CN115559787A

CN115559787A - Turbo expander, turbo expansion generator and vehicle

Info

Publication number: CN115559787A
Application number: CN202211233555.1A
Authority: CN
Inventors: 巫灵丽; 张学峰; 钟明桥; 李清林; 孙逍遥; 张鹍
Original assignee: Shijia Toubo Chengdu Technology Co ltd
Current assignee: Shijia Toubo Chengdu Technology Co ltd
Priority date: 2022-10-10
Filing date: 2022-10-10
Publication date: 2023-01-03

Abstract

The invention provides a turboexpander, a turboexpander generator and a vehicle. Wherein the turboexpander comprises a volute, a first impeller and a second impeller. The volute is provided with a chamber, an air inlet volute, a first exhaust port and a second exhaust port, the air inlet volute is communicated with the chamber, the chamber comprises a first exhaust cavity and a second exhaust cavity which are arranged along a preset direction, and the air inlet volute is located between at least one part of the first exhaust cavity and at least one part of the second exhaust cavity in the preset direction; the first impeller and the second impeller are disposed back-to-back within the chamber, and an extending direction of a rotational axis of each of the first impeller and the second impeller coincides with the preset direction. Therefore, the turboexpander of the present invention can maintain a long service life in a high-speed rotation state.

Description

Turbo expander, turbo expansion generator and vehicle

Technical Field

The invention relates to the technical field of power generation of a turboexpander, in particular to a turboexpander, a turboexpander generator and a vehicle.

Background

An Organic Rankine Cycle (ORC) is a rankine cycle which takes low-boiling-point organic matters such as refrigerants and alkanes as working media, and can convert internal energy in working medium gas into mechanical energy and finally output the mechanical energy as electric energy. The expander is a core component in the ORC system, and it uses the internal energy of the gas to output mechanical work to the outside, which has an important influence on the performance of the whole system. The centripetal turbo expander is one of the expanders, has the characteristics of large single-stage enthalpy drop and high expansion ratio, has high efficiency under the condition of low flow rate, and is very suitable for recovering waste heat of mobile devices such as an internal combustion engine and the like.

In the low power vehicle ORC turbo expander, the impeller needs to be capable of rotating at high speed under the requirement of high expansion ratio and rotation speed, so that large axial force is generated to influence the service life of the bearing and the expander. Therefore, the design and manufacture of the turboexpander with high speed and high expansion ratio are difficult.

Disclosure of Invention

The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. To this end, embodiments of the present invention provide a turboexpander in which axial forces can be cancelled out.

Embodiments of the present invention also provide a turboexpander generator.

The embodiment of the invention also provides a vehicle.

A turbo expander of an embodiment of the present invention includes:

the volute comprises a chamber, an air inlet volute, a first exhaust port and a second exhaust port, wherein the air inlet volute is communicated with the chamber and comprises a first exhaust cavity and a second exhaust cavity which are arranged along a preset direction, the first exhaust port is arranged on the peripheral wall surface of the first exhaust cavity, the second exhaust port is arranged on the peripheral wall surface of the second exhaust cavity, and the air inlet volute is positioned between at least one part of the first exhaust cavity and at least one part of the second exhaust cavity in the preset direction; and

the first impeller and the second impeller are arranged in the cavity back to back, the first impeller is located in the first exhaust cavity, the second impeller is located in the second exhaust cavity, and the extending direction of the rotation axis of each of the first impeller and the second impeller is consistent with the preset direction.

According to the turbo expander provided by the embodiment of the invention, the first impeller and the second impeller are arranged back to back, opposite axial forces are generated when the working medium gas drives the first impeller and the second impeller to rotate, and the two opposite axial forces are mutually offset, so that the axial stress of a main shaft where the impellers are located is reduced, and the long service life can be kept in a high-speed rotating state.

In some embodiments, the turbine expander of embodiments of the present invention further comprises a nozzle ring located within the chamber, the nozzle ring being located outside each of the first and second impellers, the nozzle ring being located between the first and second impellers in the predetermined direction.

In some embodiments, the nozzle ring includes a nozzle disk, a first guide vane and a second guide vane, the nozzle disk has a first surface and a second surface that are arranged oppositely in the preset direction, the first guide vane is arranged on the first surface, the second guide vane is arranged on the second surface, wherein the first guide vane has a first end surface and a second end surface that are opposite in the preset direction, the first end surface is attached to the first surface, the second end surface is attached to the wall surface of the cavity, the second guide vane has a third end surface and a fourth end surface that are opposite in the preset direction, the third end surface is attached to the second surface, and the fourth end surface is attached to the wall surface of the cavity.

In some embodiments, the nozzle disk is annular and has a receiving hole, each of the first and second impellers has a disk and a blade set, the nozzle disk is disposed around the disk, at least a portion of the disk is located in the receiving hole, the blade set is disposed on the disk, wherein the first and second impellers are symmetrically disposed with respect to the nozzle disk, and the first and second vanes are symmetrically disposed with respect to the nozzle disk.

A turboexpander generator according to an embodiment of the present invention includes:

a housing having a receiving cavity;

the main shaft is rotatably arranged in the accommodating cavity of the shell;

the stator is arranged in the accommodating cavity and sleeved on the main shaft; and

a turbo expander, the turbo expander being the turbo expander of any of the above embodiments, a volute of the turbo expander being provided on the housing, wherein a first portion of the main shaft protrudes out of the accommodation chamber and into the chamber, each of the first and second impellers being provided on the first portion of the main shaft.

According to the embodiment of the invention, the main shaft of the turbine expansion generator bears small axial force, the rotating speed of the main shaft is high, and the internal potential energy of the working medium gas can be efficiently converted into electric energy.

In some embodiments, the housing is provided with a cooling channel, which is annular or spiral.

In some embodiments, the housing is provided with a leakage port, the leakage port is communicated with the accommodating cavity, the turbine expansion generator further comprises a labyrinth seal, the labyrinth seal is sleeved on the main shaft, and the inner circumferential surface of the labyrinth seal is spaced from the main shaft.

In some embodiments, the housing has a first end and a second end opposite to each other in the axial direction of the main shaft, the first end has a through hole, the first part of the main shaft extends out of the accommodating cavity through the through hole, the volute is arranged on the first end, and at least one part of the labyrinth seal is arranged in the through hole.

In some embodiments, at least one of the circumferential surface of the main shaft and the inner circumferential surface of the stator is provided with a groove extending in the axial direction of the main shaft.

A vehicle according to an embodiment of the present invention includes the turboexpander generator according to any one of the above embodiments.

According to the vehicle provided by the embodiment of the invention, the waste heat of the organic Rankine cycle of the internal combustion engine can be efficiently recycled.

Drawings

FIG. 1 is a schematic structural view of a turboexpander generator according to an embodiment of the present invention;

FIG. 2 (a) is a schematic cross-sectional view of a turboexpander generator according to an embodiment of the present invention;

FIG. 2 (b) is a partial enlarged view of A in FIG. 2 (a);

FIG. 3 is a schematic block diagram of a turboexpander according to an embodiment of the present invention;

FIG. 4 is a schematic view of a partial structure of a turboexpander according to an embodiment of the present invention;

FIG. 5 is a schematic structural view of an impeller and nozzle ring in accordance with an embodiment of the present invention;

FIG. 6 is a schematic view of the installed position of a leak valve according to an embodiment of the present invention;

FIG. 7 is a flow diagram of working medium gas of an embodiment of the present invention.

Reference numerals:

a turbo-expansion generator 100;

a housing 10, a housing cavity 101, a first end 102, a second end 103;

cooling channel 11, joint 111, sealing sleeve 112, cooling groove 113;

leak port 12, leak valve 121;

a labyrinth seal 13, a labyrinth ring 131;

a stator 20;

a main shaft 30;

a radial air bearing 41, a thrust air bearing 42;

a turbo-expander 50;

the volute 51, the left volute 5101, the right volute 5102, the chamber 510, the air inlet scroll 511, the first exhaust port 512, the second exhaust port 513, the first exhaust cavity 514 and the second exhaust cavity 515;

a first impeller 521, a second impeller 522, a wheel disc 523, a single blade 524;

the nozzle ring 53, the nozzle disk 531, the first surface 5311, the second surface 5312, the first guide vane 532, the second end face 5321, the second guide vane 533, the fourth end face 5331.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present invention and should not be construed as limiting the present invention.

As shown in fig. 1 to 5, the turbo-expander 50 according to the embodiment of the present invention includes a scroll 51, a first impeller 521 and a second impeller 522. The scroll 51 has a chamber 510, an intake scroll 511, a first exhaust port 512, and a second exhaust port 513, the intake scroll 511 and the chamber 510 are communicated, the chamber 510 includes a first exhaust chamber 514 and a second exhaust chamber 515 arranged in a predetermined direction, the first exhaust port 512 is provided on a peripheral wall surface of the first exhaust chamber 514, and the second exhaust port 513 is provided on a peripheral wall surface of the second exhaust chamber 515. Wherein the intake volute 511 is located between at least a portion of the first discharge chamber 514 and at least a portion of the second discharge chamber 515 in the predetermined direction. First and

second impellers

521 and 522 are provided back to back in the chamber 510, the first impeller 521 is located in the first exhaust chamber 514, the second impeller 522 is located in the second exhaust chamber 515, and an extending direction of a rotational axis of each of the first and

second impellers

521 and 522 coincides with a preset direction.

In other words, the first exhaust chamber 514 and the second exhaust chamber 515 are aligned in the extending direction of the rotation axis of the first impeller 521.

According to the turbo-expander 50 provided by the embodiment of the invention, the first impeller 521 and the second impeller 522 are arranged back to back, so that the directions of the axial forces borne by the first impeller 521 and the second impeller 522 which rotate under the action of the working medium gas are opposite, the two opposite axial forces are mutually offset, and the main shaft where the first impeller 521 and the second impeller 522 are located does not bear the axial force, so that the service life of the turbo-expander in a high-speed rotating operation state can be ensured.

In the turbo expander of the embodiment of the present invention, the working medium gas enters the first exhaust cavity 514 and the second exhaust cavity 515 through the air inlet scroll 511, in the flowing process of the working medium gas, the working medium gas expands to do work to drive the first impeller 521 and the second impeller 522 to rotate, the working medium gas in the first exhaust cavity 514 is exhausted through the first exhaust port 512, and the working medium gas in the second exhaust cavity 515 is exhausted through the second exhaust port 513.

For example, referring to fig. 2 (a), the axial direction of the first impeller 521 is the same as the left-right direction, the volute 51 includes a left volute 5101 and a right volute 5102, the left volute 5101 has a first exhaust chamber 514, a first exhaust port 512 and a left side wall surface of the intake scroll 511, the right volute 5102 has a second exhaust chamber 515, a second exhaust port 513 and a right side wall surface of the intake scroll 511, the left volute 5101 and the right volute 5102 are symmetrically arranged, the left volute 5101 and the right volute 5102 are fixedly connected by bolts, and the left side wall surface of the intake scroll 511 on the left volute 5101 and the right side wall surface of the intake scroll 511 on the right volute 5102 are combined to form the intake scroll 511.

In some embodiments, the turboexpander 50 of embodiments of the present invention further comprises a nozzle ring 53, the nozzle ring 53 being located within the chamber 510, the nozzle ring 53 being located outboard of each of the first and

second impellers

521, 522, the nozzle ring 53 being located between at least a portion of the first impeller 521 and at least a portion of the second impeller 522 in the predetermined direction. The working medium gas flows through the nozzle ring 53 from the air inlet volute 511, the nozzle ring 53 divides the working medium gas, so that a part of the working medium gas flows to the first impeller 521 to drive the first impeller 521 to rotate, and the other part of the working medium gas flows to the second impeller 522 to drive the second impeller 522 to rotate.

In some embodiments, the nozzle ring 53 includes a nozzle disk 531, a first guide vane 532, and a second guide vane 533, the nozzle disk 531 having a first surface 5311 and a second surface 5312 disposed opposite each other in the predetermined direction, the first guide vane 532 disposed on the first surface 5311, the second guide vane 533 disposed on the second surface 5312. The first guide vane 532 has a first end face and a second end face 5321 opposite to each other in the predetermined direction, the first end face is attached to the first surface 5311, the second end face 5321 is attached to the wall surface of the cavity 510, the second guide vane 533 has a third end face and a fourth end face 5331 opposite to each other in the predetermined direction, the third end face is attached to the second surface 5312, and the fourth end face 5331 is attached to the wall surface of the cavity 510. The nozzle ring 53 is fastened and fixed with the volute 51, and divides the working medium gas flowing through the nozzle ring 53 equally and guides the working medium gas to the first impeller 521 and the second impeller 522, so that the quantities of the working medium gas borne by the first impeller 521 and the second impeller 522 are the same.

Referring to fig. 5, the number of the first guide vanes 532 is plural, the plural first guide vanes 532 are uniformly provided on the first surface 5311 of the nozzle disk 531 in the circumferential direction of the nozzle disk 531, the number of the second guide vanes 533 is plural, and the plural second guide vanes 533 are uniformly provided on the second surface 5312 of the nozzle disk 531 in the circumferential direction of the nozzle disk 531. The first and second pluralities of

vanes

532, 533 are symmetrically disposed in a first plane that is located on a midperpendicular to a thickness dimension of nozzle tray 531 and that is parallel to first and

second surfaces

5311, 5312 of nozzle tray 5351. The leading edges of the first guide vanes 532 and the leading edges of the second guide vanes 533 are located at one end away from the center of the nozzle tray 531, and the trailing edges of the first guide vanes 532 and the trailing edges of the second guide vanes 533 are located at one end close to the center of the nozzle tray 531.

The blade profiles of the first guide vane 532 and the second guide vane 533 can adopt NACA four-digit airfoil profiles, and the aerodynamic performance is better.

In some embodiments, the nozzle disc 531 is annular and has a receiving hole, each of the first and

second impellers

521 and 522 has a wheel disc 523 around which the nozzle disc 531 is disposed, and a blade group disposed on the wheel disc 523 in which at least a portion of the wheel disc 523 is located. The first impeller 521 and the second impeller 522 are symmetrically arranged relative to the nozzle plate 531, so that the first impeller 521 and the second impeller 522 generate axial forces with the same magnitude when bearing the same amount of working medium gas, and the two axial forces have opposite directions and can be offset with each other, so that the main shafts of the first impeller 521 and the second impeller 522 do not bear the axial force generated by the rotation of the impellers driven by the working medium gas.

Specifically, the front edge of the single blade 524 of one blade group is opposite to the front edge of the single blade 524 of the other blade group, and the two blade groups make the first impeller 521 and the second impeller 522 generate the same rotation motion under the driving of the working medium gas. The leading edge of the single blade 524 of the blade group of the first impeller 521, i.e., the single blade 524, is close to the end of the trailing edge of the first vane 532, and the leading edge of the single blade 524 of the blade group of the second impeller 522, i.e., the single blade, is close to the end of the trailing edge of the second vane 533. The working medium gas which is divided and expanded by the nozzle ring 53 enters the blade group of the first impeller 521 through the front end of the single blade of the first impeller 521 to drive the first impeller 521 to rotate, and the front end of the single blade of the second impeller 522 enters the blade group of the second impeller 522 to drive the second impeller 522 to rotate. When the working medium gas drives the first impeller 521 and the second impeller 522 to rotate, axial thrust is also generated on the first impeller 521 and the second impeller 522 respectively, the directions of the axial thrust of the first impeller 521 and the axial thrust of the second impeller 522 are opposite, and in the direction shown in fig. 2, the axial force on the first impeller 521 is leftward, and the axial force on the second impeller 522 is rightward.

The symmetrical arrangement of the first and

second guide vanes

532, 533 relative to the nozzle ring 53 enables the nozzle ring 53 to distribute the working gas evenly to the first and

second impellers

521, 522 to ensure that the first and

second impellers

521, 522 receive the same amount of working gas. The first impeller 521 and the second impeller 522 are symmetrically arranged relative to the nozzle ring 53 to ensure that the axial forces generated by the working medium gas borne by the first impeller 521 and the second impeller 522 are the same in magnitude and the same in rotation speed, so that when the main shafts of the first impeller 521 and the second impeller 522 output the rotation power, two axial thrusts in opposite directions are mutually offset, and the axial thrust borne by the wheel disc 523 is greatly reduced. Compared with the structure that a single blade group is arranged on the wheel disc in the related art, the axial thrust borne by the wheel disc 523 can be reduced when the same rotating speed is output, so that the turboexpander for the turbine expander of the embodiment of the invention has the advantage of long service life.

A turboexpander generator 100 according to an embodiment of the present invention will be described.

As shown in fig. 1 to 7, a turbo-expander generator 100 according to an embodiment of the present invention includes a housing 10, a main shaft 30, a stator 20, and a turbo-expander 50. The housing 10 has a receiving cavity 101. The main shaft 30 is rotatably disposed in the receiving chamber 101 of the housing 10. The stator 20 is disposed in the accommodating cavity 101 and sleeved on the main shaft 30. The turbo expander 50 is the turbo expander of any of the above embodiments, and the scroll 51 of the turbo expander 50 is provided on the housing 10. Wherein a first portion of the main shaft 30 protrudes out of the accommodation cavity 101 and into the chamber 510, each of the first and

second impellers

521 and 522 is disposed on the first portion of the main shaft 30.

The main shaft 30 of the turboexpander generator of the embodiment of the present invention is fixedly connected to the first impeller 521 and the second impeller 522 of the turboexpander 50 to form an integral arrangement of the turboexpander 50 and the generator, the rotation of the two impellers of the turboexpander 50 directly drives the main shaft 30 to rotate, and the two impellers bear axial forces with equal magnitude and opposite directions, and the main shaft 30 bearing the two impellers does not theoretically bear the axial force after the axial force is balanced, so the turboexpander generator 100 of the embodiment of the present invention can bear high rotation speed, and thus has higher operation efficiency and longer service life.

Specifically, the middle of the main shaft 30 is made of magnetic steel as a motor rotor, and the motor rotor is opposite to the stator. The spindle 30 is rotatably connected to the housing 10 at both ends in the accommodation chamber 101 via radial air bearings 41. By adopting the radial air bearing 41, the bearing can stably run for a long time only by the rotation of the gas and the shaft without maintaining the bearing.

In some embodiments, the housing 10 is provided with a cooling channel 11, the cooling channel 11 being annular or spiral shaped. The cooling channel 11 is used to conduct a cooling medium for cooling the inside of the housing 10. For example, referring to fig. 2 (a), the cooling channel 11 includes a cooling groove 113, a sealing sleeve 112, and two joints 111, the cooling groove 113 is recessed on the circumferential surface of the housing 10, the sealing sleeve 112 is sleeved on the housing 10 for forming a seal with the cooling groove 113, the number of the joints 111 is two, the two joints 111 are disposed on the sealing sleeve 112, the joints 111 are communicated with the cooling groove 113, and the joints 111 are used for externally connecting pipes for introducing the cooling medium into the cooling groove 113 and guiding the cooling medium out of the cooling groove 113 to circulate the cooling medium.

The cooling channel 11 is arranged to externally cool the turboexpander according to the embodiment of the present invention, and the annular or spiral arrangement of the cooling channel 11 on the casing reduces the overall volume of the turboexpander.

The cooling grooves 113 may be annular or spiral-shaped, and a person skilled in the art may select the shape and number of the cooling grooves 113 according to design requirements. In some embodiments, the sealing sleeve 112 is made of the same material as the housing 10.

In some embodiments, the casing 10 is provided with a leakage port 12, the leakage port 12 is communicated with the accommodating cavity 101, the turboexpander 100 further comprises a labyrinth seal 13, the labyrinth seal 13 is sleeved on the main shaft 30, and the inner circumferential surface of the labyrinth seal 13 is spaced apart from the main shaft 30. Referring to fig. 2 (a) and 2 (b), the labyrinth seal 13 is located between the accommodating chamber 101 and the chamber 510 to form a certain sealing function for the chamber 510, and the interval between the inner circumferential surface of the labyrinth seal 13 and the main shaft 30 enables the accommodating chamber 101 to communicate with the chamber 510, so that a part of the working medium gas in the chamber 510 overflows into the accommodating chamber 101 through the interval between the labyrinth seal 13 and the main shaft 30. The temperature of the working medium gas expanded and done work in the turbo expander 50 is reduced, so that the working medium gas can be subjected to heat exchange after overflowing to the accommodating cavity 101 to realize the cooling of the accommodating cavity 101, the temperature of the main shaft 30 and the temperature of the stator 20 are reduced, and the cooling effect is achieved. The heat-exchanged gas is discharged through the leakage port 12.

In some embodiments, to facilitate controlling the venting of the leak 12, a leak valve 121 is disposed on the leak 12, as shown in fig. 6.

Referring to fig. 2 (a), a thrust air bearing 42 is further disposed between the housing 10 and the main shaft 30, the thrust air bearing 42 is located between the labyrinth seal 13 and the housing 10 in the left-right direction, and the thrust air bearing 42 can be used for balancing the axial force applied to the main shaft 30.

In some embodiments, the housing 10 has a first end 102 and a second end 103 opposite in an axial direction of the main shaft 30, the first end 102 having a through hole through which a first portion of the main shaft 30 protrudes out of the receiving chamber 101, wherein the volute 51 is disposed on the first end 102 and at least a portion of the labyrinth seal 13 is disposed in the through hole. Referring to fig. 2 (a) and 2 (b), a plurality of grate rings 131 are protruded from an inner circumferential surface of the grate seal 13, the plurality of grate rings 131 are arranged at intervals, and the inner circumferential surface of the grate ring 131 is spaced apart from the main shaft 30. Part of the working medium gas in the first exhaust cavity 514 flows to the accommodating cavity 101 from the interval between the labyrinth ring 131 and the main shaft 30 and is exhausted from the leakage port 12 to form a cooling path of the working medium gas in the generator.

To further enhance the cooling effect of the working medium gas, in some embodiments, at least one of the circumferential surface of the main shaft 30 and the inner circumferential surface of the stator 20 is provided with a groove extending in the axial direction of the main shaft 30. The arrangement of the grooves increases the contact area of the working medium gas and the main shaft 30 and/or the stator, and improves the heat exchange efficiency and the cooling effect of the working medium gas. Illustratively, referring to fig. 2, the stator 20 is provided with a groove on an inner circumferential surface thereof, the groove extending in the left-right direction.

A vehicle of an embodiment of the invention is described below.

A vehicle according to an embodiment of the invention includes a turboexpander generator according to any of the embodiments described above.

The vehicle turboexpansion generator provided by the embodiment of the invention has a simple and compact integral structure, reduces the occupied space of the ORC system, can efficiently recycle the waste heat of the internal combustion engine ORC system, and has long service life.

In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature "under," "beneath," and "under" a second feature may be directly under or obliquely under the second feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.

Claims

1. A turboexpander, comprising:

a scroll (51), the scroll (51) having a chamber (510), an intake scroll (511), a first exhaust port (512), and a second exhaust port (513), the intake scroll (511) communicating with the chamber (510), the chamber (510) including a first exhaust chamber (514) and a second exhaust chamber (515) arranged in a preset direction, the first exhaust port (512) being provided on a peripheral wall surface of the first exhaust chamber (514), the second exhaust port (513) being provided on a peripheral wall surface of the second exhaust chamber (515), wherein the intake scroll (511) is located between at least a portion of the first exhaust chamber (514) and at least a portion of the second exhaust chamber (515) in the preset direction; and

a first impeller (521) and a second impeller (522), the first impeller (521) and the second impeller (522) being disposed back-to-back within the chamber (510), the first impeller (521) being located within the first exhaust chamber (514), the second impeller (522) being located within the second exhaust chamber (515), an extension direction of a rotation axis of each of the first impeller (521) and the second impeller (522) being coincident with the preset direction.

2. The turboexpander of claim 1, further comprising a nozzle ring (53), the nozzle ring (53) being located within the chamber (510), the nozzle ring (53) being located outside each of the first impeller (521) and the second impeller (522), the nozzle ring (53) being located between at least a portion of the first impeller (521) and at least a portion of the second impeller (522) in the predetermined direction.

3. The turboexpander of claim 2, wherein the nozzle ring (53) includes a nozzle disk (531), first and second vanes (532, 533), the nozzle disk (531) having first and second surfaces (5311, 5312) disposed opposite in the predetermined direction, the first vane (532) being disposed on the first surface (5311), the second vane (533) being disposed on the second surface (5312), wherein the first vane (532) has first and second end surfaces (5321) opposing in the predetermined direction, the first end surface abutting the first surface (5311), the second end surface (5321) abutting a wall surface of the cavity (510), the second vane (533) having third and fourth end surfaces (5331) opposing in the predetermined direction, the third end surface abutting the second surface (5312), the fourth end surface (5331) abutting a wall surface of the cavity (510).

4. The turboexpander of claim 3, wherein the nozzle disk (531) is annular and has a receiving hole, each of the first impeller (521) and the second impeller (522) has a disk (523) and a blade group, the nozzle disk (531) being disposed around the disk (523), at least a portion of the disk (523) being located in the receiving hole, and the blade group being disposed on the disk (523), wherein the first impeller (521) and the second impeller (522) are symmetrically disposed with respect to the nozzle disk (531), and the first guide vanes (532) and the second guide vanes (533) are symmetrically disposed with respect to the nozzle disk (531).

5. A turboexpander generator, comprising:

a housing (10), the housing (10) having a housing cavity (101);

a main shaft (30), wherein the main shaft (30) is rotatably arranged in a containing cavity (101) of the shell (10);

the stator (20) is arranged in the accommodating cavity (101) and sleeved on the main shaft (30); and

a turbo-expander (50), the turbo-expander (50) being as claimed in any one of claims 1 to 4, a volute (51) of the turbo-expander (50) being provided on the housing (10), wherein a first portion of the main shaft (30) protrudes out of the accommodation chamber (101) and into the chamber (510), each of the first and second impellers (521, 522) being provided on the first portion of the main shaft (30).

6. The turboexpansion generator of claim 5, characterized in that said casing (10) is provided with a cooling channel (11), said cooling channel (11) being annular or spiral.

7. The turboexpander generator according to claim 5, wherein the casing (10) is provided with a leakage port (12), the leakage port (12) is communicated with the accommodating cavity (101), the turboexpander generator further comprises a labyrinth seal (13), the labyrinth seal (13) is sleeved on the main shaft (30), and the inner circumferential surface of the labyrinth seal (13) is spaced from the main shaft (30).

8. A turboexpander generator according to claim 7, wherein the housing (10) has first and second axially opposite ends (102, 103) of the main shaft (30), the first end (102) having a through-hole through which the first portion of the main shaft (30) protrudes out of the receiving chamber (101), wherein the volute (51) is provided on the first end (102) and at least a portion of the labyrinth seal (13) is provided within the through-hole.

9. The turboexpander generator of claim 8, wherein at least one of a circumferential surface of the main shaft (30) and an inner circumferential surface of the stator (20) is provided with a groove extending in an axial direction of the main shaft (30).

10. A vehicle comprising a turboexpander generator according to any one of claims 5 to 9.