A radial turbine module and a radial turbine power generation device

Abstract

This application provides a centripetal turbine assembly, comprising an inlet housing, a turbine housing, a shroud, a guide vane, a nozzle ring, and an impeller. The inlet housing has an inlet port, and the turbine housing is detachably connected to the inlet housing. An exhaust port is located at one end of the turbine housing axially away from the inlet housing, and the exhaust port is in fluid communication with the inlet port. The shroud and the inlet housing form an inlet flow channel, and at least a portion of the radial outer dimension of the inlet flow channel increases axially towards the exhaust port. The guide vane is detachably disposed within the turbine housing and connected to the shroud, and the guide vane and the turbine housing form a deflection flow channel, at least a portion of the deflection flow channel decreasing axially towards the exhaust port. The nozzle ring is at least partially located in the deflection flow channel and detachably connected to the guide vane. The impeller is rotatably disposed within the turbine housing about a rotation axis parallel to the axial direction and corresponds to the nozzle ring. This application has a simpler structure, facilitating manufacturing and assembly / disassembly.

Description

Technical Field

[0001] This application relates generally to the technical field of turbomachinery, and more specifically to a centripetal turbine assembly and a centripetal turbine power generation device. Background Technology

[0002] A centripetal turbine is a machine that converts the energy contained in a fluid medium into mechanical work; it is also known as a centripetal turbine. In related technologies, a centripetal turbine is a radially inlet, axially exhaust centripetal turbine structure, including a volute, nozzle rings, and an impeller. During operation, high-energy airflow is collected by the volute and enters the nozzle ring circumferentially. The airflow expands and accelerates within the nozzle ring, forming a high-speed airflow that impacts the impeller, causing it to rotate and perform work, thus outputting mechanical work.

[0003] However, due to the complex structure of the traditional radial intake volute, the manufacturing, assembly, disassembly, and maintenance of the entire radial turbine are extremely inconvenient and inefficient.

[0004] Therefore, there is a need to provide a centripetal turbine assembly and a centripetal turbine power generation device to at least partially solve the above problems. Summary of the Invention

[0005] The summary section introduces a series of simplified concepts, which will be further explained in detail in the detailed description section. This summary section is not intended to limit the key and essential technical features of the claimed technical solution, nor is it intended to determine the scope of protection of the claimed technical solution.

[0006] To at least partially solve the above problems, a first aspect of this application provides a centripetal turbine assembly, the centripetal turbine assembly comprising:

[0007] An air intake housing having an air intake port extending axially;

[0008] A turbine housing, detachably connected to the intake housing, the turbine housing having an axially extending exhaust port at one end opposite to the intake housing, and the exhaust port being in fluid communication with the intake port;

[0009] A flow deflector is located inside the air intake housing and forms an air intake passage with the air intake housing. The air intake passage is in fluid communication with the air intake port. At least a portion of the radial outer dimension of the air intake passage increases along the axial direction from the air intake port to the exhaust port.

[0010] A flow guide is detachably disposed within the turbine housing and connected to the flow shield. The flow guide and the turbine housing form a steering flow channel. At least a portion of the radial outer dimension of the steering flow channel decreases along the axial direction from the air inlet to the exhaust outlet. The flow guide has flow channels that are fluidly connected to the air inlet channel and the steering flow channel, respectively.

[0011] A nozzle ring, the nozzle ring being at least partially located in the deflection channel and detachably connected to the guide frame; and

[0012] An impeller is rotatably disposed within the turbine housing about a rotation axis parallel to the axial direction and corresponds to the nozzle ring.

[0013] According to the centripetal turbine assembly of the first aspect of this application, fluid is axially transported and radially guided outward through the intake channel between the deflector and the intake casing. Then, fluid is axially transported and radially guided inward through the deflector channel between the guide frame and the turbine casing. Finally, the nozzle ring located at the deflector channel sprays fluid toward the impeller, causing the impeller to rotate, and the fluid is finally discharged from the exhaust port. Using the above-mentioned solution of this application, axial intake and axial exhaust are achieved, which helps to reduce the radial outer dimension and facilitates the layout of external pipelines. Since the guide frame is detachably connected to the intake casing and the turbine casing respectively, the manufacturing, assembly, and replacement of the intake casing, guide frame, and turbine casing are more convenient and flexible, thereby improving production efficiency. Furthermore, the intake casing with axial intake is simpler than the volute structure, which further improves the manufacturing efficiency of the intake casing.

[0014] Optionally, the intake housing has a first stop, and the turbine housing has a second stop adapted to the first stop. The first stop and the second stop are disposed opposite to each other to form a limiting groove, which is used to at least partially accommodate the guide frame and limit the radial movement of the guide frame along the axial direction and perpendicular to the axial direction.

[0015] Optionally, the first stop is a convex stop, and the second stop is a concave stop.

[0016] Optionally, the flow guide has:

[0017] Outer ring, the outer ring being located in the limiting groove;

[0018] An inner ring, located inside and concentrically positioned with the outer ring, is connected to the flow guide and the nozzle ring; and

[0019] A connecting member is located at the interval between the outer ring and the inner ring and is connected to the outer ring and the inner ring respectively. The connecting members are arranged circumferentially around the rotation axis, and the flow guide channel is formed between adjacent connecting members.

[0020] Optionally, the centripetal turbine assembly further comprises:

[0021] A wheel back seal, detachably connected to the inner ring, the wheel back seal having first sealing teeth continuously arranged circumferentially relative to the axis of rotation and spaced apart radially perpendicular to the axis of rotation.

[0022] The impeller back has a second sealing tooth adapted to engage with the first sealing tooth.

[0023] Optionally, the inner ring is recessed along the axial direction at the end near the exhaust port to form a first annular groove, and the nozzle ring is at least partially located in the first annular groove and detachably connected to the inner ring.

[0024] Optionally, the nozzle ring has:

[0025] An annular body, the annular body being completely located within the first annular groove; and

[0026] A stator blade is connected to the annular body and is at least partially located in the steering channel. The end of the stator blade away from the annular body along the axial direction abuts against the turbine housing. The stator blade is circumferentially spaced relative to the axis of rotation.

[0027] Optionally, the inner ring is recessed along the axial direction at the end near the exhaust port to form a second annular groove, and the wheel back seal is located in the second annular groove and is detachably connected to the inner ring.

[0028] Optionally, the inner surface of the outer ring extends axially along the inner surface of the intake housing and the inner surface of the turbine housing, respectively; and / or

[0029] The outer surface of the inner ring and the outer surface of the flow guide are arranged along the axial direction.

[0030] Optionally, the flow deflector is detachably connected to the flow deflector frame.

[0031] Optionally, the deflection channel extends in a direction perpendicular to the axial direction.

[0032] Optionally, the centripetal turbine assembly further includes:

[0033] An impeller shaft having a first shaft section, a second shaft section, a limiting section, and a third shaft section arranged sequentially along an axial direction; the diameter of the first shaft section is less than or equal to the diameter of the second shaft section; the diameter of the limiting section is greater than the diameters of the second shaft section and the third shaft section; the third shaft section is used to connect to a rotating shaft.

[0034] A locking nut, which is threaded onto the first shaft section.

[0035] The impeller is sleeved on the outside of the second shaft section, and the impeller is located along the axial direction between the locking nut and the limiting section.

[0036] Optionally, the flow guide and the flow guide frame enclose a cavity;

[0037] The flow guide has a flow inlet and a flow outlet. The flow inlet is fluidly connected to the cavity and the turning channel, respectively. The flow outlet is configured to extend radially from the inner surface of the inner ring through the connecting member to the outer surface of the outer ring.

[0038] The turbine housing has a vent hole, which is correspondingly provided with the drain outlet, and the vent hole is in fluid communication with the drain outlet and the outside of the turbine housing.

[0039] A second aspect of this application provides a centripetal turbine power generation device, the centripetal turbine power generation device comprising:

[0040] Based on the above-mentioned centripetal turbine assembly; and

[0041] A generator having a shaft detachably connected to the impeller shaft of the radial turbine assembly, the diameter of the shaft being larger than the diameter of the impeller shaft.

[0042] According to the radial turbine power generation device of the second aspect of this application, the impeller shaft of the radial turbine assembly is detachably connected to the rotating shaft, which makes the assembly between the impeller of the radial turbine assembly and the generator more flexible and convenient. Moreover, since it is not necessary to lengthen the generator shaft along the axial direction to install the impeller, the bending stiffness of the rotating shaft itself is improved, which helps to prevent radial vibration from occurring at the suspended end of the rotating shaft during rotation, thereby ensuring that the impeller and the rotating shaft can work stably. Attached Figure Description

[0043] The following drawings, illustrating embodiments of this application, are incorporated herein by reference and are used to understand this application. The drawings illustrate embodiments of this application and their descriptions, serving to explain the principles of this application. In the drawings,

[0044] Figure 1This is a cross-sectional view of a radial turbine assembly connected to a rotating shaft according to a preferred embodiment of this application;

[0045] Figure 2 for Figure 1 The three-dimensional cross-sectional view of the centripetal turbine assembly and shaft in a disassembled state is shown.

[0046] Figure 3 for Figure 1 The three-dimensional sectional view of the centripetal turbine assembly and shaft in the assembled state is shown.

[0047] Figure 4 for Figures 1 to 3 A perspective sectional view of the intake housing shown;

[0048] Figure 5 for Figures 1 to 3 A perspective cross-sectional view of the fairing shown;

[0049] Figure 6 for Figures 1 to 3 A perspective sectional view of the air deflector shown;

[0050] Figure 7 for Figures 1 to 3 A perspective sectional view of the turbine casing shown;

[0051] Figure 8 for Figures 1 to 3 A perspective cross-sectional view of the nozzle ring shown;

[0052] Figure 9 for Figures 1 to 3 A three-dimensional sectional view of the impeller shown;

[0053] Figure 10 for Figures 1 to 3 A perspective sectional view of the wheel back seal shown; and

[0054] Figure 11 for Figures 1 to 3 The impeller shaft shown is a three-dimensional sectional view.

[0055] Explanation of reference numerals in the attached figures:

[0056] 100: Intake housing; 101: Intake port

[0057] 102: First stop; 110: Turbine housing

[0058] 111: Exhaust port; 112: Second stop.

[0059] 114: Vent 120: Draft shield

[0060] 130: Air intake channel; 140: Air deflector.

[0061] 141: Outer ring 142: Inner ring

[0062] 142a: First annular groove; 142b: Second annular groove

[0063] 143: Connecting component; 144: Drainage inlet

[0064] 145: Drainage outlet; 146: Drainage channel

[0065] 150: Cavity; 160: Diverting flow channel

[0066] 170: Nozzle ring; 171: Annular body

[0067] 172: Still blade 180: Impeller

[0068] 180a: Second sealing tooth; 181: Impeller shaft

[0069] 181a: First axle segment; 181b: Second axle segment

[0070] 181c: Limiting segment; 181d: Third axle segment

[0071] 182: Locking nut; 190: Wheel back seal.

[0072] 190a: First sealing tooth; 200: Rotating shaft

[0073] AX: Axis of rotation Detailed Implementation

[0074] In the following description, numerous specific details are set forth to provide a more thorough understanding of this application. However, it will be apparent to those skilled in the art that embodiments of this application may be practiced without one or more of these details. In other instances, certain technical features well-known in the art have not been described to avoid confusion with embodiments of this application.

[0075] To fully understand the embodiments of this application, a detailed structure will be presented in the following description. Obviously, the implementation of the embodiments of this application is not limited to the specific details familiar to those skilled in the art.

[0076] It should be understood that the terminology used herein is intended only to describe particular embodiments and is not intended to limit the scope of this application. The singular forms “a,” “an,” and “the” are also intended to include the plural forms unless the context clearly indicates otherwise. When the terms “comprising” and / or “including” are used in this specification, they indicate the presence of the stated features, integrals, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components, and / or combinations thereof. The terms “upper,” “lower,” “front,” “rear,” “left,” “right,” and similar expressions used in this application are for illustrative purposes only and are not intended to be limiting.

[0077] Ordinal numbers such as “first” and “second” used in this application are merely identifiers and have no other meaning, such as a specific order. Moreover, for example, the term “first component” does not imply the existence of a “second component”, and the term “second component” does not imply the existence of a “first component”.

[0078] The specific embodiments of this application will be described in more detail below with reference to the accompanying drawings, which illustrate representative embodiments of this application and are not intended to limit this application.

[0079] This application provides a centripetal turbine assembly. For example... Figures 1 to 11 As shown, the radial turbine assembly according to this application includes an inlet housing 100, a turbine housing 110, a shroud 120, a guide vane 140, a nozzle ring 170, and an impeller 180. The inlet housing 100 has an axially extending inlet 101. The turbine housing 110 is detachably connected to the inlet housing 100. The turbine housing 110 has an axially extending exhaust port 111 at one end axially away from the inlet housing 100. The exhaust port 111 is in fluid communication with the inlet 101. The shroud 120 is located within the inlet housing 100 and forms an intake passage 130 with the inlet housing 100. The intake passage 130 is in fluid communication with the inlet 101. At least a portion of the radial outer dimension of the intake passage 130 increases axially from the inlet 101 to the exhaust port 111. The guide vane 140 is detachably disposed within the turbine housing 110 and connected to the shroud 120. The guide vane 140 and turbine housing 110 form a deflector duct 160. At least a portion of the deflector duct 160 has a radially decreasing outer dimension from the inlet 101 to the outlet 111 along the axial direction. The guide vane 140 has a guide duct 146. The guide duct 146 is in fluid communication with the inlet duct 130 and the deflector duct 160, respectively. A nozzle ring 170 is at least partially located in the deflector duct 160 and is detachably connected to the guide vane 140. An impeller 180 is rotatably disposed within the turbine housing 110 about a rotation axis AX parallel to the axial direction and corresponds to the nozzle ring 170.

[0080] The intake casing 100 and turbine casing 110 together form the housing of the radial turbine assembly. All other components are arranged inside the housing. The intake casing 100, turbine casing 110, shroud 120, and guide frame 140 together form the gas flow channel. The gas flow channel is divided into an intake channel 130 and a deflection channel 160, which changes the flow channel from axial intake to radial exhaust, achieving the function of airflow deflection. After being deflected, the airflow enters the nozzle ring 170, expands and accelerates, and then drives the impeller 180 to rotate and perform work.

[0081] According to the radial turbine assembly of this application, fluid is axially transported and radially guided outward through the intake passage 130 between the shroud 120 and the intake housing 100. Then, fluid is axially transported and radially guided inward through the deflector passage 160 between the guide frame 140 and the turbine housing 110. Finally, the nozzle ring 170 located at the deflector passage 160 sprays fluid toward the impeller 180 so that the impeller 180 rotates, and the fluid is finally discharged from the exhaust port 111. The above-described solution of this application enables axial air intake and axial exhaust, which helps to reduce the radial outer dimensions and facilitates the layout of external pipelines. Since the guide frame 140 is detachably connected to the intake housing 100 and the turbine housing 110, the manufacturing, assembly, and replacement of the intake housing 100, guide frame 140, and turbine housing 110 are more convenient and flexible, thereby improving production efficiency. Furthermore, the axially inlet intake housing 100 is simpler than the volute structure, further improving the manufacturing efficiency of the intake housing 100. This solves the limitations imposed by the traditional radially inlet volute structure on external pipelines and the structure of the radial turbine assembly, while also facilitating the production of each component of the radial turbine assembly, effectively improving the overall production efficiency.

[0082] See Figure 1 The intake housing 100 and the deflector 120 together form the intake duct 130. The intake duct 130 may include a radially expanding section and a radially constant section extending axially. The radial outer dimension of the radially expanding section increases towards the exhaust port 111 along the axial direction. The radial outer dimension of the radially constant section remains unchanged towards the exhaust port 111 along the axial direction. That is, the intake duct 130 gradually expands outward from a circular cross-section along the flow direction to form an annular cross-section, eventually reaching its maximum outer diameter and then becoming parallel to the axial direction. Both axial ends of the intake housing 100 are constructed as flange structures and can be bolted to the front pipe and the rear turbine housing 110. Figure 1As shown, the inner and outer walls of the deflector 120 can be constructed from smooth curves or multiple straight lines, which can be determined and adjusted according to the specific flow conditions and manufacturing requirements. The change in the inlet flow channel 130 should be gradual and smooth to reduce energy loss caused by the flow within it. The deflector frame 140 and the turbine housing 110 together form the deflector flow channel 160. After passing through the aforementioned inlet flow channel 130, the airflow enters the deflector flow channel 160, which converts the axially flowing gas from the inlet flow channel 130 into radially flowing gas.

[0083] See Figures 1 to 3 In the radial turbine assembly, the components are arranged coaxially and positioned using methods such as stops to ensure the positional accuracy of each component. For example, the intake housing 100 has a first stop 102. The turbine housing 110 has a second stop 112 adapted to the first stop 102. The first stop 102 and the second stop 112 are arranged opposite to each other to form a limiting groove. The limiting groove is used to at least partially accommodate the guide frame 140 and restrict the axial and radial movement of the guide frame 140. Installing the guide frame 140 through the limiting groove formed by the first stop 102 and the second stop 112 can restrict not only the axial degree of freedom but also the radial degree of freedom. This makes the positioning of the guide frame 140 simpler and more reliable, and also facilitates the assembly and disassembly of the guide frame 140.

[0084] See Figures 1 to 3 ,as well as Figure 4 and Figure 7 In the illustrated embodiment, the first stop 102 is constructed as a convex stop, and the second stop 112 is constructed as a concave stop.

[0085] See Figures 1 to 3 and Figure 5 The air deflector 120 can be conical to guide the airflow in all directions. The air deflector 120 can be fixed to the air deflector frame 140 with bolts.

[0086] The turbine housing 110 is the main body of the radial turbine assembly. Except for rotating parts such as the impeller 180, all other stationary parts are positioned and installed by the turbine housing 110. There is a blade tip clearance between the turbine housing 110 and the impeller 180, which needs to be determined based on the impeller's expansion and bearing clearance.

[0087] See Figure 1 For example, the steering channel 160 extends in a direction perpendicular to the axial direction. That is, the steering channel 160 extends radially. This can further reduce the axial outer dimension, making the axial structure more compact.

[0088] See Figures 1 to 3 and Figure 7For example, the flow guide 140 may have an outer ring 141, an inner ring 142, and connecting members 143. The outer ring 141 is located in a limiting groove. The inner ring 142 is located inside the outer ring 141 and is concentrically arranged with the outer ring 141. The inner ring 142 is connected to the flow guide shroud 120 and the nozzle ring 170. The connecting members 143 are located at the interval between the outer ring 141 and the inner ring 142, and are connected to the outer ring 141 and the inner ring 142 respectively. The connecting members 143 are circumferentially spaced around the axis of rotation AX. A flow channel 146 is formed between adjacent connecting members 143. For example, the outer ring 141 and the inner ring 142 are connected by a number of stiffeners. The stiffeners are an optional embodiment of the connecting members 143 described above. A flow channel 146 for gas flow is formed between the outer ring 141, the inner ring 142, and the adjacent stiffeners. The outer ring 141 positions and fixes the flow guide 140 within the turbine housing 110. The inner ring 142 is used to position and secure components such as the nozzle ring 170 and the wheel back seal 190, which will be described in detail below.

[0089] See Figure 7 Furthermore, the diffuser 140 can be constructed as a single piece. This can improve the structural strength of the diffuser 140.

[0090] See Figures 1 to 3 ,as well as Figure 9 and Figure 10 Furthermore, the radial turbine assembly may also have a wheel back seal 190. The wheel back seal 190 is detachably connected to the inner ring 142. The wheel back seal 190 has first sealing teeth 190a. The first sealing teeth 190a are continuously arranged circumferentially relative to the axis of rotation AX and are spaced apart radially perpendicular to the axis of rotation AX. The wheel back of the impeller 180 has second sealing teeth 180a adapted to engage with the first sealing teeth 190a. Through the interaction of the first sealing teeth 190a of the wheel back seal 190 and the second sealing teeth 180a of the wheel back of the impeller 180, a narrow and tortuous channel is formed, thereby reducing wheel back leakage and improving the sealing effect.

[0091] In the illustrated embodiment, the inner ring 142 is axially recessed at its end near the exhaust port 111 to form a first annular groove 142a. The nozzle ring 170 is at least partially located in the first annular groove 142a and is detachably connected to the inner ring 142.

[0092] See Figures 1 to 3 ,as well as Figure 7 and Figure 8For example, the nozzle ring 170 has an annular body 171 and stator vanes 172. The annular body 171 is entirely located within the first annular groove 142a. The stator vanes 172 are connected to the annular body 171 and are at least partially located in the turning channel 160. The ends of the stator vanes 172 axially away from the annular body 171 abut against the turbine housing 110. The stator vanes 172 are circumferentially spaced relative to the axis of rotation AX. The nozzle ring 170 has a plurality of stator vanes 172. Each stator vane 172 has the same shape. Each stator vane 172 is uniformly arranged circumferentially on the annular body 171. The shape of the stator vanes 172 can be determined according to actual aerodynamic requirements. The gap between the stator vanes 172 gradually decreases radially inward to form a flow channel with a gradually narrowing area, in which the airflow gradually expands and accelerates.

[0093] In the illustrated embodiment, the inner ring 142 is axially recessed at its end near the exhaust port 111 to form a second annular groove 142b. The wheel back seal 190 is located in the second annular groove 142b and is detachably connected to the inner ring 142.

[0094] See Figures 1 to 3 Schematic, the inner surface of the outer ring 141 may extend axially along the inner surface of the intake housing 100 and the inner surface of the turbine housing 110, respectively. The outer surface of the inner ring 142 may extend axially along the outer surface of the deflector 120.

[0095] See Figures 1 to 3 ,as well as Figure 5 and Figure 6 For example, the fairing 120 can be detachably connected to the fairing frame 140 by fasteners such as bolts.

[0096] See Figures 1 to 3 ,as well as Figure 11In addition, the centripetal turbine assembly may also have an impeller shaft 181 and a locking nut 182. The impeller shaft 181 has a first shaft section 181a, a second shaft section 181b, a limiting section 181c, and a third shaft section 181d arranged sequentially along the axial direction. The diameter of the first shaft section 181a is less than or equal to the diameter of the second shaft section 181b. The diameter of the limiting section 181c is greater than the diameters of the second shaft section 181b and the third shaft section 181d. The third shaft section 181d is used to connect to the rotating shaft 200. The locking nut 182 is threaded onto the first shaft section 181a. The impeller 180 is sleeved on the outside of the second shaft section 181b. The impeller 180 is axially positioned between the locking nut 182 and the limiting section 181c. The impeller 180 is secured between the locking nut 182 and the limiting section 181c by the locking nut 182, and the locking nut 182 applies an axial preload to the impeller 180, thereby increasing the friction between the locking nut 182 and the impeller 180, and between the impeller 180 and the limiting section 181c. When the impeller 180 is driven to rotate by the fluid, the impeller 180 transmits power to the impeller shaft 181, which in turn drives the impeller shaft 181 to rotate.

[0097] The impeller shaft 181 can be made of the same material as the shaft 200 of the generator or other device to be connected. During the tightening of the locking nut 182, the impeller shaft 181 can be stretched using a device capable of providing tensile force, such as a tensioning machine. While the impeller shaft 181 is axially extended, the locking nut 182 is tightened until it abuts against the impeller 180, after which the tensile force is released. This increases the axial preload provided by the locking nut 182 to the impeller shaft 181.

[0098] Impeller 180 operates between turbine housing 110, nozzle ring 170 and impeller back seal 190. Impeller 180 can be connected and fixed to shaft 200 by various means, including but not limited to impeller shaft 181, key, end face teeth, thread, friction welding, flange, etc.

[0099] See Figures 1 to 3 To ensure the safe and efficient operation of the impeller 180, there are certain gaps between the impeller 180 and the turbine housing 110, the nozzle ring 170, and the wheel back seal 190. These gaps need to be strictly controlled during the design and assembly process.

[0100] The impeller 180 can be an open impeller 180, a semi-open impeller 180, or a closed impeller 180. The impeller 180 has several evenly arranged blades, and the airflow impacts the blades of the impeller 180 and drives them to rotate and do work. Due to the need for axial exhaust, the impeller 180 in this application is assembled differently from the conventional impeller 180. The outlet of this impeller 180 is connected to the shaft end of the generator shaft 200, rather than the back of the impeller being connected to the shaft end of the generator shaft 200.

[0101] See Figures 1 to 3 ,as well as Figure 6 and Figure 7 In the illustrated embodiment, the deflector 120 and the deflector frame 140 enclose a cavity 150. The deflector frame 140 has a flow inlet 144 and a flow outlet 145. The flow inlet 144 is in fluid communication with the cavity 150 and the diversion channel 160, respectively. The flow outlet 145 is configured to extend radially from the inner surface of the inner ring 142 via the connecting member 143 to the outer surface of the outer ring 141. The turbine housing 110 has a vent 114. The vent 114 is correspondingly provided with the flow outlet 145. The vent 114 is in fluid communication with the flow outlet 145 and the outside of the turbine housing 110. With the use of the wheel back seal 190, the deflector 120, the guide frame 140, and the wheel back seal 190 together form the cavity 150 on the back of the impeller 180. A small amount of airflow will leak into the cavity 150 through the gap between the wheel back seal 190 and the wheel back of the impeller 180 via the inlet 144 of the guide frame 140. The cavity 150 is connected to the external pressure pipe via the outlet 145 on the guide frame 140 and the vent 114 on the turbine housing 110, guiding the gas to the low-pressure position of the outlet pipe of the radial turbine assembly. This allows for more flexible and free air intake or exhaust methods within the cavity 150, not limited to the number of stages of the impeller 180. To a certain extent, this helps simplify the structure of the turbine housing 110, thereby reducing the manufacturing cost and improving the manufacturing efficiency of the turbine housing 110.

[0102] See Figures 1 to 11 This application achieves airflow redirection through components such as the intake casing 100, guide vane 120, guide frame 140, and turbine casing 110, guiding the airflow to the nozzle ring 170 and impeller 180 for expansion and work, thus achieving axial intake and axial exhaust. Compared to the volute, the structure related to the intake air passage 130 is decomposed into multiple components, making each component easy to assemble and disassemble, resulting in a simpler, more flexible, and reliable structure suitable for various manufacturing methods. The axial cross-sectional shape of the flow channel formed between the components in this application can be constructed and adjusted using arcs, curves, and straight lines, facilitating the optimization of the flow state. The axial cross-sectional shape of the fluid flow channel composed of the intake casing 100, guide vane 120, guide frame 140, and turbine casing 110 is constructed using a combination of arcs, curves, and straight lines to form a gradually changing flow channel, ensuring smooth airflow and preventing eddies that could cause energy loss.

[0103] For applications with high pressure and strict sealing requirements, sealing rings can be added to the joint surfaces of various components to enhance the sealing effect and prevent leakage of fluid working fluid.

[0104] If the working fluid condenses into a liquid, a drainage hole (not shown) can be provided at the bottom of the housing of the centripetal turbine assembly to drain the liquid from the centripetal turbine assembly and prevent droplets from damaging the impeller 180. For example, the drainage hole can be provided at the bottom of the turbine housing 110.

[0105] See Figures 1 to 11 This application also provides a centripetal turbine power generation device, which includes a generator and a centripetal turbine assembly according to the above description. The generator has a shaft 200. The shaft 200 is detachably connected to the impeller shaft 181 of the centripetal turbine assembly. The diameter of the shaft 200 is larger than the diameter of the impeller shaft 181.

[0106] According to the radial turbine power generation device of this application, the rotor shaft 200 is detachably connected to the impeller shaft 181 of the radial turbine assembly, thereby making the assembly between the impeller 180 of the radial turbine assembly and the generator more flexible and convenient. Moreover, since it is not necessary to lengthen the rotor shaft 200 of the generator along the axial direction to install the impeller 180, the bending stiffness of the rotor shaft 200 itself is improved, which helps to prevent radial vibration from the suspended end of the rotor shaft 200 during rotation, so as to ensure that the impeller 180 and the rotor shaft 200 can work stably.

[0107] See Figures 1 to 3 and Figure 11 For example, the impeller shaft 181 and the shaft end of the rotating shaft 200 can be assembled by a threaded connection. The impeller shaft 181 can be manufactured from the same or similar material as the rotating shaft 200 and can undergo a certain amount of tensile deformation under the action of a tensile testing machine. In this way, when the impeller 180 located on the impeller shaft 181 is locked with the locking nut 182, the axial preload during locking can be increased, which helps to improve the bending stiffness of the impeller shaft 181, thereby increasing the critical speed and natural frequency of the entire rotor. Moreover, by using the impeller shaft 181, it is not necessary to extend the rotating shaft 200 axially, thereby reducing the axial dimension of the suspended end of the rotating shaft 200, increasing the rigidity of the rotating shaft 200 itself, and also helping to prevent radial vibration at the suspended end of the rotating shaft 200.

[0108] Unless otherwise defined, the technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used herein is for descriptive purposes only and is not intended to limit the scope of this application. Terms such as “setup” appearing herein can refer to either a component being directly attached to another component or a component being attached to another component via an intermediary. A feature described in one embodiment herein may be applied, alone or in combination with other features, to another embodiment, unless that feature is not applicable in that other embodiment or is otherwise stated.

[0109] This application has been described through the above embodiments; however, it should be understood that the above embodiments are for illustrative purposes only and are not intended to limit this application to the described embodiments. Those skilled in the art will understand that many more variations and modifications can be made based on the teachings of this application, and all such variations and modifications fall within the scope of protection claimed in this application.

Claims

1. A centripetal turbine assembly, characterized in that, The centripetal turbine assembly includes: An air intake housing having an air intake port extending axially; A turbine housing, detachably connected to the intake housing, the turbine housing having an axially extending exhaust port at one end opposite to the intake housing, and the exhaust port being in fluid communication with the intake port; A flow deflector is located inside the air intake housing and forms an air intake passage with the air intake housing. The air intake passage is in fluid communication with the air intake port. At least a portion of the radial outer dimension of the air intake passage increases along the axial direction from the air intake port to the exhaust port. A flow guide is detachably disposed within the turbine housing and connected to the flow shield. The flow guide and the turbine housing form a steering flow channel. At least a portion of the radial outer dimension of the steering flow channel decreases along the axial direction from the air inlet to the exhaust outlet. The flow guide has flow channels that are fluidly connected to the air inlet channel and the steering flow channel, respectively. A nozzle ring, the nozzle ring being at least partially located in the deflection channel and detachably connected to the guide frame; and An impeller, rotatably mounted within the turbine housing about a rotation axis parallel to the axial direction, and corresponding to the nozzle ring. The air intake housing has a first stop, and the turbine housing has a second stop adapted to the first stop. The first stop and the second stop are disposed opposite to each other to form a limiting groove. The limiting groove is used to at least partially accommodate the air guide frame and restrict the air guide frame from moving along the axial direction and radially perpendicular to the axial direction. Wherein, the first stop is a convex stop, and the second stop is a concave stop; and wherein The flow guide has: The outer ring is located in the limiting groove; An inner ring, located inside and concentrically positioned with the outer ring, is connected to the flow guide and the nozzle ring; and A connecting member is located at the interval between the outer ring and the inner ring and is connected to the outer ring and the inner ring respectively. The connecting members are arranged circumferentially around the rotation axis, and the flow guide channel is formed between adjacent connecting members.

2. The centripetal turbine assembly according to claim 1, characterized in that, The centripetal turbine assembly also has: A wheel back seal, detachably connected to the inner ring, the wheel back seal having first sealing teeth continuously arranged circumferentially relative to the axis of rotation and spaced apart radially perpendicular to the axis of rotation. The impeller back has a second sealing tooth adapted to engage with the first sealing tooth.

3. The centripetal turbine assembly according to claim 1, characterized in that, The inner ring is recessed along the axial direction at its end near the exhaust port to form a first annular groove, and the nozzle ring is at least partially located in the first annular groove and is detachably connected to the inner ring.

4. The centripetal turbine assembly according to claim 3, characterized in that, The nozzle ring has: An annular body, the annular body being completely located within the first annular groove; and A stator blade is connected to the annular body and is at least partially located in the steering channel. The end of the stator blade away from the annular body along the axial direction abuts against the turbine housing. The stator blade is circumferentially spaced relative to the axis of rotation.

5. The centripetal turbine assembly according to claim 2, characterized in that, The inner ring is recessed along the axial direction at the end near the exhaust port to form a second annular groove, and the wheel back seal is located in the second annular groove and is detachably connected to the inner ring.

6. The centripetal turbine assembly according to claim 1, characterized in that, The inner surface of the outer ring extends axially along the inner surface of the intake housing and the inner surface of the turbine housing, respectively; and / or The outer surface of the inner ring and the outer surface of the flow guide are arranged along the axial direction.

7. The radial turbine assembly according to any one of claims 1 to 6, characterized in that, The flow deflector is detachably connected to the flow deflector frame.

8. The radial turbine assembly according to any one of claims 1 to 6, characterized in that, The steering channel extends in a direction perpendicular to the axial direction.

9. The radial turbine assembly according to any one of claims 1 to 6, characterized in that, The centripetal turbine assembly also includes: An impeller shaft having a first shaft section, a second shaft section, a limiting section, and a third shaft section arranged sequentially along an axial direction; the diameter of the first shaft section is less than or equal to the diameter of the second shaft section; the diameter of the limiting section is greater than the diameters of the second shaft section and the third shaft section; the third shaft section is used to connect to a rotating shaft. A locking nut, which is threaded onto the first shaft section. The impeller is sleeved on the outside of the second shaft section, and the impeller is located along the axial direction between the locking nut and the limiting section.

10. The centripetal turbine assembly according to claim 1, characterized in that, The flow guide shroud and the flow guide frame enclose and form a cavity; The flow guide has a flow inlet and a flow outlet. The flow inlet is fluidly connected to the cavity and the turning channel, respectively. The flow outlet is configured to extend radially from the inner surface of the inner ring through the connecting member to the outer surface of the outer ring. The turbine housing has a vent hole, which is correspondingly provided with the drain outlet, and the vent hole is in fluid communication with the drain outlet and the outside of the turbine housing.

11. A centripetal turbine power generation device, characterized in that, The centripetal turbine power generation device has the following features: The radial turbine assembly according to any one of claims 1 to 10; and A generator having a shaft detachably connected to the impeller shaft of the radial turbine assembly, the diameter of the shaft being larger than the diameter of the impeller shaft.

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