Variable inlet radial turbine

Abstract

A variable inlet radial flow turbine is provided. The variable inlet radial flow turbine includes an impeller, a first partial inlet ring, and a second partial inlet ring. The first partial inlet ring includes a first inlet portion. The first inlet portion connects the radial inner side of the first partial inlet ring and the radial outer side of the first partial inlet ring, and extends non-circumferentially in the circumference of the first partial inlet ring. The second partial inlet ring includes a second inlet portion. The second inlet portion connects the radial inner side of the second partial inlet ring and the radial outer side of the second partial inlet ring, and extends non-circumferentially in the circumference of the second partial inlet ring. The second partial inlet ring and the first partial inlet ring can rotate relative to each other, so that the second inlet portion and the first inlet portion can overlap in the radial direction. In this way, by making the first partial inlet ring and the second partial inlet ring cooperate with each other, the variable inlet radial flow turbine can adapt to working conditions under different flow rates.

Description

Technical Field

[0001] The present application relates to the field of turbines, and more particularly to a variable inlet radial flow turbine. Background Art

[0002] Radial turbines are widely used in energy power or energy generation devices, with the advantages of compact structure, small size and high efficiency. Partial intake radial turbines can be used in thermal cycle systems and devices such as supercritical carbon dioxide cycle power generation system, organic working fluid Rankine cycle power generation system, micro gas turbine and refrigeration cycle system. The partial intake radial turbine adopts partial intake design to increase the height of the impeller blades and significantly improve the efficiency of the micro radial turbine.

[0003] The air intake has a great influence on the performance of a partial intake radial flow turbine. However, due to structural limitations, existing partial intake radial flow turbines generally adopt a fixed air intake design, which leads to a significant decrease in the performance of the turbine under variable flow conditions. Summary of the invention

[0004] The present application is made in view of the above-mentioned state of the prior art. The object of the present application is to provide a variable inlet radial flow turbine which can overcome at least one of the disadvantages described in the above-mentioned background technology.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions.

[0006] The present application provides a variable intake radial flow turbine as follows, which includes: an impeller; a first partial intake ring, which includes a first intake portion, the first intake portion connecting the radial inner side of the first partial intake ring and the radial outer side of the first partial intake ring, the first intake portion extending non-circumferentially in the circumferential direction of the first partial intake ring, and the first partial intake ring is sleeved on the radial outer side of the impeller; and a second partial intake ring, which includes a second intake portion, the second intake portion connecting the radial inner side of the second partial intake ring and the radial outer side of the second partial intake ring, the second intake portion extending non-circumferentially in the circumferential direction of the second partial intake ring, the second partial intake ring is sleeved on the radial outer side of the first partial intake ring, the second partial intake ring and the first partial intake ring can rotate relative to each other, so that the second intake portion and the first intake portion can overlap in the radial direction.

[0007] In an optional solution, the first air inlet portion extends continuously in the circumferential direction of the first partial air inlet ring, and the second air inlet portion extends continuously in the circumferential direction of the second partial air inlet ring.

[0008] In another optional solution, the sum of an extension angle of the first air inlet portion in the circumferential direction of the first partial air inlet ring and an extension angle of the second air inlet portion in the circumferential direction of the second partial air inlet ring is less than or equal to 360°.

[0009] In another optional solution, an extension angle of the first air inlet portion in the circumferential direction of the first partial air inlet ring is 180° to 270°, and / or an extension angle of the second air inlet portion in the circumferential direction of the second partial air inlet ring is 180° to 270°.

[0010] In another optional scheme, it also includes a nozzle ring, which includes a plurality of nozzle blades, and the plurality of nozzle blades are spaced apart in the circumferential direction of the nozzle ring, and nozzle flow channels are formed between adjacent nozzle blades. The nozzle ring is mounted on the radially outer side of the impeller and is located between the impeller and the first part of the intake ring, and at least a part of the plurality of nozzle flow channels connects the first intake part and the impeller.

[0011] In another optional solution, the plurality of nozzle flow channels include a first nozzle flow channel and a second nozzle flow channel, the first nozzle flow channel and the second nozzle flow channel have different throat areas, and the first partial intake ring and the nozzle ring are capable of relative rotation.

[0012] In another optional solution, at least two of the plurality of nozzle vanes have different vane outlet angles.

[0013] In another optional solution, at least two of the plurality of nozzle vanes have different vane inlet angles.

[0014] In another alternative, at least two of the plurality of nozzle vanes have different cascade densities.

[0015] In another optional solution, at least two of the plurality of nozzle vanes have different vane profiles.

[0016] By adopting the above technical solution, in the variable intake radial flow turbine of the present application, by making the first part intake ring and the second part intake ring cooperate with each other, the cross-sectional area of ​​the intake flow channel can be adjusted by the size of the overlapping part of the first intake part and the second intake part, so as to match the flow rate of the working fluid, so that the variable intake radial flow turbine can adapt to working conditions under different flow rates. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A perspective view of a variable inlet radial flow turbine according to an embodiment of the present application is shown.

[0018] Figure 2 Shows Figure 1A three-dimensional view of a variable inlet radial turbine in FIG. 1 , wherein the turbine housing is shown in section and the section lines are omitted.

[0019] Figure 3 Shows Figure 1 The first air inlet part and the second air inlet part of the variable inlet radial turbine in FIG. 1 , wherein the arrows indicate the flow direction of the working medium.

[0020] Figure 4 Shows Figure 1 FIG. 1 is an illustration of an inlet flow passage of a variable inlet radial turbine, wherein the arrow indicates the flow direction of the working medium.

[0021] Description of Reference Numerals

[0022] 1 turbine housing; 1a working chamber; 1b inlet flow passage; 1c exhaust flow passage;

[0023] 2 impeller; 2a impeller blade;

[0024] 3 nozzle ring; 3a nozzle blade; 3b nozzle flow channel;

[0025] 4 first part intake ring; 4a first intake part;

[0026] 5 second part air intake ring; 5a second air intake portion;

[0027] AIntake air duct. DETAILED DESCRIPTION

[0028] The exemplary embodiments of the present application are described below with reference to the accompanying drawings. It should be understood that these specific descriptions are only used to teach those skilled in the art how to implement the present application, and are not intended to exhaust all feasible methods of the present application, nor to limit the scope of the present application.

[0029] In the present application, two objects being “offset” in a certain direction means that there is no overlapping portion between the two objects when observed along the direction, otherwise the two objects are “overlapped” in the direction.

[0030] Figures 1 to 4 A variable intake radial flow turbine according to an embodiment of the present application is shown, which may include a turbine housing 1 , an impeller 2 , a nozzle ring 3 , a first partial intake ring 4 and a second partial intake ring 5 .

[0031] The turbine shell 1 may define a working chamber 1a, an inlet flow channel 1b and an exhaust flow channel 1c. The working chamber 1a may have a central axis. The inlet flow channel 1b may be located radially outside the working chamber 1a and extend spirally around the central axis of the working chamber 1a. The cross-sectional area of ​​the inlet flow channel 1b may gradually decrease from upstream to downstream in the direction of flow of the working medium. The exhaust flow channel 1c may be located on one side of the working chamber 1a in the axial direction of the working chamber 1a and extend along the central axis of the working chamber 1a. The inlet flow channel 1b and the exhaust flow channel 1c may connect the working chamber 1a and the outside of the turbine shell 1.

[0032] The impeller 2 may include a plurality of impeller blades 2a, and the plurality of impeller blades 2a may be evenly arranged in the circumferential direction of the impeller 2. The impeller 2 may be disposed in the working chamber 1a, and arranged coaxially with the working chamber 1a.

[0033] The nozzle ring 3 may include a plurality of nozzle blades 3a, and the plurality of nozzle blades 3a may be arranged in the circumferential direction of the nozzle ring 3. The nozzle blades 3a may extend in the radial direction of the nozzle ring 3 while extending in the circumferential direction of the nozzle ring 3, and a nozzle flow channel 3b may be formed between adjacent nozzle blades 3a. The nozzle flow channel 3b may taper from the radial outer side of the nozzle ring 3 to the radial inner side of the nozzle ring 3, so that the cross-sectional area of ​​the nozzle flow channel 3b gradually decreases from the upstream to the downstream in the flow direction of the working medium. The nozzle ring 3 may be located radially outside the impeller 2 and formed as one body with the turbine shell 1, the outlet of the nozzle flow channel 3b may be aligned with the impeller 2, and the nozzle ring 3 may be arranged coaxially with the impeller 2.

[0034] Further, the plurality of nozzle flow channels 3b may include a first nozzle flow channel and a second nozzle flow channel, and the first nozzle flow channel and the second nozzle flow channel may have different throat areas. At least two of the plurality of nozzle blades 3a may have different blade outlet angles. For example, at least one nozzle blade 3a defining the first nozzle flow channel and at least one nozzle blade 3a defining the second nozzle flow channel may have different blade outlet angles.

[0035] The first partial air intake ring 4 may be provided with a first air intake portion (notch) 4a, and the first air intake portion 4a may connect the radial inner side and the radial outer side of the first partial air intake ring 4. The first air intake portion 4a may extend continuously and non-entirely in the circumferential direction of the first partial air intake ring 4. For example, the extension angle of the first air intake portion 4a (the central angle corresponding to the extension range, the same below) may be 180° to 270°. The first partial air intake ring 4 may be sleeved on the radial outer side of the nozzle ring 3 and arranged coaxially with the impeller 2. The first partial air intake ring 4 may be pivotally connected to the turbine housing 1 so that the first partial air intake ring 4 can rotate around the impeller 2.

[0036] The second partial intake ring 5 may be provided with a second intake portion (notch) 5a, and the second intake portion 5a may connect the radial inner side and the radial outer side of the second partial intake ring 5. The second intake portion 5a may extend continuously and non-entirely in the circumferential direction of the second partial intake ring 5. For example, the extension angle of the second intake portion 5a may be 180° to 270°. The second partial intake ring 5 may be sleeved on the radial outer side of the first partial intake ring 4 and be arranged coaxially with the impeller 2. The second partial intake ring 5 may be pivotally connected to the turbine housing 1 so that the second partial intake ring 5 can rotate around the impeller 2.

[0037] Refer to the following Figure 3 and Figure 4 The working principle of variable inlet radial turbine is introduced.

[0038] Driven by an actuator (not shown in the figure), the first part of the intake ring 4 can rotate relative to the second part of the intake ring 5, so that the first intake part 4a and the second intake part 5a overlap in the radial direction of the impeller 2. The overlapping parts of the first intake part 4a and the second intake part 5a can be jointly formed into an intake flow channel A by the definition of the volute 1, and the working fluid can enter the nozzle flow channel 3b through the intake flow channel 1b and the intake flow channel A in sequence. The nozzle flow channel 3b can convert the pressure energy of the working fluid into kinetic energy, so that the working fluid leaving the nozzle flow channel 3b can impact the impeller blades 2a at a higher speed, thereby driving the impeller 2 to rotate. Afterwards, the working fluid can leave the turbine shell 1 from the exhaust flow channel 1c.

[0039] When the flow rate of the working medium is large, the first portion of the intake ring 4 can be rotated relative to the second portion of the intake ring 5, so that the cross-sectional area of ​​the intake flow channel A increases. Alternatively, when the flow rate of the working medium is small, the first portion of the intake ring 4 can be rotated relative to the second portion of the intake ring 5, so that the cross-sectional area of ​​the intake flow channel A decreases. In this way, by making the first portion of the intake ring 4 and the second portion of the intake ring 5 cooperate with each other, the cross-sectional area of ​​the intake flow channel A can be matched with the flow rate of the working medium, so that the variable intake radial flow turbine can adapt to working conditions under different flow rates.

[0040] Furthermore, the first portion of the intake ring 4 and the second portion of the intake ring 5 can be rotated so that the intake flow channel A is aligned with one or more specific nozzle blades 3a. When the flow rate of the working fluid is large, the intake flow channel A can be aligned with the nozzle flow channel 3b with a larger throat area. When the flow rate of the working fluid is small, the intake flow channel A can be aligned with the nozzle flow channel 3b with a smaller throat area. In this way, by matching the first portion of the intake ring 4 and the second portion of the intake ring 5 with the nozzle ring 3, the throat area of ​​the nozzle flow channel 3b can be matched with the flow rate of the working fluid, so that the variable intake radial flow turbine can adapt to working conditions under different flow rates.

[0041] In addition, the sum of the extension angle of the first air inlet portion 4a in the circumferential direction of the first air inlet ring 4 and the extension angle of the second air inlet portion 5a in the circumferential direction of the second air inlet ring 5 can be less than or equal to 360°. The first air inlet ring 4 can be rotated relative to the second air inlet ring 5, so that the first air inlet portion 4a and the second air inlet portion 5a are staggered in the radial direction of the impeller 2. In this way, the air inlet passage 1b and the working chamber 1a can be separated by the first air inlet ring 4 and the second air inlet ring 5, so that the working medium in the air inlet passage 1b will not enter the working chamber 1a.

[0042] This application has at least the following advantages:

[0043] (i) By making the first partial intake ring 4 cooperate with the second partial intake ring 5, the cross-sectional area of ​​the intake flow channel A can be adjusted by the size of the overlapping portion of the first intake portion 4a and the second intake portion 5a, so as to match the flow rate of the working medium, so that the variable intake radial flow turbine can adapt to working conditions under different flow rates.

[0044] (ii) By matching the first partial intake ring 4 and the second partial intake ring 5 with the nozzle ring 3, the intake passage A can be aligned with the nozzle flow channel 3b having a specific throat area, so that the throat area of ​​the nozzle flow channel 3b can be matched with the flow rate of the working medium, so that the variable intake radial flow turbine can adapt to operating conditions under different flow rates.

[0045] It should be understood that the above embodiments are merely exemplary and are not intended to limit the present application. Those skilled in the art may make various modifications and changes to the above embodiments under the guidance of the present application without departing from the scope of the present application.

[0046] It should be understood that the first partial intake ring 4 and the second partial intake ring 5 are not limited to being both pivotally connected to the turbine housing 1. For example, one of the first partial intake ring 4 and the second partial intake ring 5 may be fixed to the turbine housing 1, and the other of the first partial intake ring 4 and the second partial intake ring 5 may be pivotally connected to the turbine housing 1.

[0047] It should be understood that the first air inlet portion 4a is not limited to extending continuously in the circumferential direction of the first partial air inlet ring 4, and the second air inlet portion 5a is not limited to extending continuously in the circumferential direction of the second partial air inlet ring 5. For example, the first air inlet portion 4a may extend discontinuously in the circumferential direction of the first partial air inlet ring 4, so that the first air inlet portion 4a is divided into a plurality of sub-first air inlet portions. The second air inlet portion 5a may extend discontinuously in the circumferential direction of the second partial air inlet ring 5, so that the second air inlet portion 5a is divided into a plurality of sub-second air inlet portions. Further, the number of sub-first air inlets and sub-second air inlets may be the same as the number of nozzle flow channels 3b. The first partial air inlet ring 4 may be fixed to the nozzle ring 3, and one sub-first air inlet portion may be aligned with one nozzle flow channel 3b. Alternatively, the second partial air inlet ring 5 may be fixed to the nozzle ring 3, and one second air inlet portion may be aligned with one nozzle flow channel 3b.

[0048] It should be understood that the first air inlet portion 4a and the second air inlet portion 5a are not limited to the manner shown in the embodiment. For example, the first air inlet portion 4a and the second air inlet portion 5a may be through holes penetrating in the radial direction.

[0049] It should be understood that at least two of the plurality of nozzle vanes 3a are not limited to having different vane outlet angles. For example, at least two of the plurality of nozzle vanes 3a may have different vane inlet angles, cascade densities, or vane profiles.

Claims

1. A variable inlet radial flow turbine, characterized in that: include: A turbine shell (1), wherein the turbine shell (1) defines a working chamber (1a), an inlet flow passage (1b) and an exhaust flow passage (1c); An impeller (2), the impeller (2) being arranged in the working chamber (1a); A nozzle ring (3), the nozzle ring (3) comprising a plurality of nozzle blades (3a), the plurality of nozzle blades (3a) being spaced apart in the circumferential direction of the nozzle ring (3), a nozzle flow channel (3b) being formed between adjacent nozzle blades (3a), the nozzle ring (3) being sleeved on the radially outer side of the impeller (2), the nozzle ring (3) being formed as a whole with the turbine shell (1), the plurality of nozzle flow channels (3b) comprising a first nozzle flow channel and a second nozzle flow channel, the first nozzle flow channel and the second nozzle flow channel having different throat areas; A first partial intake ring (4), comprising a first intake portion (4a), the first intake portion (4a) communicating with the radial inner side of the first partial intake ring (4) and the radial outer side of the first partial intake ring (4), the first intake portion (4a) extending non-circumferentially in the circumferential direction of the first partial intake ring (4), the first partial intake ring (4) being sleeved on the radial outer side of the impeller (2) and being pivotally connected to the turbine shell (1), the nozzle ring (3) being located between the impeller (2) and the first partial intake ring (4), and at least a portion of the plurality of nozzle flow channels (3b) communicating with the first intake portion (4a) and the impeller (2); and The second partial intake ring (5) comprises a second intake portion (5a), wherein the second intake portion (5a) communicates with the radial inner side of the second partial intake ring (5) and the radial outer side of the second partial intake ring (5), and the second intake portion (5a) extends non-entirely in the circumferential direction of the second partial intake ring (5). The second partial intake ring (5) is sleeved on the radial outer side of the first partial intake ring (4) and is pivotally connected to the turbine shell (1), so that the second partial intake ring (5) and the first partial intake ring (4) can rotate relative to each other, and the second intake portion (5a) and the first intake portion (4a) can overlap in the radial direction. The first air inlet portion (4a) extends continuously in the circumferential direction of the first partial air inlet ring (4), and the second air inlet portion (5a) extends continuously in the circumferential direction of the second partial air inlet ring (5). The sum of the extension angles of the first air inlet portion (4a) in the circumferential direction of the first partial air inlet ring (4) and the extension angles of the second air inlet portion (5a) in the circumferential direction of the second partial air inlet ring (5) is less than or equal to 360°, so that the first air inlet portion (4a) and the second air inlet portion (5a) can be staggered in the radial direction of the impeller (2).

2. The variable inlet radial flow turbine according to claim 1, characterized in that: The extension angle of the first air inlet portion (4a) in the circumferential direction of the first partial air inlet ring (4) is 180° to 270°, or The extension angle of the second air inlet portion (5a) in the circumferential direction of the second partial air inlet ring (5) is 180° to 270°.

3. The variable inlet radial flow turbine according to claim 1 or 2, characterized in that: At least two of the plurality of nozzle vanes (3a) have different vane outlet angles.

4. The variable inlet radial flow turbine according to claim 1 or 2, characterized in that: At least two of the plurality of nozzle vanes (3a) have different vane inlet angles.

5. The variable inlet radial flow turbine according to claim 1 or 2, characterized in that: At least two of the plurality of nozzle vanes (3a) have different cascade densities.

6. The variable inlet radial flow turbine according to claim 1 or 2, characterized in that: At least two of the plurality of nozzle vanes (3a) have different vane profiles.

Images