Variable inlet axial flow turbine

Abstract

A variable-intake axial-flow turbine is provided. The variable-intake axial-flow turbine includes an impeller, a first-part inlet disc, and a second-part inlet disc. The first-part inlet disc includes a first inlet portion. The first inlet portion connects one axial side of the first-part inlet disc and the other axial side of the first-part inlet disc, and extends non-entirely in the circumferential direction of the first-part inlet disc. The second-part inlet disc includes a second inlet portion. The second inlet portion connects one axial side of the second-part inlet disc and the other axial side of the second-part inlet disc, and extends non-entirely in the circumferential direction of the second-part inlet disc. The second-part inlet disc and the first-part inlet disc can rotate relative to each other, so that the second inlet portion and the first inlet portion can overlap in the axial direction. In this way, by making the first-part inlet disc and the second-part inlet disc cooperate with each other, the variable-intake axial-flow turbine can adapt to working conditions under different flow rates, thereby improving the performance and efficiency of the turbine under different working conditions.

Description

Technical Field

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

[0002] Axial flow turbines are widely used in energy and power devices such as gas turbines, steam turbines and aircraft engines, and have the advantages of high power density and high efficiency. Partial intake axial flow turbines can be used in thermal cycle systems and devices such as supercritical carbon dioxide cycle power generation systems, organic working fluid Rankine cycle power generation systems, micro gas turbines and refrigeration cycle systems. By adopting a partial intake design, the impeller blades can have a higher height, thereby significantly improving the efficiency of micro axial flow turbines.

[0003] The air intake has a great influence on the performance of partial intake axial flow turbines. However, due to structural limitations, existing partial intake axial 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 axial 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 axial flow turbine as follows, which comprises: an impeller; a first partial intake disk, which comprises a first intake portion, the first intake portion connecting one axial side of the first partial intake disk and the other axial side of the first partial intake disk, the first intake portion extending non-circumferentially in the circumferential direction of the first partial intake disk, the first partial intake disk being located on one axial side of the impeller and being coaxially arranged with the impeller; and a second partial intake disk, which comprises a second intake portion, the second intake portion connecting one axial side of the second partial intake disk and the other axial side of the second partial intake disk, the second intake portion extending non-circumferentially in the circumferential direction of the second partial intake disk, the second partial intake disk being located on one axial side of the impeller and being coaxially arranged with the impeller, the first partial intake disk being located between the second partial intake disk and the impeller, the second partial intake disk and the first partial intake disk being able to rotate relative to each other, so that the second intake portion and the first intake portion can overlap in the axial direction.

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

[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 disk and an extension angle of the second air inlet portion in the circumferential direction of the second partial air inlet disk 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 disk 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 disk is 180° to 270°.

[0010] In another optional scheme, it also includes a nozzle, which includes a nozzle disk and a plurality of nozzle blades, the plurality of nozzle blades are arranged on the outer peripheral surface of the nozzle disk and are spaced apart in the circumferential direction of the nozzle disk, and a nozzle flow channel is formed between adjacent nozzle blades, the nozzle is coaxially arranged with the impeller, the nozzle is located between the impeller and the first part of the air intake disk, and at least a part of the plurality of nozzle flow channels connects the first air 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 air intake disk and the nozzle 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 axial flow turbine of the present application, by making the first part of the intake disc and the second part of the intake disc 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 medium, so that the variable intake axial flow turbine can adapt to the operating conditions under different flow rates, thereby improving the performance and efficiency of the turbine under different operating conditions. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

[0019] Figure 3 Shows Figure 1 Exploded view of a variable inlet axial turbine in which the housing is shown in section and the hatching is omitted.

[0020] Figure 4 Shows Figure 1 Front view of the inlet disc of the first part of the variable inlet axial turbine.

[0021] Figure 5 Shows Figure 1 Front view of the second part of the intake disc of the variable inlet axial turbine.

[0022] Figure 6 Shows Figure 1 Schematic diagram of the intake duct of the variable inlet axial flow turbine.

[0023] Description of Reference Numerals

[0024] 1 housing; 1a working chamber; 1b air inlet chamber; 1c exhaust flow channel;

[0025] 2 impeller; 2a impeller blade;

[0026] 3 nozzle; 3a nozzle disk; 3b nozzle blade; 3c nozzle flow channel;

[0027] 4 first part air intake disc; 4a first air intake portion;

[0028] 5 second air intake plate; 5a second air intake portion;

[0029] AIntake air duct. DETAILED DESCRIPTION

[0030] 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.

[0031] 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.

[0032] Figures 1 to 6A variable intake axial flow turbine according to an embodiment of the present application is shown, and the variable intake axial flow turbine may include a housing 1 , an impeller 2 , a nozzle 3 , a first partial intake disk 4 , and a second partial intake disk 5 .

[0033] The housing 1 may define a working chamber 1a, an air inlet chamber 1b, and an exhaust flow channel 1c. The working chamber 1a may be cylindrical. The air inlet chamber 1b may be located at one end of the working chamber 1a and extend along the central axis of the working chamber 1a. The exhaust flow channel 1c may be located at the other end of the working chamber 1a and extend in the radial direction of the working chamber 1a. The air inlet chamber 1b and the exhaust flow channel 1c may communicate with the working chamber 1a and the outside of the housing 1.

[0034] The impeller 2 may include a plurality of impeller blades 2a, which may be disposed on the outer circumferential surface of the impeller 2 and arranged uniformly 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.

[0035] The nozzle 3 may include a nozzle disk 3a and a plurality of nozzle blades 3b. The plurality of nozzle blades 3b may be disposed on the outer peripheral surface of the nozzle disk 3a and uniformly arranged in the circumferential direction of the nozzle disk 3a. The nozzle blades 3b may extend in the axial direction of the nozzle disk 3a while extending in the circumferential direction of the nozzle disk 3a. A nozzle flow channel 3c may be formed between adjacent nozzle blades 3b. The nozzle flow channel 3c may gradually contract from one axial side of the nozzle disk 3a (the side where the first part of the air intake disk 4 is located) to the other axial side of the nozzle disk 3a (the side where the impeller 2 is located), so that the cross-sectional area of ​​the nozzle flow channel 3c gradually decreases from the upstream of the working medium flow direction to the downstream of the working medium flow direction. The nozzle 3 may be coaxially arranged with the impeller 2 and fixed to the housing 1, and the outlet of the nozzle flow channel 3c may be aligned with the impeller blades 2a.

[0036] Further, the plurality of nozzle flow channels 3c 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 3b may have different blade outlet angles. For example, at least one nozzle blade 3b defining the first nozzle flow channel and at least one nozzle blade 3b defining the second nozzle flow channel may have different blade outlet angles.

[0037] The first partial air inlet disc 4 may be provided with a first air inlet portion 4a, and the first air inlet portion 4a may connect one axial side and the other axial side of the first partial air inlet disc 4. The first air inlet portion 4a may extend continuously and non-entirely in the circumferential direction of the first partial air inlet disc 4. For example, the extension angle of the first air inlet portion 4a (the central angle corresponding to the extension range) may be 180° to 270°. The first partial air inlet disc 4 may be located on one axial side of the impeller 2 and arranged coaxially with the impeller 2, and the nozzle 3 may be located between the first partial air inlet disc 4 and the impeller 2. The first partial air inlet disc 4 may be pivotally connected to the housing 1 so that the first partial air inlet disc 4 can rotate relative to the nozzle 3.

[0038] The second partial air inlet disc 5 may be provided with a second air inlet portion 5a, and the second air inlet portion 5a may connect one axial side and the other axial side of the second partial air inlet disc 5. The second air inlet portion 5a may extend continuously and non-entirely in the circumferential direction of the second partial air inlet disc 5. For example, the extension angle of the second air inlet portion 5a may be 180° to 270°. The second partial air inlet disc 5 may be located on one axial side of the impeller 2 and arranged coaxially with the impeller 2, and the first partial air inlet disc 4 may be located between the second partial air inlet disc 5 and the nozzle 3. The second partial air inlet disc 5 may be pivotally connected to the housing 1 so that the second partial air inlet disc 5 can rotate relative to the first partial air inlet disc 4.

[0039] Refer to the following Figures 4 to 6 The working principle of variable inlet axial flow turbine is introduced.

[0040] Driven by an actuator (not shown in the figure), the first air intake disc 4 can rotate relative to the second air intake disc 5, so that the first air intake portion 4a and the second air intake portion 5a overlap in the axial direction. The overlapping parts of the first air intake portion 4a and the second air intake portion 5a can be jointly formed into an intake flow channel A, and the working fluid can enter the nozzle flow channel 3c through the intake cavity 1b and the intake flow channel A in sequence. The nozzle flow channel 3c can convert the pressure energy of the working fluid into kinetic energy, so that the working fluid leaving the nozzle flow channel 3c can impact the impeller blades 2a at a higher speed, thereby driving the impeller 2 to rotate. Afterwards, the working fluid can leave the housing 1 from the exhaust flow channel 1c.

[0041] When the flow rate of the working medium is large, the first air intake disc 4 can be rotated relative to the second air intake disc 5 to increase the cross-sectional area of ​​the inlet flow channel A. When the flow rate of the working medium is small, the first air intake disc 4 can be rotated relative to the second air intake disc 5 to reduce the cross-sectional area of ​​the inlet flow channel A. In this way, by making the first air intake disc 4 and the second air intake disc 5 cooperate with each other, the cross-sectional area of ​​the inlet flow channel A can be adjusted by the size of the overlapping part of the first air intake part 4a and the second air intake part 5a, so as to match the flow rate of the working medium, so that the variable air intake axial flow turbine can adapt to the working conditions under different flow rates, thereby improving the performance and efficiency of the turbine under different working conditions.

[0042] Furthermore, the first air intake disc 4 and the second air intake disc 5 can be rotated so that the intake flow channel A is aligned with one or more specific nozzle flow channels 3c. When the flow rate of the working medium is large, the intake flow channel A can be aligned with the nozzle flow channel 3c with a larger throat area. When the flow rate of the working medium is small, the intake flow channel A can be aligned with the nozzle flow channel 3c with a smaller throat area. In this way, by matching the first air intake disc 4 and the second air intake disc 5 with the nozzle 3, the throat area of ​​the nozzle flow channel 3c can be matched with the flow rate of the working medium, so that the variable intake axial flow turbine can adapt to working conditions under different flow rates.

[0043] This application has at least the following advantages:

[0044] (i) By making the first partial air intake disk 4 cooperate with the second partial air intake disk 5, the cross-sectional area of ​​the intake flow channel A can be adjusted by the size of the overlapping portion of the first air intake portion 4a and the second air intake portion 5a, so as to match the flow rate of the working medium, so that the variable intake axial flow turbine can adapt to working conditions under different flow rates.

[0045] (ii) By matching the first partial air intake disk 4 and the second partial air intake disk 5 with the nozzle 3, the air intake passage A can be aligned with the nozzle flow channel 3c having a specific throat area, so that the throat area of ​​the nozzle flow channel 3c can be matched with the flow rate of the working medium, so that the variable intake axial flow turbine can adapt to operating conditions under different flow rates.

[0046] 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.

[0047] It should be understood that the first partial air inlet disk 4 and the second partial air inlet disk 5 are not limited to being both pivotally connected to the housing 1. For example, one of the first partial air inlet disk 4 and the second partial air inlet disk 5 may be fixed to the housing 1, and the other of the first partial air inlet disk 4 and the second partial air inlet disk 5 may be pivotally connected to the housing 1.

[0048] 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 disk 4, and the second air inlet portion 5a is not limited to extending continuously in the circumferential direction of the second partial air inlet disk 5. For example, the first air inlet portion 4a may extend discontinuously in the circumferential direction of the first partial air inlet disk 4, so that the first air inlet portion 4a is divided into a plurality of first sub-air inlets. The second air inlet portion 5a may extend discontinuously in the circumferential direction of the second partial air inlet disk 5, so that the second air inlet portion 5a is divided into a plurality of second sub-air inlets. Further, the number of first sub-air inlets and second sub-air inlets may be the same as the number of nozzle flow channels 3c. The first partial air inlet disk 4 may be fixed to the nozzle 3, and one first sub-air inlet portion may be aligned with one nozzle flow channel 3c. Alternatively, the second partial air inlet disk 5 may be fixed to the nozzle 3, and one second sub-air inlet portion may be aligned with one nozzle flow channel 3c.

[0049] 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.

[0050] It should be understood that at least two of the plurality of nozzle vanes 3b are not limited to having different vane outlet angles. For example, at least two of the plurality of nozzle vanes 3b may have different vane inlet angles, cascade densities, or vane profiles.

[0051] It should be understood that the extension angle of the first air inlet portion 4a in the circumferential direction of the first air inlet disk 4 and the extension angle of the second air inlet portion 5a in the circumferential direction of the second air inlet disk 5 are not limited to the angles shown in the embodiment. For example, the sum of the extension angle of the first air inlet portion 4a in the circumferential direction of the first air inlet disk 4 and the extension angle of the second air inlet portion 5a in the circumferential direction of the second air inlet disk 5 can be less than or equal to 360°. The first air inlet disk 4 can be rotated relative to the second air inlet disk 5, so that the first air inlet portion 4a and the second air inlet portion 5a are staggered in the axial direction of the impeller 2. In this way, the air inlet chamber 1b and the working chamber 1a can be separated by the first air inlet disk 4 and the second air inlet disk 5, so that the working medium in the air inlet chamber 1b will not enter the nozzle flow channel 3c.

Claims

1. A variable intake axial flow turbine, characterized in that: include: Housing (1); An impeller (2) disposed in the housing (1); A first partial air intake disc (4), comprising a first air intake portion (4a), wherein the first air intake portion (4a) is connected to one axial side of the first partial air intake disc (4) and the other axial side of the first partial air intake disc (4), and the first air intake portion (4a) extends non-entirely in the circumferential direction of the first partial air intake disc (4); the first partial air intake disc (4) is located on one axial side of the impeller (2) and is arranged coaxially with the impeller (2); a second partial air inlet disc (5), comprising a second air inlet portion (5a), the second air inlet portion (5a) communicating with one axial side of the second partial air inlet disc (5) and the other axial side of the second partial air inlet disc (5), the second air inlet portion (5a) extending non-entirely in the circumferential direction of the second partial air inlet disc (5), the second partial air inlet disc (5) being located on one axial side of the impeller (2) and being coaxially arranged with the impeller (2), the first partial air inlet disc (4) being located between the second partial air inlet disc (5) and the impeller (2), the second partial air inlet disc (5) being pivotally connected to the housing (1) and being relatively rotatable with the first partial air inlet disc (4), so that the second air inlet portion (5a) and the first air inlet portion (4a) can overlap in the axial direction; and A nozzle (3), comprising a nozzle disk (3a) and a plurality of nozzle blades (3b), wherein the plurality of nozzle blades (3b) are arranged on the outer peripheral surface of the nozzle disk (3a) and are spaced apart in the circumferential direction of the nozzle disk (3a), and a nozzle flow channel (3c) is formed between adjacent nozzle blades (3b), the nozzle (3) is coaxially arranged with the impeller (2), the nozzle (3) is located between the impeller (2) and the first partial air intake disk (4), at least a portion of the plurality of nozzle flow channels (3c) communicates the first air intake portion (4a) with the impeller (2), the plurality of nozzle flow channels (3c) 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, the first partial air intake disk (4) is pivotally connected to the housing (1), and is relatively rotatable with the nozzle (3), wherein The first air inlet portion (4a) extends continuously in the circumferential direction of the first partial air inlet disk (4), and the second air inlet portion (5a) extends continuously in the circumferential direction of the second partial air inlet disk (5). The sum of the extension angles of the first air inlet portion (4a) in the circumferential direction of the first partial air inlet disk (4) and the extension angles of the second air inlet portion (5a) in the circumferential direction of the second partial air inlet disk (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 axial direction of the impeller (2).

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

3. The variable intake axial flow turbine according to claim 1, characterized in that: At least two of the plurality of nozzle vanes (3b) have different vane inlet angles.

4. The variable intake axial flow turbine according to claim 1, characterized in that: At least two of the plurality of nozzle vanes (3b) have different cascade densities.

5. The variable intake axial flow turbine according to claim 1, characterized in that: At least two of the plurality of nozzle vanes (3b) have different vane profiles.

Images