Inlet passage system including turbocharger and vane assembly

Abstract

An inlet passage system includes a turbocharger for receiving exhaust gas and delivering compressed air to an internal combustion engine. The system also includes a blade assembly having a blade ring on which a plurality of blades are disposed. The blade assembly includes a plurality of spacers positioned adjacent a leading edge or trailing edge of a respective blade, and each spacer is separated from an adjacent spacer by at least one blade. A blade gap distance defined between any portion of an adjacent side of the first blade and a blade ring surface of the blade ring is greater than a blade gap distance defined between any portion of an adjacent side of the second blade and the blade ring surface of the blade ring in order to control a blade torque associated with the first blade generated during operation of the system.

Description

[0001] Cross-reference to related applications

[0002] This application claims priority and all benefits to U.S. Provisional Patent Application No. 63 / 529182 (filed July 27, 2023), the entire contents of which are incorporated herein by reference. Technical Field

[0003] The present invention generally relates to an inlet channel system comprising a single or split volute turbocharger having a variable turbine geometry, and including aerodynamic spacers and a blade ring having multiple blades. Background Technology

[0004] The inlet passage system of a turbocharger receives exhaust gas from an internal combustion engine and delivers compressed air to it. The turbocharger increases the power output of the internal combustion engine, reduces its fuel consumption, and / or reduces 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 the vehicle's mass and aerodynamic frontal area, which helps reduce fuel consumption and improve fuel economy.

[0005] Some turbochargers include a turbine with a single volute turbine housing. The single volute 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 the engine's exhaust manifold or cylinder head) and includes multiple inlet ports configured to be in fluid communication with the engine's exhaust path upon attachment. The internal volume of the turbine housing delivers exhaust gas from the internal combustion engine to a turbine impeller arranged within the internal volume. After energy is extracted from the exhaust gas by the turbine impeller, the exhaust gas exits the turbine housing via the turbine outlet. The volute guides 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, causing the turbine impeller to rotate.

[0006] Some turbochargers include a turbine with a separate volute turbine housing; therefore, the turbocharger is sometimes optionally referred to as a separate volute turbocharger (or, when two volutes are used, a twin-volute turbocharger). The volutes of a separate volute turbine housing are typically isolated from each other so that the exhaust gases do not mix until after the exhaust gases have passed through the tongues of their respective volutes. The separate volute 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 the 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 to deliver exhaust gases from the internal combustion engine to a turbine impeller arranged within the internal volume. After energy is extracted from the exhaust gases by the turbine impeller, the exhaust gases exit the turbine housing via the turbine outlet. The volute guides the exhaust from the engine's exhaust manifold into an arc flow to distribute the exhaust around the circumference of the turbine impeller, causing the turbine impeller to rotate.

[0007] The turbocharger also includes a compressor. The compressor includes a compressor impeller connected to the 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] To help uniformly guide and control the exhaust flow from the volute or separate volute to the turbine impeller, a blade assembly, including a blade ring with multiple blades (sometimes optionally called a nozzle ring or bladed nozzle stator), can be arranged on an annular disk inside the turbine housing between the volute and the turbine impeller. These blades can be fixed to the annular disk (sometimes optionally called a fixed nozzle ring or fixed bladed nozzle stator) or can be rotatably coupled to the annular disk (sometimes optionally called a variable nozzle ring or variable bladed nozzle stator) to produce a variable turbine geometry (VTG).

[0009] In an inlet channel system with rotatable blades, each of the plurality of blades further includes a first shaft and an opposing second shaft extending from opposite flat sides of the blade. A blade rod is connected to the second shaft of the blade, preferably fixed to the second shaft by riveting or welding. Each blade rod includes a body portion and a flange portion. The blade rods are configured to allow each blade to rotate in a coordinated manner about its respective blade pivot point (VPP) between a closed position and an open position, and through one or more intermediate positions. An adjusting ring is held between the blade rod and a second blade ring, wherein the flange portion of each blade rod is arranged within an opening in the adjusting ring.

[0010] Blade assemblies typically also include multiple spacers arranged radially outward from the multiple blades between the blade rings. The spacers are used to minimize flow disturbances in the exhaust gas flowing from the volute through the multiple blades to the turbine impeller.

[0011] In typical inlet channel systems and turbochargers with VTG, the combination of rotatable blades and spacers provides sufficient performance for supplying exhaust gas to the turbine blades. However, in current systems, due to differences in the blade moments of multiple blades during operation of the inlet channel system (where multiple blades routinely move between open and closed positions), uneven and accelerated wear has been found on the flange portion of the blade shank, which has a higher relative blade moment compared to most other blade moments.

[0012] Therefore, there is still a need to optimize the construction of rotatable blades and spacers on blade assemblies used in VTG-equipped inlet channel systems and turbochargers in order to balance the blade torque of each of the multiple blades, including those with associated spacers and others without associated spacers, thereby reducing overall wear on the blade shank. Summary of the Invention

[0013] The inlet channel system includes a turbocharger and a blade assembly. The turbocharger receives exhaust gas from an internal combustion engine and delivers compressed air to the internal combustion engine. The blade assembly is coupled to the turbocharger. The turbocharger includes: a turbine housing including a turbine housing interior for receiving a turbine impeller having a plurality of equally spaced turbine blades, the turbine housing defining a turbine housing outlet in fluid communication with the turbine housing interior; and one or more volutes in fluid communication with the internal combustion engine and the turbine housing interior for delivering exhaust gas from the internal combustion engine to the turbine housing interior. The blade assembly coupled to the turbocharger includes: a blade ring disposed within the turbine housing and surrounding the turbine impeller, the blade ring including an annular disk comprising a blade ring surface disposed between an inner circumferential ring and an outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller, the blade ring surface including a plurality of blades rotatably disposed at a spacer along the blade ring surface, wherein each of the blades is rotatable between an open position and a closed position (including one or more intermediate positions); and a plurality of spacers disposed at a spacer on the blade ring surface and positioned circumferentially outward relative to each of the plurality of blades, wherein each corresponding spacer is positioned adjacent to the leading or trailing edge of a corresponding blade among the plurality of blades, and each spacer among the plurality of spacers is separated from an adjacent spacer among the plurality of spacers by at least one blade among the plurality of blades. An inlet channel system includes a blade clearance distance defined between any portion of an adjacent side of a first blade of the plurality of blades and the blade ring surface of the blade ring, which is greater than the blade clearance distance defined between any portion of an adjacent side of a second blade of the plurality of blades and the blade ring surface of the blade ring, in order to control a blade torque associated with the first blade of the plurality of blades having the blade clearance distance, which occurs during operation of the inlet channel system.

[0014] The present invention also relates to a blade assembly for an inlet channel system, comprising the aforementioned bypass recess in a blade ring and / or another blade ring, and / or comprising altered adjacent surfaces or altered opposing adjacent surfaces of a first blade to increase the blade clearance distance between the first blade and the blade ring surfaces of the blade ring or another blade ring.

[0015] The blade assembly, including the aforementioned bypass recess in the blade ring and / or additional blade rings and / or modified adjacent surfaces or modified opposing adjacent surfaces of the first blade to increase the blade clearance distance, serves to reduce wear on the blade shank of the blade assembly in the inlet passage system. In particular, in some embodiments, it reduces wear on the blade shank associated with the first blade among a plurality of blades.

[0016] The subject matter of this invention also relates to an associated method for reducing wear on the blade shank of a blade assembly in an inlet passage system during operation by increasing the blade clearance distance between any portion of the adjacent side of a first blade of a plurality of blades and the blade ring surface of a blade ring such that the blade clearance distance is greater than the blade clearance distance between any portion of the adjacent side of a second blade of a plurality of blades and the blade ring surface of a blade ring, thereby controlling the blade torque associated with the first blade of a plurality of blades. Attached Figure Description

[0017] Other advantages of the invention will become readily apparent from the following detailed description taken in conjunction with the accompanying drawings, in which:

[0018] Figure 1 It is a schematic diagram of an inlet channel system including a turbocharger, the turbocharger having a variable turbine geometry, and having a turbine housing including a volute and a turbine impeller arranged in the turbine housing;

[0019] Figure 2 It is a schematic diagram of an internal combustion engine and Figure 1 A cross-sectional end view of a single volute turbine casing for fluid communication with an internal combustion engine, which also includes a portion of a blade ring having rotatable blades and aerodynamic spacers arranged on an annular disk.

[0020] Figure 3 yes Figure 2 A side perspective view of the turbine section of a turbocharger, without the turbine impeller and turbocharger shaft;

[0021] Figure 4 yes Figure 3 A partial side section view;

[0022] Figure 5 This is a schematic diagram of an internal combustion engine and a device for fluid communication with the internal combustion engine. Figure 1 A cross-sectional end view of the casing of a double-volute turbine, which also includes a portion of a blade ring having rotatable blades arranged on an annular disk and aerodynamic spacers.

[0023] Figure 6 yes Figure 5A side perspective view of the turbine section of a turbocharger, without the turbine impeller and turbocharger shaft;

[0024] Figure 7 yes Figure 6 A partial side section view;

[0025] Figure 8 It is used in Figure 2 or Figure 5 Exploded view of the blade assembly used in a single-volute or double-volute system;

[0026] Figure 9 This is an end view of the blade of the blade ring, showing the blade pivot point (VPP).

[0027] Figure 10 This is a partial end view of a plurality of blades and spacers arranged on a second blade ring adjacent to an adjustment ring in a pair of blade rings of a blade assembly, and the blade ring includes a bypass recess.

[0028] Figure 11 yes Figure 10 A cross-sectional view of a portion of the blade assembly, including a first blade ring of the pair of blade rings;

[0029] Figure 12 This is a partial end view of a plurality of blades and spacers arranged on a second blade ring adjacent to an adjustment ring in a pair of blade rings of a blade assembly, the blade ring including a bypass recess.

[0030] Figure 13 yes Figure 12 A cross-sectional view of a portion of the blade assembly, which also includes a first blade ring of the pair of blade rings;

[0031] Figure 14 This is a partial end view of a plurality of blades and spacers arranged on a second blade ring adjacent to an adjustment ring in a pair of blade rings of a blade assembly, and the blade ring includes a bypass recess.

[0032] Figure 15 yes Figure 14 A cross-sectional view of a portion of the blade assembly, including a first blade ring of the pair of blade rings;

[0033] Figure 16 This is a cross-sectional view of a portion of a blade assembly according to another embodiment of the subject matter of the invention, showing a single blade among a plurality of blades arranged between a pair of blade rings of the blade assembly, wherein the single blade includes a tapered side adjacent to a first blade ring of the pair of blade rings;

[0034] Figure 17 This is a cross-sectional view of a portion of a blade assembly according to another embodiment of the subject matter of the invention, showing a single blade among a plurality of blades arranged between a pair of blade rings of the blade assembly, wherein the single blade includes a chamfered side adjacent to a first blade ring of the pair of blade rings in order to define a recessed slot;

[0035] Figure 18 This is a cross-sectional view of a portion of a blade assembly according to another embodiment of the invention, showing a single blade among a plurality of blades arranged between a pair of blade rings of the blade assembly, wherein the single blade includes a shorter length between the blade pivot point and the blade leading edge.

[0036] Figure 19 It is a side sectional view showing the relationship between the outer surfaces of the various body parts of the blade rod and the corresponding outer surfaces of the openings defined by the adjusting ring;

[0037] Figure 20 This is a graph showing the blade moment magnitude of each of the multiple blades in embodiments of a single volute inlet channel system compared to blade assemblies with four spacers and six spacers and thirteen blades; and

[0038] Figure 21 It is a graph plotting the blade moment magnitudes of multiple blades in a single volute inlet channel system with six spacers, and comparing the changes in blade moment resulting from adding a chamfered recessed slot, a spherical bypass recess associated with the trailing edge of blade 2, and a cylindrical bypass recess associated with the trailing edge of blade 2, wherein blade 2 corresponds to a blade assembly with thirteen blades in various cases, and corresponds to a single blade that is not adjacent to the trailing or leading edge when the blade assembly is in the closed position, wherein blade 2 also does not have spacers adjacent to the leading or trailing edge. Detailed Implementation

[0039] Referring to the accompanying drawings, in which the same reference numerals denote the same parts throughout all the views, a schematic diagram of system 30 (i.e., inlet channel system 30) is shown. Figure 1 The system 30 includes a turbocharger 32 having a turbine section 33 for receiving exhaust gas from an internal combustion engine 34 and a compressor section 35 for delivering compressed air to the internal combustion engine 34. While not strictly necessary, the turbocharger 32 is typically used in passenger car and commercial vehicle applications. However, it should be understood that the turbocharger 32 can be used in non-automotive applications, such as heavy equipment applications, non-automotive diesel engine applications, non-automotive motor applications, etc.

[0040] The turbine section 33 includes a turbine housing 36 having an inner surface 38 defining a turbine housing interior 40. The turbine housing interior 40 is used to receive a plurality of turbine blades 45 (see [link to interior section]). Figure 2 The turbocharger 32 comprises a turbine impeller 42, which consists of a plurality of evenly spaced turbine blades 45. Additionally, the turbocharger 32 typically includes a turbocharger shaft 44, a compressor impeller 46, a compressor housing 48, and a bearing housing 50. During operation of the turbocharger 32, the turbine impeller 42 (particularly the turbine blades 45) receives exhaust gas from the internal combustion engine 34, which causes the turbine impeller 42 to rotate. When present, the turbocharger shaft 44 is coupled to and can rotate through the turbine impeller 42. When present, the compressor impeller 46 is arranged in the compressor housing 48, coupled to and can rotate through the turbocharger shaft 44 to deliver compressed air to the internal combustion engine 34. The bearing housing 50 extends about the turbocharger shaft 44 between the turbine impeller 42 and the compressor impeller 46. The turbocharger 32 typically also includes a bearing 52 arranged in a bearing housing 50 around the turbocharger shaft 44 to rotatably support the turbocharger shaft 44.

[0041] In some other embodiments, such as Figures 2-4 As shown, the inner surface 38 of the turbine housing 36 has a single volute 53 in fluid communication with the internal combustion engine 34 and the turbine housing interior 40 for delivering exhaust gas from the internal combustion engine 34 to the turbine housing interior 40. Therefore, the inlet passage system 30 may optionally be referred to as a single volute inlet passage system 30. In some other embodiments, the inner surface 38 of the turbine housing 36 defines a plurality of volutes separated by walls, thus defining the turbine housing 36 as a split volute turbine housing. In this embodiment, as... Figures 4-6 As shown, the split volute turbine housing 36 is a double volute turbine housing 36, and the inlet passage system 30 can be referred to as a double volute inlet passage system 30, wherein the inner surface 38 defines a first volute 54 and a second volute 56, which are separated by walls 60. The walls 60 include a first tongue 61 and a second tongue 63, which represent different spaced-apart portions of the walls 60, such that multiple portions of the first volute 54 and the second volute 56 are separated.

[0042] A single volute 53 or the first and second volutes 54 and 56 are respectively in fluid communication with the internal combustion engine 34 and the turbine housing interior 40, for delivering exhaust gas from the internal combustion engine 34 to the turbine housing interior 40. For example... Figures 1-6As shown, the inner surface 38 also defines a turbine housing outlet 58. The turbine housing outlet 58 is in fluid communication with the turbine housing interior 40 for discharging exhaust gas from the turbine housing interior 40. Additionally, the inner surface 38 defines an exhaust valve that fluidly connects a single volute 53 to the turbine housing outlet 58, or fluidly connects each or either of the first volute 54 and the second volute 56 to the turbine housing outlet 58. The turbine housing 36 can be made of any suitable metal. Typically, the turbine housing 36 is made of iron or a steel alloy.

[0043] Refer again Figure 2 and 5 The internal combustion engine 34 includes a plurality of cylinders 68. In the illustrated embodiment, the internal combustion engine 34 includes a single volute inlet passage system (see [link to documentation]). Figure 2 The internal combustion engine 34 comprises three cylinders 68 and six cylinders 68 for the dual volute inlet passage system 30. However, it should be understood that the internal combustion engine 34 can include any number of cylinders 68 in either the single or dual volute inlet passage system 30. For example, the internal combustion engine 34 can include two, four, six, eight, or more cylinders 68. The internal combustion engine 34 can also include an odd number of cylinders (e.g., three or five cylinders 68). The internal combustion engine 34 can have a V-type engine configuration, a flat-opposed / horizontally opposed engine configuration, a W-type engine configuration, an inline engine configuration, etc. Figure 2 and 5 In the embodiment shown, the internal combustion engine 34 has an inline engine configuration.

[0044] for Figures 5-7 The internal combustion engine 34 comprises a dual-volute inlet channel system, including a first group of cylinders 70 and a second group of cylinders 72. In the illustrated embodiment, both the first group of cylinders 70 and the second group of cylinders 72 comprise half of the cylinders 68 included in the internal combustion engine 34. For example, when the internal combustion engine 34 includes six cylinders 68, such as... Figure 5 As shown, the first group of cylinders 70 includes three cylinders 68, and the second group of cylinders 72 includes another three cylinders 68. The first group of cylinders 70 and the second group of cylinders 72 generate exhaust gas with a series of pulses corresponding to the exhaust stroke of each of the first group of cylinders 70 and the second group of cylinders 72. The timing of the exhaust stroke of the cylinders 68 causes exhaust pulses to be emitted alternately from the first group of cylinders 70 and the second group of cylinders 72.

[0045] For ease of explanation, additional aspects of the invention may be described in relation to a universal inlet channel system 30 having a volute 57, which is equally applicable to a single volute inlet channel system (i.e., having a single volute 53) or a double volute inlet channel system 30 (having volutes 54, 56), unless otherwise specified below.

[0046] In addition to Figure 2 , 5 In addition to the turbocharger 32 best shown in Figures 8 and 10, the inlet passage system 30 also includes a blade assembly 80. The blade assembly 80 includes blade rings 100, more typically including a pair of spaced-apart blade rings 100 (hereinafter referred to as blade rings 100, or first blade ring 100A and second blade ring 100B (or blade ring 100A and additional blade ring 100B)), which are arranged within the turbine housing 40 between the volutes 57 and around the turbine impeller 42. The blade rings 100 have a plurality of blades, indicated as first and second blades 130 and 140, rotatably arranged on and between the respective blade rings 100, 100A, 100B in a symmetrical or asymmetrical blade pattern, preferably as shown, and a symmetrical blade pattern is described below. The inlet passage system 30 also includes a plurality of spacers 400 arranged at intervals on and between the blade rings 100, 100A, and 100B, wherein the blades on the blade rings 100, 100A, and 100B and the spacers 400 are used to control the flow of exhaust gas from one or more volutes 54, 56 to the turbine impeller 42. In particular, the spacers 400 are used to minimize flow disturbances of the exhaust gas from one or more volutes 54, 56 to the turbine impeller 42.

[0047] Each blade ring 100 includes or otherwise incorporates an annular disk 101 disposed within the turbine housing interior 40 between separate first and second volutes 54, 56 and the turbine impeller 42. In a particular embodiment with a pair of spaced-apart blade rings 100A, 100B (see, for example, [link to relevant documentation]). Figure 8 In the blade rings 100A and 100B, the blade rings include or contain a pair of spaced-apart annular disks 101A and 101B (annular disk 101A may sometimes be referred to as the first annular disk 101A or the lower annular disk 101A, while annular disk 101B may sometimes be referred to as the second annular disk 101B or the upper annular disk 101B, or more commonly as the second blade ring 100B).

[0048] In the embodiments shown herein, a plurality of blades 130, 140 are rotatably arranged between the respective blade rings 100A, 100B in the aforementioned symmetrical or asymmetrical pattern, and are particularly shown in the figures as arranged in a symmetrical blade pattern, wherein the respective blades 130, 140 are equidistant from each other and equidistant from each other relative to the inner peripheral edge 104 and the outer peripheral edge 106 (defined below). In these embodiments, the spacer 400 also serves to provide axial separation between the first blade ring 100A and the second blade ring 100B, and is arranged between the respective blade rings 100A, 100B.

[0049] Best placeFigure 2 , 5 As shown in Figures 8 and 9, each blade ring 100 includes a blade ring surface 102, which includes an inner blade ring surface 102A extending between an inner peripheral edge 104 and an outer peripheral edge 106, and an opposing outer blade ring surface 102B. In the illustrated embodiment, the inner peripheral edge 104 defines a circular orifice for receiving the turbine impeller 42 of the turbocharger 32.

[0050] In the various illustrated embodiments, the blade ring 100 is represented as a circular shape, and the inner peripheral edge 104 and the outer peripheral edge 106 are also described and represented as circular. However, in other embodiments herein, the blade ring 100 may be a non-circular shape, and thus one or both of the inner peripheral edge 104 and the outer peripheral edge 106 may also be non-circular. Therefore, the term "blade ring" (as in "blade ring 100") specifically describes circular and non-circular shapes on the inner peripheral edge 104 and / or the outer peripheral edge 106.

[0051] For the dual volute inlet channel system, each blade ring 100, 100A, 100B is arranged in the turbine housing 36 and has a first tongue 61 and a second tongue 63, which each terminates at a position adjacent to the outer peripheral ring 106.

[0052] In the single volute inlet channel system 30, the optimal position is as follows: Figure 2 As shown, the blade rings 100, 100A, and 100B are arranged in the turbine housing 36. The first set of blades 130 (i.e., at least two blades in the first set) and the second set of blades 140 are rotatably arranged in a spaced-apart manner such that each blade 130 or 140 is located downstream of a portion of the volute 53. Each blade 130, 140 is rotatable along the blade ring surface 102, particularly about the blade pivot axis (corresponding to the blade pivot point VPP) along the inner blade ring surface 102A of the respective blade rings 100, 100A, and 100B. Figure 9 It rotates between the closed and open positions and passes through one or more intermediate positions between the closed and open positions. As defined herein and as... Figure 9 As shown, the blade pivot axis VPA extends in a direction perpendicular to the plane defining the blade ring surface 102 of the blade ring 100.

[0053] For the dual-volute inlet channel system 30, the optimal... Figure 5As shown, a first set of blades 130 (i.e., a first set of at least two blades 130) is rotatably arranged on the blade ring surface 102 in a spaced-apart manner, such that the first set of blades 130 is located downstream of the first volute 54. Furthermore, a second set of blades 140 is rotatably arranged in a spaced-apart manner, such that the second set of blades 140 (i.e., a second set of at least two blades 140) is located downstream of the second volute 56. Similar to the single volute inlet channel system 30, each blade 130, 140 is rotatable along the blade ring surface 102, particularly about the blade pivot axis (corresponding to the blade pivot point VPP – see [link]) along the inner blade ring surface 102A of the respective blade rings 100, 100A, 100B. Figure 9 And rotate between the closed and open positions and through one or more intermediate positions between the closed and open positions (below) Figure 2 , 5 The open position, closed position, and intermediate position are best represented and described in 10-16. The blade pivot axis VPA, as defined herein, extends in a direction perpendicular to the plane defining the blade ring surface 102 of the blade ring 100.

[0054] exist Figure 2 and 5 In the illustrated embodiment, the first group of blades 130 includes seven blades 130 positioned adjacent to each other around the blade ring surface 102 of the blade ring 100, while the second group of blades 140 includes six blades 140 positioned adjacent to each other around the blade ring surface 102 of the blade ring 100. Therefore, in Figure 2 , 5 In embodiments 8 and 9, there are a total of thirteen blades 130, 140 on the blade ring 102, which provide exhaust flow to the turbine impeller 42 having ten equally spaced turbine blades 45. Although the embodiments provided herein include thirteen blades 130, 140, alternative relative numbers of blades and impellers are conceivable, preferably wherein the number of blades 130, 140 is a different odd number, such as a prime number, and the number of turbine blades 42 on the turbine impeller 42 is not equal to the number of blades 130, 140.

[0055] Best as Figure 9 As shown, each blade 130 and 140 extends along its length between leading edges 132, 142 and trailing edges 134, 144, and includes adjacent edges 225 and opposing adjacent edges 227, each separately connecting the leading edges 132, 142 to the trailing edges 134, 144. Furthermore, the adjacent edges 225 and opposing adjacent edges 227 respectively define blade surfaces 225A and 227A (i.e., adjacent blade surface 225A and opposing adjacent blade surface 227A, see [reference]). Figure 8 Moreover, the best is...Figure 8 As shown, each of the plurality of blades 130, 140 further includes a first shaft 133, 143 and an opposing second shaft 137, 147 extending from the opposing flat sides of the blades 130, 140. A blade rod 153 is coupled to the second shafts 137, 147 of the blades 130, 140, and is preferably fixed to the second shafts 137, 147 of the blades 130, 140 by riveting or welding. In other embodiments, the blade rod 153 may be coupled by forging or by bolting, etc. Each blade rod 153 includes a body portion 157 and a flange portion 159. The blade rod 153 is configured to allow each blade 130 and 140 to rotate in a coordinated manner about its respective blade pivot point (VPP) between a closed position and an open position and through one or more intermediate positions, as will be further described below. In some embodiments, for example, as Figure 8 , 11 As shown in 13 and 15, the adjusting ring 199 is held between the blade rod 153 and the second blade ring 100B. The flange portion 159 of each blade rod 153 is arranged in the opening 201 of the adjusting ring 199. The adjusting ring 199 defines each corresponding opening 201, and the opening 201 is further defined by the inner surface 202 of the adjusting ring 199.

[0056] For example Figure 8 As shown, assembly 203, including pin 205 and block 207, is fixed to adjusting ring 199, for example by riveting or welding, wherein a pivot (not shown) connects assembly 203. The pivot is rotated via a connecting rod (not shown) connected to an actuator (not shown). The actuator rotates the connecting rod based on specific engine operating conditions to regulate the exhaust flow through blades 130, 140. In particular, the actuator rotates the connecting rod, which in turn rotates the pivot and adjusting ring 199 via assembly 203. The rotation of adjusting ring 199 causes adjusting ring 199 to contact blade rod 153, and in response causes blade rod 153 to rotate, which in turn moves the coupled blades 130, 140 between a closed position and an open position and through one or more intermediate positions to regulate the exhaust flow through blades 130, 140 based on engine operating conditions (e.g., engine speed).

[0057] More specifically, it is best to be like Figure 8 and 19As shown, the flange portion 159 of the blade rod 153 defines an opening drive surface 159A, a closing drive surface 159B, and a wall portion 159C connecting the opening drive surface 159A and the closing drive surface 159B. The wall portion 159C is used to position and limit the radial movement of the adjusting ring 199. When the blade assembly 80 is opened toward the intermediate and open positions, the opening drive surface 159A moves in a rolling and sliding contact with the inner surface 202 of the opening 201 of the adjusting ring 199, while when the blade assembly 80 is closed from the open or intermediate position toward the closed position, the closing drive surface 159B moves in a rolling and sliding contact with the inner surface 202 of the opening 201 of the adjusting ring 199. As described below, the present invention provides a solution for limiting wear of the blade rod 153 along the open drive surface 159A and the closed drive surface 159B of the blade rod 153, particularly for the blade rod 153 associated with the corresponding blade 130' or 140' excluding the spacer 400 (which is positioned in normal operation near the front end 132 or 142 or the rear end 134 or 144 of the blade by increasing the blade clearance distance VCD between the blade ring surfaces of one of the plurality of blades 130 or 140 and one or two blade rings 100, 100A, 100B).

[0058] Each blade ring 100, 100A, 100B further defines a plurality of first openings 107 between the inner peripheral edge 104 and the outer peripheral edge 106, the number of openings 107 corresponding to the number of the plurality of blades 130, 140, and configured to receive the shafts 133, 137, 143, 147 of a corresponding blade among the plurality of blades 130, 140, as will be explained further below. Therefore, the openings 107 also define the blade pivot point (VPP) of a corresponding blade among the plurality of blades 130, 140 arranged therein. In an embodiment including a first blade ring 100A and a second blade ring 100B, a plurality of openings 107 in at least one of the first blade ring 100A and the second blade ring 100B extend from the inner blade ring surface 102A to the outer blade ring surface 102B, such that the entire second shaft 137, 147 extends through the openings 107 of the second blade ring 100B, thereby positioning the blade rod 153 within the turbine housing interior 40 between the outer blade ring surface 102B of the second blade ring 100B and the turbine housing 36.

[0059] See again Figure 2 , 5And 8, and as described above, the inlet passage system 30 also includes a plurality of spacers 400. In particular, the plurality of spacers 400 are arranged in a spaced-apart manner on the blade ring surface 102 of the blade ring 100 (or along the inner blade ring surface 102A of each of the spaced-apart blade rings 100A, 100B), and are positioned circumferentially outward from each of the first set of blades and the second set of blades 130, 140. The spacers 400, together with the blades 130, 140, are used to regulate the flow of exhaust gas entering from the volute 53 or the corresponding first volute 54 or second volute 56 before it is received by the turbine blades 45.

[0060] exist Figure 2 and 5 In one embodiment, each spacer 400 is arranged at intervals on the blade ring surface 102 and positioned outward in a circumferential direction relative to each of the plurality of blades 130, 140, wherein each corresponding spacer among the plurality of spacers 400 is positioned adjacent to the leading edge 132, 142 or the trailing edge 134, 144 of the corresponding blade among the plurality of blades 130, 140.

[0061] As defined herein with respect to the relationship of spacers 400, the term “adjacent” means that the corresponding spacer 400 is positioned circumferentially on the outside of blades 130, 140 along a radial line (RL) extending from the axis of rotation AA of the turbine impeller 42 to the outer peripheral edge 106.

[0062] Therefore, in the embodiment having a total of thirteen blades 130, 140, there are a plurality of spacers 400 arranged on the blade rings 100, 100A, 100B, wherein a corresponding spacer 400 is positioned adjacent to the leading edge 132, 142 or the trailing edge 134, 144 of a corresponding blade among the six corresponding blades 110, 140.

[0063] In the embodiments described and illustrated herein according to the invention, each of the plurality of spacers 400 is separated from its adjacent spacer by at least one of the plurality of blades 130, 140. In other words, in embodiments having an even number of blades 130, 140 (e.g., an inlet channel system 30 with twelve blades 130, 140), the number of blades 130, 140 is twice the number of spacers 400 (i.e., 2N, where N is the number of spacers and 2N is the number of blades), or in embodiments having an odd number of spacers 400 (e.g., an inlet channel system 30 with thirteen blades 130, 140), the number of blades 130, 140 is one more than twice the number of spacers 400 (i.e., 2N+1, where N is the number of spacers).

[0064] In a preferred embodiment, the spacing between each pair of adjacent spacers 140 is the same (measured as radial distance), and this spacing includes exactly one blade 130 or 140 located therebetween. In an inlet channel system 30 having an odd number of blades 130, 140, the spacing S1 between a pair of adjacent spacers 400 separated by a pair of blades 130 or 140 (see...) Figure 2 It is also measured as a radial distance, which is greater than the remaining pair of adjacent spacers 400 separated by another blade 130' or 140' (see also...). Figure 2 The distance S2 is twice the distance S1 in a particular embodiment.

[0065] The following is for reference. Figure 9 The diagram shows the blade pivot point (VPP) of each blade 130, 140. This blade pivot point represents a point along blade 130, 140 about which blade 130, 140 rotates in the direction of rotation about a pivot axis perpendicular to the blade annular surface 102, between open, closed, and intermediate positions. The blade pivot point (VPP) of each blade 130, 140 is also defined as a distance “x” from the leading edge 132, 142 along the mean line ML. The mean line ML (e.g., a mean chord) is defined by the trajectory of a point located between the leading edge 132, 142 and the trailing edge 134, 144 of a single blade 130, 140 (typically located midway between the first side and the opposite second side of the single blade 130, 140, respectively), which extends through the blade pivot point (VPP). Leading edges 132 and 142 are used conventionally herein; however, the blade pivot point (VPP) of a single blade 130 or 140 can alternatively be defined as a distance “y” from the trailing edge 134 or 144 along the mean chord ML, reaching the same blade pivot point (VPP). The distance “x” defining the VPP lies at a certain distance from the leading edge 132 or 142 to the trailing edge 134 or 144, which corresponds to the length x of the mean chord ML (see [link to documentation]). Figure 9 For example, the length y is approximately 20% to 45% of the total length of the average chord ML, where the length y is equal to the remaining portion of the total length of the average chord ML. However, it should be noted that although the position of the VPP may be the same or different for each individual blade 130, 140, when symmetrical blades are used, the VPPs for each blade 130, 140 on any given blade ring 100 are located in the same relative position (i.e., the lengths x and y on blades 130, 140 are constant in the symmetrical blade pattern). In the embodiments provided herein, the blade pivot point (VPP) of the respective blades 130, 140 corresponds to a line extending along the lengths of the axes 133, 137, 143, 147 of the respective blades 130, 140 and within the respective openings 107 of the respective blade rings 100, 100A, 100B.

[0066] Although not shown, the blade angle (α) is defined by the radial line RL extending from the axis of rotation AA of the turbine impeller 42 through the blade pivot point (VPP) (see Figure 10 The angle formed by the tangent TL (not shown) relative to the bottom of the corresponding blades 130 and 140 is the angle between the blade and the radial line RL. Alternatively, the tangent TL can be defined by a straight chord passing through the leading and trailing edges of the blade. The angle of the tangent TL relative to the radial line RL is a function of the relative radial distances of the leading edges 132 and 142 (defined as the first radial distance) and the trailing edges 134 and 144 (defined as the second radial distance) of the corresponding blades 130 and 140. Typically, the first radial distance is equal to or greater than the second radial distance, where the blade angle (α) is within the range of 90 degrees (the maximum theoretical blade angle (α) when the first radial distance is equal to the second radial distance) and the minimum theoretical blade angle (α) when the first radial distance is maximum and the second radial distance is minimum (so that the tangent TL extends together with the radial line RL). When the blade angle (α) decreases from the theoretical maximum blade angle (α) of 90 degrees to the theoretical minimum blade angle (α) of 0 degrees, the exhaust flow from the volute 54, 56 to the turbine impeller 42, which is disturbed by the corresponding blades 130 and 140, decreases accordingly.

[0067] The blade angle (α) is also used to describe the closed position, open position, and various intermediate positions of the corresponding blades at 130° and 140°. In particular, in the closed position (see example...) Figure 10 , 12In (14), the leading edge 132, 142 of each of the plurality of blades 130, 140 is positioned adjacent to the trailing edge 134, 144 of an adjacent blade among the plurality of blades 130, 140, so that the blade angle (α) is 85 to 95 degrees, for example 88 to 90 degrees, for example approximately 90 degrees, for example 90 degrees, which is also referred to herein as 0% blade opening. The term “adjacent” as used herein refers to the position where the leading edge 132, 142 of a corresponding blade among the plurality of blades 130, 140 contacts the trailing edge 134, 144 of an adjacent blade among the plurality of blades 130, 140. The term “adjacent” can also refer to a situation where there is a very small gap between the leading edges 132, 142 of a corresponding blade among the plurality of blades 130, 140, or where the leading edges 132, 142 contact the trailing edges 134, 144 of an adjacent blade among the plurality of blades 130, 140. As defined herein, “small clearance” takes into account the blade angle (α) range of 85 to 95 degrees as described above. Conversely, in the open position (which is typically used when the engine is running at high engine speeds), the leading edge 132, 142 of each of the plurality of blades 130, 140 is spaced apart by the maximum distance from the trailing edge 134, 144 of the adjacent blade of the plurality of blades 130, 140. In some embodiments, for example in Figure 10 , 12 As shown in Figure 14, the blade angle (α) in the closed position is between 30 degrees and 65 degrees, for example, from 35 degrees to 55 degrees, for example, from 40 degrees to 45 degrees, for example, approximately 45 degrees, for example, 45 degrees. The intermediate position refers to any position between the closed position and the open position, so the blade angle (α) is between the blade angle (α) defining the closed position and the blade angle (α) defining the open position.

[0068] As described above, the present invention relates to reducing wear in the blade rod 153, particularly to a single blade 130' or 140' of a plurality of blades 130, 140 excluding a corresponding spacer among the plurality of spacers 400 adjacent to the leading edge 132 or 142 or adjacent to the trailing edge 134 or 144 (see...). Figure 10 , 12 and 14).

[0069] In the inlet channel system 30, where the blade torque varies from blades 130 and 140 to blades 130 and 140 respectively, the blade rod 153 typically wears unevenly, particularly in the area where the blade rod 153 contacts the inner surface 202 of the adjusting ring 199. Specifically, the wear of the blade rod 153 is more severe when blades 130 and 140 have higher blade torques relative to other blades in the blade inlet channel system (which have lower blade torques). Figure 2 and5 In the embodiments, the maximum blade moment of the plurality of blades 130, 140 is equal to that of a single blade 130' or 140' excluding the spacer 400 (see Figure 20 and 21 (related to)

[0070] To reduce the blade moment of certain blades to correspond with that of other blades, spacers 400 are introduced radially outward from certain blades 130, 140 in these inlet passage systems 30, as previously described. However, including spacers 400 will restrict or otherwise alter the exhaust flow through the blades 130, 140 in the various open and intermediate positions, and thus limit the efficiency and capability of the turbocharger to rotate the turbine blades 45 at a given blade position. Therefore, it is desirable to carefully balance between the number of spacers 400 provided and the number of blades 130, 140 to achieve efficiency and reduce wear in the blade rod 153, wherein the addition of spacers 400 allows for desired exhaust volume movement while maintaining a positive blade moment associated with each blade 130, 140 to limit wear on the blade rod 153.

[0071] This invention provides a method for balancing the blade moments of individual blades 130, 140 in a single-casing and double-casing inlet passage system 30, wherein the number of spacers 400 is less than or equal to half that of blades 130, 140, and the individual blade moments are greater than zero. By achieving balanced positive blade moments at each blade 130, 140, wear on the blade rod 153 associated with the contact of the corresponding portions of the open drive surface 159A, the closed drive surface 159B, and the inner surface 202 of the opening 201 in the adjusting ring 199 is minimized and balanced. Furthermore, this balanced positive blade moment allows the exhaust gas to efficiently and effectively rotate the turbine blades 45 as needed at a given open, intermediate, or closed position of the blades 130, 140.

[0072] To achieve this balanced positive blade moment (sometimes simply referred to as blade moment), the present invention provides modifications or alterations to one or both of the blade rings 100, 100A, 100B or to one or more of the blades 130, 140, which reduce the blade moment on the corresponding blades 130, 140, particularly reducing the blade moment on the blades 130' or 140' excluding the spacer 400, resulting in a blade moment that is balanced relative to the blade moments of the other blades 130, 140 in the inlet passage system 30, including the associated spacer 400.

[0073] In some embodiments, the modifications or alterations described above include modifying the blade ring surface 102 of one or both of the annular disks 101, 101A, and 101B of the blade rings 100, 100A, and 100B to include a bypass recess 500 extending within the blade ring surface 102A of the blade rings 100, 100A, and 100B. More specifically, the modifications include modifying the blade ring surface 102A of one or both of the annular disks 101, 101A, and 101B of the blade rings 100, 100A, and 100B to include a bypass recess 500 positioned along the annular disks 101, 101A, and 101B adjacent to the corresponding blade 130 or 140 thereto, and extending within the blade ring surface 102A of the blade rings 100, 100A, and 100B.

[0074] In some of these embodiments, the blade ring surfaces 102A of the annular disks 101, 101A, 101B of the blade rings 100, 100A, 100B have been modified to include a bypass recess 500, which, when the blades 130', 140' are in the closed position, is positioned along the annular disks 101, 101A, 101B adjacent to the corresponding blade 130' or 140' and extends within the blade ring surface 102A of the blade ring 100B adjacent to the blades 130', 140'.

[0075] In such Figures 10-15 In one example embodiment shown, the blade ring surface 102A of the annular disk 101B of the blade ring 100B has been modified to include a bypass recess 500, which, when the blades 130' and 140' are in the closed position, is positioned along the annular disk 101B at a position adjacent to the length x of the corresponding blade 130' or 140' between the blade pivot point VPP and the leading edge 132 or 142, and extends within the blade ring surface 102A of the blade ring 100B adjacent to the blades 130' and 140'.

[0076] For example Figures 10-15 As shown, the width W1 of the bypass recess 500 (see...) Figure 10 (Measured along a direction parallel to the length of the associated blade 130' or 140' of the plurality of blades 130, 140 when the associated blade 130 or 140 is in the closed position) less than or equal to the length x of the associated blade 130 or 140 of the plurality of blades 130, 140 (see [reference]). Figure 9(Measured from the blade pivot point of the associated blade 130 or 140 of the plurality of blades 130, 140 to the leading edge 132 or 142), and when the associated blade 130 or 140 of the plurality of blades 130, 140 is in the closed position, the bypass recess 500 is arranged entirely below the length x of the associated blade 130 or 140 of the plurality of blades 130, 140 between the blade pivot point VPP and the leading edge 132 or 142.

[0077] In addition, in such Figures 10-15 In the illustrated embodiment, the width WW1 of the bypass recess 500 (measured along the annular disks 101, 101A, 101B in a direction perpendicular to the length x of the blades 130, 140 in the closed position) (see [reference]). Figure 10 It can extend to a position adjacent to but spaced apart from the inner peripheral edge 104 of the corresponding blade disk 100, 100A, 100B, and / or can extend to a position adjacent to but spaced apart from the outer peripheral edge 106 of the corresponding blade disk 100, 100A, 100B.

[0078] although Figures 10-15 The diagram shows a bypass recess 500 (when the blades 130', 140' are in the closed position, the bypass recess 500 is positioned along the annular disk 101A at a position adjacent to the length x of the corresponding blade 130' or 140' between the blade pivot point VPP and the leading edge 132 or 142, and extends within the blade ring surface 102A of the blade ring 100B adjacent to the blades 130', 140'), but in other embodiments, when the blades 130', 140' are in the closed position, the bypass recess 500 may be positioned along the annular disk 101A at a position adjacent to the length y of the corresponding blade 130' or 140' between the blade pivot point VPP and the trailing edge 134 or 144, and extend within the blade ring surface 102A of the blade ring 100B adjacent to the blades 130', 140'. Furthermore, in other related embodiments, a pair of bypass recesses 500 may be included, wherein the first of the pair of bypass recesses is positioned as described above to be adjacent to the length x of the blade 130' or 140', and the second of the pair of recesses 500 is positioned as described above to be adjacent to the length y.

[0079] In a further related embodiment, one or more additional bypass recesses 500 may alternatively be positioned at any other desired location and extend within the blade surface 102A of the blade ring 100A with the same parameters as described above. In a further embodiment, the one or more additional bypass recesses 500 may be positioned in conjunction with bypass recesses 500 positioned as described above and extending within the blade surface 102A of the blade ring 100B at any other desired location and extending within the blade surface 102A of the blade ring 100A.

[0080] In various embodiments of these corresponding embodiments, the annular disks 101, 101A, 101B of the corresponding blade rings 100, 100A, 100B define a blade ring surface 102A' within a corresponding bypass recess 500. This blade ring surface 102A' is further away from the blade surface 225A of the adjacent side surface 225 of the blades 130', 140' than the remaining portion of the blade ring surface 102A not included in the bypass recess. Therefore, the blade clearance distance VCD defined between the blade ring surface 102A' and the blade surface 225A of the adjacent side surface 225 is greater than the corresponding clearance distance CD defined between the blade ring surface 102A and the blade surface 225A of the adjacent side surface 225.

[0081] In some embodiments, such as Figure 10 and 11 As shown, the bypass recess 500 is spherical in shape, and is therefore further defined as a spherical bypass recess 500A. In this embodiment, the blade ring surface 102A' defined within the spherical bypass recess 500A is curved and defines a vertex 504, which also defines the depth D1 of the spherical bypass recess 500A below the blade ring surface 102A. Furthermore, the intersection of the blade ring surface 102A' and the blade ring surface 102A of the spherical bypass recess 500A defines a circular edge 506. Additionally, the blade clearance distance VCD is defined between the blade ring surface 102A' corresponding to the vertex 514 and the blade surface 225A of the adjacent side surface 225.

[0082] In some embodiments, such as Figure 12 and 13 As shown, the bypass recess 500 is ellipsoidal in shape, and is therefore further defined as an ellipsoidal bypass recess 500B. In this embodiment, the blade annular surface 102A' defined within the ellipsoidal bypass recess 500B is curved and defines a vertex 514, which also defines the depth D2 of the ellipsoidal bypass recess 500B below the blade annular surface 102A. Furthermore, the intersection of the blade annular surface 102A' and the blade annular surface 102A of the ellipsoidal bypass recess 500B defines an elliptical edge 516. The elliptical edge 516 includes a primary width MW along its primary length and a secondary width MMW perpendicular to the primary width MW. In some embodiments, such as... Figure 12 and 13As shown, when blade 130' or 140' moves to the closed position, the primary width MW is positioned parallel or substantially parallel to the average chord length ML of blade 130' or 140'. In other embodiments, when blade 130' or 140' moves to the closed position, the secondary width MMW is positioned parallel or substantially parallel to the average chord length ML of blade 130' or 140'. In other embodiments, when blade 130' or 140' moves to the closed position, the primary width MW and the secondary width are respectively positioned laterally aligned with the average chord length ML of blade 130' or 140'.

[0083] In addition, the blade clearance distance VCD is defined between the blade annular surface 102A' corresponding to the vertex 514 and the blade surface 225A of the adjacent side surface 225.

[0084] In some embodiments, such as Figure 14 and 15 As shown, the bypass recess 500 is cylindrical in shape, and is therefore further defined as a cylindrical bypass recess 500C. In this embodiment, the blade ring surface 102A' is a circular bottom surface 224 defined within the spherical bypass recess 500A, which defines the depth D3 of the cylindrical bypass recess 500A below the blade ring surface 102A. Furthermore, the intersection of the blade ring surface 102A' and the blade ring surface 102A of the cylindrical bypass recess 500A defines a circular edge 526. Additionally, the blade clearance distance VCD is defined between the blade ring surface 102A' corresponding to the circular bottom surface 224 and the blade surface 225A of the adjacent side surface 225.

[0085] In addition, the blade clearance distance VCD is defined between the blade annular surface 102A' corresponding to the bottom surface 224 of the cylindrical bypass recess 500A and the blade surface 225A of the adjacent side surface 225.

[0086] exist Figures 10-15In various embodiments, the depths D1, D2, and D3 of the corresponding bypass recesses 500A, 500B, and 500C can vary between greater than 0% and less than 100% of the thickness of the corresponding annular disk 101B. When the corresponding blades 130' and 140' are in the closed position or even in some intermediate positions, the increased depths D1, D2, and D3 allow more exhaust gas to flow between the blades 130' and 140' and the blade ring surface 102A', which in turn alters the blade torque of the blades 130' and 140' associated with the corresponding bypass recesses 500A, 500B, and 500C. In some embodiments, the depths D1, D2, and D3 of the corresponding bypass recesses 500A, 500B, and 500C are between 0.1% and 25% of the thickness of the annular disk 101B. Although not shown, the depth of the corresponding bypass recess 500 in the alternative position on the annular disk 101B or the depth of the corresponding bypass recess 500 in the alternative position on the annular disk 101A can be determined according to... Figures 10-15 The embodiments shown may vary.

[0087] In a further embodiment, as an addition such as Figures 10-15 The alternatives or additions to the bypass recess 500 shown in the representative embodiments or as described above may modify one or more of the plurality of blades 130, 140, particularly blades 130' or 140', in order to reduce the blade torque of the corresponding blade 130, 130' or 140, 140'.

[0088] In some embodiments, such as Figure 16 As shown, along one of the multiple blades 130, 140 (in Figure 16 The blade surface 252A, defined by the opposing adjacent sides 252 of the blade (represented as blade 130' or 140') and extending between the blade pivot point VPP and the leading edges 132, 142, is tapered. In these embodiments, the blade clearance distance CD1 between the blade surface 252A of the associated blades 130, 130' or 140, 140' of the plurality of blades 130, 140 and the blade ring surface 102A, 102A' of the blade ring 100 increases along a direction from the blade pivot point VPP to the leading edge 132 or 142 of the associated blade 130, 130' or 140, 140' of the plurality of blades 130, 140.

[0089] exist Figure 16 In the embodiment, the angle of the cone (measured to define the corresponding annular disk 101) Figure 16The angle α between the plane of the blade surface 102A (represented as an annular disk 101A) and the plane defined by the conical blade surface 252A can vary between greater than 0 degrees and less than 90 degrees. In some embodiments, the angle α varies between greater than 0 degrees and 30 degrees. It should be noted that increasing the angle α allows more exhaust gas to flow between the blades 130', 140' and the blade annular surfaces 102, 102A' when the respective blades 130', 140' are in the closed position or even in some intermediate positions, which in turn changes the blade torque of the conical blades 130', 140'.

[0090] although Figure 16 The embodiment illustrates a conical blade surface 252A associated with the annular disk 101A of the blade ring 100A, but in other embodiments, the conical blade surface 250A (in...) Figure 16 (Indicated by dashed lines) may also be formed or alternatively formed on the adjacent side 250 of one of the blades 130, 130' or 140, 140', extending between the blade pivot point VPP and the leading edge 132 or 142 associated with the annular disk 101B of the blade ring 100B.

[0091] Furthermore, in another alternative embodiment, the tapered blade surface may be formed on adjacent sides 250 and / or opposite adjacent sides 252 of a respective blade 130, 130' or 140, 140', extending between the blade pivot point VPP and the corresponding trailing edges 134, 144. In a further related embodiment, first tapered surfaces 250A, 252A may be formed on adjacent sides 250 and opposite adjacent sides 252 of blades 130, 130', 140, 140', extending between the blade pivot point VPP and the leading edges 132, 142, while second tapered surfaces may be formed on adjacent sides 250 and opposite adjacent sides 252 of blades 130, 130', 140, 140', extending between the blade pivot point VPP and the trailing edges 134, 144.

[0092] In some embodiments, such as Figure 17 As shown, a blade surface 250A, defined along the opposing adjacent sides 252 of one of the plurality of blades 130, 140, 130', 140, 140', and extending between the blade pivot point VPP and the leading edges 132, 142, is chamfered to form a recessed slot 255, while the opposing adjacent sides 252 also define a slot surface 260A. In these embodiments, the slot surface 260A of the opposing adjacent sides 252 of the associated blades 130, 130' or 140, 140' and the blade ring 100 (in Figure 17The gap distance CD2 between the blade ring surfaces 102 of the blade ring (represented as blade ring 100B) is larger than the blade gap distance of another blade among the plurality of blades 130, 140 (which is not included in the recessed slot 520 on the adjacent side 250).

[0093] Similar to Figure 16 In embodiments where the recessed slot 255 is located along the blades 130, 130', 140, 140', various alternative configurations are conceivable. For example, although Figure 17 The embodiment shows a recessed slot 255 formed in the opposing adjacent sides 252 of the blades 130', 140' associated with the annular disk 101A of the blade ring 100A, but in other embodiments, the recessed slot 257 (in Figure 16 (Indicated by dashed lines) may also be formed or alternatively formed on the adjacent side 250 of one of the blades 130, 130' or 140, 140', extending between the blade pivot point VPP and the leading edge 132 or 142 associated with the annular disk 101B of the blade ring 100B.

[0094] Furthermore, in another alternative embodiment, recessed slots may be formed on adjacent sides 250 and / or opposite adjacent sides 252 of a respective blade 130, 130' or 140, 140', extending between the blade pivot point VPP and the corresponding trailing edges 134, 144. In a further related embodiment, recessed slots 257, 255 may be formed on adjacent sides 250 and opposite adjacent sides 252 of blades 130, 130', 140, 140', extending between the blade pivot point VPP and the leading edges 132, 142, while additional recessed slots may be formed on adjacent sides 250 and opposite adjacent sides 252 of blades 130, 130', 140, 140', extending between the blade pivot point VPP and the trailing edges 134, 144.

[0095] The depth D5 of the recessed slot 255 (and the corresponding depth of the recessed slot 257 or any other recessed slot), measured between the planes defining the original blade surface 250A and the slot surface 260A, can vary between greater than 0% and less than 100% of the thickness of the blades 130, 130', 140, 140' (measured between adjacent side 250 and opposite adjacent side 252). In some embodiments, the depth D5 varies between 0.1% and 25%. It should be noted that in the closed position or even in some intermediate positions, increasing the depth D5 allows more exhaust gas to flow between the slot surface 260A and the adjacent blade ring surface 102A of the annular disk 101B of the blade ring 100B, which in turn alters the blade torque associated with the blades 130', 140' in the closed or intermediate positions during operation of the inlet channel system 30.

[0096] In a further embodiment, in addition to including, Figures 10-15 The bypass recesses 500A, 500B, and 500C, or including Figure 16 The conical blade surfaces 250A, 252A in various configurations, or including Figure 17 In addition to the recessed slots 255 and 257 in various configurations, one or more blades 130 and 140 may be shortened between the blade pivot point VPP and the leading edge 132 and 142 or the trailing edge 134 and 144. Figure 18 The diagram shows shortened blades 130, 130', 140, and 140' (excluding the conical or recessed slots) extending between the blade pivot point VPP and the leading edges 132 and 142. The shortened leading edges 132 and 142 are denoted as 132' and 142', and the corresponding lengths of the other blades 130 and 140 are indicated by the extended leading edges 132 and 142 (indicated by dashed lines).

[0097] When the corresponding blades 130', 140' are in the closed position or even in some intermediate positions, the shortening of the corresponding blades 130, 130', 140, 140' allows more exhaust gas to flow between the shortened blades 130', 140' and the corresponding adjacent blades 130 or 140, which in turn changes the blade torque associated with the blades 130', 140' in the closed or intermediate positions during the operation of the inlet channel system 30.

[0098] The following is for reference. Figure 19 In addition to providing such Figures 10-15 The bypass recess 500 shown or via, as Figure 16 The blade surface 250 or 252 is shown to be conical or formed by means of, for example, Figure 17 The recessed slot shown or by using, for example Figure 18In addition to using shortened blades to control the blade torque of the corresponding blades 130, 130', 140, 140', the subject matter of the invention also envisions modifying the shape of the opening drive surface 159A or the closing drive surface 159B to more closely conform to the shape of the inner surface 202 of the opening 201 in the adjusting ring 199. Specifically, the shape of the opening drive surface 159A or the closing drive surface 159B is rounded to more closely conform to the corresponding rounded shape of the inner surface 202. Thus, when the opening drive surface 159A contacts the first portion of the inner surface 202 of the opening 201 when the blades 130, 130', 140, 140' are moved to the open position, a larger portion of the surface area defined by the opening drive surface 159A contacts a corresponding larger portion of the surface area of ​​the inner surface 202, thereby distributing the force between the blade rod 153 and the adjusting ring 199. Similarly, when the closing drive surface 159B contacts another portion of the inner surface 202 of the opening 201 as the blades 130, 130', 140, 140' move to the closed position, a larger portion of the surface area defined by the closing drive surface 159B contacts a corresponding larger portion of the surface area of ​​the inner surface 202, thereby distributing the force between the blade rod 153 and the adjusting ring 199. This increased force distribution proportionally limits the wear of the corresponding opening drive surface 159A and closing drive surface 159B of the blade rod 153. When compared with the above... Figures 10-18 When the control of blade torque of blades 130 and 140 described herein is used in combination, particularly when used in combination with the control of blade torque of blades 130' and 140' excluding spacers 400 adjacent to leading edges 132, 142 or trailing edges 134, 144, the wear on the opening and closing drive surfaces 159A, 159B of the blade rod 153 associated with blades 130' and 140' is balanced, thereby corresponding to the wear on the opening and closing drive surfaces 159A, 159B of the blade rod 153 associated with other blades 130 and 140 (which include spacers 400 positioned adjacent to leading edges 132, 142 or trailing edges 134, 144). This can further increase the lifespan of the blade assembly 80 as well as the lifespan of the turbocharger 32 and the inlet passage system 30.

[0099] See again Figure 1In some embodiments, system 30 further includes a controller 146 coupled to turbocharger 32 and / or internal combustion engine 34, which controls various other components of turbocharger 32 and / or internal combustion engine 34. Controller 146 may include one or more processors or microprocessors for processing instructions stored in memory 150 to control various functions of turbocharger 32 related to the introduction of exhaust gas into turbine housing interior 40 via first volute 54 and second volute 56. These instructions may be any of the functions, algorithms, or techniques described herein that are executed by controller 146. Alternatively or additionally, controller 146 may include one or more microcontrollers, field-programmable gate arrays, systems-on-a-chip, discrete circuitry, and / or other suitable hardware, software, or firmware capable of performing the functions described herein. In some embodiments, controller 146 is an engine control unit (ECU) that controls various other components of turbocharger 32 and / or internal combustion engine 34. In embodiments where controller 146 is an engine control unit, controller 146 is decoupled from turbocharger 32. In other words, controller 146 is a separate component not included on or within turbocharger 32. In other embodiments, controller 146 is separate from the ECU. For example, controller 146 may be included on or within turbocharger 32. In other words, controller 146 is a component included on or within turbocharger 32. Reference Figure 1 The system 30 may include a turbocharger 32, an internal combustion engine 34, and a controller 146. Typically, the system 30 also includes at least one sensor 148.

[0100] The following is for reference. Figure 20 and 21 Two graphs are provided that compare the magnitudes of the blade torques of the individual blades 130, 130', 140, 140' on the thirteen-bladed single volute inlet channel system 30 under various treatments according to the invention.

[0101] First of all, Figure 20 In the middle, a comparison was made between having four spacers and having six spacers (corresponding to...) Figures 2-4The thirteen-bladed single-volute inlet channel system shown is an embodiment with six spacers 400. As illustrated, the addition of two additional spacers reduces the magnitude of the blade moments (as shown in the diamond diagram) of each blade 1 and 3-13 (corresponding to blades 130 and 140 with spacers 400 adjacent to leading edges 132, 142 or trailing edges 134, 144) to substantially the same magnitude, while the individual blade 2 (corresponding to blades 130 and 140' without spacers 400 adjacent to leading edges 132, 142 or trailing edges 134, 144) remains at a higher magnitude. Conversely, the thirteen-bladed single-volute inlet channel system with four spacers has a higher magnitude associated with blades 2, 3, 6, 9, and 12 (as shown in the square diagram). Therefore, Figure 20 This confirms the desirability of including additional spacers in a thirteen-bladed single-volute inlet channel system.

[0102] The following is for reference. Figure 21 The blade moment magnitude curves of a thirteen-bladed single-volute inlet passage system with six spacers were compared, where: without further processing (represented by square line graphs) corresponding to Figures 2-4 The recessed slots 255 and 257 are included on blade 2 (i.e., blade 130' or 140'), corresponding to Figure 17 (Represented by a diamond-shaped line diagram); the spherical bypass recess 500A is located on the annular disk 101B of the blade ring 100B at a position corresponding to the position below the blades 130' and 140', and between the blade pivot point VPP and the trailing edges 134 and 144, as shown. Figure 16 As shown (represented by a triangular line diagram); the cylindrical bypass recess 500C is located on the annular disk 101B of the blade ring 100B at a position corresponding to the position below the blades 130' and 140', and between the blade pivot point VPP and the leading edges 132 and 142, as shown. Figure 18 As shown (represented by circular line diagrams). In each of these line diagrams, compared to a thirteen-bladed single volute inlet channel system with six spacers without further treatment, the blade moment at blade 2 is reduced by introducing recessed slots 255, 257 or by using spherical or cylindrical bypass recesses 500A, 500C.

[0103] Embodiments of the invention may also be described with reference to the following numbered clauses, wherein specific features are listed in the dependent clauses:

[0104] I. An entrance access system, comprising:

[0105] A turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine, the turbocharger comprising:

[0106] A turbine housing, comprising a housing interior for receiving a turbine impeller having a plurality of equally spaced turbine blades, the turbine housing defining a turbine housing outlet in fluid communication with the housing interior; and

[0107] One or more volutes for fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the internal combustion engine into the interior of the turbine housing: and

[0108] A blade assembly, connected to the turbocharger, comprising:

[0109] A blade ring disposed within the turbine housing and surrounding the turbine impeller, the blade ring comprising an annular disk including a blade ring surface disposed between an inner and outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller, the blade ring surface including a plurality of blades rotatably arranged at intervals along the blade ring surface, each blade being rotatable between an open position and a closed position, including one or more intermediate positions; and

[0110] A plurality of spacers are arranged at intervals on the surface of the blade ring and positioned circumferentially outward relative to each of the plurality of blades, wherein each corresponding spacer is positioned adjacent to the leading or trailing edge of a corresponding blade, and each spacer is separated from its adjacent spacers by at least one blade.

[0111] Wherein, the blade gap distance defined between any portion of the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring is greater than the blade gap distance defined between any portion of the adjacent side of the second blade of the plurality of blades and the blade ring surface of the blade ring, in order to control the blade torque associated with the first blade of the plurality of blades generated during operation of the inlet channel system.

[0112] II. The inlet passage system according to Clause I, wherein: the blade gap distance defined between any portion of the adjacent side of the third blade of the plurality of blades and the first blade ring surface of the first blade ring is greater than the blade gap distance between any portion of the adjacent side of the second blade of the plurality of blades and the first blade ring surface of the first blade ring.

[0113] III. An entrance passage system according to Clause I or Clause II, wherein: the first blade of the plurality of blades corresponds to a single blade of the plurality of blades, the single blade not including a corresponding spacer of the plurality of spacers arranged adjacent to the front edge or adjacent to the rear edge.

[0114] IV. The entrance passage system according to Clause III, wherein: the second blade of the plurality of blades corresponds to another single blade of the plurality of blades, the other single blade comprising a corresponding spacer of the plurality of spacers arranged adjacent to the front edge or adjacent to the rear edge.

[0115] V. An entrance passage system according to any one of clauses I-III, wherein: the second blade of the plurality of blades corresponds to a single blade of the plurality of blades, the single blade not including a corresponding spacer of the plurality of spacers arranged adjacent to the front edge or adjacent to the rear edge.

[0116] VI. An inlet passage system according to any one of Clauses IV, wherein: the blade clearance distance between any portion of an adjacent side of one or more of the plurality of blades and the blade ring surface of the blade ring is greater than the blade clearance distance between any portion of an adjacent side of a second blade of the plurality of blades and the blade ring surface of the blade ring.

[0117] VII. An entrance passage system according to any one of clauses I-VI, wherein: the number of the plurality of spacers is equal to or less than half the number of the plurality of blades.

[0118] VIII. An inlet channel system according to any one of clauses I-VII, wherein: the blade ring includes a bypass recess extending within the blade ring surface of the blade ring.

[0119] IX. The entrance access system as described in Clause VIII, wherein: the bypass recess is a spherical bypass recess.

[0120] X. The entrance channel system as described in Clause VIII, wherein: the bypass recess is an ellipsoidal bypass recess.

[0121] XI. The entrance access system according to Clause VIII, wherein: the bypass recess is a cylindrical bypass recess.

[0122] XII. An entrance passage system according to any one of clauses VIII-XI, wherein: when the first blade of the plurality of blades is in the closed position, the bypass recess is arranged adjacent to and below the adjacent side of the first blade of the plurality of blades.

[0123] XIII. The inlet channel system according to Clause XII, wherein: the width of the bypass recess extending within the surface of the blade ring, measured in a direction parallel to the length of the first blade among the plurality of blades, when the first blade of the plurality of blades is in the closed position, is less than or equal to the length of the first blade among the plurality of blades, measured from the blade pivot point of the first blade among the plurality of blades to the leading edge, and

[0124] When the first blade of the plurality of blades is in the closed position, the bypass recess is arranged entirely below the length of the first blade of the plurality of blades between the blade pivot point and the leading edge.

[0125] XIV. The inlet channel system according to Clause XII, wherein: when the first blade of the plurality of blades is in the closed position, the width of the bypass recess extending within the surface of the blade ring, measured in a direction parallel to the length of the first blade of the plurality of blades, is less than or equal to the length of the first blade of the plurality of blades, measured from the blade pivot point of the first blade of the plurality of blades to the trailing edge, and

[0126] Wherein, when the first blade of the plurality of blades is in the closed position, the bypass recess is arranged entirely below the length of the first blade of the plurality of blades between the blade pivot point and the trailing edge.

[0127] XV. An inlet channel system according to any one of clauses I-XIV, wherein: a blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is tapered, such that the blade clearance distance between the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

[0128] XVI. An inlet passage system according to any one of clauses I-XIV, wherein: a blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is tapered, such that the blade clearance distance between the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

[0129] XVII. An inlet channel system according to any one of clauses I-XIV, wherein: the blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the leading edge.

[0130] XVIII. An inlet channel system according to any one of clauses I-XIV, wherein: the blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the trailing edge.

[0131] XIX. An inlet passage system according to any one of clauses I-XVII, wherein: the length of the first blade of the plurality of blades, measured between the blade pivot point and the leading edge of the first blade of the plurality of blades, is shorter than the length of the second blade of the plurality of blades, measured between the blade pivot point and the leading edge of the second blade of the plurality of blades.

[0132] XX. An inlet passage system according to any one of clauses I-XVIII, wherein: the blade assembly further includes an additional blade ring, the plurality of blades and the plurality of spacers are arranged between the blade ring and the additional blade ring, wherein the blade clearance distance between any portion of an adjacent side of the first blade of the plurality of blades and the blade ring surface of the additional blade ring is greater than the blade clearance distance between any portion of an adjacent side of the second blade of the plurality of blades and the blade ring surface of the additional blade ring.

[0133] XXI. The inlet channel system according to Clause XX, wherein: the blade ring surface of the additional blade ring includes at least one bypass recess extending within the blade surface of the additional blade ring.

[0134] XXII. An inlet channel system according to Clause XX or Clause XXI, wherein: a blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is tapered, such that the blade clearance distance between the opposite adjacent sides of the first blade of the plurality of blades and the blade ring surface of the other blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

[0135] XXIII. An inlet passage system according to Clause XX or Clause XXI, wherein: a blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is tapered, such that the blade clearance distance between the opposite adjacent sides of the first blade of the plurality of blades and the blade ring surface of the other blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

[0136] XXIV. An inlet channel system according to Clause XX or Clause XXI, wherein: the blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the leading edge.

[0137] XXV. An inlet channel system according to Clause XX or Clause XXI, wherein: the blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the trailing edge.

[0138] XXVI. An inlet passage system according to any one of clauses XX-XXV, wherein: the length of the first blade of the plurality of blades, measured between the blade pivot point and the leading edge of the first blade of the plurality of blades, is shorter than the length of the second blade of the plurality of blades, measured between the blade pivot point and the leading edge of the second blade of the plurality of blades.

[0139] XXVII. An inlet passage system according to any one of clauses XX-XXVI, wherein: the blade assembly further comprises:

[0140] An adjusting ring, adjacent to one of the other blade rings, such that the other blade ring is positioned between the first blade ring and the adjusting ring, the adjusting ring including a plurality of spaced-apart retaining slots: and

[0141] A plurality of blade rods, wherein a corresponding one of the plurality of blade rods includes a body portion and a wall portion extending laterally from the body portion, the body portion being coupled to a corresponding one of the plurality of blades, and the wall portion being coupled within a corresponding one of the spaced-apart retaining slots to restrict radial movement of the adjusting ring, wherein each of the plurality of blade rods moves in a rolling and sliding contact with the adjusting ring as the plurality of blades move between the open position and the closed position.

[0142] XXVII. A blade assembly for use in conjunction with a turbocharger in an inlet channel system, the blade assembly comprising:

[0143] A first blade ring is disposed inside the turbine housing and surrounds the turbine impeller. The first blade ring includes an annular disk with a first blade ring surface disposed between an inner circumferential ring and an outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller.

[0144] A second blade ring, disposed within the turbine housing and surrounding the turbine impeller, includes an annular disk comprising a second blade ring surface disposed between an inner and an outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller, and the second blade ring surface is spaced apart from the first blade to define an interior between them.

[0145] A plurality of blades are rotatably arranged in the interior at a spaced-apart arrangement along the surfaces of the first and second blade rings, wherein each blade is rotatable between an open position and a closed position, including one or more intermediate positions.

[0146] A plurality of spacers are arranged at intervals along the surfaces of the first and second blade rings and positioned circumferentially outward relative to each of the plurality of blades. Each corresponding spacer is positioned adjacent to the leading or trailing edge of a corresponding blade, and each spacer is spaced apart from its adjacent counterpart by at least one of the blades.

[0147] Wherein, the blade gap distance between any portion of the adjacent side of the first blade of the plurality of blades and the first blade ring surface of the first blade ring is greater than the blade gap distance between any portion of the adjacent side of the second blade of the plurality of blades and the first blade ring surface of the first blade ring, so as to control the blade torque associated with the first blade of the plurality of blades having the blade gap distance generated during the operation of the inlet channel system.

[0148] XXVIII. The blade assembly according to Clause XXVII, wherein: the blade clearance distance between any portion of the adjacent side of the third blade of the plurality of blades and the first blade ring surface of the first blade ring is greater than the second clearance distance between any portion of the adjacent side of the second blade of the plurality of blades and the first blade ring surface of the first blade ring.

[0149] XXIX. A blade assembly according to Clause XXVII or Clause XXVIII, wherein: the blade clearance distance between any portion of the opposite adjacent side of the first blade of the plurality of blades and the second blade ring surface of the second blade ring is greater than the blade clearance distance between any portion of the opposite adjacent side of the second blade of the plurality of blades and the second blade ring surface of the second blade ring.

[0150] XXX. The blade assembly according to any one of clauses XXVII-XXIX further includes:

[0151] An adjusting ring, positioned adjacent to the second blade ring such that the second blade ring is positioned between the first blade ring and the adjusting ring, the adjusting ring including a plurality of spaced-apart retaining slots: and

[0152] A plurality of blade rods, wherein a corresponding one of the plurality of blade rods includes a body portion and a wall portion extending laterally from the body portion, the body portion being coupled to a corresponding one of the plurality of blades, the wall portion being coupled within a corresponding one of the spaced-apart retaining slots to restrict radial movement of the adjusting ring, wherein each of the plurality of blade rods moves in a rolling and sliding contact with the adjusting ring as the plurality of blades move between the open position and the closed position.

[0153] XXXI. A blade assembly according to any one of clauses XXVII-XXX, wherein: the first blade of the plurality of blades corresponds to a single blade of the plurality of blades, the single blade not including a corresponding one of the plurality of spacers arranged adjacent to the leading edge or adjacent to the trailing edge.

[0154] XXXII. A blade assembly according to any one of clauses XXVII-XXXI, wherein: the second blade of the plurality of blades corresponds to another single blade of the plurality of blades, the other single blade comprising a corresponding one of the plurality of spacers arranged adjacent to the leading edge or adjacent to the trailing edge.

[0155] XXXIII. A blade assembly according to any one of clauses XXVII-XXXI, wherein: the second blade of the plurality of blades corresponds to another single blade of the plurality of blades, the other single blade not including a corresponding one of the plurality of spacers arranged adjacent to the leading edge or adjacent to the trailing edge.

[0156] XXXIV. A blade assembly according to any one of clauses XXVII-XXXIII, wherein: the number of the plurality of spacers is equal to or less than half the number of the plurality of blades.

[0157] XXXV. A blade assembly according to any one of clauses XXVII-XXXIV, wherein: the first blade ring includes a bypass recess extending within the first blade ring surface of the first blade ring.

[0158] XXXVI. The blade assembly according to clause XXXV, wherein: the bypass recess is a spherical bypass recess.

[0159] XXXVII. The blade assembly according to clause XXXV, wherein: the bypass recess is an ellipsoidal bypass recess.

[0160] XXXVIII. The blade assembly according to clause XXXV, wherein: the bypass recess is a cylindrical bypass recess.

[0161] XXXIX. A blade assembly according to any one of clauses XXXV-XXXVII, wherein: when the first blade of the plurality of blades is in the closed position, the bypass recess in the blade ring surface of the first blade ring is arranged adjacent to the adjacent side of the first blade of the plurality of blades.

[0162] XL. A blade assembly according to any one of clauses XXXV-XXXIX, wherein: when the first blade of the plurality of blades is in the closed position, the width of the bypass recess extending within the blade ring surface of the first blade ring, measured in a direction parallel to the length of the first blade of the plurality of blades, is less than or equal to the length of the first blade of the plurality of blades measured from the blade pivot point of the first blade of the plurality of blades to the leading edge, and

[0163] Wherein, when the first blade of the plurality of blades is in the closed position, the bypass recess is arranged entirely below the length of the first blade of the plurality of blades between the blade pivot point and the leading edge.

[0164] XLI. A blade assembly according to any one of clauses XXXV-XXXIX, wherein: when the first blade of the plurality of blades is in the closed position, the width of the bypass recess extending within the surface of the first blade ring, measured in a direction parallel to the length of the first blade of the plurality of blades, is less than or equal to the length of the first blade of the plurality of blades measured from the blade pivot point of the first blade of the plurality of blades to the trailing edge, and

[0165] Wherein, when the first blade of the plurality of blades is in the closed position, the bypass recess is arranged entirely below the length of the first blade of the plurality of blades between the blade pivot point and the trailing edge.

[0166] XLII. A blade assembly according to any one of the clauses XXXV-XLI, wherein: a blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is tapered, such that the blade clearance distance between the adjacent side of the first blade of the plurality of blades and the blade ring surface of the first blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

[0167] XLIII. A blade assembly according to any one of clauses XXXV-XLII, wherein: a blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is tapered, such that the blade clearance distance between the adjacent side of the first blade of the plurality of blades and the first blade ring surface of the first blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

[0168] XLIV. A blade assembly according to any one of the clauses XXXV-XLI, wherein: the blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the leading edge.

[0169] XLV. A blade assembly according to any one of the clauses XXXV-XLII, wherein: the blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is chamfered to form a recessed slot in the first blade of the plurality of blades between the blade pivot point and the trailing edge.

[0170] XLVI. A blade assembly according to any one of the clauses XXXV-XLV, wherein: the length of the first blade of the plurality of blades, measured between the blade pivot point and the leading edge of the first blade of the plurality of blades, is shorter than the length of the second blade of the plurality of blades, measured between the blade pivot point and the leading edge of the second blade of the plurality of blades.

[0171] XLVII. A blade assembly according to any one of clauses XXXV-XLVI, wherein: the second blade ring includes at least one bypass recess extending within the blade ring surface of the second blade ring.

[0172] XLVIII. A blade assembly according to clause XLVII, wherein: a blade surface defined along the opposing adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is tapered, such that the gap distance between the opposing adjacent sides of the first blade of the plurality of blades and the blade ring surface of the second blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

[0173] XLIX. A blade assembly according to clause XLVII or clause XLVIII, wherein: a surface defined along the opposing adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is tapered, such that the gap distance between the opposing adjacent sides of the first blade of the plurality of blades and the blade ring surface of the second blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

[0174] L. A blade assembly according to any one of clauses XLVII-XLIX, wherein: a surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the leading edge.

[0175] 1. A blade assembly according to any one of clauses XLVII-XLIX, wherein: a surface defined along opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the trailing edge.

[0176] LII. A blade assembly according to any one of clauses XLVII-LI, wherein: the length of the first blade of the plurality of blades, measured between the blade pivot point and the leading edge of the first blade of the plurality of blades, is shorter than the length of the second blade of the plurality of blades, measured between the blade pivot point and the leading edge of the second blade of the plurality of blades.

[0177] LIII. A blade assembly according to any one of clauses XLVII-LII, wherein: the length of the first blade of the plurality of blades, measured between the blade pivot point and the trailing edge of the first blade of the plurality of blades, is shorter than the length of the second blade of the plurality of blades, measured between the blade pivot point and the trailing edge of the second blade of the plurality of blades.

[0178] LIV. A method for reducing wear on the body portion of the blade shank of a blade assembly in an inlet passage system during operation, the inlet passage system comprising:

[0179] A turbocharger, used to receive exhaust gas from an internal combustion engine and to deliver compressed air to the internal combustion engine, includes:

[0180] A turbine housing, comprising a housing interior for receiving a turbine impeller having a plurality of equally spaced turbine blades, and a housing outlet in fluid communication with the housing interior, and...

[0181] One or more volutes for fluid communication with the interior of the internal combustion engine and turbine housings, for delivering exhaust gas from the internal combustion engine to the interior of the turbine housing:

[0182] The blade assembly, which is connected to the turbocharger, includes:

[0183] A blade ring, disposed within a turbine housing and surrounding a turbine impeller, includes an annular disk comprising a blade ring surface disposed between an inner and outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller, and the blade ring surface includes a plurality of blades rotatably disposed thereon at spaced intervals along the blade ring surface, each blade being rotatable between an open position and a closed position, including one or more intermediate positions.

[0184] Multiple spacers are arranged at intervals on the surface of the blade ring and positioned circumferentially outward relative to each of the multiple blades, wherein each corresponding spacer is positioned adjacent to the leading or trailing edge of a corresponding blade of the multiple blades, and each of the multiple spacers is separated from its adjacent spacer by at least one blade of the multiple blades.

[0185] An adjusting ring, positioned adjacent to a second blade ring such that the second blade ring is positioned between the first blade ring and the adjusting ring, the adjusting ring including a plurality of spaced-apart retaining slots; and

[0186] A plurality of blade rods, wherein a corresponding one of the plurality of blade rods includes a body portion and a wall portion extending laterally from the body portion, the body portion being coupled to a corresponding one of the plurality of blades, and the wall portion being coupled within a corresponding one of the spaced-apart retaining slots to restrict radial movement of an adjusting ring, wherein each of the plurality of blade rods moves in rolling and sliding contact with the adjusting ring as the plurality of blades move between an open position and a closed position;

[0187] The method includes:

[0188] The blade torque associated with the first blade is controlled by increasing the blade clearance distance between any portion of the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring, such that the blade clearance distance is greater than the blade clearance distance between any portion of the adjacent side of the second blade of the plurality of blades and the blade ring surface of the blade ring.

[0189] LV. The method according to Clause LIV, wherein the step of controlling the blade torque associated with the first blade of the plurality of blades includes: introducing a bypass recess that, when the first blade of the plurality of blades is in the closed position, extends within the blade surface of the blade ring at a location adjacent to and below the first blade of the plurality of blades on an adjacent side.

[0190] LVI. The method described in accordance with Clause LIV or Clause LV, wherein: the bypass recess is a spherical bypass recess.

[0191] LVII. The method described in accordance with Clause LIV or Clause LV, wherein: the bypass recess is an ellipsoidal bypass recess.

[0192] LVIII. The method described in accordance with Clause LIV or Clause LV, wherein: the bypass recess is a cylindrical bypass recess.

[0193] LVIX. The method according to any one of clauses LV-LVIII, wherein: when the first blade of the blades is in the closed position, the width of the bypass recess, measured in a direction parallel to the length of the first blade of the plurality of blades, is less than or equal to the length of the first blade of the plurality of blades measured from the blade pivot point of the first blade of the plurality of blades to the leading edge, and

[0194] When the first blade of the plurality of blades is in the closed position, the bypass recess is arranged entirely below the length of the first blade of the plurality of blades between the blade pivot point and the leading edge.

[0195] LVX. The method according to any one of clauses LV-LVIII, wherein: when the first blade of the blades is in the closed position, the width of the bypass recess, measured in a direction parallel to the length of the first blade of the plurality of blades, is less than or equal to the length of the first blade of the plurality of blades measured from the blade pivot point of the first blade of the plurality of blades to the trailing edge, and

[0196] When the first blade of the plurality of blades is in the closed position, the bypass recess is arranged entirely below the length of the first blade of the plurality of blades between the blade pivot point and the trailing edge.

[0197] LVXI. The method according to any one of the clauses LIV-LVX, wherein the step of controlling the blade moment associated with the first blade of the plurality of blades comprises: tapering a surface defined along the adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge, such that the blade clearance distance between the adjacent sides of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

[0198] LVXII. The method according to any one of the clauses LIV-LVXI, wherein the step of controlling the blade moment associated with the first blade of the plurality of blades comprises: tapering a surface defined along the adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge, such that the blade clearance distance between the adjacent sides of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

[0199] LVXIII. The method according to any one of the clauses LIV-LVXI, wherein the step of controlling the blade torque associated with the first blade of the plurality of blades comprises: chamfering a surface defined along an adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge to form a recessed slot.

[0200] LVXIX. The method according to any one of the clauses LIV-LVXI, wherein the step of controlling the blade moment associated with a first blade among a plurality of blades comprises: chamfering a surface defined along an adjacent side of the first blade among the plurality of blades and extending between the blade pivot point and the trailing edge to form a recessed slot.

[0201] LVXX. The method according to any one of the clauses LIV-LVXIX, wherein the step of controlling the blade moment associated with the first blade of the plurality of blades includes: reducing the length of the first blade of the plurality of blades, measured between the blade pivot point and the leading edge of the first blade of the plurality of blades.

[0202] LVXXI. The method according to any one of the clauses LIV-LVXIX, wherein the step of controlling the blade moment associated with the first blade of the plurality of blades includes: reducing the length of the first blade of the plurality of blades, measured between the blade pivot point and the trailing edge of the first blade of the plurality of blades.

[0203] The invention has been described by way of example, and it should be understood that the terminology used is descriptive rather than limiting. Based on the foregoing teachings, the invention is capable of many modifications and variations, and can be implemented in ways different from those specifically described.

Claims

1. An entrance access system, comprising: A turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine, the turbocharger comprising: A turbine housing, the turbine housing including a turbine housing interior for receiving a turbine impeller, the turbine impeller having a plurality of equally spaced turbine blades, the turbine housing defining a turbine housing outlet in fluid communication with the turbine housing interior; and One or more volutes, the volutes being in fluid communication with the interior of an internal combustion engine and the turbine housing, for delivering exhaust gas from the internal combustion engine into the interior of the turbine housing: and A blade assembly, connected to the turbocharger, comprising: A blade ring, disposed within the turbine housing and surrounding the turbine impeller, the blade ring including an annular disk, the annular disk including a blade ring surface disposed between an inner circumferential ring and an outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller, the blade ring surface including a plurality of blades rotatably arranged at intervals along the blade ring surface, each blade being rotatable between an open position and a closed position, including one or more intermediate positions; and A plurality of spacers are arranged at intervals on the surface of the blade ring and positioned circumferentially outward relative to each of the plurality of blades. Each corresponding spacer is positioned adjacent to the leading or trailing edge of a corresponding blade, and each spacer is separated from its adjacent spacer by at least one blade. Wherein, the blade gap distance defined between any portion of the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring is greater than the blade gap distance defined between any portion of the adjacent side of the second blade of the plurality of blades and the blade ring surface of the blade ring, in order to control the blade torque associated with the first blade of the plurality of blades generated during the operation of the inlet channel system.

2. The entrance access system according to claim 1, wherein: The blade gap distance defined between any portion of the adjacent side of the third blade of the plurality of blades and the first blade ring surface of the first blade ring is greater than the blade gap distance between any portion of the adjacent side of the second blade of the plurality of blades and the first blade ring surface of the first blade ring.

3. The entrance access system according to claim 1, wherein: The first blade of the plurality of blades corresponds to a single blade of the plurality of blades, the single blade not including a corresponding spacer of the plurality of spacers arranged adjacent to the front edge or adjacent to the rear edge.

4. The entrance access system according to claim 3, wherein: The second blade of the plurality of blades corresponds to another single blade of the plurality of blades, the other single blade including a corresponding spacer of the plurality of spacers arranged adjacent to the front edge or adjacent to the rear edge.

5. The entrance access system according to claim 1, wherein: The second blade of the plurality of blades corresponds to a single blade of the plurality of blades, wherein the single blade does not include a corresponding spacer of the plurality of spacers arranged adjacent to the front edge or adjacent to the rear edge.

6. The entrance access system according to claim 3, wherein: The blade gap distance between any portion of an adjacent side of one or more of the plurality of blades and the blade ring surface of the blade ring is greater than the blade gap distance between any portion of an adjacent side of the second blade of the plurality of blades and the blade ring surface of the blade ring.

7. The entrance access system according to claim 1, wherein: The number of the plurality of spacers is equal to or less than half the number of the plurality of blades.

8. The entrance access system according to claim 1, wherein: The blade ring includes a bypass recess extending within the blade ring surface of the blade ring.

9. The entrance access system according to claim 8, wherein: The bypass recess is a spherical bypass recess.

10. The entrance access system according to claim 8, wherein: The bypass recess is an ellipsoidal bypass recess.

11. The entrance access system according to claim 8, wherein: The bypass recess is a cylindrical bypass recess.

12. The entrance access system according to claim 8, wherein: When the first blade of the plurality of blades is in the closed position, the bypass recess is arranged adjacent to and below the adjacent side of the first blade of the plurality of blades.

13. The entrance access system according to claim 12, wherein: When the first blade of the plurality of blades is in the closed position, the width of the bypass recess extending within the surface of the blade ring in the blade ring, measured in a direction parallel to the length of the first blade of the plurality of blades, is less than or equal to the length of the first blade of the plurality of blades, measured from the blade pivot point of the first blade of the plurality of blades to the leading edge. Wherein, when the first blade of the plurality of blades is in the closed position, the bypass recess is arranged entirely below the length of the first blade of the plurality of blades between the blade pivot point and the leading edge.

14. The entrance access system according to claim 12, wherein: When the first blade of the plurality of blades is in the closed position, the width of the bypass recess extending within the surface of the blade ring in the blade ring, measured in a direction parallel to the length of the first blade of the plurality of blades, is less than or equal to the length of the first blade of the plurality of blades, measured from the blade pivot point of the first blade of the plurality of blades to the trailing edge, and Wherein, when the first blade of the plurality of blades is in the closed position, the bypass recess is arranged entirely below the length of the first blade of the plurality of blades between the blade pivot point and the trailing edge.

15. The entrance access system according to claim 1, wherein: The blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is tapered, such that the blade clearance distance between the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

16. The entrance access system according to claim 1, wherein: The blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is tapered, such that the blade clearance distance between the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

17. The entrance access system according to claim 8, wherein: The blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is tapered, such that the blade clearance distance between any portion of the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

18. The entrance access system according to claim 8, wherein: The blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is tapered, such that the blade clearance distance between any portion of the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

19. The entrance access system according to claim 8, wherein: The blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the leading edge.

20. The entrance access system according to claim 8, wherein: The blade surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the trailing edge.

21. The entrance access system according to claim 8, wherein: The length of the first blade, measured between its pivot point and leading edge, is shorter than the length of the second blade, measured between its pivot point and leading edge, among the plurality of blades.

22. The entrance access system according to claim 1, wherein: The blade assembly further includes an additional blade ring, the plurality of blades and the plurality of spacers being arranged between the blade ring and the additional blade ring, wherein the blade clearance distance between any portion of the opposite adjacent side of the first blade of the plurality of blades and the blade ring surface of the additional blade ring is greater than the blade clearance distance between any portion of the adjacent side of the second blade of the plurality of blades and the blade ring surface of the additional blade ring.

23. The entrance access system according to claim 22, wherein: The blade ring surface of the additional blade ring includes at least one bypass recess extending within the blade surface of the additional blade ring.

24. The entrance access system according to claim 22, wherein: The blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is tapered, such that the blade clearance distance between the opposite adjacent sides of the first blade of the plurality of blades and the blade ring surface of the other blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

25. The entrance access system according to claim 22, wherein: The blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is tapered, such that the blade clearance distance between the opposite adjacent sides of the first blade of the plurality of blades and the blade ring surface of the other blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

26. The entrance access system according to claim 23, wherein: The blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is tapered, such that the blade clearance distance between the opposite adjacent sides of the first blade of the plurality of blades and the blade ring surface of the other blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the leading edge.

27. The entrance access system according to claim 23, wherein: The blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is tapered, such that the blade clearance distance between the opposite adjacent sides of the first blade of the plurality of blades and the blade ring surface of the other blade ring increases in the direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

28. The entrance access system according to claim 22, wherein: The blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the leading edge.

29. The entrance access system according to claim 22, wherein: The blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the trailing edge.

30. The entrance access system according to claim 23, wherein: The blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the leading edge.

31. The entrance access system according to claim 23, wherein: The blade surface defined along the opposite adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge is chamfered to create a recessed slot in the first blade of the plurality of blades between the blade pivot point and the trailing edge.

32. The entrance access system according to claim 23, wherein: The length of the first blade, measured between its pivot point and leading edge, is shorter than the length of the second blade, measured between its pivot point and leading edge, among the plurality of blades.

33. The entrance access system according to claim 22, wherein: The blade assembly also includes: An adjusting ring, positioned adjacent to one of the additional blade rings such that the additional blade ring is positioned between the first blade ring and the adjusting ring, the adjusting ring including a plurality of spaced-apart retaining slots: and A plurality of blade rods, wherein a corresponding blade rod of the plurality of blade rods includes a body portion and a wall portion extending laterally from the body portion, the body portion being coupled to a corresponding blade of the plurality of blades, and the wall portion being coupled within a corresponding retaining slot of the spaced retaining slots to restrict radial movement of the adjusting ring, wherein each blade rod of the plurality of blade rods moves in a rolling and sliding contact with the adjusting ring when the plurality of blades move between the open position and the closed position.

34. A blade assembly for use in conjunction with a turbocharger in an inlet channel system, the blade assembly comprising: A first blade ring, disposed within the turbine housing and surrounding the turbine impeller, includes an annular disk comprising a first blade ring surface disposed between an inner and an outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller. A second blade ring, disposed within the turbine housing and surrounding the turbine impeller, includes an annular disk comprising a second blade ring surface disposed between an inner and an outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller, and the second blade ring surface is spaced apart from the first blade to define an interior between them. A plurality of blades are rotatably arranged in the interior at intervals along the surfaces of a first blade ring and a second blade ring, wherein each blade is rotatable between an open position and a closed position, including one or more intermediate positions; and A plurality of spacers are arranged at intervals along the surfaces of the first and second blade rings and positioned circumferentially outward relative to each of the plurality of blades. Each corresponding spacer is positioned adjacent to the leading or trailing edge of a corresponding blade, and each spacer is spaced apart from its adjacent spacer by at least one blade. Wherein, the blade gap distance between any portion of the adjacent side of the first blade of the plurality of blades and the first blade ring surface of the first blade ring is greater than the blade gap distance between any portion of the adjacent side of the second blade of the plurality of blades and the first blade ring surface of the first blade ring, so as to control the blade torque associated with the first blade of the plurality of blades having the blade gap distance generated during the operation of the inlet channel system.

35. A method for reducing wear on the body portion of a blade shank of a blade assembly in an inlet passage system during operation, the inlet passage system comprising: A turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine, the turbocharger comprising: A turbine housing, comprising a turbine housing interior for receiving a turbine impeller having a plurality of equally spaced turbine blades, the turbine housing defining a turbine housing outlet in fluid communication with the turbine housing interior, and... One or more volutes, the volutes being in fluid communication with the interior of the internal combustion engine and the turbine housing, for delivering exhaust gas from the internal combustion engine into the interior of the turbine housing: Blade assembly, the blade assembly being connected to the turbocharger, the blade assembly comprising: A blade ring, disposed within the turbine housing and surrounding the turbine impeller, the blade ring comprising an annular disk, the annular disk including a blade ring surface disposed between an inner circumferential ring and an outer circumferential ring, wherein the inner circumferential ring defines an orifice for receiving the turbine impeller, and the blade ring surface including a plurality of blades rotatably disposed thereon at spaced intervals along the blade ring surface, each blade being rotatable between an open position and a closed position, including one or more intermediate positions; and A plurality of spacers are arranged at intervals on the surface of the blade ring and positioned circumferentially outward relative to each of the plurality of blades, wherein each corresponding spacer is positioned adjacent to the leading or trailing edge of a corresponding blade among the plurality of blades, and each spacer is separated from an adjacent spacer among the plurality of spacers by at least one blade among the plurality of blades. An adjusting ring, positioned adjacent to a second blade ring such that the second blade ring is positioned between the first blade ring and the adjusting ring, the adjusting ring including a plurality of spaced-apart retaining slots; and A plurality of blade rods, wherein a corresponding blade rod of the plurality of blade rods includes a body portion and a wall portion extending laterally from the body portion, the body portion being coupled to a corresponding blade of the plurality of blades, the wall portion being coupled within a corresponding retaining slot of the spaced retaining slots to restrict radial movement of the adjusting ring, wherein each blade rod of the plurality of blade rods moves in rolling and sliding contact with the adjusting ring when the plurality of blades move between an open position and a closed position; The method includes: The blade torque associated with the first blade among the plurality of blades is controlled by increasing the blade clearance distance between any portion of the adjacent side of the first blade among the plurality of blades and the blade ring surface of the blade ring, such that the blade clearance distance is greater than the blade clearance distance between any portion of the adjacent side of the second blade among the plurality of blades and the blade ring surface of the blade ring.

36. The method of claim 35, wherein: The step of controlling the blade torque associated with the first blade of the plurality of blades includes: introducing a bypass recess that, when the first blade of the plurality of blades is in the closed position, extends within the blade surface of the blade ring at a position adjacent to and below the adjacent side of the first blade of the plurality of blades.

37. The method of claim 35, wherein: The step of controlling the blade torque associated with the first blade of the plurality of blades includes: tapering a surface defined along the adjacent sides of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge, such that the blade clearance distance between the adjacent sides of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the leading edge, and / or The step of controlling the blade torque associated with the first blade of the plurality of blades includes: making a surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the trailing edge tapered, such that the blade clearance distance between the adjacent side of the first blade of the plurality of blades and the blade ring surface of the blade ring increases in a direction from the blade pivot point of the first blade of the plurality of blades to the trailing edge.

38. The method of claim 35, wherein: The step of controlling the blade torque associated with the first blade of the plurality of blades includes: chamfering a surface defined along the adjacent side of the first blade of the plurality of blades and extending between the blade pivot point and the leading edge to form a recessed slot, and / or The step of controlling the blade torque associated with the first blade among the plurality of blades includes: chamfering a surface defined along the adjacent side of the first blade among the plurality of blades and extending between the blade pivot point and the trailing edge to form a recessed slot.

39. The method according to claim 36, wherein: The step of controlling the blade moment associated with the first blade among the plurality of blades includes: reducing the length of the first blade among the plurality of blades, measured between the blade pivot point and the leading edge of the first blade, and / or The step of controlling the blade torque associated with the first blade among the plurality of blades includes: reducing the length of the first blade among the plurality of blades, measured between the blade pivot point and the trailing edge of the first blade among the plurality of blades.

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