Double volute turbine casing

Abstract

A turbine assembly may include: a turbine housing defining a longitudinal axis and including a first vortex and a first tongue at a first angle about the longitudinal axis, and a second vortex and a second tongue at a second angle about the longitudinal axis, wherein the angular span between the first angle and the second angle is greater than 1 degree and less than 180 degrees; and a first blade group and a second blade group disposed in the turbine housing, wherein a blade of the first blade group is aligned with the first tongue, and a blade of the second blade group is aligned with the second tongue.

Description

Technical Field

[0001] The main topics discussed in this article concern turbochargers. Background Technology

[0002] A turbocharger can increase the output of an internal combustion engine. A turbocharger may include an exhaust turbine assembly that receives exhaust gas from the cylinders of the internal combustion engine. The exhaust gas can be directed to a turbine impeller, allowing energy to be extracted, for example, to drive the compressor impeller of a compressor assembly. Attached Figure Description

[0003] When combined with the examples shown in the accompanying drawings, a more complete understanding can be gained by referring to the following detailed description, in which:

[0004] Figure 1 This is a schematic diagram illustrating an example of a turbocharger, internal combustion engine, and controller;

[0005] Figure 2 These are schematic diagrams illustrating examples of internal combustion engines and turbine components;

[0006] Figure 3 A series of views showing an example of a twin-scroll turbine assembly;

[0007] Figure 4 A perspective view of an example of a twin-scroll turbine assembly;

[0008] Figures 5A and 5B are perspective views of a portion of an example of a twin-scroll turbine assembly;

[0009] Figure 6 This is a cross-sectional view of a portion of an example of a turbocharger;

[0010] Figure 7A and Figure 7B This is a cross-sectional view of a portion of a twin-scroll turbine assembly;

[0011] Figure 8A and Figure 8B This is a cross-sectional view of a portion of a twin-scroll turbine assembly;

[0012] Figure 9 This is a perspective view of an example of a blade assembly.

[0013] Figure 10 yes Figure 6 A cross-sectional view of a portion of the turbocharger;

[0014] Figure 11 This is a perspective view of an example flow channel.

[0015] Figure 12This is a perspective view of an example flow channel; and

[0016] Figure 13 This is a perspective cutaway view of a portion of an example turbocharger, showing the exhaust valve in the open position. Detailed Implementation

[0017] Turbochargers are frequently used to increase the output of internal combustion engines. (Reference) Figure 1 As an example, system 100 may include an internal combustion engine 110 and a turbocharger 120. Figure 1 As shown, system 100 may be part of vehicle 101, wherein system 100 is disposed in the engine compartment and connected to exhaust duct 103, which directs exhaust gas to exhaust outlet 109, for example, located behind passenger compartment 105. Figure 1 In one example, a processing unit 107 may be provided to process exhaust gas (e.g., to reduce emissions via catalytic conversion of molecules, etc.).

[0018] like Figure 1 As shown, the internal combustion engine 110 includes an engine block 118, an intake port 114, and an exhaust port 116. The engine block 118 houses one or more combustion chambers that operatively drive a shaft 112 (e.g., via a piston). The intake port 114 provides a flow path for air to the engine block 118, and the exhaust port 116 provides a flow path for exhaust gas from the engine block 118.

[0019] The turbocharger 120 can be used to extract energy from the exhaust and provide energy to the intake air, which can be combined with fuel to form combustion gases. For example... Figure 1 As shown, the turbocharger 120 includes an air inlet 134, a shaft 122, a compressor housing assembly 124 for a compressor impeller 125, a turbine housing assembly 126 for a turbine impeller 127, another housing assembly 128, and an exhaust outlet 136. The housing assembly 128 may be referred to as the central housing assembly because it is disposed between the compressor housing assembly 124 and the turbine housing assembly 126. The shaft 122 may be a shaft assembly comprising multiple components. The shaft 122 may be rotatably supported by a bearing system (e.g., journal bearings, rolling element bearings, etc.) disposed in the housing assembly 128 (e.g., in a bore defined by one or more bore walls), such that rotation of the turbine impeller 127 causes rotation of the compressor impeller 125 (e.g., rotatably coupled by the shaft 122). As an example, the central housing rotating assembly (CHRA) may include a compressor impeller 125, a turbine impeller 127, a shaft 122, a housing assembly 128, and various other components (e.g., a compressor side plate disposed at an axial position between the compressor impeller 125 and the housing assembly 128).

[0020] exist Figure 1 In the example, the variable geometry component 129 is shown partially disposed between the housing assembly 128 and the housing assembly 126. This variable geometry component may include blades or other components to change the geometry of the passageway leading to the turbine impeller space in the turbine housing assembly 126. As an example, a variable geometry compressor assembly may be provided.

[0021] exist Figure 1 In the example, the exhaust valve (or simply exhaust valve) 135 is positioned near the exhaust inlet of the turbine housing assembly 126. The exhaust valve 135 can be controlled to allow at least some of the exhaust gas from the exhaust port 116 to bypass the turbine impeller 127. Various exhaust valves, exhaust valve components, etc., can be applied to conventional fixed-nozzle turbines, fixed-blade nozzle turbines, variable-nozzle turbines, twin-scroll turbochargers, etc. As an example, the exhaust valve can be an internal exhaust valve (e.g., at least partially inside the turbine housing). As an example, the exhaust valve can be an external exhaust valve (e.g., operatively connected to a duct in fluid communication with the turbine housing).

[0022] exist Figure 1 The example also shows an exhaust gas recirculation (EGR) duct 115, which may optionally be provided with one or more valves 117, for example, to allow exhaust gas to flow to a location upstream of the compressor impeller 125.

[0023] Figure 1 Example arrangement 150 for directing exhaust gas flow to exhaust turbine housing assembly 152 and another example arrangement 170 for directing exhaust gas flow to exhaust turbine housing assembly 172 are also shown. In arrangement 150, cylinder head 154 internally includes passage 156 to guide exhaust gas from cylinders to turbine housing assembly 152, while in arrangement 170, manifold 176 provides mounting for turbine housing assembly 172, for example, without any separate, medium-length exhaust pipe. In example arrangements 150 and 170, turbine housing assemblies 152 and 172 can be configured for use with wastegates, variable geometry assemblies, etc.

[0024] exist Figure 1In this document, an example of controller 190 is shown including one or more processors 192, memory 194, and one or more interfaces 196. Such a controller may include a circuit system, such as the circuit system of an engine control unit (ECU). As described herein, various methods or techniques may be optionally incorporated into the controller, for example, through control logic. The control logic may depend on one or more engine operating conditions (e.g., turbo rpm, engine rpm, temperature, load, lubricant, cooling, etc.). For example, sensors may transmit information to controller 190 via one or more interfaces 196. The control logic may depend on such information, and controller 190 may then output control signals to control engine operation. Controller 190 may be configured to control lubricant flow, temperature, variable geometry components (e.g., variable geometry compressors or turbines), exhaust valves (e.g., via actuators), electric motors, or one or more other components associated with the engine, turbocharger (or multiple turbochargers), etc. As an example, turbocharger 120 may include one or more actuators and / or one or more sensors 198, which may be coupled, for example, to one or more interfaces 196 of controller 190. As an example, wastegate 135 may be controlled by a controller including actuators responsive to electrical signals, pressure signals, etc. As an example, the actuator for wastegate may be a mechanical actuator, for example, one that can operate without requiring electrical power (e.g., consider a mechanical actuator configured to respond to a pressure signal supplied via a duct).

[0025] Such as Figure 1 The internal combustion engine of engine 110 can generate exhaust with a pulsating flow. In so-called constant-pressure turbocharging (e.g., Stauaufladung), an exhaust manifold with a sufficiently large volume can be used to reduce the mass flow and pressure pulses, making the flow of exhaust to the turbine relatively stable. Another approach is called pulse turbocharging (e.g., Stoβaufladung), the purpose of which can be to utilize the kinetic energy of the exhaust as it leaves the cylinder exhaust port. For example, relatively short, small-cross-section ducts can connect each exhaust port to the turbine, thus allowing the utilization of most of the kinetic energy associated with exhaust discharge. As an example, appropriate grouping of the exhaust ports of different cylinders can organize the exhaust pulses so that they are continuous, for example, with minimal overlap. In this way, exhaust flow instability can be kept at an acceptable level. As an example, the decision to implement constant-pressure or pulse turbocharging can depend on one or more factors, such as, for example, power requirements, efficiency requirements, fuel type, number of cylinders, cylinder / stroke volume, engine size, etc.

[0026] Figure 2A schematic diagram of an example internal combustion engine 200 and an example turbine assembly 260 is shown, wherein one or more manifolds 216 provide fluid communication between the cylinders of the internal combustion engine 200 and the turbine assembly 260. Figure 2 In the example, the internal combustion engine 200 is shown as comprising an even number of cylinders divided into two groups, wherein the first group is in fluid communication with manifold 217 and the second group is in fluid communication with manifold 219. As shown, these manifolds 217 and 219 are exhaust manifolds that receive exhaust from the cylinders of the internal combustion engine 200 (e.g., cylinders 1-3 and 4-6, respectively) and direct this exhaust flow to passages 267 and 269 of the turbine assembly 260.

[0027] exist Figure 2 In the example, turbine assembly 260 includes a flange 261 and walls 262 and 264 defining channels 267 and 269. As shown, channels 267 and 269 may be defined as vortex tubes (e.g., volutes).

[0028] A vortex tube is generally a helical channel that can be defined by a housing, which can be called a vortex casing. A vortex tube can guide exhaust flow from a single channel, such as a duct, to an annular channel, which can be called an annular nozzle. For example, a vortex tube can guide exhaust from a manifold to the vicinity of a turbine impeller via an annular nozzle.

[0029] A key characteristic of a vortex turbine is its area-to-radius ratio (A / R). A / R is defined as the cross-sectional area of ​​the inlet (or the outlet for the compressor housing) divided by the radius from the turbine centerline to the center of mass of that region. Both the area and radius change as the vortex spirals radially inward from its inlet to its annular nozzle, reducing the cross-sectional flow area. A / R can be selected based on various factors to help ensure that the internal combustion engine efficiently propels the turbine impeller as exhaust gas flows through the turbine housing. Choosing an appropriate A / R can help optimize performance. For example, too small an A / R will impede exhaust flow and result in power loss, especially in the upper RPM power band; however, too large an A / R will make the turbine sluggish in response to changes in exhaust flow.

[0030] Generally, for a twin-scroll shell, A / R can be defined as the sum of the inlet areas of the two scrolls divided by the radius at the inlet. As an example, for a twin-scroll shell, A / R can be defined on a per-scroll basis or on a global basis.

[0031] Figure 3These are a series of views illustrating an example of a twin-scroll turbine assembly 360. As shown, the twin-scroll turbine assembly 360 includes a flange 361 that serves as an intake for exhaust gas into two passages 367 and 369. A cross-sectional view along line BB about passage 367 shows wall 362-1 forming the swirl of passage 367, which terminates at tongue 363-1, and a cross-sectional view along line CC about passage 369 shows wall 362-2 forming the swirl of passage 369, which terminates at tongue 363-2. Figure 3 In the example, tongues 363-1 and 363-2 overlap. As shown, an A / R can be defined for each vortex in the vortex tube, where their inlets can be defined relative to the respective ends of tongues 363-1 and 363-2.

[0032] Figure 4 This is a perspective view of an example of a twin-scroll turbine assembly 460, where channels 467 and 469 are twin-scroll channels ending at tongues 463-1 and 463-2. In such an example, the A / R ratio can be determined for each scroll in the scroll or for both scrolls in general.

[0033] Figures 5A and 5B are perspective views of a portion of an example of a twin-scroll turbine assembly 560, where channels 567 and 569 are offset twin-scroll channels at tongues 563-1 and 563-2. In such an example, the same radial line cannot be used to determine the A / R of the two scrolls; instead, two radial lines at different angular positions (e.g., azimuth angles around the centerline) can be used to determine the A / R of the two scrolls.

[0034] In the examples of Figures 5A and 5B, the angular offset can be greater than 0 degrees and less than 180 degrees. For example, consider a range of approximately 1 degree to approximately 120 degrees. In this approach, the angular offset can provide spatial benefits and / or blade-related benefits. For example, regarding spatial benefits, consider a turbine assembly including an exhaust valve, where the angular offset can provide space for exhaust valve passages branching off from each of passages 567 and 569. Regarding blades, consider an example of a turbine assembly 560 including two sets of blades, where the two sets of blades are angularly offset such that the blades of one set are not aligned with the blades of the other set.

[0035] Regarding the potential misalignment of the two sets of blades, consider reducing high cyclic fatigue (HCF). In such an example, the two sets of blades are not angularly aligned, which helps reduce the risk of HCF in a way that can be achieved without compromising performance. Regarding the alignment of the blades with the tongue, this method can help smooth the flow from the vortex channel to the turbine impeller space.

[0036] As an example, a turbine assembly may include angled twin-scroll tubes with two sets of blades disposed within the turbine assembly. One blade from one set is aligned with the tongue-shaped end of one of the twin-scroll tubes (e.g., with or without clearance), and one blade from the other set is aligned with the tongue-shaped end of the other twin-scroll tube. In this approach, exhaust flow can flow more efficiently from the inlet to the annular nozzle, where the blades define a throat within the annular nozzle.

[0037] Regarding the purpose of the blades, they help accelerate the exhaust flow, which can reduce stage losses in a way that leads to higher efficiency. As explained, the tongue can be aligned with the blades to smooth the exhaust flow. Furthermore, by offsetting the tongue at a specific angle, blades from one set of blades can be offset from blades from another set, thereby reducing high cyclic fatigue (HCF).

[0038] As an example, a turbine assembly including a twin-scroll turbine and two sets of blades may include one or more seals that help seal, position, and / or secure the blade sets. For example, consider using ring seals, which may be open-ring seals (e.g., piston ring seals). Such seals may be located at the outer circumference (e.g., circumference) of the two sets of blades, facilitating alignment of the two sets of blades with corresponding tongues during installation, wherein the seals also provide a sealing alignment between the turbine housing and the two sets of blades. In such an example, the two sets of blades may be a first set of fixed blades and a second set of fixed blades of a blade ring or spaced-apart blade rings. In such an example, the two sets of blades may be adjusted in terms of their angular offset, for example, to accommodate one or more twin-scroll turbine housings (e.g., with different tongue angular offsets, etc.).

[0039] Such as about Figure 2 The exhaust gas can originate from different cylinders in an internal combustion engine, where these cylinders ignite and exhaust at different times, causing exhaust pulsation. In this case, at a given point in time, the pressure in one passage may be lower than the pressure in another. Given this pressure difference, leakage can occur from the higher-pressure passage to the lower-pressure passage if the passages are not properly sealed. As an example, seals such as ring seals can be used to seal one or more areas where the blade assembly is connected to the turbine housing. This approach can help reduce the risk of inter-passage exhaust leakage that may be driven by exhaust pulsation. For example, in a six-cylinder internal combustion engine, the seals can help reduce exhaust leakage from one passage for cylinders 1, 2, and 3 to another passage for cylinders 4, 5, and 6.

[0040] As an example, consider 15 blades in two sets of blades, spaced 24 degrees apart (360° / 15 = 24°), such that the angular offset can be within the range of greater than 0 degrees to less than 24 degrees, because at 24 degrees, the blades from both sets of blades will match again. This can be achieved through multiplicative repetition (e.g., the first blade and the third blade will be arranged, and then the blade ring can be rotated within the range of greater than zero degrees to less than 24 degrees). In this method, the volute tongue is aligned with the corresponding blade, so that the vortex tube (e.g., the volute) must also be angularly displaced. This method can provide the opportunity to arrange an exhaust valve passage (or multiple exhaust valve passages) route in a manner different from the aligned blade sets and aligned vortex tube tongues. As an example, in the aforementioned case of matching the first and third blades, the vortex tube tongue can be displaced from (3 * 24°) to (3 * 24° + 23.9°).

[0041] Figure 6 This is a cross-sectional view of a portion of an example of a turbocharger 600, which includes a central housing 601 (e.g., a bearing housing), a shaft 602, a bearing assembly 603 rotatably supporting the shaft 602 in a through-hole in the central housing 601, a heat shield 604, and a turbine impeller 607, which may be part of the shaft 602 to form a shaft and impeller assembly (SWA). For example, the turbine impeller 607 may be welded to the shaft 602 to form the SWA. As shown, the shaft 602 includes a free end to which a compressor impeller may be mounted to form a rotating assembly including the turbine impeller 607 and the compressor impeller supported by the bearing assembly 603, which may be a rolling element bearing assembly; note that journal bearings or multiple bearings and / or bearing assemblies may be used.

[0042] exist Figure 6 In the example, turbine assembly 660 is coupled to central housing 601, wherein heat shield 604 may perform one or more functions. For example, heat shield 604 may help reduce heat transfer from exhaust to central housing 601, and / or heat shield 604 may be a spring that applies an axially outward force away from central housing 601 and toward turbine assembly 660.

[0043] like Figure 6 As shown in the example, turbine assembly 660 may include turbine housing 662 (e.g., single or multiple pieces) that defines passages 667 and 669 as a double-scroll tube that can guide exhaust gas into the turbine impeller space, wherein the exhaust gas can exit turbine assembly 660 via an outlet passage 665 defined by the turbine housing 662.

[0044] like Figure 6As shown in the example, turbine assembly 660 may include two sets of blades 680 and 690, wherein blade set 680 defines a throat for exhaust gas in passage 667, and wherein blade set 690 defines a throat for exhaust gas in passage 669. As mentioned, heat shield 604 may function as a spring, wherein... Figure 6 In the example, the heat shield 604 applies a force to the blade assemblies 680 and 690 to push them against the turbine housing 662. In this approach, the force can help reduce leakage, which can be facilitated by using a seal. For example, consider a compressible seal, where the spring force applied by the heat shield 604 can compress the seal, allowing it to remain in contact with the opposing surface to form a suitable seal. Figure 6 As shown in the example, the heat shield 604 may be an annular disc and function as a disc spring (e.g., similar to a Basswell washer). For example, the heat shield 604 may contact the surface of the central housing 601 at its inner periphery and the surface of the blade assembly 680 at its outer periphery. In such an example, the heat shield 604 itself may be compressed (e.g., preloaded) when the turbine assembly 660 is coupled to the central housing 601.

[0045] exist Figure 6 In the example, exhaust gas can flow in channels 667 and 669 and through the throats of two sets of blades 680 and 690 to rotatably drive turbine impeller 607. As shown, turbine impeller 607 has blades including a leading edge of an inlet section portion of turbine impeller 607, wherein the blades also include a trailing edge of an outlet section portion of turbine impeller 607. As exhaust gas flows through the throats of blade sets 680 and 690 into the turbine impeller space, turbine impeller 607 rotates as exhaust gas flows through the turbine impeller space into exhaust outlet channel 665, which can be in fluid communication with an exhaust system (e.g., catalytic converter, muffler / silencer, etc.) that may include an outlet under ambient conditions.

[0046] Figure 6Another cross-sectional view of a portion of the turbocharger 600 is also shown, wherein the anti-rotation mechanism includes a pin hole 606 in the center housing 601, a pin hole 664 in the turbine housing 662, and a pin 609 partially disposed in the pin hole 606 and partially disposed in the pin hole 664. As shown, a portion of the turbine housing 662 may cover a portion of the center housing 601, wherein the pin 609 may be inserted from the outside of the turbine housing 662 through the pin hole 664 to enter the pin hole 606 of the center housing 601. In such an example, the rotational positions of the center housing 601 and the turbine housing 662 can be fixed relative to each other, which can provide proper alignment of the blade sets 680 and 690. In particular, this anti-rotation feature helps ensure that the blade set 690 includes blades properly aligned with the tongues of the corresponding vortex tubes.

[0047] Figure 7A and Figure 7B This is a cross-sectional view of an example portion of a twin-scroll turbine assembly 660. As shown, the turbine housing 662 may include a flange 661, a first wall portion 662-1 that defines a tongue-like portion 663-1 for a passage 667 (see figure). Figure 7B ) and the second wall portion 662-2 that can be defined for the tongue-shaped portion 663-2 of the channel 669 (see Figure 7A ). For example in Figure 7A and Figure 7B As shown, with Figure 7A Compared to the view, Figure 7B The view is axially further away from the central housing 601 (see, for example, the cross-sectional shape and area of ​​the turbine impeller 607).

[0048] like Figure 7A and Figure 7B As shown, blade assembly 680 is not aligned with blade assembly 690 because they have different angular positions about a central axis (e.g., the axis of rotation of turbine impeller 607). Specifically, blade assembly 680 includes a blade aligned with tongue 663-1, and blade assembly 690 includes a blade aligned with tongue 663-2, as mentioned, tongues 663-1 and 663-2 may be angularly offset from each other.

[0049] exist Figure 7A and Figure 7B In the example, angles Θ1 and Θ2 are shown as representing the positions of tongue 663-1 and tongue 663-2, respectively, and ΔΘ as the angular offset or angular span between tongue 663-1 and tongue 663-2. In such an example, the axis of rotation of turbine impeller 607 can be used as the z-axis of a cylindrical coordinate system (z, r, and Θ) and / or flange 661 can be used as a reference, which can be a common flange for channels 667 and 669 (see example). Figure 11( ), or one or more other features, coordinates, etc., can be used as one or more references. As shown in the figure, the angular offset ΔΘ can be determined relative to tongue 663-1 and tongue 663-2. In Figure 7A and Figure 7B In the example, the angular offset is approximately 45 degrees. As an example, angles Θ1 and Θ2 can be used to determine the A / R value of each vortex channel in vortex channel 667 and vortex channel 669.

[0050] As an example, blade assembly 690 can be positioned relative to the central housing, and blade assembly 680 can be positioned relative to the turbine housing, such that blade assembly 690 rotates when the central housing rotates, and blade assembly 680 rotates when the turbine housing rotates. In such an example, if the turbine housing 662 rotates, only blade assembly 680 will rotate, where rotation of turbine housing 662 may cause misalignment of the blades of blade assembly 690 with the tongue 663-2 of turbine housing 662. As explained, an anti-rotation mechanism between the turbine housing and the central housing can be used to maintain proper alignment of the blades with the tongue. As an example, one or more other methods can be used to position one or more sets of blades, where assembly and operation are unimpeded.

[0051] Figure 8A and Figure 8B This is a cross-sectional view of an example portion of the twin-scroll turbine assembly 660. Specifically, in... Figure 8A In the image, leaf blade 691 is shown aligned with tongue-shaped portion 663-2, and... Figure 8B In the image, leaf blade 681 is shown aligned with tongue-shaped portion 663-1. Figure 8A and Figure 8B In the example, blades 681 and 691 can be positioned at a distance from their respective tongues 663-1 and 663-2, wherein the gap between the leading edge of the blade and the trailing edge of the tongue can range from approximately 0 mm to approximately 10 mm, depending on the size of the turbine impeller, etc. As an example, as shown in the illustration, blade 691 (or blade 681) may have a longer length than other blades within blade group 690 (e.g., or blade group 680), such that it extends closer to tongue 691. As an example, the gap may or may not exist between the blade and the tongue (e.g., considering tongue and blade contact, or tongue extending into the blade space to effectively function as a blade defining one or more throats together with one or more adjacent blades).

[0052] Figure 9This is an example of a blade assembly 900 and a perspective view in cylindrical coordinates z and r, wherein the blade assembly 900 includes two sets of blades 680 and 690 marked with blades 681 and 691, which may be blades aligned with corresponding tongues (e.g., tongue tips). As shown, blade sets 680 and 690 can be fixedly disposed between rings 686, 688, 696, and 698, wherein rings 686, 688, 696, and 698 may include one or more features 683-1, 683-2, 683-3, etc., which facilitate installation, positioning, fixation, sealing, etc. in the turbine assembly. Figure 9 In one example, the blade assembly 900 includes a slot 692 defined in the space formed by the connection between the blade groups 680 and 690. As an example, the slot 692 can be formed by placing the blade groups 680 and 690 in contact with each other.

[0053] Figure 9 Examples of pins 673 and pin holes 613, 666, 683, and 693 are also shown. In such examples, pins and pin holes can be used to position one component relative to another component, which can include positioning to limit positional changes such as rotational position. For example, pins and pin holes can be part of an anti-rotation mechanism.

[0054] exist Figure 9 In the example, the ring 696 of the blade assembly 690 may be stepped, such that it includes a stepped portion 697. In such an example, the stepped portion 697 may include one or more positioning features, such as, for example, one or more pin holes (e.g., as one or more key and keyway features) that can receive one or more corresponding pins. For example, as shown in the illustration, pin holes 693 may be in the ring 696 (e.g., in the stepped portion 697), such as in the axial surface of the ring 696, wherein the central housing includes pin holes 614 as corresponding pin holes, such that pins 693 can be partially disposed in pin holes 693 and partially disposed in pin holes 614 of the central housing. Figure 9 As shown in another illustration of the example, pin hole 683 may be in ring 686 (e.g., axial face of ring 686), wherein the turbine housing may include pin hole 666 as a corresponding pin hole, such that pin 673 may be partially received in pin hole 683 and partially received in pin hole 666 of the turbine housing.

[0055] Figure 10 yes Figure 6A cross-sectional view of a portion of a turbocharger 600, wherein a turbine impeller 607 is disposed in a turbine impeller space defined at least partially by a turbine housing 662, which can house blade sets 680 and 690 and connect them to a central housing 601, such that the blade sets 680 and 690 are disposed between the turbine housing 662 and the central housing 601.

[0056] As in Figure 10 As shown, the turbine housing 662 may include a partition wall portion separating passage 66 and passage 669. As explained, seal 671 may be used to prevent leakage between passage 667 and passage 669, leakage that can be driven by exhaust pulsations. Furthermore, as... Figure 10 As shown in the example, seal 671 can be symmetrical, such that one or both of blade assemblies 680 and 690 can rotate, for example, during assembly. In this method, one or more pins 673 (e.g., see...) Figure 9 Various examples of these can be used to secure one or both of the blade assemblies 680 and 690 in a desired angular orientation for proper blade-tongue alignment. For example, one or more instances of pin holes 693 can be considered in the stepped portion 697 of the ring 696, wherein one or more instances of pin holes 693 can receive a portion of one or more instances of pins 673, wherein another portion of each instance of pins 673 can be received in a corresponding instance of pin holes 613 of the central housing 601.

[0057] exist Figure 10 The example also shows another seal 675, which can be used to prevent leakage in instances where the heat shield 604 flexes (e.g., in response to heat, force, etc.). In such an example, the seal 675 may be disposed in a recess 668 of the turbine housing 662. As an example, the blade assembly 680 may alternatively or additionally include such a recess in which the seal 675 may be at least partially disposed.

[0058] exist Figure 10In the example, heat shield 604 is shown including an opening 605, allowing exhaust gas to pass from one side of heat shield 604 to the other, and vice versa. To further impede exhaust leakage, a seal 677 may be used at the interface between the central housing 601 and the turbine housing 662. As mentioned, one or more seals may be compressible, and may be compressible in one or more directions (e.g., axially, radially, etc.). As explained, seal 671 may be a sealing ring such as an open-ring seal. As an example, an open-ring seal may be configured similarly to a piston ring, which can provide radial compression and expansion. For example, seal 671 may be positioned in a slot 692 defined by blade groups 680 and 690 and apply a radially outward biasing force to ensure surface contact with the partition wall portion to impede exhaust leakage between passages.

[0059] As an example, to reduce leakage that would lower turbine stage performance, seal 671 can seal the area between the surface of the turbine housing partition wall and the surface of the blade assembly. Figure 10 In the example, each set of blades may contact another set of blades via metal-to-metal contact (e.g., in a ring-to-ring contact area, etc.). This contact may be maintained, for example, by using a heat shield 604. As an example, seals 675 and / or 677 may be C-shaped seals, which may be compressible, each of which may be disposed in one or more suitable recesses.

[0060] Regarding pin 673 and pin hole 693, this key-keyway interaction helps to impede the rotation of one or more sets of blades, thereby ensuring the alignment of the blades with the tongue. For example, pin 673 and pin hole 693 can be anti-rotation features, which fixes the angular position. Although Figure 10 The example shows pin 673 and pin hole 693 as anti-rotation features for blade assembly 690. Turbine assembly 660 may include one or more instances of pins and / or pin holes for blade assembly 680 (see example...). Figure 9 Various examples).

[0061] exist Figure 10In the example, the angular position of the blade assembly 690 can be set relative to the central housing 601, while the angular position of the blade assembly 680 can be set relative to the turbine housing 662. As explained, the heat shield 604 can apply a biasing force against the blade assemblies 680 and 690, causing metal-to-metal (e.g., alloy-to-alloy) contact. As shown, this contact can provide for the formation of a slot 692 (e.g., an outer peripheral slot) that can receive a portion of the seal 671; note that the blade assemblies 680 and 690 can include inner peripheral portions 689 and 699 that act as separators connecting their throats. As shown, portions 689 and 699 can be connected at a radius greater than the minimum radius of the blade assemblies 680 and / or 690.

[0062] Figure 10 Various dimensions of the radius measured from the axis of rotation of the turbine impeller are also shown. As shown, r1 extends to the inner periphery of blade assembly 690, r2 extends to the inner periphery of blade assembly 680, r3 extends to the connection between blade assemblies 680 and 690, and r4 extends to the partition portion of turbine housing 662. The radial dimensions measured between the two radii include Δr1 as the radial thickness of blade assembly 690, Δr2 as the radial thickness of blade assembly 680, Δr3 as the radial distance between the inner and outer peripheries of the connection between blade assemblies 680 and 690, Δr4 as the radial depth of slot 692 for seal 671 (e.g., sealing member), and Δr9 as the radial distance (e.g., pin hole diameter) of pin hole 693. The axial dimensions measured between the two axial positions include Δz1 as the axial thickness of the blade assembly 690, Δz2 as the axial thickness of the blade assembly 680, Δz3 as the axial throat dimension of the blade assembly 690, Δz4 as the axial throat dimension of the blade assembly 680, Δz5 as the axial throat dimension of the blade assembly 690, Δz6 as the axial throat dimension of the blade assembly 680, Δz7 as the axial throat dimension of the partition portion of the turbine housing 662, Δz8 as the axial dimension of the slot 692, and Δz9 as the axial dimension of the pin hole 693, wherein the axial length of the pin 673 is greater than the axial depth of the pin hole 693.

[0063] like Figure 10As shown, a gap exists between the blade sets 680 and 690 and the separator portion of the turbine housing 662, where the gap may be defined by r4 and r1 and Δr1, r2, and Δr2, etc. As shown, the seal 671 may be at least partially disposed in the slot 692 and contact the surface at the inner periphery of the separator portion of the turbine housing 662. As explained, this method allows some expansion and contraction of the blade sets 680 and 690 and / or the turbine housing 662, while impeding exhaust flow between the volutes 667 and 669. As an example, the seal 671 may be spring-loaded to increase the contact force and maintain a proper seal. The spring force may be provided by the stiffness of the sealing ring and / or by a separate spring behind the sealing ring. As explained, the sealing ring may be an open ring (e.g., consider a piston ring).

[0064] like Figure 10 As shown, the throats of blade sets 680 and 690 converge toward a centerline defined by the connection between blade sets 680 and 690. As an example, the sum of dimensions Δz5 and Δz6 can be approximately the turbine impeller leading-edge blade height of turbine impeller 607. For example, blade sets 680 and 690 can be used to reduce the cross-sectional flow area from channels 667 and 669 (e.g., see Δz3 and Δz4 at approximately r1 or r4) to a smaller cross-sectional flow area (e.g., at approximately r1 or r2). The flow area decreases as the radius decreases from the outer periphery to the inner periphery of blade sets 680 and 690. In such an example, the exhaust can be accelerated as it flows through the throat defined by adjacent blades toward the inlet section of the turbine impeller.

[0065] exist Figure 10 In the example, the axial dimensions Δz11 and Δz12 for channels 669 and 667 are shown respectively. As shown, the axial dimension Δz3 of blade assembly 690 may be greater than the axial dimension Δz11 of turbine housing 662, and the axial dimension Δz4 of blade assembly 680 may be greater than the axial dimension Δz12 of turbine housing 662. In such an example, when such exhaust flow reaches the leading edges of the blades fixed in blade assembly 680 and the leading edges of the blades fixed in blade assembly 690, the exhaust flow from channels 667 and 669 may be unaffected by the edges of one or more rings of one or more blade assemblies. For example, consider the criteria Δz11 < Δz3 and Δz12 < Δz4 to avoid creating one or more steps in the exhaust flow, which would introduce additional disturbances in the exhaust flow and thus cause efficiency losses.

[0066] As explained, the heat shield 604 can be used as a spring that forces the blade sets 680 and 690 axially away from the central housing 601. In this approach, features of the turbine housing (e.g., recesses that receive and provide space for the blade set 680) can limit the axial position of the blade sets 680 and 690 such that the portion of the blade set 690 at r1 does not interfere with the turbine impeller (e.g., the back disc, the leading edge of the blades, etc.).

[0067] As in Figure 10 As shown in the example, the turbine housing 662 may include an annular recess for housing the blade assembly 680, wherein the annular recess may include a radial dimension Δr11, which is greater than or equal to the radial dimension Δr2 of the blade assembly 680. The annular recess may also include axial dimensions Δz13 and Δz14, which may be as follows: Figure 9 The example shows the axial dimensions of the inner and outer peripheries of ring 686; note that ring 686 can be a single ring or a multi-piece ring. As shown, the annular recess and ring 686 have an axial thickness at their inner periphery greater than that at their outer periphery, wherein ring 686 can be tilted such that the axial throat dimension Δz6 is smaller than the axial dimension Δz4. As shown, the ring 696 of blade assembly 690 can also be provided for an axial throat dimension Δz5 smaller than the axial dimension Δz3. In this method, blade assemblies 680 and 690 can convergently guide exhaust gas inward toward the inlet section portion of turbine impeller 607, which is disposed in a turbine impeller space defined at least partially by turbine housing 662.

[0068] like Figure 10 As shown in the example, turbine housing 662 may include a wall portion defining a channel 669, wherein the inner peripheral surface of the wall portion (e.g., at or approximately at radius r4) may face and / or contact the outer peripheral surface of the stepped portion 697 of ring 696. As shown, the stepped portion 697 may be partially received by an annular recess of central housing 601, which may have an axial dimension Δz15 and a radial dimension Δr15. As shown, the axial dimension Δz15 may be sufficient to allow some movement, expansion, etc., even without contact between the axial surface of the stepped portion 697 and the bottom of the annular recess; again, note that blade assemblies 680 and 690 may be forcibly biased by a heat shield 604, which may be referred to as a spring. See again Figure 6 The heat shield 604 is shown optionally positioned against the central housing 601 at the inner periphery using a locking ring, and has a portion that contacts the blade assembly 690 at or near the outer periphery.

[0069] like Figure 6 and Figure 10As shown, the radial inward movement of blade assemblies 680 and 690 can be restricted via annular recesses in the central housing 601 and turbine housing 662, for example, to prevent the ring 696 from moving radially inward in a manner that could potentially contact a portion of the turbine impeller 607. As shown, the corner of the ring 696 can be aligned with the lower portion of the leading edge of the blades of the turbine impeller 607, wherein the hub portion of the turbine impeller 607 can be slightly lower than the corner. Regarding the shroud edge of the blades of the turbine impeller 607, it can be spaced relatively close to the shroud portion of the turbine housing 662. For example, in Figure 10 In the diagram, turbine housing 662 is shown including an annular flat portion between an annular recess for ring 686 and a shroud portion. In this arrangement, the inner radius of ring 686 is greater than the inner radius of ring 696; note that the annular flat portion can be shortened or omitted, such that the inner peripheries of rings 686 and 696 can be approximately equal. As mentioned, radius r3 can be greater than radius r1 and / or radius r2, such that exhaust flows from channels 667 and 669 can converge before encountering the inlet section of turbine impeller 607, wherein the leading edge of turbine impeller 607 can be defined by a leading edge radius that can be less than r1, less than r2, and less than r3.

[0070] Such as about Figure 6 As explained, the rotational positions of the center housing 601 and the turbine housing 662 can be fixed relative to each other (e.g., via an anti-rotation mechanism), which can provide proper alignment of the blade sets 680 and 690. For example, when the blade sets 680 and 690 are in contact with each other via a force applied by a heat shield 604 acting as a spring, optionally without one or more interlocking features between them, if the turbine housing 662 rotates relative to the center housing 601, the blade set 680 can rotate relative to the blade set 690, particularly where pin / pin hole features are provided for the blade set 680 with respect to the turbine housing 662 and the blade set 690 with respect to the center housing 601. As an alternative example, an anti-rotation mechanism (e.g., a positioning mechanism) for the blade set 690 can be provided between the turbine housing 662 and the blade set 690. For example, consider a pin 673 rotating 90 degrees about a corresponding pin hole in the blade set 690 and the turbine housing 662, where, for example, clamping the turbine housing 662 to the center housing 601 can be used to lock the pin in place in the pin hole.

[0071] As explained, the turbine assembly may include: a turbine housing defining a longitudinal axis and including a first vortex and a first tongue at a first angle about the longitudinal axis, and a second vortex and a second tongue at a second angle about the longitudinal axis, wherein the angular span between the first angle and the second angle is greater than 1 degree and less than 180 degrees; and a first blade group and a second blade group disposed in the turbine housing, wherein the blades in the first blade group are aligned with the first tongue, and the blades in the second blade group are aligned with the second tongue.

[0072] When less than 180 degrees is mentioned, an angular span (e.g., angular offset) can be selected to ensure that blades from the first blade group do not align with each other from the blades from the second blade group. In this approach, blade misalignment can help reduce high-cycle fatigue (HCF), which can improve the performance of the turbine assembly and extend its life. As an example, the angular offset or angular span can be determined in part by the number of blades, where the spacing can be defined. For example, for 10 blades, the spacing between adjacent blades can be approximately 36 degrees. Therefore, one set of blades can rotate (e.g., angular offset) relative to another set of blades from 1 degree to 35 degrees, from 37 degrees to 71 degrees, from 109 degrees to 143 degrees, etc. As an example, angular offset can provide space for arranging the exhaust valve passage from the vortex passage to the exhaust valve in a more compact and / or more efficient manner.

[0073] As an example, a turbine assembly may include: a turbine housing defining a longitudinal axis, the turbine housing including a first vortex and a first tongue at a first angle about the longitudinal axis, and a second vortex and a second tongue at a second angle about the longitudinal axis; a blade assembly including a first blade assembly and a second blade assembly disposed in the turbine housing; and a sealing ring disposed between the blade assembly and the turbine housing, wherein the sealing ring contacts the turbine housing in the space between the outlet of the first vortex and the outlet of the second vortex. In such an example, the first blade assembly and the second blade assembly may be separate units. As an example, the first blade assembly may be adjustable to align one of its blades with the first tongue of the first vortex in the turbine housing, and the second blade assembly may be adjustable to align one of its blades with the second tongue of the second vortex in the turbine housing. In such an example, the first tongue and the second tongue may be at a common angle measured from the longitudinal axis of the turbine housing, which corresponds to the axis of rotation of the turbine impeller, or the first tongue and the second tongue may be offset by, for example, an angular offset greater than 0 degrees and less than 360 degrees. For example, although as Figure 10The blade sets in the examples can be used with offset tongues of a twin-scroll turbine housing, but they can also be used with aligned tongues of a twin-scroll turbine housing. Regarding the number of blades in a set of blades, it can be greater than 5 and less than 40, wherein, for example, one set of blades can have the same or different number of blades as another set of blades. As an example, for two sets of blades, the blade shape and / or size can be the same or can be different. As explained, a set of blades can include blades of different sizes and / or shapes, wherein the blades will mate with the tongues of the scroll (see, for example, Figure 8A (Example).

[0074] Figure 11 This is a perspective view of an example flow passage 1100, which includes an exhaust valve passage 1157 in fluid communication with a vortex passage 1167 and an exhaust valve passage 1159 in fluid communication with a vortex passage 1169. In such an example, one or more exhaust valves can regulate the flow from one or both of the vortex passages 1167 and 1169 through the exhaust valve passages 1157 and 1159 to the outlet passage 1165.

[0075] like Figure 11 As shown in the example, the vortex channels 1167 and 1169 have an angular offset, making space available for the exhaust valve channel 1159. Figure 11 In the example, an angular offset ΔΘ is shown in cylindrical coordinates (z, r, and Θ), where an exhaust valve passage 1159 extends between a vortex passage 1167 and a vortex passage 1169. The exhaust valve passage 1159 may be at approximately the same angle as the exhaust valve passage 1157, such that the exhaust valve passages 1157 and 1159 may extend to the exhaust valve in a substantially parallel and side-by-side manner. The exhaust valve may be a single exhaust valve with a single plug that can regulate the flow from both exhaust valve passages 1157 and 1159.

[0076] Figure 12 This is a perspective view of an example of a flow passage 1200 without the angular offset of the vortex tongue, wherein the flow passage includes an exhaust valve passage 1257 in fluid communication with a vortex passage 1267 and an exhaust valve passage 1259 in fluid communication with a vortex passage 1269. In such an example, one or more exhaust valves can regulate the flow from one or both of the vortex passages 1267 and 1269 through the exhaust valve passages 1257 and 1259 to the outlet passage 1265. However, due to space constraints, the exhaust valve passage 1259 has an external route; however, in Figure 11 In the example, the exhaust valve passage 1159 may have an internal route.

[0077] exist Figure 11In the example, due to the angular displacement of the vortex tube, the exhaust valve passage can be inside the turbine housing, making the passage shorter. This allows for a more compact turbine design and better casting. For example, in sand casting, long and thin sand cores are brittle and pose a risk of cracking during mold pouring. For example, in Figure 12 In this process, the exhaust valve passage 1259 is positioned outside the vortex passages 1267 and 1269, such that the casting process involves using relatively long and fine sand cores to form the exhaust valve passage 1259 within the cast turbine housing. In this method, the portion of the cast turbine housing forming the exhaust valve passage 1259 is not as... Figure 11 The exhaust valve passage 1159 in the example is protected. Therefore, for a cast turbine housing with exhaust valve passage 1259, contact could lead to fracture (e.g., cracking) of the wall of the cast turbine housing forming exhaust valve passage 1259. To compensate for this risk, the wall could be made thicker; however, this comes at the cost of more material and therefore greater mass. Figure 11 The method may be beneficial in terms of reducing the risk of damage, ease of casting, and compactness.

[0078] As an example, such as Figure 10 The blade groups 680 and 690 shown in the example can be used with, for example Figure 11 Examples of turbine housings with flow channels and / or such as Figure 12 The example uses a turbine housing with flow channels. As explained, in Figure 11 In the example, the tongue-shaped portion of the vortex tube can be offset, and... Figure 12 In the example, the tongues of the vortex tube can be aligned.

[0079] Figure 13 This is a perspective cutaway view of a portion of an example turbocharger 1300, showing an exhaust valve assembly 1400 with an exhaust valve 1460 in the open position, wherein exhaust valve passages 657 and 659 are visible and in fluid communication with exhaust valve outlet 1490 and outlet passage 665. In such an example, the exhaust valve assembly 1400 can be used to control the flow of exhaust gas into the turbine impeller space.

[0080] like Figure 13As shown in the example, exhaust valve passages 657 and 659 may be formed within a turbine housing 662, wherein a portion 1410 of the turbine housing 662 extends axially away from the outer vortex of passage 667. In such an example, the portion 1410 of the turbine housing 662 forms portions of exhaust valve passages 657 and 659, wherein this portion 1410 may be adjacent to a cylindrical wall portion 1415 of the turbine housing 662 that defines an outlet passage 665, such that an exhaust valve outlet 1490 can be readily formed as an opening in the cylindrical wall portion 1415 of the turbine housing 662. As shown, the turbine housing 662 may also form a bore 1416 for receiving a shaft 1462 coupled to a plug 1466, which can be positioned to close or open exhaust valve passages 657 and 659. As shown, shaft 1462 can be coupled to control link 1500, which in turn can be coupled to actuator 1600. For example, consider an electronic or other actuator that can be suitably controlled to cause the opening or closing of plug 1466 of exhaust valve 1460. As an example, exhaust valve passages 657 and 659 can converge to form a single outlet that can be covered by plug 1466, or they can be separate to form two outlets that can be covered by one or more instances of plug 1466.

[0081] As an example, a turbine assembly may include: a turbine housing defining a longitudinal axis, the turbine housing including a first vortex and a first tongue forming a first angle about the longitudinal axis, and a second vortex and a second tongue forming a second angle about the longitudinal axis, wherein the angular span between the first and second angles is greater than 1 degree and less than 180 degrees; and a first blade group and a second blade group disposed in the turbine housing, wherein the blades of the first blade group are aligned with the first tongue, and the blades of the second blade group are aligned with the second tongue. In such an example, the turbine assembly may include a seal that seals the space between the turbine housing and the first and second blade groups. For example, consider an open-ring seal (e.g., a piston ring type seal, etc.).

[0082] As an example, a turbine assembly may include key and keyway anti-rotation features that prevent the first blade set from rotating relative to the turbine housing, such as a key as a pin or including a pin and a keyway as a pin hole or including a pin hole.

[0083] As an example, a turbine assembly may include a first blade group and a second blade group, wherein the second blade group includes one or more keyways for receiving one or more keys to impede rotation of the second blade group relative to a central housing of a turbine housing coupled to the turbine assembly.

[0084] As an example, the turbine assembly may include an exhaust valve that can be positioned relative to an exhaust valve seat. In such an example, a first exhaust valve passage in fluid communication with a first vortex tube and a second exhaust valve passage in fluid communication with a second vortex tube may be included, wherein the exhaust valve is positioned relative to the exhaust valve seat to control the flow of exhaust gas through the first and second exhaust valve passages. In such an example, the turbine housing may be a cast turbine housing, wherein the first and second exhaust valve passages are internal channels.

[0085] As an example, the radial position of the second exhaust valve passage, as measured from the longitudinal axis of the turbine housing, can be smaller than the maximum radial position of the second vortex tube, as measured from the longitudinal axis of the turbine housing. For instance, in the case where the first vortex tube with a first tongue and the second vortex tube with a second tongue are offset and the second vortex tube is axially positioned between the first vortex tube and the central housing, the exhaust valve passage in fluid communication with the second vortex tube can extend axially through the space between the azimuth positions of the first and second tongues, without having to sweep radially across the first vortex tube in the path to the exhaust valve seat.

[0086] As an example, the first vortex of the turbine assembly may be characterized by a first area to radius ratio as measured along a radial line at a first angle, and the second vortex of the turbine assembly may be characterized by a second area to radius ratio as measured along a radial line at a second angle, wherein the first angle and the second angle are different. In such an example, the first angle may correspond to a first tongue position, and the second angle may correspond to a second tongue position. As explained, the tongues of the twin-scroll turbine housing may be offset by an offset angle, and the two sets of blades may also be offset by an offset angle.

[0087] As an example, the blades of the first blade group may be aligned with the first tongue, and the blades of the second blade group may be aligned with the second tongue, wherein the two blades are not aligned to reduce high cyclic fatigue (HCF) of the turbine assembly.

[0088] As an example, the first blade group may have fixed blades, and the second blade group may have fixed blades. In such an example, the blades can be fixed so that they do not pivot. For example, consider blades fixed between opposing rings, where such blades and rings may optionally be formed from a single piece of material.

[0089] As an example, the turbine assembly may include a heat shield for applying forces to the first and second blade sets to forcefully bias the first blade set against the turbine housing. In such an example, the first and second blade sets may be separable components in contact with each other. For example, consider providing two sets of blades as separate units, where one set of blades is positioned, followed by the positioning of a seal. Once the seal is positioned, the other set can be positioned to effectively form a slot that can hold the seal. In such an example, the seal may be a seal that impedes mixing of exhaust gas flowing from the two vortex tubes to the blade set, whereby, once the exhaust gas flows through the blade set, it can mix as it enters the turbine impeller space.

[0090] As an example, a turbine assembly may include: a turbine housing defining a longitudinal axis, the turbine housing including a first vortex and a first tongue at a first angle about the longitudinal axis, and a second vortex and a second tongue at a second angle about the longitudinal axis; a blade assembly including a first blade assembly and a second blade assembly disposed in the turbine housing; and a sealing ring disposed between the blade assembly and the turbine housing, wherein the sealing ring contacts the turbine housing in the space between the outlet of the first vortex and the outlet of the second vortex. In such an example, the first blade assembly and the second blade assembly may be separate units.

[0091] As an example, the first blade set may be adjustable to align one of its blades with a first tongue of a first vortex tube in the turbine housing, and the second blade set may be adjustable to align one of its blades with a second tongue of a second vortex tube in the turbine housing. In such an example, the first and second tongues may be positioned at a first angle and a second angle, respectively, as measured from the longitudinal axis of the turbine housing, which corresponds to the axis of rotation of a turbine impeller at least partially disposed within the turbine housing. In such an example, the first and second angles may be aligned or offset. For example, alignment of the first and second tongues may correspond to 0 degrees (e.g., no offset or alignment), and offset of the first and second tongues is characterized by an angle between the first and second tongues ranging from greater than 0 degrees to less than 360 degrees, optionally to 180 degrees or less.

[0092] Although some examples of methods, apparatuses, systems, arrangements, etc. have been illustrated in the accompanying drawings and described in detail above, it should be understood that the disclosed exemplary embodiments are not limiting, but are capable of various rearrangements, modifications and substitutions.

Claims

1. A turbine assembly, comprising: A turbine housing defining a longitudinal axis and including a first vortex and a first tongue forming a first angle around the longitudinal axis, and a second vortex and a second tongue forming a second angle around the longitudinal axis, wherein the angular span between the first angle and the second angle is greater than 1 degree and less than 180 degrees; and A first blade group and a second blade group are disposed in the turbine housing at a first axial position along the longitudinal axis and at a second axial position along the longitudinal axis, wherein the first axial position is different from the second axial position, and wherein the blades of the first blade group are aligned with the first tongue-shaped portion, and the blades of the second blade group are aligned with the second tongue-shaped portion. The first blade assembly includes one or more keyways for receiving one or more keys to impede rotation of the first blade assembly relative to the turbine housing, allowing the turbine housing and the first blade assembly to rotate as a first assembly unit; the second blade assembly includes one or more keyways for receiving one or more keys to impede rotation of the second blade assembly relative to the central housing, allowing the central housing and the second blade assembly to rotate as a second assembly unit; and the turbine housing includes one or more keyways for receiving one or more keys when the turbine housing and the central housing are aligned, to impede rotation of the first assembly unit relative to the second assembly unit.

2. The turbine assembly of claim 1, wherein the turbine assembly includes a seal that seals the space between the turbine housing and the first blade assembly and the second blade assembly.

3. The turbine assembly according to claim 2, wherein, The sealing element is an open ring seal.

4. The turbine assembly of claim 1, wherein the key comprises a pin, and wherein the keyway comprises a pin hole.

5. The turbine assembly according to claim 1, wherein, The turbine assembly includes an exhaust valve that can be positioned relative to the exhaust valve seat.

6. The turbine assembly according to claim 5, wherein, The turbine assembly includes a first exhaust valve passage in fluid communication with the first vortex tube and a second exhaust valve passage in fluid communication with the second vortex tube, wherein the exhaust valve is positionable relative to the exhaust valve seat to control the flow of exhaust gas through the first exhaust valve passage and the second exhaust valve passage.

7. The turbine assembly of claim 6, wherein the turbine housing is a cast turbine housing, and wherein the first exhaust valve passage and the second exhaust valve passage are internal passages.

8. The turbine assembly according to claim 7, wherein, The radial position of the second exhaust valve passage, measured from the longitudinal axis of the turbine housing, is less than the maximum radial position of the second vortex tube, measured from the longitudinal axis of the turbine housing.

9. The turbine assembly according to claim 1, wherein, The first vortex tube is characterized by the ratio of a first area to a radius measured along a radial line at the first angle, and the second vortex tube is characterized by the ratio of a second area to a radius measured along a radial line at the second angle.

10. The turbine assembly of claim 1, wherein the blades of the first blade group aligned with the first tongue and the blades of the second blade group aligned with the second tongue are not aligned to reduce high cyclic fatigue of the turbine assembly.

11. The turbine assembly of claim 1, wherein the first blade group includes fixed blades, and wherein the second blade group includes fixed blades.

12. The turbine assembly of claim 1, wherein the turbine assembly includes a heat shield for applying force to the first blade group and the second blade group to forcibly bias the first blade group against the turbine housing.

13. The turbine assembly of claim 12, wherein, The first blade group and the second blade group are separable components that are in contact with each other.

14. A turbine assembly, comprising: A turbine housing that defines a longitudinal axis and includes a first vortex and a first tongue at a first angle about the longitudinal axis, and a second vortex and a second tongue at a second angle about the longitudinal axis. The blade assembly includes a first blade assembly disposed in the turbine housing at a first axial position on the longitudinal axis and a second blade assembly disposed in the turbine housing at a second axial position on the longitudinal axis, wherein the first axial position is different from the second axial position, and wherein the blades of the first blade assembly are aligned with the first tongue portion, and the blades of the second blade assembly are aligned with the second tongue portion. as well as A sealing ring is disposed between the blade assembly and the turbine housing, wherein the sealing ring contacts the turbine housing in the space between the outlet of the first vortex tube and the outlet of the second vortex tube. The first blade assembly includes one or more keyways for receiving one or more keys to impede rotation of the first blade assembly relative to the turbine housing, allowing the turbine housing and the first blade assembly to rotate as a first assembly unit; the second blade assembly includes one or more keyways for receiving one or more keys to impede rotation of the second blade assembly relative to the central housing, allowing the central housing and the second blade assembly to rotate as a second assembly unit; and the turbine housing includes one or more keyways for receiving one or more keys when the turbine housing and the central housing are aligned, to impede rotation of the first assembly unit relative to the second assembly unit.

15. The turbine assembly of claim 14, wherein the first blade group and the second blade group are separate units.

16. The turbine assembly of claim 14, wherein, The first blade group is adjustable to align one of its blades with the first tongue, and the second blade group is adjustable to align one of its blades with the second tongue.

Images