CN211397668U - Partial air axial flow type supercritical carbon dioxide turbo expander - Google Patents
Partial air axial flow type supercritical carbon dioxide turbo expander Download PDFInfo
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- CN211397668U CN211397668U CN201921413154.8U CN201921413154U CN211397668U CN 211397668 U CN211397668 U CN 211397668U CN 201921413154 U CN201921413154 U CN 201921413154U CN 211397668 U CN211397668 U CN 211397668U
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- impeller
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- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 title claims abstract description 76
- 229910002092 carbon dioxide Inorganic materials 0.000 title claims abstract description 38
- 239000001569 carbon dioxide Substances 0.000 title claims abstract description 38
- 238000007789 sealing Methods 0.000 claims abstract description 81
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 72
- 238000006243 chemical reaction Methods 0.000 claims abstract description 7
- 230000005611 electricity Effects 0.000 claims abstract description 4
- 239000000919 ceramic Substances 0.000 claims description 32
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 2
- 239000000306 component Substances 0.000 description 13
- 238000010586 diagram Methods 0.000 description 5
- 238000004804 winding Methods 0.000 description 4
- 230000008602 contraction Effects 0.000 description 3
- 239000002918 waste heat Substances 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- QILCUDCYZVIAQH-UHFFFAOYSA-N 1-$l^{1}-oxidanyl-2,2,5,5-tetramethylpyrrole-3-carboxylic acid Chemical compound CC1(C)C=C(C(O)=O)C(C)(C)N1[O] QILCUDCYZVIAQH-UHFFFAOYSA-N 0.000 description 1
- 239000002028 Biomass Substances 0.000 description 1
- CBENFWSGALASAD-UHFFFAOYSA-N Ozone Chemical compound [O-][O+]=O CBENFWSGALASAD-UHFFFAOYSA-N 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 239000002440 industrial waste Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 231100000252 nontoxic Toxicity 0.000 description 1
- 230000003000 nontoxic effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000003908 quality control method Methods 0.000 description 1
- 230000001846 repelling effect Effects 0.000 description 1
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Abstract
The utility model discloses a partial air axial flow type supercritical carbon dioxide turbo expander, which comprises a turbine part and a motor part; the turbine part adopts a partial air inlet axial flow pneumatic mode and comprises a partial air inlet nozzle and an impeller, at least one nozzle flow channel is arranged on the partial air inlet nozzle, and working medium accelerated by the partial air inlet nozzle axially enters the impeller to drive the impeller to rotate; the motor part comprises a motor shaft, the impeller is fixedly connected to the motor shaft, and the motor shaft is driven to rotate through the rotation of the impeller so as to drive the motor to generate electricity; and dynamic sealing is realized between the turbine part and the motor part through a four-section carbon ring sealing structure. The utility model discloses a partial axial compressor pneumatic mode of admitting air can increase the blade height and easily process the impeller and reduce the easy high-speed motor of turbine rotational speed and the matching of bearing, realizes the high-efficient heat-work conversion of turbo expander at the miniwatt level.
Description
Technical Field
The utility model relates to a turbo expander technique, in particular to axial-flow type supercritical carbon dioxide turbo expander admits air partially suitable for transcritical carbon dioxide power cycle or carbon dioxide brayton cycle.
Background
The trans-critical carbon dioxide power cycle (CTPC for short) or Brayton cycle is a Rankine cycle thermal power generation system using supercritical carbon dioxide as a working medium, and has wide application prospects in the fields of nuclear energy, solar energy, biomass energy, geothermal energy, engine waste heat recovery, industrial waste heat and the like. Compared with other waste heat recovery technologies, the system has the advantages of relatively high efficiency, simple system and low operation and maintenance cost, and carbon dioxide is used as a working medium, so that the system is non-toxic, is non-flammable and non-explosive, and cannot cause ozone layer damage after leakage. The turboexpander is used as a core component for heat-power conversion of carbon dioxide power cycle, and the efficiency of the turboexpander directly influences the efficiency of the cycle and the technical economy of a unit.
The axial flow type turbo expander is used as a turbo expander of a carbon dioxide power circulation system, the research is mainly focused on megawatt or hundred kilowatt level at present, most of the pneumatic forms are all-around air inlet, the research on the low-power supercritical carbon dioxide turbo expander all over the world is few, and the low-power carbon dioxide expander mostly adopts a volume type expander such as a vortex expander or a piston expander and the like and has low efficiency. Therefore, there is a need for a more efficient, low power carbon dioxide turboexpander suitable for use in applications with less waste heat.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a partial air inlet axial flow type supercritical carbon dioxide turbo expander to the carbon dioxide power cycle of low-power order of magnitude, the utility model discloses the expander adopts partial air inlet axial flow pneumatic mode, and the structural arrangement is simple, can realize the high-efficient heat-work conversion of low-power order of magnitude.
The utility model adopts the technical proposal that: a partial air axial flow type supercritical carbon dioxide turbo-expander comprises a turbine part and a motor part;
the turbine section includes:
the air inlet volute comprises a first end surface and a second end surface, and an expansion air outlet is formed in the first end surface of the air inlet volute;
the nozzle ring seat comprises a first end surface and a second end surface, the first end surface of the nozzle ring seat is fixedly connected with the second end surface of the air inlet volute and forms an air inlet chamber with an inner cavity of the air inlet volute;
the partial air inlet nozzle is fixedly connected to the first end face of the nozzle ring seat; at least one nozzle flow channel is arranged on the partial air inlet nozzle, and an air inlet of the nozzle flow channel is communicated with the air inlet chamber; and the number of the first and second groups,
the impeller is arranged between the partial air inlet nozzle and the expansion air outlet, and the air outlet of the nozzle flow channel is positioned at the position of a blade of the impeller, so that the working medium accelerated by the partial air inlet nozzle axially enters the impeller to drive the impeller to rotate;
the motor part includes:
the expansion machine body comprises a first end face and a second end face, and the first end face of the expansion machine body is fixedly connected with the second end face of the nozzle ring seat; and the number of the first and second groups,
the motor shaft is arranged in the center of the expander body and comprises a first end part and a second end part, the first end part of the motor shaft penetrates out of the expander body and sequentially penetrates through the nozzle ring seat and the partial air inlet nozzles to the air inlet volute, the impeller is fixedly connected to the motor shaft, and the motor shaft is driven to rotate through the rotation of the impeller so as to drive the motor to generate electricity.
Furthermore, the air inlet degree of the partial air inlet nozzle is 1/31-1.
Further, when two or more nozzle flow passages are provided, the two or more nozzle flow passages are uniformly arranged along the circumferential direction of the partial air intake nozzle.
Further, the nozzle flow channel is arranged on the outer surface of the partial air inlet nozzle and adopts a through groove type contraction flow channel, and the inlet angle and the outlet angle of the nozzle flow channel are respectively 0 degree and 70 degrees.
Further, the impeller has a reaction degree of 0.3; the inlet thickness of the blade of the impeller is 0.3mm, the outlet thickness of the blade of the impeller is 0.3mm, the inlet angle of the blade of the impeller is 60 degrees, and the outlet angle of the blade of the impeller is 70 degrees.
Further, the turbine part and the motor part are in dynamic sealing through a four-section carbon ring sealing structure, and the four-section carbon ring is arranged in a sealing cavity formed between the motor shaft and the nozzle ring seat and between the motor shaft and the partial air inlet nozzle in a sealing mode.
Wherein, four sections carbocycle seal structure include:
the shaft sleeve is sleeved on the motor shaft and is positioned in the sealing cavity between the partial air inlet nozzle and the motor shaft; the shaft sleeve adopts an intermittent boss structure and comprises a first step surface and a second step surface;
the first carbon ring sealing assembly is sleeved outside the first step surface of the shaft sleeve, the inner wall surface of the first carbon ring sealing assembly is matched with the first step surface of the shaft sleeve, and the outer wall surface of the first carbon ring sealing assembly is matched with the inner wall surface of the sealing cavity;
the second carbon ring sealing assembly is sleeved outside the second step surface of the shaft sleeve and is arranged close to the first carbon ring sealing assembly; the inner wall surface of the second carbon ring sealing assembly is matched with the second step surface of the shaft sleeve, and the outer wall surface of the second carbon ring sealing assembly is matched with the inner wall surface of the sealing cavity;
the third carbon ring sealing assembly is sleeved on the motor shaft and is arranged close to the shaft sleeve and the second carbon ring sealing assembly sleeved on the second step surface of the shaft sleeve; the inner wall surface of the third carbon ring sealing component is matched with the motor shaft, and the outer wall surface of the third carbon ring sealing component is matched with the inner wall surface of the sealing cavity; and the number of the first and second groups,
the fourth carbon ring sealing assembly is sleeved on the motor shaft and is arranged close to the connection position of the nozzle ring seat and the expander body; the inner wall surface of the fourth carbon ring sealing component is matched with the motor shaft, and the outer wall surface of the fourth carbon ring sealing component is matched with the inner wall surface of the sealing cavity.
Further, the motor shaft is supported by a first ceramic ball angular contact bearing, a second ceramic ball angular contact bearing and a third ceramic ball angular contact bearing, and is rotationally connected with the expander body by the first ceramic ball angular contact bearing, the second ceramic ball angular contact bearing and the third ceramic ball angular contact bearing; the first ceramic ball angular contact bearing is disposed at a first end face of the expander block, and the second ceramic ball angular contact bearing and the third ceramic ball angular contact bearing are both disposed at a second end face of the expander block.
Furthermore, the inlet of the expansion machine is provided with a three-way electromagnetic valve to realize emergency bypass, so that the expansion machine is protected.
Further, a vibration displacement sensor is arranged on the expander body to detect the vibration condition of the expander.
The utility model has the advantages that:
the partial air inlet axial flow type supercritical carbon dioxide turbo expander of the utility model mainly comprises a turbine part and a motor part, wherein the turbine part adopts a partial air inlet axial flow pneumatic scheme, a nozzle adopts a partial air inlet structure with two nozzle runners symmetrically arranged, and the nozzle and the inner wall of an air inlet chamber form a nozzle runner; the nozzle is fixed on a nozzle ring seat of the air inlet chamber, and a four-section carbon ring sealing structure is arranged between the nozzle and the motor to realize effective dynamic sealing of the turbine, reduce the external leakage of the turboexpander and improve the air tightness of the unit; and the low-power turbo expander adopts a partial air inlet pneumatic scheme, so that the blade height of the turbine can be increased, the processing difficulty is reduced, the rotating speed of the expander can be effectively reduced, the requirements of the expander on a bearing and a motor are reduced, and the equipment processing cost is reduced. The utility model discloses the expander is equipped with three solenoid valve at the air inlet, can realize the effective protection to the machine when the expander rotational speed is too high, bearing and coil high temperature or vibration are unusual.
The utility model discloses a part axial-flow type supercritical carbon dioxide turboexpander that admits air adopts the part to admit air the axial compressor aerodynamic scheme and has realized the applicability of turboexpander at the miniwatt level of magnitude, and the part scheme of admitting air can increase the leaf height effectively and reduce the processing degree of difficulty, can reduce the rotational speed of expander simultaneously and reduce the harsh requirement of expander to generator and bearing to realize the part and admit air the application of axial-flow supercritical carbon dioxide turboexpander in the miniwatt level of magnitude system that admits air.
Drawings
FIG. 1: the utility model relates to a partial air axial flow type supercritical carbon dioxide turbo expander structure schematic diagram;
FIG. 2: a partial enlarged view in fig. 1 (i.e., a four-segment carbon ring sealing structure schematic);
FIG. 3: the utility model relates to a pipeline layout diagram of a partial air axial flow type supercritical carbon dioxide turbo expander;
FIG. 4 a: the utility model discloses a schematic view structure diagram of a part of air inlet nozzles;
FIG. 4 b: FIG. 4a is a schematic view of a cross-sectional structure B-B;
FIG. 4 c: the three-dimensional structure schematic diagram of part of the air inlet nozzle of the utility model;
FIG. 5 a: the structure schematic diagram of the impeller of the utility model;
FIG. 5 b: FIG. 5a is a schematic view of the cross-sectional structure C-C;
the attached drawings are marked as follows: 1-an expander; 2-an air inlet volute; 3-an expansion air outlet; 4-nozzle ring seat; 5-an air inlet chamber; 6-part of the air inlet nozzle; 6.1-nozzle flow channel; 7-an impeller; 7.1-leaf; 8-expander body; 9-motor shaft; 10-sealing the cavity; 11-a shaft sleeve; 12-a first carbon ring seal assembly; 13-a second carbon ring seal assembly; 14-a third carbon ring seal assembly; 15-a fourth carbon ring seal assembly; 16-a first ceramic ball angular contact bearing; 17-a second ceramic ball angular contact bearing; 18-a third ceramic ball angular contact bearing; 19-a motor coil winding; 20-a machine base; 21-three-way solenoid valve; 22-an air intake line; 23-a bypass line; 24. and an air outlet pipeline.
Detailed Description
For further understanding of the contents, features and functions of the present invention, the following embodiments will be exemplified in conjunction with the accompanying drawings as follows:
as shown in fig. 1 to 5b, a partial gas axial flow supercritical carbon dioxide turboexpander 1 comprises a turbine section and a motor section.
The turbine section comprises an inlet volute 2, a nozzle ring seat 4, a partial inlet nozzle 6 and an impeller 7. The air inlet volute 2 comprises a first end surface and a second end surface, and an expansion air outlet 3 is formed in the first end surface of the air inlet volute 2. The nozzle ring seat 4 comprises a first end surface and a second end surface, the first end surface of the nozzle ring seat 4 is fixedly connected with the second end surface of the air inlet volute 2, and forms an air inlet chamber 5 with the inner cavity of the air inlet volute 2. The height of the partial air inlet nozzle 6 is 4 mm; one side of the partial air inlet nozzle 6 is fixedly connected to the first end surface of the nozzle ring seat 4 through a bolt; as shown in fig. 4a to 4c, a nozzle flow channel 6.1 is arranged on the partial air inlet nozzle 6, the nozzle flow channel 6.1 is arranged on the outer surface of the partial air inlet nozzle 6 and adopts a through groove type contraction flow channel, and a working medium flow channel is formed between the through groove type contraction flow channel and the inner wall of the air inlet volute 2; the inlet angle of the nozzle runner 6.1 (the included angle between the air inlet tangent of the nozzle runner 6.1 and the axis is the inlet angle) is 0 °, the outlet angle (the included angle between the air outlet tangent of the nozzle runner 6.1 and the axis is the outlet angle) is 70 °, and 1/31 is increased for each arrangement of one nozzle runner 6.1 and the air admission degree of the partial air admission nozzle 6 (the ratio of the flow area of the partial air admission nozzle 6 to the full circumferential area thereof is the air admission degree) is increased, in the utility model, at least one nozzle runner 6.1 and at most thirty nozzle runners 6.1 are arranged for the partial air admission nozzle 6, and a proper number of nozzle runners 6.1 are arranged according to different partial air admission degrees or different power levels, when one nozzle runner 6.1 is arranged, the air admission degree of the partial air admission nozzle 6 is 1/31, when thirty nozzle runners 6.1 are arranged, the air admission degree of the partial air admission nozzle 6 is 1 (at this time, full air intake), when the nozzle flow channels 6.1 are provided with two or more nozzle flow channels 6.1, the two or more nozzle flow channels 6.1 are uniformly arranged along the circumferential direction of the partial air intake nozzle 6, in this embodiment, the partial air intake nozzle 6 is symmetrically provided with two nozzle flow channels 6.1, and the two nozzle flow channels 6.1 are symmetrically arranged, so that on one hand, the air blast and air repelling loss of the impeller 7 can be effectively reduced, and on the other hand, the vibration deterioration phenomenon of the motor shaft 9 caused by uneven stress can be reduced; the inlet of the nozzle flow channel 6.1 is connected to the inlet chamber 5. The impeller 7 is arranged between the partial air inlet nozzle 6 and the expansion air outlet 3, and the partial air inlet nozzle 6, the impeller 7 and the expansion air outlet 3 are axially and sequentially arranged, so that the pneumatic type of the expansion machine 1 is axial flow, and meanwhile, the expanded supercritical carbon dioxide enters an exhaust pipeline from the expansion air outlet 3 through a conical pipe; the air outlet of the nozzle flow channel 6.1 is positioned at the position of a blade 7.1 of the impeller 7, and the working medium accelerated by the partial air inlet nozzle 6 axially enters the impeller 7 to drive the impeller 7 to rotate; the impeller 7 is made of a titanium alloy material, so that the vibration of a quality control shaft system is reduced; the impeller 7 has a reaction degree of 0.3 and a height of 4mm, as shown in fig. 5a and 5b, an inlet thickness of the blade 7.1 of the impeller 7 is 0.3mm, an outlet thickness is 0.3mm, an inlet angle of the blade 7.1 of the impeller 7 is 60 °, and an outlet angle is 70 °.
The expander 1 of the utility model has smaller power and flow, and adopts partial air intake to effectively improve the height of the partial air intake nozzle 6 and the blades 7.1, thus reducing the flow loss of the boundary layer of the flow channel and reducing the processing difficulty and cost of the partial air intake nozzle 6 and the impeller 7; meanwhile, the adoption of part of the air inlet nozzles 6 can effectively reduce the turbine rotating speed and reduce the strict requirements on the high-speed motor and the bearing, and the matching of the high-speed motor and the bearing is easy, so that the applicability of the turboexpander 1 in a low-power-level system is realized, and the high-efficiency heat-power conversion is realized; furthermore, the desired expansion ratio can be achieved by effective expansion of part of the flow path of the inlet nozzle 6 and the impeller 7.
The motor part comprises an expander body 8, a motor coil winding 19, a motor shaft 9 and a base 20. The expander body 8 is fixed on the base 20, the expander body 8 comprises a first end surface and a second end surface, and the first end surface of the expander body 8 is fixedly connected with the second end surface of the nozzle ring seat 4. The motor coil winding 19 is arranged in the expander body 8, the motor shaft 9 is arranged at the center of the motor coil winding 19, the motor shaft 9 comprises a first end part and a second end part, the first end part of the motor shaft 9 penetrates out of the expander body 8 and sequentially penetrates through the nozzle ring seat 4 and the partial air inlet nozzles 6 to the inside of the air inlet volute 2, the impeller 7 is fixedly connected to the motor shaft 9, and the motor shaft 9 is driven to rotate through the rotation of the impeller 7, so that the motor is driven to generate electricity. The motor shaft 9 is supported by a first ceramic ball angular contact bearing 16, a second ceramic ball angular contact bearing 17 and a third ceramic ball angular contact bearing 18, and is rotationally connected with the expander body 8 by the first ceramic ball angular contact bearing 16, the second ceramic ball angular contact bearing 17 and the third ceramic ball angular contact bearing 18; the first ceramic ball angular contact bearing 16 is arranged at a first end face of the expander body 8 (i.e., near the turbine portion), and lubricated with oil; the second ceramic ball angular contact bearing 17 and the third ceramic ball angular contact bearing 18 are both disposed at the second end face of the expander body 8 and lubricated with grease, and the second ceramic ball angular contact bearing 17 and the third ceramic ball angular contact bearing 18 are mounted back to provide a bearing configuration with higher rigidity relative to one bearing and can bear overturning moment.
The turbine part with the mounting means that the motor part adopted coaxial direct connection adopts a main shaft promptly, the utility model discloses in, the main shaft does motor shaft 9, rated revolution 40000 rpm.
Dynamic sealing is realized between the turbine part and the motor part through a four-section carbon ring sealing structure, so that effective isolation is realized, and the phenomenon that high-pressure supercritical carbon dioxide enters an inner cavity of an expander body 8 of the motor part to cause wind resistance loss is avoided. The four-section carbon ring is arranged in a sealing cavity 10 formed between the motor shaft 9 and the nozzle ring seat 4 and the part of the air inlet nozzle 6 in a sealing mode. As shown in fig. 2, the four-stage carbon ring sealing structure includes a shaft sleeve 11, a first carbon ring sealing assembly 12, a second carbon ring sealing assembly 13, a third carbon ring sealing assembly 14, and a fourth carbon ring sealing assembly 15. The shaft sleeve 11 is sleeved on the motor shaft 9 and is positioned in the sealed cavity 10 between the partial air inlet nozzle 6 and the motor shaft 9; the shaft sleeve 11 adopts an intermittent boss structure and comprises a first step surface and a second step surface. The first carbon ring sealing component 12 is sleeved outside the first step surface of the shaft sleeve 11, the inner wall surface of the first carbon ring sealing component 12 is matched with the first step surface of the shaft sleeve 11, and the outer wall surface of the first carbon ring sealing component 12 is matched with the inner wall surface of the sealing cavity 10. The second carbon ring sealing assembly 13 is sleeved outside the second step surface of the shaft sleeve 11 and is arranged close to the first carbon ring sealing assembly 12; the inner wall surface of the second carbon ring sealing component 13 is matched with the second step surface of the shaft sleeve 11, and the outer wall surface of the second carbon ring sealing component 13 is matched with the inner wall surface of the sealing cavity 10. The third carbon ring sealing assembly 14 is sleeved on the motor shaft 9 and is arranged close to the shaft sleeve 11 and the second carbon ring sealing assembly 13 sleeved on the second step surface of the shaft sleeve 11; the inner wall surface of the third carbon ring sealing component 14 is matched with the motor shaft 9, and the outer wall surface of the third carbon ring sealing component 14 is matched with the inner wall surface of the sealing cavity 10. The fourth carbon ring sealing assembly 15 is sleeved on the motor shaft 9 and is arranged close to the joint of the nozzle ring seat 4 and the expander body 8; the inner wall surface of the fourth carbon ring sealing component 15 is matched with the motor shaft 9, and the outer wall surface of the fourth carbon ring sealing component 15 is matched with the inner wall surface of the sealing cavity 10. During operation, the shaft sleeve 11 rotates together with the motor shaft 9, and the first carbon ring seal assembly 12, the second carbon ring seal assembly 13 and the third carbon ring seal assembly 14 remain stationary. The principle of the four-section carbon ring sealing structure is as follows: the high-pressure supercritical carbon dioxide leaked from the gap of the part of the gas inlet nozzle 6 in the turbine part leaks and reduces pressure along the radial gap axial direction at the first carbon ring seal assembly 12, leaks along the axial gap and then leaks axially at the second carbon ring seal assembly 13, leaks along the radial gap axial direction at the interface of the second carbon ring seal assembly 13 and the third carbon ring seal assembly 14, leaks along the radial gap axial direction of the inner diameters of the third carbon ring seal assembly 14 and the fourth carbon ring seal assembly 15, and reduces the leakage amount through turning, throttling and pressure reduction for several times.
As shown in fig. 3, a three-way electromagnetic valve 21 is arranged at an inlet of a turbine part of the expander 1, an inlet of the three-way electromagnetic valve 21 is connected with an inlet pipeline 22, one outlet is connected to an inlet chamber 5 of the turbine part, and the other outlet is connected to an outlet pipeline 24 of the turbine part of the expander 1 through a bypass pipeline 23, so that working medium bypass is realized under the conditions of overhigh rotating speed, overhigh pressure, abnormal vibration or overhigh bearing temperature and the like of the expander 1, and the expander 1 is protected. The utility model discloses the carbon dioxide working medium after the partial axial flow type supercritical carbon dioxide turbo expander 1 expands gets into back regenerator or condenser through the exhaust pipe.
In addition, a vibration displacement sensor is arranged on the expander body 8 to detect the vibration condition of the expander 1, so that the expander can be effectively protected when the abnormal rotating speed vibration quantity is too large.
Although the preferred embodiments of the present invention have been described with reference to the accompanying drawings, the present invention is not limited to the above-mentioned embodiments, which are only illustrative and not restrictive, and those skilled in the art can make many forms without departing from the spirit and scope of the present invention, which is within the protection scope of the present invention.
Claims (10)
1. A partial gas axial flow supercritical carbon dioxide turboexpander (1) comprising a turbine section and a motor section,
the turbine section includes:
the air inlet volute (2) comprises a first end surface and a second end surface, and an expansion air outlet (3) is formed in the first end surface of the air inlet volute (2);
the nozzle ring seat (4) comprises a first end surface and a second end surface, the first end surface of the nozzle ring seat (4) is fixedly connected with the second end surface of the air inlet volute (2) and forms an air inlet chamber (5) with the inner cavity of the air inlet volute (2);
the partial air inlet nozzle (6), the partial air inlet nozzle (6) is fixedly connected to the first end face of the nozzle ring seat (4); at least one nozzle flow channel (6.1) is arranged on the partial air inlet nozzle (6), and an air inlet of the nozzle flow channel (6.1) is communicated with the air inlet chamber (5); and the number of the first and second groups,
the impeller (7) is arranged between the partial air inlet nozzle (6) and the expansion air outlet (3), and the air outlet of the nozzle flow channel (6.1) is positioned at the position of a blade (7.1) of the impeller (7), so that the working medium accelerated by the partial air inlet nozzle (6) axially enters the impeller (7) to drive the impeller (7) to rotate;
the motor part includes:
the expansion machine body (8) comprises a first end face and a second end face, and the first end face of the expansion machine body (8) is fixedly connected with the second end face of the nozzle ring seat (4); and the number of the first and second groups,
motor shaft (9), motor shaft (9) set up the center of expander organism (8), motor shaft (9) include first end and second end, the first end of motor shaft (9) is worn out outside expander organism (8) and pass in proper order nozzle ring seat (4) with partial inlet nozzle (6) extremely in air inlet volute (2), impeller (7) fixed connection is in on motor shaft (9), through the rotatory drive of impeller (7) motor shaft (9) are rotatory to drive the motor electricity generation.
2. The partial-air axial-flow supercritical carbon dioxide turbo-expander (1) according to claim 1, characterized in that the degree of air admission of the partial-air inlet nozzle (6) is 1/31-1.
3. A partial gas axial flow supercritical carbon dioxide turbo expander (1) according to claim 1, characterized by that when said nozzle flow channels (6.1) are provided with at least two, at least two of said nozzle flow channels (6.1) are arranged uniformly in the circumferential direction of said partial gas inlet nozzle (6).
4. A partial inlet axial flow supercritical carbon dioxide turbo expander (1) according to claim 1, characterized by the nozzle flow channels (6.1) arranged on the outer surface of the partial inlet nozzle (6) and using channel type convergent flow channels, the inlet angle of the nozzle flow channels (6.1) is 0 ° and the outlet angle is 70 °.
5. A partial gas axial flow supercritical carbon dioxide turbo expander (1) according to claim 1, characterized by the impeller (7) having a reaction degree of 0.3; the inlet thickness of the blade (7.1) of the impeller (7) is 0.3mm, the outlet thickness is 0.3mm, the inlet angle of the blade (7.1) of the impeller (7) is 60 degrees, and the outlet angle is 70 degrees.
6. A partial gas axial flow supercritical carbon dioxide turbo-expander (1) according to claim 1, characterized in that the dynamic sealing between the turbine part and the motor part is achieved by a four-stage carbon ring sealing structure, which is arranged in the sealing cavity (10) formed between the motor shaft (9) and the nozzle ring seat (4) and the partial inlet nozzle (6).
7. A partial gas axial flow supercritical carbon dioxide turbo-expander (1) according to claim 6, characterized by the four-stage carbon ring sealing structure comprising:
the shaft sleeve (11) is sleeved on the motor shaft (9), and is positioned in the sealed cavity (10) between the partial air inlet nozzle (6) and the motor shaft (9); the shaft sleeve (11) adopts an intermittent boss structure and comprises a first step surface and a second step surface;
the first carbon ring sealing assembly (12) is sleeved outside a first step surface of the shaft sleeve (11), the inner wall surface of the first carbon ring sealing assembly (12) is matched with the first step surface of the shaft sleeve (11), and the outer wall surface of the first carbon ring sealing assembly (12) is matched with the inner wall surface of the sealing cavity (10);
the second carbon ring sealing assembly (13) is sleeved outside the second step surface of the shaft sleeve (11), and the second carbon ring sealing assembly (13) is arranged close to the first carbon ring sealing assembly (12); the inner wall surface of the second carbon ring sealing component (13) is matched with a second step surface of the shaft sleeve (11), and the outer wall surface of the second carbon ring sealing component (13) is matched with the inner wall surface of the sealing cavity (10);
the third carbon ring sealing assembly (14) is sleeved on the motor shaft (9) and is arranged close to the shaft sleeve (11) and the second carbon ring sealing assembly (13) sleeved on a second step surface of the shaft sleeve (11); the inner wall surface of the third carbon ring sealing component (14) is matched with the motor shaft (9), and the outer wall surface of the third carbon ring sealing component (14) is matched with the inner wall surface of the sealing cavity (10); and the number of the first and second groups,
the fourth carbon ring sealing assembly (15), the fourth carbon ring sealing assembly (15) is sleeved on the motor shaft (9) and is arranged close to the connection position of the nozzle ring seat (4) and the expander body (8); the inner wall surface of the fourth carbon ring sealing component (15) is matched with the motor shaft (9), and the outer wall surface of the fourth carbon ring sealing component (15) is matched with the inner wall surface of the sealing cavity (10).
8. The partial gas axial flow supercritical carbon dioxide turbo expander (1) according to claim 1, characterized in that the motor shaft (9) is supported by a first ceramic ball angular contact bearing (16), a second ceramic ball angular contact bearing (17) and a third ceramic ball angular contact bearing (18) and is rotationally connected with the expander body (8) by the first ceramic ball angular contact bearing (16), the second ceramic ball angular contact bearing (17) and the third ceramic ball angular contact bearing (18); the first ceramic ball angular contact bearing (16) is arranged at a first end face of the expander block (8), and the second ceramic ball angular contact bearing (17) and the third ceramic ball angular contact bearing (18) are both arranged at a second end face of the expander block (8).
9. A partial gas axial flow supercritical carbon dioxide turbo expander (1) according to claim 1, characterized by the inlet of the expander (1) being provided with a three-way solenoid valve (21) to achieve emergency bypass and thus protection of the expander (1).
10. The partial gas axial flow supercritical carbon dioxide turbo expander (1) according to claim 1, characterized in that a vibration displacement sensor is provided on the expander body (8) to detect the vibration of the expander (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921413154.8U CN211397668U (en) | 2019-08-28 | 2019-08-28 | Partial air axial flow type supercritical carbon dioxide turbo expander |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110454240A (en) * | 2019-08-28 | 2019-11-15 | 天津大学 | A kind of partial-air admission axial-flow type supercritical carbon dioxide turbo-expander |
| CN112502796A (en) * | 2020-11-26 | 2021-03-16 | 中国科学院工程热物理研究所 | SCO2Operation control system and operation control method for expansion machine |
| CN110454240B (en) * | 2019-08-28 | 2024-09-06 | 天津大学 | Partial air inlet axial flow type supercritical carbon dioxide turbine expander |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110454240A (en) * | 2019-08-28 | 2019-11-15 | 天津大学 | A kind of partial-air admission axial-flow type supercritical carbon dioxide turbo-expander |
| CN110454240B (en) * | 2019-08-28 | 2024-09-06 | 天津大学 | Partial air inlet axial flow type supercritical carbon dioxide turbine expander |
| CN112502796A (en) * | 2020-11-26 | 2021-03-16 | 中国科学院工程热物理研究所 | SCO2Operation control system and operation control method for expansion machine |
| CN112502796B (en) * | 2020-11-26 | 2022-11-18 | 中国科学院工程热物理研究所 | Operation control system and operation control method of SCO2 expander |
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