Vaned diffuser, turbocharger and engine

Abstract

The invention provides a vaned diffuser, a turbocharger and an engine, and relates to the technical field of turbochargers, and the vaned diffuser comprises a back disc, multiple layers of diffusion blades and a driving mechanism. The back disc is of an annular structure, multiple sets of blade-shaped grooves are formed in the end face of the back disc, all the blade-shaped grooves in each set are formed in the same direction, and the blade-shaped grooves in different sets are formed in different directions. All the diffusion blades of each layer of the multiple layers of diffusion blades are evenly distributed in the circumferential direction of the end face, embedded into the corresponding blade-shaped grooves in a sliding mode and synchronously move in the corresponding blade-shaped grooves in the axial direction of the back disc. The driving mechanism comprises a plurality of driving parts, and each driving part corresponds to one target layer of the multiple layers of diffusion blades and is connected with all the diffusion blades in the target layer. According to the vaned diffuser, the axial movement distance of each layer of the multiple layers of diffusion blades is adjusted, the blade height of each layer is dynamically changed, and therefore the vaned diffuser is suitable for all working conditions.

Description

Technical Field

[0001] This disclosure belongs to the field of turbocharger technology, specifically relating to a vaned diffuser, a turbocharger, and an engine. Background Technology

[0002] The working principle of a diffuser is based on the conversion of kinetic energy into pressure energy through changes in the cross-sectional area of ​​the flow channel. Diffusers are broadly classified into two categories: bladed diffusers and bladeless diffusers. A bladed diffuser consists of a fixed backplate and a casing, with blades of a specific airfoil positioned in the middle. These blades, through their geometry, restrict the direction of airflow, thereby shortening the structural dimensions of the diffuser channel. This allows the airflow to be decelerated and pressurized with a shorter flow path and limited increase in channel diameter.

[0003] In related technologies, most vaned diffusers are limited to a single-blade adjustment mode, namely fixed blades or single-layer axially moving blades. Vaned diffusers with fixed blades cannot flexibly adjust the blade state according to changes in operating conditions. In variable operating scenarios, the stability of this type of vaned diffuser is poor, and it cannot meet the requirements of high efficiency. Vaned diffusers with single-layer axially moving blades can only be adjusted in one dimension, and their adjustment flexibility is low. Under extreme or complex operating conditions, their performance is usually greatly reduced, and their adaptability to multiple operating conditions needs to be improved. Summary of the Invention

[0004] This disclosure provides a vaned diffuser, a turbocharger, and an engine, aiming to at least partially solve the technical problem in the related art that vaned diffusers with a single vane adjustment mode are difficult to adapt to all operating conditions of an engine.

[0005] At least one embodiment of this disclosure provides a vaned diffuser, comprising:

[0006] The back plate has an annular structure and multiple sets of blade grooves are formed on the end face of the back plate. Each set of blade grooves includes multiple blade grooves located in different circumferential directions on the end face. All blade grooves in each set are arranged in the same direction, and the blade grooves in different sets are arranged in different directions.

[0007] The multi-layer diffuser blade includes multiple diffuser blades in each layer, and all diffuser blades in each layer are evenly distributed in a circumferential direction on the end face and slidably embedded in the corresponding air groove. All diffuser blades in each layer are configured to move synchronously along the axial direction of the back disk in the corresponding air groove.

[0008] The drive mechanism includes multiple drive units, each of which corresponds to a target layer of the multilayer diffuser blades and is connected to all diffuser blades in the target layer.

[0009] In at least one embodiment of the bladed diffuser provided in this disclosure, the drive mechanism further includes:

[0010] A first push rod corresponding to the first target layer in the multi-layer diffuser blade, one end of the first push rod is connected to the diffuser blade corresponding to the first target layer, and the other end of the first push rod is connected to the drive unit corresponding to the first target layer. The first target layer is any layer of the multi-layer diffuser blade.

[0011] A first motor, the output shaft of which is connected to a drive unit corresponding to the first target layer, and the first motor is used to drive the drive unit corresponding to the first target layer to move along the axial direction of the back disk, so as to drive all the diffuser blades in the first target layer to move synchronously along the axial direction of the back disk in the corresponding air groove.

[0012] In at least one embodiment of the bladed diffuser provided in this disclosure, the drive mechanism further includes:

[0013] A second push rod is provided, which corresponds to a second target layer in the multi-layer diffuser blade that is different from the first target layer. One end of the second push rod is connected to the diffuser blade in the second target layer, and the other end of the second push rod is connected to the drive unit in the second target layer.

[0014] The second motor has its output shaft connected to the drive unit corresponding to the second target layer. The second motor is used to drive the drive unit corresponding to the second target layer to move along the axial direction of the back disk, so as to drive all the diffuser blades in the second target layer to move synchronously along the axial direction of the back disk in the corresponding air groove.

[0015] In at least one embodiment of the bladed diffuser provided in this disclosure, each of the drive units is provided with a synchronization ring, which is connected to all the diffuser blades in the corresponding target layer. The multi-layer diffuser blades include a leading edge blade layer, a middle blade layer, and a trailing edge blade layer arranged sequentially along the inner circumference to the outer circumference of the back disk. The leading edge blade layer, the middle blade layer, and the trailing edge blade layer are each driven by different drive units.

[0016] In the multi-layer diffuser blades, the long axes of the diffuser blades in the leading edge blade layer, the middle blade layer, and the trailing edge blade layer, all located in the same set of airfoil slots, coincide.

[0017] In at least one embodiment of the vaned diffuser provided in this disclosure, the operating modes of the vaned diffuser include a vaneless diffuser mode and a conventional vaned diffuser mode, and the vaned diffuser further includes:

[0018] Controller, the controller being used to control the action of the drive mechanism,

[0019] The controller is configured as follows:

[0020] Upon receiving a first control command to activate the bladeless diffuser mode, all drive units in the drive mechanism are controlled to move to move each layer of the multi-layer diffuser blade to a preset first axial position, so that the blade height of each layer of the multi-layer diffuser blade reaches a first preset height that matches the bladeless diffuser mode.

[0021] Upon receiving a second control command to activate the conventional bladed diffuser mode, all drive units in the drive mechanism are controlled to move to move each layer of the multi-layer diffuser blades to a preset second axial position, so that the blade height of each layer of the multi-layer diffuser blades reaches a second preset height that matches the conventional bladed diffuser mode, wherein the second preset height is greater than the first preset height.

[0022] In the vaned diffuser provided in at least one embodiment of this disclosure, in the vaneless diffuser mode or the conventional vaned diffuser mode, all drive units in the drive mechanism move synchronously; and...

[0023] The operating mode of the valved diffuser also includes a first special operating condition mode, wherein the first special operating condition in the first special operating condition mode is configured such that the actual operating parameters of the valved diffuser meet a preset narrowband threshold range and the target performance parameters of the valved diffuser exceed a preset performance parameter standard, and the controller is configured to:

[0024] Upon receiving a third control command to initiate the first special operating mode, the drive unit corresponding to the leading edge blade layer is controlled to move to the third axial position, while the drive units corresponding to the middle blade layer and the trailing edge blade layer are controlled to maintain their original positions, so that the blade height of all diffuser blades in the leading edge blade layer is reduced and the blade height of all diffuser blades in the middle blade layer and the trailing edge blade layer remains unchanged.

[0025] In at least one embodiment of the vaned diffuser provided in this disclosure, the operating mode of the vaned diffuser further includes a second special operating condition mode. The second special operating condition mode is configured such that the diffusion ratio of the vaned diffuser exceeds a first preset ratio and the turbulence intensity exceeds a preset intensity. Furthermore, the controller is further configured to:

[0026] Upon receiving the fourth control command for activating the second special operating mode, the drive unit corresponding to the middle blade layer is moved to move the middle blade layer to the fourth axial position, while the drive units corresponding to the leading edge blade layer and the trailing edge blade layer maintain their original positions, so that the blade height of all diffuser blades in the middle blade layer is reduced and the blade height of all diffuser blades in the leading edge blade layer and the trailing edge blade layer remains unchanged.

[0027] In at least one embodiment of the vaned diffuser provided in this disclosure, the operating mode of the vaned diffuser further includes a third special operating condition mode. The third special operating condition mode refers to a situation where the diffusion ratio of the vaned diffuser is lower than a second preset ratio and the dynamic response index of the vaned diffuser exceeds a preset value. Furthermore, the controller is configured to:

[0028] Upon receiving the fifth control command for activating the third special operating mode, the drive unit corresponding to the trailing edge blade layer is controlled to move to the fifth axial position, while the drive units corresponding to the leading edge blade layer and the middle blade layer remain in their original positions, so that the blade height of all diffuser blades in the trailing edge blade layer is reduced and the blade height of all diffuser blades in the leading edge blade layer and the middle blade layer remains unchanged.

[0029] In at least one embodiment of the bladed diffuser provided in this disclosure, all the diffuser blades in the multilayer diffuser are perpendicular to the end face of the back disk, and the controller is further configured to:

[0030] Obtain the actual operating parameters and target performance parameters of the bladed diffuser under the current operating conditions, wherein the actual operating parameters include the diffusion ratio and turbulence intensity, and the target performance parameters include dynamic response indicators;

[0031] When the current operating mode of the bladed diffuser does not match the current operating condition based on the actual operating parameters and the target performance parameters, a target operating mode that matches the current operating condition is obtained; and...

[0032] Generate corresponding control commands to initiate the target operating mode, so that the lobed diffuser switches from the current operating mode to the target operating mode.

[0033] At least one embodiment of this disclosure also provides a turbocharger, the turbocharger including the bladed diffuser provided as in any embodiment of this disclosure.

[0034] At least one embodiment of this disclosure also provides an engine that includes the bladed diffuser provided in any embodiment of this disclosure.

[0035] Compared to related technologies, the bladed diffuser, turbocharger, and engine provided in this disclosure present a bladed diffuser with multiple layers of axially movable blades. By adjusting the axial movement distance of each layer of the multi-layer diffuser blades, the blade height of different layers in the multi-layer diffuser is dynamically changed, thereby guiding the airflow inside the bladed diffuser. This optimizes the blade height of the diffuser blades participating in diffusion in the flow channel, ensuring that the bladed diffuser maintains efficient and stable operation under various extreme conditions, meeting the performance requirements of turbochargers or engines under different operating conditions. Furthermore, since the axial movement distance of each layer of diffuser blades can be adjusted independently, the adjustment methods are highly diverse, allowing the displacement or axial position of different layers in the multi-layer diffuser blades to be determined according to actual operating requirements. Because the displacement or axial position of each layer of diffuser blades can be set individually, different displacement combinations can be formed between the multi-layer diffuser blades, thus constructing a novel bladed diffuser structure. This design can adapt to the needs of all operating conditions, ensuring optimal diffusion effect under various operating conditions. By precisely controlling the axial movement distance of each layer of blades, the airflow channel can be effectively optimized, improving the overall performance of the turbocharger or engine, and enabling it to maintain a highly efficient and stable operating state under different working conditions.

[0036] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the embodiments of this disclosure, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0038] Figure 1 A schematic diagram of the structure of a bladed diffuser provided for at least one embodiment of this disclosure.

[0039] Figure 2 A schematic diagram of the back plate structure provided in at least one embodiment of this disclosure;

[0040] Figure 3 A partial schematic diagram of a bladed diffuser provided for at least one embodiment of this disclosure;

[0041] Figure 4 This is a schematic diagram of the structure of a multilayer diffuser blade provided in at least one embodiment of the present disclosure;

[0042] Figure 5 for Figure 4 A cross-sectional view of the location of the same group of airfoil grooves;

[0043] Figure 6 A structural block diagram of a turbocharger provided for at least one embodiment of this disclosure;

[0044] Figure 7 This is a structural block diagram of an engine provided for at least one embodiment of the present disclosure.

[0045] Figure Labels

[0046] 1-Back disk; 2-Multi-layer diffuser blade; 3-Drive mechanism; 11-End face; 12-Airfoil groove; 13-Inner circumference; 14-Outer circumference; 21-Diffuser blade; A-Leading edge blade layer; B-Middle blade layer; C-Tail edge blade layer; 21a-Long shaft;

[0047] 21A - Diffuser blade in the leading edge layer; 21B - Diffuser blade in the middle layer; 21C - Diffuser blade in the middle layer; 31 - Drive unit; 10 - Turbocharger; 20 - Engine; 100 - Bladed diffuser. Detailed Implementation

[0048] The present disclosure will be further described in detail below with reference to the accompanying drawings and embodiments. It should be particularly noted that the following embodiments are for illustrative purposes only and do not limit the scope of the disclosure. Similarly, the following embodiments are only some, not all, embodiments of the present disclosure, and all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0049] The terms "first," "second," and "third" used in the embodiments of this disclosure are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined as "first," "second," and "third" may explicitly or implicitly include at least one of that feature.

[0050] In the description of this disclosure, "multiple" means at least two, such as two or three, unless otherwise expressly and specifically limited.

[0051] In this disclosure, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this disclosure. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0052] The terms “comprising” and “having”, and any variations thereof, used in embodiments of this disclosure, are intended to cover non-exclusive inclusion. For example, a process, vaned diffuser, system, product, or device that includes a series of steps or units is not limited to the steps or units listed, but may optionally include steps or units not listed, or may optionally include other steps or components inherent to such processes, vaned diffusers, products, or devices.

[0053] In this disclosure, the term "pre-swirling circumferential non-uniformity" refers to the rotational inertia effect that occurs when the airflow is driven by the impeller upstream of the diffuser before entering the diffuser. Ideally, the rotational speed and direction of the airflow at the inlet of the bladed diffuser should be consistent. However, if the circumferential distribution of the airflow at the inlet of the bladed diffuser exhibits uneven rotational intensity—that is, some regions rotate excessively while others rotate insufficiently, or even rotate in the opposite direction—this phenomenon is called pre-swirling circumferential non-uniformity.

[0054] In this disclosure, the term "narrow operating condition" refers to the situation where the performance of a vaned diffuser is limited when operating within a flow range deviating from its design point. That is, it performs well at a specific design point of rotational speed and flow rate, but its performance is limited when the operating condition deviates from that design point.

[0055] In this disclosure, the term "diffraction gradient" refers to the rate at which the pressure of the airflow increases in the flow channel of a bladed diffuser. A larger diffusion gradient results in a more rapid pressure increase, but also makes airflow separation easier; a smaller diffusion gradient results in a more stable pressure increase and more precise airflow control.

[0056] The term "surge margin" in this disclosure refers to the safe distance of the system from a surge condition. During the operation of a turbocharger or turbine, when the fluid flow rate is below the surge margin, the airflow direction reverses, causing severe vibrations in the equipment (bladed diffuser, turbocharger, or engine), posing a risk of damage. A larger surge margin results in higher equipment stability and better safety.

[0057] In related technologies, bladed diffusers with a single-blade adjustment mode are difficult to adapt to all engine operating conditions.

[0058] To address the technical problem that single-blade adjustment mode vaned diffusers in related technologies are difficult to adapt to all engine operating conditions, this disclosure proposes a multi-layer axially movable vaned diffuser. This vaned diffuser dynamically changes the effective blade height of each layer by controlling the axial movement of each layer of the multi-layer diffuser blades on the back disk, guiding the airflow inside the vaned diffuser to meet the performance requirements of the turbocharger or engine under different operating conditions.

[0059] Figure 1 This is a schematic diagram of a bladed diffuser provided for at least one embodiment of this disclosure. Figure 1 As shown, the vaned diffuser may include a back plate 1, multiple diffuser blades 2, and a drive mechanism 3.

[0060] The back plate 1 has an annular structure, and multiple sets of blade grooves are formed on the end face 11 of the back plate 1. Each set of blade grooves includes multiple blade grooves located on the end face 11 in different circumferential directions. Figure 1 Not shown in the image; see the image for the specific location. Figure 2 Furthermore, all air slots in each group are set in the same direction, while air slots in different groups are set in different directions.

[0061] Each layer of the multi-layer diffuser blade 2 includes multiple diffuser blades 21, and all the diffuser blades 21 in each layer are evenly distributed in a circumferential direction on the end face 11 and slide into the corresponding air groove. All the diffuser blades 21 in each layer are configured to move synchronously along the axial direction of the back disk 1 in the corresponding air groove.

[0062] The drive mechanism 3 includes a plurality of drive units 31, each of which corresponds to a target layer of the multilayer diffuser blade 2 and is connected to all the diffuser blades 21 in the target layer.

[0063] It should be noted that in the multi-layer diffuser blades 2, the number of diffuser blades in each layer can be the same or different, and each diffuser blade 21 can be perpendicular or not perpendicular to the back disk 1. The shape of the diffuser blades 21 is not limited in the embodiments of this disclosure and can be adjusted according to specific design requirements. Furthermore, Figure 1 The three-layer diffuser blades given are merely examples. The number of layers of multi-layer diffuser blades 2 and the number of diffuser blades in each layer can be set according to actual needs, and the embodiments disclosed herein do not limit this.

[0064] In the above scheme, since the back plate 1 is a ring structure, the axial direction of the back plate 1 is perpendicular to the end face 11 of the back plate 1. That is, the running direction of each movable target layer in the multi-layer diffuser blade 2 is perpendicular to the end face 11 of the back plate 1, and each movable target layer runs independently, which limits the axial movement of the multi-layer diffuser of this disclosure.

[0065] In the above scheme, "multiple" refers to two or more layers, including two. "Multi-layer" refers to two or more layers, including two layers. At least two layers of the multi-layer diffuser blade 2 are provided with drive units 31, so that the blade height (referring to the effective blade height) of at least two layers of diffuser blades in the multi-layer diffuser blade 2 is adjustable. That is, the multi-layer diffuser blade 2 of this disclosure can be configured to have adjustable blade heights for some layers or all layers.

[0066] For the specific structure of the back plate 1 in the above scheme, please refer to [link / reference]. Figure 2 .like Figure 2 As shown, in Figure 1 Based on this, the back plate 1 has a circular structure, and multiple sets of blade grooves 12 are evenly distributed on the end face 11 of the back plate 1. Each set of blade grooves 12 is arranged along one direction, and the specific direction is not limited in the embodiments of this disclosure. The blade grooves 12 correspond one-to-one with the diffuser blades 21. These blade grooves 12 extend along the circumferential direction of the back plate 1 and are used to accommodate the structure of the diffuser blades 21 in the multi-layer diffuser blades 2. The design of the blade grooves 12 ensures the stable installation and sliding of the diffuser blades 21 on the back plate 1, while allowing the diffuser blades 21 to move synchronously in the axial direction of the back plate to adapt to different working conditions. The material of the back plate 1 is usually selected as a high-strength and wear-resistant material to ensure its stability and durability in high-speed rotation and harsh working environments.

[0067] In the above-described scheme, this disclosure does not limit the structure and drive type of the drive unit 31. The drive unit 31 can be a drive element or a drive component. For example, the structure of the drive unit 31 may include a synchronizing ring or other drive structures. The drive unit 31 can be an electric drive unit, a hydraulic drive unit, or a pneumatic drive unit, etc. These different structures and types of drive units can all achieve the adjustment of the diffuser blade height.

[0068] In the above scheme, the drive unit 31 can be directly or indirectly connected to the diffuser blades 21, so that the diffuser blades 21 of each layer form a whole, thereby enabling all the diffuser blades 21 in each layer to move synchronously along the axial direction of the back plate 1 when displaced. The axial movement distance of each layer can be adjusted individually, and the specific axial movement distance is set according to actual needs. The embodiments disclosed herein do not limit this. In the case of direct connection, the drive unit 31 can be fixedly connected to the corresponding diffuser blade 21 by bolts, welding or other fastening methods to ensure the synchronicity of the two during rotation. Indirect connection may be achieved through intermediate parts, such as connecting plates, connecting shafts, etc., to connect the drive unit 31 and the diffuser blades 21. This connection method is more flexible when it is necessary to adjust the height of the diffuser blades 21 or to perform maintenance.

[0069] In the above scheme, the axial movement distance of each layer in the multi-layer diffuser blade 2 (also called the distance the diffuser blade 21 moves axially along the back plate 1) can be set to be the same or different according to actual needs. Furthermore, only one or two layers of the multi-layer diffuser blade 2 can participate in axial movement, while other layers do not, achieving a more refined diffusion effect. In practical applications, this adjustment mechanism significantly enhances the flexibility and adaptability of the vaned diffuser to different operating conditions. For example, when the engine is under low load, reducing the number of diffuser blade layers participating in axial movement or shortening their axial movement distance can reduce airflow resistance and improve engine fuel economy. Conversely, under high load, increasing the number of diffuser blade layers participating in axial movement or extending their axial movement distance can enhance the diffusion effect, improve the turbocharger's boosting efficiency, and thus increase the engine's power output. In addition, this adjustment mechanism also allows for fine adjustment of the axial movement distance of the diffuser blade 21 according to the engine's specific operating conditions (also called specific operating conditions) to achieve optimal airflow control and energy conversion efficiency. This not only helps improve the overall performance of the engine, but also extends its service life to some extent and reduces maintenance costs.

[0070] Some embodiments of this disclosure also provide turbochargers and engines corresponding to the bladed diffusers described above.

[0071] The vaned diffuser provided in at least one embodiment of this disclosure is applicable to any existing turbocharger or engine application scenario equipped with a vaned diffuser, and the embodiments of this disclosure are not limited thereto. For example, in the aviation field, this vaned diffuser can be applied to high-performance aero engines to improve the engine's boost efficiency and power output in the thin air at high altitudes by finely adjusting airflow, thereby enhancing the aircraft's flight performance and climb capability. In the automotive industry, it can be used to improve the response speed and fuel economy of turbocharged gasoline and diesel engines, providing drivers with a smoother driving experience and lower operating costs. Furthermore, in large power machinery such as ships and power plants, this vaned diffuser can also leverage its unique advantages to improve the overall system efficiency and reliability by optimizing airflow control.

[0072] Compared to related technologies, this disclosure proposes a bladed diffuser with multiple layers of axially movable blades. By adjusting the axial movement distance of each layer of the multi-layer diffuser blades 2, the blade height of different layers in the multi-layer diffuser blades 2 is dynamically changed, thereby guiding the airflow inside the bladed diffuser. This optimizes the height of the diffuser blades 21 participating in diffusion in the flow channel, ensuring that the bladed diffuser maintains efficient and stable operation under various extreme conditions, meeting the performance requirements of turbochargers or engines under different operating conditions. Furthermore, since the axial movement distance of each layer of diffuser blades can be adjusted independently, the adjustment methods are highly diverse, allowing the displacement or axial position of different layers in the multi-layer diffuser blades 2 to be determined according to actual operating requirements. Because the displacement or axial position of each layer of diffuser blades 21 can be set independently, different displacement combinations can be formed between the multi-layer diffuser blades 2, thus constructing a novel bladed diffuser structure. This design can adapt to the needs of all operating conditions, ensuring optimal diffusion performance under various operating conditions. By precisely controlling the axial movement distance of each layer of blades, the airflow channel can be effectively optimized, improving the overall performance of the turbocharger or engine, and enabling it to maintain a highly efficient and stable operating state under different working conditions.

[0073] The main function of the backplate 1 is to support the diffuser blades 21 and guide the airflow, ensuring smooth airflow within the bladed diffuser, thereby improving the overall efficiency of the turbocharger or engine. The backplate 1 is designed with the dynamic characteristics of airflow in mind; by optimizing its shape and structure, airflow losses are reduced and the diffusion effect is enhanced. Furthermore, the backplate 1 possesses high strength and wear resistance, enabling it to adapt to various complex working environments and ensuring the long-term stable operation of the turbocharger or engine.

[0074] The primary function of the multi-layer diffuser blade 2 is to gradually reduce airflow velocity and convert kinetic energy into pressure energy through a multi-stage stacked design. Each layer of the diffuser blade 21 undergoes precise calculation and testing to ensure optimal diffusion performance under specific operating conditions. Working in conjunction with the backplate 1, the multi-layer diffuser blade 2 further optimizes the airflow path, reducing eddies and turbulence, thereby improving the overall efficiency and performance of the turbocharger or engine. Furthermore, the multi-layer diffuser blade 2 is made of wear-resistant materials to enhance its durability and reliability, enabling it to withstand prolonged high-load operating environments.

[0075] The main function of the drive mechanism 3 is to provide reliable blade adjustment power for the multi-layer diffuser blades 2. It typically consists of high-performance bearings, precision gears, and efficient transmission devices to ensure good smoothness and low noise levels during high-speed operation. The drive mechanism 3 has high strength and excellent corrosion resistance, enabling it to operate stably for extended periods in harsh working environments, ensuring that all diffuser blades 21 in each layer reach the preset blade height, thereby effectively improving the overall performance and efficiency of the turbocharger or engine.

[0076] In some embodiments, to improve the overall efficiency of the turbocharger or engine, each layer of the multi-layer diffuser blades 2 has the same number of diffuser blades. All diffuser blades 21 in each layer are evenly distributed on the circumference of the backplate 1 to ensure uniform airflow distribution and effective diffusion. Furthermore, this design helps reduce airflow turbulence during diffusion, improving the overall efficiency of the turbocharger or engine. The arrangement of the multi-layer diffuser blades 2 is precisely calculated to achieve optimal aerodynamic effects, further enhancing the performance and stability of the equipment.

[0077] In some embodiments, to reduce energy consumption and noise, all diffuser blades 21 in the multi-layer diffuser blade 2 are perpendicular to the end face 11 of the backplate 1. The vertical design of the diffuser blades 21 maximizes the utilization of airflow energy, ensuring effective deceleration and pressurization of the airflow as it passes through the diffuser blades 21. This design not only improves the intake efficiency of the turbocharger or engine but also helps reduce energy consumption and noise. Furthermore, the vertically arranged diffuser blades 21 are easier to manufacture and maintain, reducing production costs and operational complexity. In some advanced applications, the material and shape of the diffuser blades 21 can be optimized according to specific requirements to achieve better performance.

[0078] In some embodiments, to enhance the stability and efficiency of the vaned diffuser in the turbocharger, the central axis of the backplate 1 coincides with the rotation axis of the turbocharger. This design ensures the stability and efficiency of the multi-layered diffuser blades 2 during turbocharger operation. This design allows the diffuser blades 21 to more effectively convert the kinetic energy of the airflow received from the turbocharger into pressure energy, thereby improving the efficiency of the entire engine system. Simultaneously, the close fit between the backplate 1 and the turbocharger ensures the stability and continuity of the airflow during transmission, avoiding energy loss.

[0079] Figure 3 This is a partial schematic diagram of a bladed diffuser provided for at least one embodiment of the present disclosure. Figure 1 and Figure 2 On the basis of Figure 3As shown, to reduce airflow disturbance and energy loss between diffuser blades 21, in multi-layer diffuser blades 2, the major axes 21a of diffuser blades 21 in different layers located in the same set of airfoils coincide, i.e., are collinear. This design of coincident major axes 21a helps ensure that the airflow remains continuous and stable as it flows through different layers of diffuser blades 21, reducing airflow disturbance and energy loss between diffuser blades 21. This design not only improves the efficiency of the bladed diffuser but also makes the turbocharger or engine run more smoothly, reducing vibration and noise. Furthermore, the multi-layer diffuser blade 2 with coincident major axes 21a has a compact structure and occupies less space, which is beneficial for the overall layout and lightweight design of the turbocharger or engine. In some special applications, the coincidence degree of the major axes 21a of the diffuser blades 21 can be adjusted to meet different performance requirements, further enhancing the flexibility and adaptability of the equipment.

[0080] In some embodiments, to achieve precise control of any layer in the multi-layer diffuser blade 2, the drive mechanism 3 further includes a first push rod and a first motor corresponding to the first target layer in the multi-layer diffuser blade 2. One end of the first push rod is connected to the diffuser blade 21 corresponding to the first target layer, and the other end of the first push rod is connected to the drive unit 31 corresponding to the first target layer. The first target layer is any layer of the multi-layer diffuser blade 2. The output shaft of the first motor is connected to the drive unit 31 corresponding to the first target layer, and the first motor is used to drive the drive unit 31 corresponding to the first target layer to move axially along the back plate 1, so as to drive all the diffuser blades 21 in the first target layer to move synchronously along the axial direction of the back plate 1 in the corresponding airfoil slots. This design allows at least one layer in the multi-layer diffuser blade 2 to be precisely axially adjusted by the combination of the first motor and the first push rod. When it is necessary to change the blade height of the first target layer to adapt to different working conditions, the first motor is started, driving the drive unit 31 to move axially along the back plate 1. The movement of the drive unit 31 is then transmitted to the diffuser blades 21 in the first target layer through the first push rod, so that they move synchronously in the corresponding airfoil slots. This synchronous movement ensures that the relative positions between the diffuser blades 21 remain constant, thereby maintaining the continuity and stability of the airflow channel. Furthermore, due to the precise control of the first push rod and the drive unit 31, the adjustment of the diffuser blades 21 can be very fine and accurate, further improving the performance and adaptability of the bladed diffuser.

[0081] In some embodiments, to achieve precise control of any two layers of the multi-layer diffuser blades 2, the drive mechanism 3 further includes a second push rod and a second motor corresponding to a second target layer in the multi-layer diffuser blades 2 that is different from the first target layer. One end of the second push rod is connected to the corresponding diffuser blade 21 in the second target layer, and the other end of the second push rod is connected to the corresponding drive unit 31 in the second target layer. The output shaft of the second motor is connected to the drive unit 31 in the second target layer, and the second motor is used to drive the drive unit 31 in the second target layer to move axially along the back plate 1, so as to drive all the diffuser blades 21 in the second target layer to move synchronously along the axial direction of the back plate 1 in the corresponding airfoil slots. The first motor and the second motor can work independently or in concert to achieve independent or synchronous adjustment of the diffuser blades 21 in different layers of the multi-layer diffuser blades 2. This design allows the bladed diffuser to be flexibly adjusted according to different operating conditions or performance requirements, further improving the working efficiency and performance stability of the turbocharger or engine.

[0082] In some embodiments, to achieve precise control of any three layers in the multi-layer diffuser blade 2, the drive mechanism 3 further includes a third push rod and a third motor corresponding to a third target layer in the multi-layer diffuser blade 2 that is different from the first and second target layers. One end of the third push rod is connected to the corresponding diffuser blade 21 in the third target layer, and the other end of the third push rod is connected to the corresponding drive unit 31 in the third target layer. The output shaft of the third motor is connected to the drive unit 31 in the third target layer, and the third motor is used to drive the drive unit 31 in the third target layer to move axially along the back plate 1, so as to drive all the diffuser blades 21 in the third target layer to move synchronously along the axial direction of the back plate 1 in the corresponding airfoil slots. The first motor, the second motor, and the third motor can work independently or in concert to achieve independent or synchronous adjustment of the diffuser blades 21 in different layers of the multi-layer diffuser blade 2. This design allows the bladed diffuser to be flexibly adjusted according to different operating conditions or performance requirements, further improving the working efficiency and performance stability of the turbocharger or engine.

[0083] In some embodiments, to achieve a precise linkage mechanism, the first, second, and third motors are all linear motors. The direct power generated by the linear motors precisely drives the drive unit 31 to move smoothly and efficiently in the axial direction. Simultaneously, a carefully designed pushrod mechanism transmits this power to the corresponding blade layers, ensuring that the blade layers remain synchronized with the drive unit 31, achieving a coordinated and consistent movement. This precise linkage mechanism not only improves the system's operational accuracy but also significantly enhances the overall operational stability and reliability.

[0084] In some embodiments, each drive unit is provided with a synchronization ring, which drives the movement of the corresponding target layer, and the synchronization ring is connected to all the diffuser blades in the corresponding target layer. This design ensures that when the synchronization ring rotates, it can drive all the diffuser blades connected to it to move synchronously and stably. Through this design, each drive unit can independently and precisely control the diffuser blades of the corresponding target layer, achieving fine-tuning of the airflow inside the entire bladed diffuser, further improving the operating efficiency and performance stability of the turbocharger or engine.

[0085] In some embodiments, to achieve precise control of four or more layers of multi-layer diffuser blades 2, the drive structure may include more push rods and motors for multi-layer diffuser blades 2 with four or more layers. Each layer of diffuser blades 21 corresponds to an independent push rod and motor. One end of the push rod is connected to the diffuser blade 21 of the corresponding layer, and the other end is connected to the drive unit 31 of that layer. The output shaft of the motor is connected to the drive unit 31 of that layer, and is used to drive the drive unit 31 to move axially along the back plate 1, thereby driving multiple diffuser blades 21 of the corresponding layer to move synchronously along the axial direction of the back plate 1 in the corresponding airfoil slots. This design is not only applicable to four-layer multi-layer diffuser blades 2, but also to diffuser blades 21 with more layers, greatly enhancing the flexibility and adaptability of the bladed diffuser, enabling it to be adjusted more precisely according to different operating conditions or performance requirements, and further improving the overall performance and stability of the turbocharger or engine.

[0086] Figure 4 This is a schematic diagram of the structure of a multi-layer diffuser blade provided in at least one embodiment of this disclosure. Figure 4 As shown, the multi-layer diffuser blade 2 includes blades extending from the inner circumference 13 to the outer circumference 14 along the back disk 1 (i.e., the airflow direction, see [reference]). Figure 1The multi-layer diffuser blade 2 consists of a leading-edge blade layer A, a middle blade layer B, and a trailing-edge blade layer C, arranged sequentially. Each of these layers is driven by a different drive ring. Furthermore, in the multi-layer diffuser blade 2, the major axes of the diffuser blades 21A (leading-edge layer), 21B (middle-edge layer), and 21C (trailing-edge layer), all located in the same set of airfoils, coincide. The diffuser blades 21A (leading-edge layer), 21B (middle-edge layer), and 21C (trailing-edge layer) are designed with specific airfoils to adapt to fluid flow requirements. The shape and angle of the diffuser blade 21A in the leading-edge layer are designed to effectively receive high-speed airflow and guide it sequentially to the diffuser blades 21B (middle-edge layer) and 21C (trailing-edge layer). The middle blade layer B is responsible for further decelerating and diffuserizing the airflow, ensuring a smooth transition to the trailing-edge blade layer C. The trailing edge blade layer C is located furthest from the turbocharger, and its diffuser blades 21 are designed to guide airflow evenly to the engine intake for optimal combustion efficiency and power output. Each layer of diffuser blades 21 is precisely controlled by an independent drive mechanism 3 to ensure that each layer moves in a predetermined sequence and speed, thereby effectively regulating the airflow. This design not only improves the overall performance of the bladed diffuser but also enhances its adaptability to different operating conditions.

[0087] Figure 5 for Figure 4 A cross-sectional view of the location of the same group of airfoil grooves. (See attached image.) Figure 5 As shown, the diffuser blades 21A of the leading edge blade layer, 21B of the middle blade layer, and 21C of the trailing edge blade layer can move axially to adapt to different working conditions and optimize the airflow path.

[0088] In some embodiments, the initial state of the multi-layer diffuser blades 2 is such that the blade heights of the leading edge blade layer A, the middle blade layer B, and the trailing edge blade layer C are equal, all at their default blade heights. These default blade heights are preset based on the engine's operating requirements under standard conditions to ensure that the multi-layer diffuser blades 2 provide adequate diffusion in most situations. When the blade heights of each layer are equal in the initial state, the airflow experiences uniform resistance upon entering the bladed diffuser, thus contributing to a smooth transition and uniform distribution of the airflow. Furthermore, this design simplifies the initial adjustment and calibration process of the bladed diffuser, improving its operational convenience. During engine operation, as operating conditions change, the heights of each blade layer can be dynamically adjusted via the corresponding drive mechanism 3 to adapt to different airflow speeds and pressure requirements, thereby further optimizing the diffusion effect and improving engine performance.

[0089] In some embodiments, the diffuser blades 21 move in such a way that the axial movement distance of the multiple diffuser blades 2 is the same. In this mode of movement, to be suitable for wide operating conditions and high pressure ratios, the operating modes of the vaned diffuser include a vaneless diffuser mode and a conventional vaned diffuser mode. Furthermore, the vaned diffuser also includes a controller for controlling the operation of the drive mechanism 3. The controller is configured to execute steps S10-S20 as described below.

[0090] Step S10: After receiving the first control command for starting the bladeless diffuser mode, all drive units 31 in the control drive mechanism 3 move to move each layer of the multi-layer diffuser blade 2 to a preset first axial position, so that the blade height of each layer of the multi-layer diffuser blade 2 reaches a first preset height that matches the bladeless diffuser mode.

[0091] Step S20: After receiving the second control command for starting the conventional bladed diffuser mode, all drive units 31 in the control drive mechanism 3 move to move each layer of the multi-layer diffuser blade 2 to a preset second axial position, so that the blade height of each layer of the multi-layer diffuser blade 2 reaches a second preset height that matches the conventional bladed diffuser mode, wherein the second preset height is greater than the first preset height.

[0092] It should be noted that the first axial position and the second axial position, as well as the first set height and the second set height, can be obtained through testing and calibration, so that the performance indicators of the vane diffuser in the corresponding mode meet the set standards.

[0093] In step S10, the axial movement distance of the diffuser blades 21 in each layer is small, meaning the vane diffuser uses a low blade height. Its operating environment is similar to that of a vaneless diffuser, resulting in low noise, a wide operating range, and suitability for scenarios where stability is paramount across a wide range of operating conditions. In the vaneless diffuser mode of step S10, the small axial movement distance of the diffuser blades 21 leads to a relatively open flow channel inside the vane diffuser, reducing friction and turbulence between the airflow and the blades, thus effectively lowering the noise level. Simultaneously, this low blade height design allows the vane diffuser to maintain stable performance over a wider range of operating conditions. In step S20, the axial movement distance of the diffuser blades 21 in each layer is large, meaning the vane diffuser uses a high blade height. Its operating environment is similar to that of a conventional vane diffuser, improving flow conditions and increasing efficiency. It is suitable for scenarios with high pressure ratio requirements, meeting the demands for power output. In the conventional vaned diffuser mode of step S20, the axial movement distance of the diffuser blades 21 is increased, and the blade height is correspondingly raised. This allows the vaned diffuser to better guide and control airflow, improve flow conditions, and thus increase operating efficiency. The high blade height design enables the vaned diffuser to provide a higher pressure ratio, meeting the needs of scenarios with high power output and pressure ratio requirements. Therefore, through precise control of the controller, the vaned diffuser can flexibly switch between two operating modes according to actual needs, achieving optimal performance.

[0094] In some embodiments, to improve the operational stability of the vaned diffuser, in the vaneless diffuser mode or the conventional vaned diffuser mode, i.e., steps S10-S20, all drive units 31 in the drive mechanism 3 are configured to move synchronously. The movement of the drive units 31 is precisely controlled by a controller to ensure that the diffuser blades 21 of each layer can move axially at a predetermined distance and speed. This design not only improves the operational stability of the vaned diffuser but also enables it to maintain high efficiency under different operating conditions. The synchronous movement characteristic of the drive units 31 further enhances the vaned diffuser's ability to guide and control airflow, allowing for smoother airflow within the vaned diffuser, reducing energy loss, and improving overall operational efficiency. Therefore, in these embodiments, the performance of the vaned diffuser is significantly optimized, enabling it to better adapt to various complex operating scenarios.

[0095] In some embodiments, the movement of the diffuser blades 21 is such that the axial movement distances of the multiple diffuser blades 2 are different. In this movement mode, to be suitable for narrow operating conditions, the operating mode of the vaned diffuser includes a first special operating condition mode. The first special operating condition in the first special operating condition mode is configured such that the actual operating parameters of the vaned diffuser meet a preset narrow-band threshold range and the target performance parameters of the vaned diffuser exceed a preset performance parameter standard. Furthermore, the controller is configured to execute the following step S30.

[0096] Step S30: After receiving the third control command for starting the first special operating mode, control the drive unit 31 corresponding to the leading edge blade layer A to move the leading edge blade layer A to the third axial position, and control the drive unit 31 corresponding to the middle blade layer B and the drive unit 31 corresponding to the trailing edge blade layer C to maintain their original positions, so that the blade height of all diffuser blades 21 in the leading edge blade layer A is reduced and the blade height of all diffuser blades 21 in the middle blade layer B and the trailing edge blade layer remains unchanged.

[0097] It should be noted that the actual operating parameters and target performance parameters of the vane diffuser can be selected according to the operating conditions. The narrowband threshold range and performance parameter standards can be obtained through testing and calibration, so that the performance indicators of the vane diffuser in the first special operating mode reach the set standards.

[0098] In step S30, when applied to a bladed diffuser with three or more layers of diffuser blades, the movement of the leading-edge blade layer A aims to adjust the airflow angle and velocity at the diffuser inlet, thereby optimizing the airflow distribution within the diffuser. Lowering the height of the leading-edge blade layer A increases the airflow velocity at the inlet, suppresses flow separation at the leading-edge blade layer A, weakens the circumferential non-uniformity of the pre-swirling flow at the inlet, reduces the impact of the leading-edge blade layer A, improves intake uniformity, and increases diffusion efficiency. This adjustment not only improves the efficiency of the bladed diffuser but also helps reduce noise and vibration, further enhancing overall performance. Simultaneously, keeping the positions of the middle blade layer B and the trailing-edge blade layer C unchanged ensures that the bladed diffuser maintains stable pressure distribution and flow characteristics even when operating conditions change. Step S30 is suitable for high-performance scenarios with narrow operating conditions.

[0099] In some embodiments, in order to be suitable for strong turbulent conditions, the operating mode of the bladed diffuser further includes a second special operating mode, and the second special operating mode is configured such that the diffusion ratio of the bladed diffuser exceeds a first set ratio and the turbulence intensity exceeds a set intensity, and the controller is further configured to perform the following step S40.

[0100] Step S40: After receiving the fourth control command for starting the second special operating mode, control the drive unit 31 corresponding to the middle blade layer B to move the middle blade layer B to the fourth axial position, while the drive unit 31 corresponding to the leading edge blade layer A and the drive unit 31 corresponding to the trailing edge blade layer C maintain their original positions, so that the blade height of all diffuser blades 21 in the middle blade layer B is reduced and the blade height of all diffuser blades 21 in the leading edge blade layer A and the trailing edge blade layer C remains unchanged.

[0101] It should be noted that the diffusion ratio of a vaned diffuser refers to the ratio of the outlet cross-sectional area to the inlet cross-sectional area when fluid passes through the diffuser. This ratio reflects the diffuser's ability to convert kinetic energy into pressure energy. In a vaned diffuser, the diffusion ratio is a key parameter that directly affects its performance, as well as the overall efficiency of the turbocharger and engine. The initial set ratio and intensity can be obtained through testing and calibration, ensuring that the vaned diffuser's performance indicators meet the set standards under the second special operating condition.

[0102] In step S40, when applied to a bladed diffuser with three layers of diffusers, the blade height of the middle blade layer B is reduced, while the blade heights of the leading-edge blade layer A and the trailing-edge blade layer C remain unchanged. Reducing the blade height of the middle blade layer B decreases the cross-sectional area of ​​the middle flow channel, lowering the mid-section diffusion ratio, optimizing the diffusion gradient, increasing the flow velocity in the middle blade layer B, reducing the risk of trailing-edge separation, reducing the degree of mid-section diffusion, and improving surge margin, making it suitable for high-pressure ratio and highly turbulent inlet scenarios. Maintaining the original height of the leading-edge blade layer A preserves the guiding effect at the diffuser front end, ensuring that the airflow can smoothly enter the diffuser. Similarly, maintaining the same height of the trailing-edge blade layer C helps stabilize the pressure distribution of the airflow at the diffuser end, preventing excessive turbulence at the diffuser outlet. This adjustment method not only improves the adaptability and stability of the diffuser but also ensures efficient engine operation under different operating conditions.

[0103] In some embodiments, in order to be suitable for high dynamic response conditions, the operating mode of the vaned diffuser also includes a third special operating condition mode, and the third special operating condition in the third special operating condition mode refers to the diffusion ratio of the vaned diffuser being lower than the second set ratio and the dynamic response index of the vaned diffuser exceeding the set value. Furthermore, the controller is also configured to perform the following step S50.

[0104] Step S50: After receiving the fifth control command for starting the third special operating mode, control the drive unit 31 corresponding to the trailing edge blade layer C to move the trailing edge blade layer C to the fifth axial position, while the drive units 31 corresponding to the leading edge blade layer A and the middle blade layer B maintain their original positions, so that the blade height of all diffuser blades 21 in the trailing edge blade layer C is reduced and the blade height of all diffuser blades 21 in the leading edge blade layer A and the middle blade layer B remains unchanged.

[0105] It should be noted that the dynamic response indicators of the vaned diffuser include the rate of change of rotational speed, the rate of change of pressure, and the rate of change of flow rate, which can be selected and set according to usage requirements. These indicators comprehensively reflect the performance of the vaned diffuser under high dynamic response conditions. Specifically, the rate of change of rotational speed measures the speed at which the diffuser blade rotational speed changes with engine operating conditions; the rate of change of pressure reflects the response speed of the diffuser's internal pressure adjustment with rotational speed; and the rate of change of flow rate reflects the diffuser's ability to adjust the inlet and outlet flow rates according to demand. The second set ratio and set value can be obtained through testing and calibration, ensuring that the performance indicators of the vaned diffuser in the third special operating mode meet the set standards.

[0106] In step S50, the blade height of the trailing edge blade layer C is significantly reduced after adjustment, while the blade heights of the leading edge blade layer A and the middle blade layer B remain unchanged. The reduced blade height of the trailing edge blade layer C effectively increases the flow velocity at the blade tips, thus effectively suppressing the pressure rise along the flow direction during fluid flow. This design successfully suppresses flow separation in the trailing edge blade layer C region, further enhancing the energy recovery efficiency at the diffuser tip. This not only improves the overall system flow stability but also significantly enhances its adaptability across a wide range of operating conditions. This optimized design is particularly suitable for applications with low pressure ratios and high dynamic response, effectively coping with complex and changing operating conditions and ensuring stable and efficient system operation.

[0107] In some embodiments, in order to maintain efficient and stable operation under various complex operating conditions, the controller is also configured to perform the following steps S60-S80.

[0108] Step S60: Obtain the actual operating parameters and target performance parameters of the vaned diffuser under the current operating conditions. The actual operating parameters include the diffusion ratio and turbulence intensity, and the target performance parameters include the dynamic response index.

[0109] Step S70: Based on the actual operating parameters and target performance parameters, identify when the current operating mode of the vaned diffuser does not match the current operating condition, and obtain the target operating mode that matches the current operating condition.

[0110] Step S80: Generate the corresponding control command to start the target operating mode, so that the vane diffuser switches from the current operating mode to the target operating mode.

[0111] In step S60, actual operating parameters such as diffusion ratio and turbulence intensity are acquired in real time by sensors installed inside the bladed diffuser. These parameters accurately reflect the operating status of the bladed diffuser under the current operating conditions. Target performance parameters, especially dynamic response indicators, are pre-set based on the overall performance requirements of the engine. By comparing the actual operating parameters with the target performance parameters, the controller can quickly identify whether the operating mode of the bladed diffuser matches the current operating conditions. In step S70, once a mismatch between the current operating mode and the operating conditions is identified, the controller immediately initiates a search algorithm. This algorithm, based on a pre-set operating condition-mode matching database, quickly finds the target operating mode that best matches the current operating conditions. This process ensures that the bladed diffuser can adjust to its optimal operating state in the shortest possible time. Step S80 generates corresponding control commands based on the identified target operating mode and sends them to the actuator of the bladed diffuser via a signal transmission system. These control commands precisely guide the movement of the drive units 31 of the trailing edge blade layer C, the leading edge blade layer A, and the middle blade layer B to adjust the height of each blade layer, thereby enabling the switching of the vaned diffuser's operating mode. This intelligent control strategy significantly improves the adaptability and flexibility of the vaned diffuser, allowing it to maintain efficient and stable operation under various complex conditions.

[0112] Figure 6 This is a structural block diagram of a turbocharger provided for at least one embodiment of the present disclosure. (See diagram below.) Figure 6 As shown, the turbocharger 10 includes a vaned diffuser 100 as described in the above embodiment.

[0113] In some embodiments, the turbocharger can determine the specific operating mode of starting the vaned diffuser 100 by using the turbocharger's operating parameters. These operating parameters can be selected as boost pressure and impeller speed; the classification of low / medium / high load and speed depends on the specific turbocharger. The compressor load is typically related to the engine's intake air demand. When the engine requires more air (e.g., high speed, high throttle), the compressor needs to provide higher boost pressure, resulting in a high load. Low load may occur at idle speed or low speed and low throttle, where the boost demand is small. Medium load falls between these two conditions. The boost pressure can be detected by a turbocharger pressure sensor, and the intake manifold pressure can be measured to assess the compressor load status in the turbocharger. The impeller speed can be obtained directly by a speed sensor or indirectly through a model.

[0114] Figure 7 This is a structural block diagram of an engine provided for at least one embodiment of the present disclosure. (See diagram below.) Figure 7 As shown, the engine 20 includes a bladed diffuser 100 as described in the above embodiment.

[0115] In some embodiments, the engine 20 further includes an engine controller ECU and a compressor, and a vane diffuser 100 may be disposed within the compressor.

[0116] During full-condition engine calibration, if the engine performance fails to meet the predetermined standards, the ECU will send an electronic control signal to the controller in the vaned diffuser 100. The ECU then calculates the corresponding values ​​and adjusts the compressor and engine performance accordingly. The ECU will evaluate whether the engine has met the performance requirements; if not, it will continue to execute the above control cycle until the performance standards are met; if they are met, it will maintain the current state.

[0117] For high-performance scenarios under narrow operating conditions, the compressor speed and pressure ratio are monitored. By real-time monitoring of whether the speed reaches or exceeds the designed high-performance threshold and whether the pressure ratio reaches the preset high level, it can be determined whether the current operating condition is narrow and the stability of the flow can be assessed. If the pressure fluctuation is a stable, small fluctuation, it indicates that the flow is stable and in the high-efficiency stage. By comparing the performance curve under the design operating condition, it can be confirmed whether the current parameters are within the high-efficiency region. For narrow operating conditions, step S30 is executed.

[0118] For high-pressure, high-turbulence inlet scenarios, pressure and turbulence intensity are monitored. Turbulence intensity can be measured using a hot-wire anemometer or laser Doppler velocimeter, combined with a dynamic pressure sensor to capture changes in turbulence intensity and determine the strong turbulence condition. For strong turbulence conditions, step S40 is executed.

[0119] For low-pressure-ratio, high-dynamic-response scenarios, pressure is monitored to determine if the pressure ratio is low, and the dynamic rate of change of compressor speed is simultaneously monitored to determine if the compressor is in a high-dynamic-response condition. Step S50 is executed for high-dynamic-response conditions.

[0120] Although embodiments of the present disclosure have been shown and described above, it is to be understood that the above embodiments are exemplary and should not be construed as limiting the present disclosure. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present disclosure.

Claims

1. A vane diffuser, characterized in that, include: The back plate has an annular structure and multiple sets of blade grooves are formed on the end face of the back plate. Each set of blade grooves includes multiple blade grooves located in different circumferential directions on the end face. All blade grooves in each set are arranged in the same direction, and the blade grooves in different sets are arranged in different directions. The multi-layer diffuser blade includes multiple diffuser blades in each layer, and all diffuser blades in each layer are evenly distributed in a circumferential direction on the end face and slidably embedded in the corresponding air groove. All diffuser blades in each layer are configured to move synchronously along the axial direction of the back disk in the corresponding air groove. as well as, The drive mechanism includes multiple drive units, each of which corresponds to a target layer of the multilayer diffuser blades and is connected to all diffuser blades in the target layer.

2. The vaned diffuser according to claim 1, characterized in that, The drive mechanism also includes: A first push rod corresponding to the first target layer in the multi-layer diffuser blade, one end of the first push rod being connected to the diffuser blade corresponding to the first target layer, and the other end of the first push rod being connected to the drive unit corresponding to the first target layer, wherein the first target layer is any layer of the multi-layer diffuser blade; and, A first motor, the output shaft of which is connected to a drive unit corresponding to the first target layer, and the first motor is used to drive the drive unit corresponding to the first target layer to move along the axial direction of the back disk, so as to drive all the diffuser blades in the first target layer to move synchronously along the axial direction of the back disk in the corresponding air groove.

3. The vaned diffuser according to claim 2, characterized in that, The drive mechanism also includes: A second push rod corresponding to a second target layer in the multilayer diffuser blades that is different from the first target layer; one end of the second push rod is connected to the corresponding diffuser blade in the second target layer, and the other end of the second push rod is connected to the drive unit corresponding to the second target layer; and... The second motor has its output shaft connected to the drive unit corresponding to the second target layer. The second motor is used to drive the drive unit corresponding to the second target layer to move along the axial direction of the back disk, so as to drive all the diffuser blades in the second target layer to move synchronously along the axial direction of the back disk in the corresponding air groove.

4. The vaned diffuser according to any one of claims 1-3, characterized in that, Each of the aforementioned drive units is provided with a synchronization ring, which is connected to all the diffuser blades in the corresponding target layer. The multi-layer diffuser blades include a leading edge blade layer, a middle blade layer, and a trailing edge blade layer arranged sequentially along the inner circumference to the outer circumference of the back disk. The leading edge blade layer, the middle blade layer, and the trailing edge blade layer are each driven by different drive units. In the multi-layer diffuser blades, the long axes of the diffuser blades in the leading edge blade layer, the middle blade layer, and the trailing edge blade layer, all located in the same set of airfoil slots, coincide.

5. The vaned diffuser according to claim 4, characterized in that, The operating modes of the valved diffuser include a vaneless diffuser mode and a conventional valved diffuser mode, and the valved diffuser further includes: Controller, the controller being used to control the action of the drive mechanism; The controller is configured as follows: Upon receiving a first control command to activate the bladeless diffuser mode, all drive units in the drive mechanism are controlled to move to move each layer of the multi-layer diffuser blades to a preset first axial position, so that the blade height of each layer of the multi-layer diffuser blades reaches a first preset height matching the bladeless diffuser mode; and, Upon receiving a second control command to activate the conventional bladed diffuser mode, all drive units in the drive mechanism are controlled to move to move each layer of the multi-layer diffuser blades to a preset second axial position, so that the blade height of each layer of the multi-layer diffuser blades reaches a second preset height that matches the conventional bladed diffuser mode, wherein the second preset height is greater than the first preset height.

6. The vaned diffuser according to claim 5, characterized in that, In the bladeless diffuser mode or the conventional vaned diffuser mode, all drive units in the drive mechanism move synchronously; and... The operating mode of the valved diffuser also includes a first special operating condition mode, wherein the first special operating condition in the first special operating condition mode is configured such that the actual operating parameters of the valved diffuser meet a preset narrowband threshold range and the target performance parameters of the valved diffuser exceed a preset performance parameter standard, and the controller is configured to: Upon receiving a third control command to initiate the first special operating mode, the drive unit corresponding to the leading edge blade layer is controlled to move to the third axial position, while the drive units corresponding to the middle blade layer and the trailing edge blade layer are controlled to maintain their original positions, so that the blade height of all diffuser blades in the leading edge blade layer is reduced and the blade height of all diffuser blades in the middle blade layer and the trailing edge blade layer remains unchanged.

7. The vaned diffuser according to claim 5, characterized in that, The operating mode of the bladed diffuser also includes a second special operating condition mode. In this second special operating condition mode, the second special condition is configured such that the diffusion ratio of the bladed diffuser exceeds a first preset ratio and the turbulence intensity exceeds a preset intensity. Furthermore, the controller is also configured to: Upon receiving the fourth control command for activating the second special operating mode, the drive unit corresponding to the middle blade layer is moved to move the middle blade layer to the fourth axial position, while the drive units corresponding to the leading edge blade layer and the trailing edge blade layer maintain their original positions, so that the blade height of all diffuser blades in the middle blade layer is reduced and the blade height of all diffuser blades in the leading edge blade layer and the trailing edge blade layer remains unchanged.

8. The vaned diffuser according to claim 5, characterized in that, The operating mode of the vaned diffuser also includes a third special operating condition mode. The third special operating condition mode refers to a situation where the diffusion ratio of the vaned diffuser is lower than a second preset ratio and the dynamic response index of the vaned diffuser exceeds a preset value. Furthermore, the controller is configured to: Upon receiving the fifth control command for activating the third special operating mode, the drive unit corresponding to the trailing edge blade layer is controlled to move to the fifth axial position, while the drive units corresponding to the leading edge blade layer and the middle blade layer remain in their original positions, so that the blade height of all diffuser blades in the trailing edge blade layer is reduced and the blade height of all diffuser blades in the leading edge blade layer and the middle blade layer remains unchanged.

9. The vaned diffuser according to any one of claims 5-8, characterized in that, All diffuser blades in the multi-layer diffuser are perpendicular to the end face of the back disk, and the controller is further configured to: Obtain the actual operating parameters and target performance parameters of the bladed diffuser under the current operating conditions, wherein the actual operating parameters include the diffusion ratio and turbulence intensity, and the target performance parameters include dynamic response indicators; When the current operating mode of the bladed diffuser does not match the current operating condition based on the actual operating parameters and the target performance parameters, a target operating mode that matches the current operating condition is obtained; and... Generate corresponding control commands to initiate the target operating mode, so that the lobed diffuser switches from the current operating mode to the target operating mode.

10. A turbocharger, characterized in that, The turbocharger includes a vaned diffuser as described in any one of claims 1 to 9.

11. An engine, characterized in that, The engine includes a bladed diffuser as described in any one of claims 1 to 9.

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