled to the blade partition 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 separating slot 78 and the turbine housing slot 76, as shown in Fig. Figure 7 shows that the outer circumferential ring 72 can define an outer blade annular slot 88, and the turbine housing 34 can define a second turbine housing slot 90, with the second pin 86 being arranged in the outer blade annular slot 88 and the second turbine housing slot 90.

[0029] As in Fig. 8 and Fig. As shown in Figure 9, the inlet system 30 can include a spring 91 coupled to the blade ring 52 to preload the blade ring 52 against the turbine housing 34 to reduce vibrations during operation of the segmented spiral turbocharger 32 and also to reduce any end-side leakage of the blade ring 52. In one embodiment, the spring 91 can further be defined as a disc spring, wave spring, coil spring, leaf spring, Belleville washer, or the like. The spring 91 can also preload the blade ring 52 during installation of the blade ring 52. The inlet system 30 can include a heat shield 92 coupled to the blade ring 52 and the spring 91 and arranged between them with respect to the turbine housing axis THA. The inlet system 30 can include an adapter 94 coupled to the heat shield 92 and the blade ring 52 and arranged between them.

[0030] With reference to Fig. 2 and Fig. 10. The turbine housing 34 can have a first turbine housing surface 96 which engages with the blade ring 52 and points in a first direction with respect to the turbine housing axis THA, and the outer circumferential ring 72 can have a second surface 98 which points in a second direction opposite to the first direction with respect to the turbine housing axis THA. The first turbine housing surface 96 and / or the second surface 98 of the outer circumferential ring 72 are angled with respect to the turbine housing axis THA. In one embodiment, the first turbine housing surface 96 is angled with respect to the turbine housing axis THA, and additionally or alternatively, the second surface 98 of the outer circumferential ring 72 is also angled with respect to the turbine housing axis THA.By angling the second surface 98 and the first turbine casing surface with respect to the turbine casing axis THA, a conical configuration is created which can be helpful when aligning and pre-tensioning the blade ring 52 during the assembly of the inlet system 30.

[0031] With reference to Fig. 2 and Fig. 5. The blade partition 54 can have an inner partition tip 100 extending to the turbine wheel 38, and the inner partition tip 100 can be chamfered. The inner partition tip 100 can have a tip radius TR defined with the turbine casing axis THA between it and the turbine wheel 38, and the turbine wheel 38 can have a turbine wheel radius TWR, wherein the tip radius TR is optionally 1.05-1.25 times larger than the turbine wheel radius TWR or 1.15-1.25 times larger.

[0032] It is understood that the turbocharger 32 with divided spiral may further be defined as a twin-scroll turbocharger (often referred to as a twin-scroll turbocharger, the first and second scrolls being parallel around 360 degrees of the turbine wheel inlet), a twin-scroll turbocharger, and the like.

[0033] In a further embodiment, the inlet system 30 comprises the turbocharger 32 with a segmented spiral for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine. The internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein the relative impulse of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke. The turbocharger 32 with a segmented spiral comprises the turbine housing 34, which includes the turbine housing interior 36 configured to accommodate the turbine wheel 38 with the multiple turbine blades 40. The turbine housing 34 extends along the turbine housing axis THA.The turbocharger 32 with a segmented spiral also comprises the first spiral 42, which is configured for flow communication with the internal combustion engine and the turbine housing interior 36 for supplying exhaust gas from the first set of cylinders to the turbine housing interior 36, and the second spiral 44, which is configured for flow communication with the internal combustion engine and the turbine housing interior 36 for supplying exhaust gas from the second set of cylinders to the turbine housing interior 36 independently of the first spiral 42. The turbocharger 32 with a segmented spiral further comprises the turbine housing outlet 46 in flow communication with the turbine housing interior 36 and the wall 48, which separates the first spiral 42 from the second spiral 44. With reference to . Fig. 2. Wall 48 has a first wall surface that points towards the turbine casing axis THA. With further reference to Fig.2 The inlet system 30 also includes the blade ring 52, which is coupled to the turbine housing 34 and arranged inside the turbine housing 36 between the first and second spirals 42, 44 and around the turbine wheel 38. The blade ring 52 includes the blade partition 54, which further separates the first spiral 42 from the second spiral 44. The blade partition 54 has the blade parting surface 56, which faces the first wall surface 50, and the blade ring 52 includes the multiple blades 58 that are coupled to the blade partition 54. The inlet system 30 further includes a pin that is coupled to the blade ring 52 and the turbine housing 34 to prevent rotation of the blade ring 52 relative to the turbine housing 34. The wall 48 includes the tongue 82, the tongue 82 being the first wall surface 50.The pin 74 abuts the first wall surface 50, such that the pin 74 is configured to be the leading edge 83 of one of the blades of the multiple blades 58. By being configured as the leading edge 83 of one of the blades of the multiple blades 58, the pin 74 is permitted to conduct exhaust gas flow. The pin 74 can advantageously be configured to guide the exhaust gas flow through the multiple blades 58, such that the leading edge is curved, angled, or otherwise configured to guide the exhaust gas flow through the multiple blades 58. Furthermore, the leading edge 83 of the pin 74 can be located below the tongue 82, thereby mitigating or even eliminating any interruption of the exhaust gas flow and / or any side-to-side leakage around the pin as exhaust gas flows through the blade ring 52, since it follows the tongue 82.

[0034] Although the present invention is described above, it is understood that the present invention can also be defined according to the following embodiments: Embodiment 1: Entry system comprising the following: A split-spiral turbocharger for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine, wherein the internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein a relative impulse of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke, wherein the split-spiral turbocharger comprises: a turbine casing comprising a turbine casing interior designed to accommodate a turbine wheel with multiple turbine blades, wherein the turbine casing extends along a turbine casing axis, a first spiral, designed for flow connection with the combustion engine and the turbine housing interior to supply exhaust gas from the first set of cylinders to the turbine housing interior, a second spiral, designed to connect the combustion engine and the turbine housing interior to supply exhaust gas from the second set of cylinders to the turbine housing interior independently of the first spiral, a turbine casing outlet in flow connection with the turbine casing interior, and a wall separating the first spiral from the second spiral, the wall having a first wall surface pointing towards the turbine casing axis, and a blade ring coupled to the turbine casing and arranged inside the turbine casing between the first and second spirals and around the turbine wheel, wherein the blade ring comprises a blade partition wall further separating the first spiral from the second spiral, the blade partition wall having a blade parting surface facing the first wall surface, and wherein the blade ring comprises several blades coupled to the blade partition wall; wherein the first wall surface of the wall and the blade parting surface of the blade partition define a constraint path between each other with respect to the turbine casing axis and wherein at least one section of the constraint path is not parallel to the turbine casing axis, such that exhaust gas leakage from the first or the second spiral to the other spiral - the first or the second - is reduced. Embodiment 2: Inlet system according to embodiment 1, wherein the restriction path has a coiled configuration with respect to the turbine housing axis. Embodiment 3: Inlet system according to one of the preceding embodiments, wherein the restriction path has a curved configuration with respect to the turbine housing axis. Embodiment 4: Inlet system according to one of the preceding embodiments, wherein the confinement path defined between the blade parting surface and the first wall surface of the wall comprises a first confinement path adjacent to the first spiral and extending parallel to the turbine casing axis, a second confinement path adjacent to the second spiral and extending parallel to the turbine casing axis, and a third confinement path extending from the first confinement path to the second confinement path. Embodiment 5: Inlet system according to embodiment 4, wherein the third constraint path defines a first angle to the first constraint path and defines a second angle to the second constraint path, and wherein the first and second angles are acute with respect to the turbine housing axis. Embodiment 6: Entry system according to embodiment 5, wherein the first angle is between 45-90 degrees and the second angle is between 45-90 degrees. Embodiment 7: Inlet system according to embodiment 4, wherein the third constraint path defines a first angle to the first constraint path and defines a second angle to the second constraint path, and wherein the first and second angles are obtuse with respect to the turbine housing axis. Embodiment 8: Entry system according to embodiment 7, wherein the first angle is between 90-135 degrees and the second angle is between 90-135 degrees. Embodiment 9: Inlet system according to embodiment 4, wherein the third restriction path is orthogonal with respect to the turbine housing axis and / or the first and second restriction paths. Embodiment 10: Inlet system according to embodiment 1, wherein the restriction path is angled with respect to the turbine housing axis. Embodiment 11: Inlet system according to one of the preceding embodiments, wherein the restriction path has a Z-configuration with respect to the turbine housing axis. Embodiment 12: Inlet system according to one of the preceding embodiments, wherein the restriction path is defined to 360 degrees around the turbine housing axis. Embodiment 13: Entry system according to one of the preceding embodiments, wherein a rubbing surface is arranged on the first wall surface and / or the blade parting surface. Embodiment 14: Inlet system according to one of embodiments 1-12, wherein a seal is arranged between the first wall surface and the blade parting surface. Embodiment 15: Inlet system according to one of embodiments 1-12, wherein a metallic foam is arranged between the first wall surface and the blade parting surface. Embodiment 16: Inlet system according to one of embodiments 1-12, wherein a para-aramid synthetic fiber is arranged between the first wall surface and the blade parting surface. Embodiment 17: Inlet system according to one of the preceding embodiments, wherein the blade ring further comprises an outer circumferential ring coupled to the blade partition. Embodiment 18: Inlet system according to one of the preceding embodiments, wherein the multiple blades are further defined as multiple first blades projecting from the blade partition and into the first spiral, and multiple second blades projecting from the blade partition and into the second spiral. Embodiment 19: Inlet system according to embodiment 18, wherein the multiple first blades, the multiple second blades and the blade partition are integral to each other. Embodiment 20: Inlet system according to one of embodiments 17-19, wherein the multiple blades, the blade partition and the outer circumferential ring are integral to each other. Embodiment 21: Inlet system according to one of the preceding embodiments, further comprising a pin coupled to the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing. Embodiment 22: Entry system according to embodiment 21, wherein the pin is coupled to the blade partition. Embodiment 23: Inlet system according to one of embodiments 21 and 22, wherein the pin is coupled to the blade partition and / or the outer circumferential ring of the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing. Embodiment 24: Entry system according to one of embodiments 21-23, wherein the pin extends parallel to the turbine housing axis. Embodiment 25: Inlet system according to one of embodiments 21-23, wherein the pin extends perpendicular to the turbine housing axis. Embodiment 26: Entry system according to one of embodiments 21-25, wherein the turbine housing defines a turbine housing slot and wherein the pin is arranged in the turbine housing slot. Embodiment 27: Inlet system according to one of embodiments 21-26, wherein the blade partition defines a separation slot and wherein the pin is arranged in the separation slot. Embodiment 28: Entry system according to one of embodiments 21-27, wherein the outer circumferential ring defines an outer ring slot and wherein the pin is arranged in the outer ring slot. Embodiment 29: Inlet system according to one of the preceding embodiments, wherein the wall comprises a tongue, wherein the tongue constitutes the first wall surface and wherein the pin is adjacent to the first wall surface such that the pin is configured to be a leading edge of one of the blades. Embodiment 30: Inlet system according to embodiment 21, wherein the pin is further defined as a first pin and which further comprises a second pin, wherein the first pin is coupled to the blade partition and the turbine housing and wherein the second pin is coupled to the outer circumferential ring and the turbine housing. Embodiment 31: Inlet system according to embodiment 30, wherein the blade partition defines a separation slot and the turbine housing defines a first turbine housing slot, and wherein the first pin is arranged in the separation slot and the first turbine housing slot. Embodiment 32: Inlet system according to embodiment 31, wherein the outer circumferential ring defines an outer blade annular slot and the turbine housing defines a second turbine housing slot, and wherein the second pin is arranged in the outer blade annular slot and the second turbine housing slot. Embodiment 33: Inlet system according to one of the preceding embodiments, further comprising a spring coupled to the blade ring for pre-tensioning the blade ring to the turbine housing for reducing vibrations during operation of the segmented spiral turbocharger. Embodiment 34: Entry system according to embodiment 33, wherein the spring is further defined as a disc spring, wave spring, coil spring, leaf spring or Belleville spring washer. Embodiment 35: Inlet system according to one of embodiments 33 and 34, which further comprises a heat shield coupled to the blade ring and the spring and arranged between them with respect to the turbine housing axis. Embodiment 36: Inlet system according to one of the preceding embodiments, wherein the turbine housing has a first turbine housing surface which engages with the blade ring and points in a first direction with respect to the turbine housing axis, wherein the outer circumferential ring has a second surface which points in a second direction opposite to the first direction with respect to the turbine housing axis, and wherein the first turbine housing surface and / or the second surface of the outer circumferential ring are angled with respect to the turbine housing axis. Embodiment 37: Inlet system according to embodiment 36, wherein the first turbine housing surface is angled with respect to the turbine housing axis. Embodiment 38: Inlet system according to one of embodiments 36 and 37, wherein the second surface of the outer circumferential ring is angled with respect to the turbine housing axis. Embodiment 39: Inlet system according to one of the preceding embodiments, wherein the blade partition has an inner partition tip extending to the turbine wheel, and wherein the inner partition tip is chamfered. Embodiment 40: Inlet system according to embodiment 39, wherein the inner partition tip has a tip radius defined by the turbine housing axis between it, wherein the turbine wheel has a turbine wheel radius and wherein the tip radius is 1.05-1.25 times larger than the turbine wheel radius. Embodiment 41: Inlet system according to one of the preceding embodiments, wherein the multiple blades are fixed to the blade partition. Embodiment 42: Inlet system according to one of the preceding embodiments, wherein the turbocharger with subdivided spiral is further defined as a turbocharger with two spirals. Embodiment 43: Entry system comprising the following: A split-spiral turbocharger for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine, wherein the internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein a relative impulse of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke, wherein the split-spiral turbocharger comprises: a turbine casing comprising a turbine casing interior designed to accommodate a turbine wheel with multiple turbine blades, wherein the turbine casing extends along a turbine casing axis, a first spiral, designed for flow connection with the combustion engine and the turbine housing interior to supply exhaust gas from the first set of cylinders to the turbine housing interior, a second spiral, designed to connect the combustion engine and the turbine housing interior to supply exhaust gas from the second set of cylinders to the turbine housing interior independently of the first spiral, a turbine casing outlet in flow connection with the turbine casing interior, and a wall separating the first spiral from the second spiral, the wall having a first wall surface pointing towards the turbine casing axis, and a blade ring coupled to the turbine casing and arranged inside the turbine casing between the first and second spirals and around the turbine wheel, the blade ring comprising a blade partition that further separates the first spiral from the second spiral, the blade partition having a blade parting surface facing the first wall surface, the blade ring comprising multiple blades coupled to the blade partition, and the multiple blades being fixed to the blade partition; and a pin coupled to the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing. Embodiment 44: Entry system according to embodiment 43, wherein the pin is coupled to the blade partition. Embodiment 45: Inlet system according to one of embodiments 43 and 44, wherein the blade ring further comprises an outer circumferential ring coupled to the blade partition, and wherein the pin is coupled to the blade partition and / or the outer circumferential ring of the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing. Embodiment 46: Entry system according to one of embodiments 43-45, wherein the pin extends parallel to the turbine housing axis. Embodiment 47: Inlet system according to one of embodiments 43-46, wherein the pin extends perpendicular to the turbine housing axis. Embodiment 48: Entry system according to one of embodiments 43-47, wherein the turbine housing defines a turbine housing slot and wherein the pin is arranged in the turbine housing slot. Embodiment 49: Inlet system according to one of embodiments 43-48, wherein the blade partition defines a separation slot and wherein the pin is arranged in the separation slot. Embodiment 50: Entry system according to one of embodiments 43-49, wherein the outer circumferential ring defines an outer ring slot and wherein the pin is arranged in the outer ring slot. Embodiment 51: Inlet system according to one of embodiments 43-50, wherein the wall comprises a tongue, wherein the tongue is the first wall surface and wherein the pin is adjacent to the first wall surface such that the pin is configured to be a leading edge of one of the blades. Embodiment 52: Inlet system according to embodiment 43, wherein the pin is further defined as a first pin and which further comprises a second pin, wherein the first pin is coupled to the blade partition and the turbine housing and wherein the second pin is coupled to the outer circumferential ring and the turbine housing. Embodiment 53: Inlet system according to embodiment 52, wherein the blade partition defines a separation slot and the turbine housing defines a first turbine housing slot, and wherein the first pin is arranged in the separation slot and the first turbine housing slot. Embodiment 54: Inlet system according to embodiment 53, wherein the outer circumferential ring defines an outer blade annular slot and the turbine housing defines a second turbine housing slot, and wherein the second pin is arranged in the outer blade annular slot and the second turbine housing slot. Embodiment 55: Entry system according to one of embodiments 45-54, wherein the inner circumferential ring and the outer circumferential ring are integral to each other. Embodiment 56: Entry system according to one of embodiments 45-54, wherein the inner circumferential ring and the outer circumferential ring are separate from each other. Embodiment 57: Inlet system according to one of embodiments 45-56, wherein the turbocharger with subdivided spiral is further defined as a turbocharger with two spirals. Embodiment 58: Entry system comprising the following: A split-spiral turbocharger for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine, wherein the internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein a relative impulse of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke, wherein the split-spiral turbocharger comprises: a turbine casing comprising a turbine casing interior designed to accommodate a turbine wheel with multiple turbine blades, wherein the turbine casing extends along a turbine casing axis, a first spiral, designed for flow connection with the combustion engine and the turbine housing interior to supply exhaust gas from the first set of cylinders to the turbine housing interior, a second spiral, designed to connect the combustion engine and the turbine housing interior to supply exhaust gas from the second set of cylinders to the turbine housing interior independently of the first spiral, a turbine casing outlet in flow connection with the turbine casing interior, and a wall separating the first spiral from the second spiral, the wall having a first wall surface pointing towards the turbine casing axis, and a blade ring coupled to the turbine housing and arranged inside the turbine housing between the first and second spirals and around the turbine wheel, wherein the blade ring comprises a blade partition which further separates the first spiral from the second spiral, wherein the blade partition has a blade parting surface which faces the first wall surface, wherein the blade ring comprises several blades coupled to the blade partition, wherein the several blades are fixed to the blade partition, and wherein the blade ring further comprises an outer circumferential ring coupled to the blade partition; where the outer circumferential ring and the blade partition are separate components. Embodiment 59: Inlet system according to embodiment 58, wherein the multiple blades are further defined as multiple first blades projecting from the blade partition and into the first spiral, and multiple second blades projecting from the blade partition and into the second spiral. Embodiment 60: Inlet system according to embodiment 59, wherein the multiple first blades, the multiple second blades and the blade partition are integral to each other. Embodiment 61: Entry system comprising the following: A split-spiral turbocharger for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine, wherein the internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein a relative impulse of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke, wherein the split-spiral turbocharger comprises: a turbine casing comprising a turbine casing interior designed to accommodate a turbine wheel with multiple turbine blades, wherein the turbine casing extends along a turbine casing axis, a first spiral, designed for flow connection with the combustion engine and the turbine housing interior to supply exhaust gas from the first set of cylinders to the turbine housing interior, a second spiral, designed to connect the combustion engine and the turbine housing interior to supply exhaust gas from the second set of cylinders to the turbine housing interior independently of the first spiral, a turbine casing outlet in flow connection with the turbine casing interior, and a wall separating the first spiral from the second spiral, the wall having a first wall surface pointing towards the turbine casing axis, and a blade ring coupled to the turbine housing and arranged inside the turbine housing between the first and second spirals and around the turbine wheel, wherein the blade ring comprises a blade partition which further separates the first spiral from the second spiral, wherein the blade partition has a blade parting surface which faces the first wall surface, wherein the blade ring comprises several blades coupled to the blade partition, wherein the several blades are fixed to the blade partition, and wherein the blade ring further comprises an outer circumferential ring coupled to the blade partition; where the outer circumferential ring and the blade partition are integral to each other. Embodiment 62: Inlet system according to embodiments 61, wherein the multiple blades are further defined as multiple first blades projecting from the blade partition and into the first spiral, and multiple second blades projecting from the blade partition and into the second spiral. Embodiment 63: Inlet system according to embodiment 62, wherein the multiple blades, the blade partition and the outer circumferential ring are integral to each other. Embodiment 64: Entry system comprising the following: A split-spiral turbocharger for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine, wherein the internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein a relative impulse of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke, wherein the split-spiral turbocharger comprises: a turbine casing comprising a turbine casing interior designed to accommodate a turbine wheel with multiple turbine blades, wherein the turbine casing extends along a turbine casing axis, a first spiral, designed for flow connection with the combustion engine and the turbine housing interior to supply exhaust gas from the first set of cylinders to the turbine housing interior, a second spiral, designed to connect the combustion engine and the turbine housing interior to supply exhaust gas from the second set of cylinders to the turbine housing interior independently of the first spiral, a turbine casing outlet in flow connection with the turbine casing interior, and a wall separating the first spiral from the second spiral, the wall having a first wall surface pointing towards the turbine casing axis, and a blade ring coupled to the turbine housing and arranged inside the turbine housing between the first and second spirals and around the turbine wheel, wherein the blade ring comprises a blade partition which further separates the first spiral from the second spiral, wherein the blade partition has a blade parting surface which faces the first wall surface, wherein the blade ring comprises several blades coupled to the blade partition, wherein the several blades are fixed to the blade partition, and wherein the blade ring further comprises an outer circumferential ring coupled to the blade partition; wherein the turbine housing has a first turbine housing surface which engages with the inner circumferential ring and points in a first direction with respect to the turbine housing axis, wherein the outer circumferential ring has a second surface which points in a second direction opposite to the first direction with respect to the turbine housing axis, and wherein the first turbine housing surface and / or the second surface of the outer circumferential ring are angled with respect to the turbine housing axis. Embodiment 65: Inlet system according to embodiment 64, wherein the first turbine housing surface is angled with respect to the turbine housing axis. Embodiment 66: Inlet system according to one of embodiments 64 and 65, wherein the second surface of the outer circumferential ring is angled with respect to the turbine housing axis. Embodiment 67: Entry system comprising the following: A split-spiral turbocharger for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine, wherein the internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein a relative impulse of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke, wherein the split-spiral turbocharger comprises: a turbine casing comprising a turbine casing interior designed to accommodate a turbine wheel with multiple turbine blades, wherein the turbine casing extends along a turbine casing axis, a first spiral, designed for flow connection with the combustion engine and the turbine housing interior to supply exhaust gas from the first set of cylinders to the turbine housing interior, a second spiral, designed to connect the combustion engine and the turbine housing interior to supply exhaust gas from the second set of cylinders to the turbine housing interior independently of the first spiral, a turbine casing outlet in flow connection with the turbine casing interior, and a wall separating the first spiral from the second spiral, the wall having a first wall surface pointing towards the turbine casing axis; a blade ring coupled to the turbine casing and arranged inside the turbine casing between the first and second spirals and around the turbine wheel, wherein the blade ring comprises a blade partition that further separates the first spiral from the second spiral, the blade partition having a blade parting surface that faces the first wall surface, and wherein the blade ring comprises several blades coupled to the blade partition; and a pin coupled to the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing; wherein the wall includes a tongue, wherein the tongue represents the first wall surface, and wherein the pin is adjacent to the first wall surface such that the pin is configured to be a leading edge of one of the blades. Embodiment 68: Entry system according to embodiment 67, wherein the pin extends parallel to the turbine housing axis. Embodiment 69: Inlet system according to one of embodiments 67 and 68, wherein the blade ring further comprises an outer circumferential ring which is coupled to the blade partition. Embodiment 70: Inlet system according to one of embodiments 67-69, wherein the multiple blades are further defined as multiple first blades projecting from the blade partition and into the first spiral, and multiple second blades projecting from the blade partition and into the second spiral. Embodiment 71: Inlet system according to embodiment 70, wherein the multiple first blades, the multiple second blades and the blade partition are integral to each other. Embodiment 72: Inlet system according to one of embodiments 69-71, wherein the multiple blades, the blade partition and the outer circumferential ring are integral to each other. Embodiment 73: Entry system according to one of embodiments 67-72, wherein the pin is coupled to the blade partition. Embodiment 74: Inlet system according to embodiment 73, wherein the pin is coupled to the blade partition and / or the outer circumferential ring of the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing. Embodiment 75: Entry system according to one of embodiments 67-74, wherein the turbine housing defines a turbine housing slot and wherein the pin is arranged in the turbine housing slot. Embodiment 76: Inlet system according to one of embodiments 67-75, wherein the blade partition defines a separation slot and wherein the pin is arranged in the separation slot. Embodiment 77: Entry system according to one of embodiments 67-76, wherein the outer circumferential ring defines an outer ring slot and wherein the pin is arranged in the outer ring slot. Embodiment 78: Inlet system according to one of embodiments 67-77, wherein the pin is further defined as a first pin and further comprising a second pin, wherein the first pin is coupled to the blade partition and the turbine housing and wherein the second pin is coupled to the outer circumferential ring and the turbine housing. Embodiment 79: Inlet system according to embodiment 78, wherein the outer circumferential ring defines an outer blade annular slot and the turbine housing defines a second turbine housing slot, and wherein the second pin is arranged in the outer blade annular slot and the second turbine housing slot. Embodiment 80: Inlet system according to one of embodiments 69-79, wherein the outer circumferential ring and the blade partition are integral to each other. Embodiment 81: Inlet system according to embodiment 80, wherein the multiple blades, the blade partition and the outer circumferential ring are integral to each other. Embodiment 82: Inlet system according to one of embodiments 69-79, wherein the outer circumferential ring and the blade partition are separate components. QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] US 63 / 644,172

[0001]

Claims

[1] Entry system comprising the following: A split-spiral turbocharger for receiving exhaust gas from an internal combustion engine and supplying compressed air to the internal combustion engine, wherein the internal combustion engine comprises a first set of cylinders and a second set of cylinders, wherein a relative impulse of the exhaust gas supplied by the first and second sets of cylinders is generally the same for each exhaust stroke, wherein the split-spiral turbocharger comprises: a turbine casing comprising a turbine casing interior designed to accommodate a turbine wheel with multiple turbine blades, wherein the turbine casing extends along a turbine casing axis, a first spiral, designed for flow connection with the combustion engine and the turbine housing interior to supply exhaust gas from the first set of cylinders to the turbine housing interior, a second spiral, designed to connect the combustion engine and the turbine housing interior to supply exhaust gas from the second set of cylinders to the turbine housing interior independently of the first spiral, a turbine casing outlet in flow connection with the turbine casing interior, and a wall separating the first spiral from the second spiral, the wall having a first wall surface pointing towards the turbine casing axis, and a blade ring coupled to the turbine casing and arranged inside the turbine casing between the first and second spirals and around the turbine wheel, wherein the blade ring comprises a blade partition wall further separating the first spiral from the second spiral, the blade partition wall having a blade parting surface facing the first wall surface, and wherein the blade ring comprises several blades coupled to the blade partition wall; wherein the first wall surface of the wall and the blade parting surface of the blade partition define a constraint path between each other with respect to the turbine casing axis and wherein at least one section of the constraint path is not parallel to the turbine casing axis, such that exhaust gas leakage from the first or the second spiral to the other spiral - the first or the second - is reduced. [2] Inlet system according to claim 1, wherein the restriction path has a coiled configuration with respect to the turbine housing axis. [3] Inlet system according to one of the preceding claims, wherein the restriction path has a curved configuration with respect to the turbine housing axis. [4] Inlet system according to one of the preceding claims, wherein the confinement path defined between the blade parting surface and the first wall surface of the wall comprises a first confinement path adjacent to the first spiral and extending parallel to the turbine casing axis, a second confinement path adjacent to the second spiral and extending parallel to the turbine casing axis, and a third confinement path extending from the first confinement path to the second confinement path. [5] Inlet system according to claim 4, wherein the third restriction path defines a first angle to the first restriction path and defines a second angle to the second restriction path, and wherein the first and the second angles are acute with respect to the turbine housing axis. [6] Inlet system according to one of the preceding claims, wherein the restriction path is defined to 360 degrees around the turbine housing axis. [7] Inlet system according to one of the preceding claims, wherein the blade ring further comprises an outer circumferential ring coupled to the blade partition. [8] Inlet system according to one of the preceding claims, wherein the multiple blades are further defined as multiple first blades projecting from the blade partition and into the first spiral, and multiple second blades projecting from the blade partition and into the second spiral. [9] Inlet system according to claim 8, wherein the multiple first blades, the multiple second blades and the blade partition are integral to each other. [10] Inlet system according to one of claims 8 and 9, wherein the multiple blades, the blade partition and the outer circumferential ring are integral to each other. [11] Inlet system according to one of the preceding claims, further comprising a pin coupled to the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing. [12] Entry system according to claim 11, wherein the pin is coupled to the blade partition. [13] Inlet system according to one of claims 11 and 12, wherein the pin is coupled to the blade partition and / or the outer circumferential ring of the blade ring and the turbine housing to prevent rotation of the blade ring relative to the turbine housing. [14] Inlet system according to one of the preceding claims, wherein the wall comprises a tongue, wherein the tongue is the first wall surface and wherein the pin is adjacent to the first wall surface such that the pin is configured to be a leading edge of one of the blades. [15] Inlet system according to one of the preceding claims, wherein the turbine housing has a first turbine housing surface which engages with the blade ring and points in a first direction with respect to the turbine housing axis, wherein the outer circumferential ring has a second surface which points in a second direction opposite to the first direction with respect to the turbine housing axis, and wherein the first turbine housing surface and / or the second surface of the outer circumferential ring are angled with respect to the turbine housing axis.

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