CN117365689A - Closed brayton cycle power generation device with multilayer flow guide sleeve structure - Google Patents
Closed brayton cycle power generation device with multilayer flow guide sleeve structure Download PDFInfo
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- CN117365689A CN117365689A CN202311228710.5A CN202311228710A CN117365689A CN 117365689 A CN117365689 A CN 117365689A CN 202311228710 A CN202311228710 A CN 202311228710A CN 117365689 A CN117365689 A CN 117365689A
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- 238000010248 power generation Methods 0.000 title abstract description 32
- 238000010438 heat treatment Methods 0.000 claims abstract description 81
- 238000001816 cooling Methods 0.000 claims abstract description 72
- 230000008929 regeneration Effects 0.000 claims abstract description 9
- 238000011069 regeneration method Methods 0.000 claims abstract description 9
- 230000001172 regenerating effect Effects 0.000 claims description 54
- 238000011084 recovery Methods 0.000 claims description 12
- 238000007789 sealing Methods 0.000 claims description 12
- 239000002918 waste heat Substances 0.000 claims description 8
- 238000009413 insulation Methods 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 claims description 3
- 238000002955 isolation Methods 0.000 claims description 2
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- 229910052751 metal Inorganic materials 0.000 description 5
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- 238000004891 communication Methods 0.000 description 3
- 239000011261 inert gas Substances 0.000 description 3
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- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/10—Heating, e.g. warming-up before starting
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
- F01D25/145—Thermally insulated casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the field of closed cycle power generation, and discloses a closed Brayton cycle power generation device with a multilayer flow guide sleeve structure, which comprises: the core unit comprises a motor unit, a high-speed shaft, a compressor unit and a turbine unit, wherein the motor unit comprises a low-temperature air inlet chamber, and the low-temperature air inlet chamber is communicated with an air inlet of the compressor unit; the multi-layer flow guiding sleeve assembly comprises a low-temperature exhaust chamber, a high-temperature air inlet chamber and an exhaust backheating chamber, wherein the low-temperature exhaust chamber is communicated with an exhaust port of the compressor unit, the high-temperature air inlet chamber is communicated with an air inlet of the turbine unit, and the exhaust backheating chamber is communicated with an exhaust port of the turbine unit; one end of each heating pipe is communicated with the low-temperature exhaust chamber, the other end of each heating pipe is communicated with the high-temperature air inlet chamber, and at least one part of each heating pipe is positioned in the exhaust heat regeneration chamber; one end of the cooling pipes is communicated with the exhaust backheating chamber, and the other end is communicated with the low-temperature air inlet chamber. The invention can reduce the flow pressure drop loss of working medium, reduce the volume of the system and improve the compactness.
Description
Technical Field
The invention relates to the technical field of closed cycle power generation, in particular to a closed Brayton cycle power generation device with a multilayer flow guide sleeve structure.
Background
The closed Brayton cycle power generation system is a thermoelectric conversion technology adopting inert gas working media, has the characteristics of high efficiency, compact structure, wide power coverage range, wide heat source adaptability, air cooling capability and the like, and has good application prospects in the fields of space nuclear power generation, star meter energy station construction, distributed power generation, solar thermal power generation, waste heat power generation and the like.
In a closed brayton cycle power generation system, a regenerator is generally arranged to improve system performance, however, in the existing closed brayton cycle power generation system, the regenerator is used as an independent device and is arranged outside a host machine and is connected with the host machine through a pipeline, and the arrangement mode of the regenerator increases the pipeline on one hand, generates additional pipeline pressure drop, reduces the performance of a power generation device, and on the other hand, increases the size and weight of the whole power generation device due to the fact that the size of the regenerator is large, and is difficult to meet the arrangement requirement for compactification of the power generation system in an application scene.
Disclosure of Invention
The invention aims to provide a closed Brayton cycle power generation device with a multilayer flow guide sleeve structure, which not only can reduce the flow pressure drop loss of working media, but also can reduce the volume of a system and improve the compactness.
The technical scheme provided by the invention is as follows:
a closed brayton cycle power plant of a multilayer flow sleeve structure comprising:
the core machine assembly comprises a motor group, a high-speed shaft, a compressor group and a turbine group, wherein a rotating shaft of the motor group is in transmission connection with the high-speed shaft, the compressor group and the turbine group are respectively arranged on the high-speed shaft, the motor group comprises a low-temperature air inlet chamber, and the low-temperature air inlet chamber is communicated with an air inlet of the compressor group;
the multi-layer flow guide sleeve assembly comprises a low-temperature exhaust chamber, a high-temperature air inlet chamber and an exhaust backheating chamber, wherein the low-temperature exhaust chamber is communicated with an exhaust port of the compressor unit, the high-temperature air inlet chamber is communicated with an air inlet of the turbine unit, and the exhaust backheating chamber is communicated with the exhaust port of the turbine unit;
the heating pipe assembly comprises a plurality of heating pipes which are arranged at intervals along the circumferential direction and used for exchanging heat with an external heat source, one end of each heating pipe is positioned in the exhaust backheating cavity and communicated with the low-temperature exhaust cavity, and the other end of each heating pipe is communicated with the high-temperature air inlet cavity;
the cooling pipe assembly comprises a plurality of cooling pipes which are arranged at intervals along the circumferential direction and used for exchanging heat with an external cold source, one end of each cooling pipe is communicated with the exhaust heat recovery chamber, and the other end of each cooling pipe is communicated with the low-temperature air inlet chamber.
In some embodiments, when the compressor unit works, the low-temperature low-pressure working medium in the low-temperature air inlet chamber is sucked, and the low-temperature low-pressure working medium enters the low-temperature air outlet chamber after being pressurized by the compressor unit;
the low-temperature high-pressure working medium in the low-temperature exhaust cavity enters the heating pipe to exchange heat with the waste heat in the exhaust heat recovery cavity and an external heat source to form a high-temperature high-pressure working medium which enters the high-temperature air inlet cavity;
after the high-temperature high-pressure working medium in the Gao Wenjin air cavity enters the turbine group and pushes the turbine group to rotate to do work, the temperature and the pressure of the working medium are reduced and enter an exhaust heat recovery cavity to exchange heat with the low-temperature low-pressure working medium in the heating pipe and then enter the cooling pipe, and the working medium exchanges heat with an external cold source in the cooling pipe to form a low-temperature low-pressure working medium and enters the low-temperature air inlet cavity.
In some embodiments, the motor unit includes a motor housing, a motor cooling member and a motor body, the motor housing is internally provided with the low-temperature air inlet chamber, the motor cooling member and the motor body are respectively arranged in the motor housing, and the motor cooling member is arranged outside the motor body and is communicated with the low-temperature air inlet chamber and is used for cooling the motor body.
In some embodiments, the compressor unit includes a compressor inlet runner, a compressor impeller and a compressor guide vane, wherein one side of the compressor inlet runner is fixedly connected with the motor housing and is communicated with the low-temperature air inlet chamber, the compressor impeller is mounted on the high-speed shaft, and the compressor guide vane is arranged on the outer side of the compressor impeller and is fixedly connected with the other side of the compressor inlet runner, and is used for recompression and transportation of working medium compressed by the compressor impeller to the low-temperature air outlet chamber.
In some embodiments, the turbomachine includes a turbine wheel fixedly mounted to the high speed shaft, a turbine inlet runner fixedly connected to the compressor vane, and a turbine exhaust runner fixedly connected to the turbine inlet runner, the high temperature inlet chamber in communication with the turbine inlet runner, and the turbine exhaust runner in communication with the exhaust regeneration chamber.
In some embodiments, the turbine inlet runner has an outer diameter that is greater than an outer diameter of the turbine outlet runner, the turbine outlet runner being disposed inboard of the turbine inlet runner.
In some embodiments, the turbomachine further comprises a support ring and a radial bearing, the support ring being connected with the high speed shaft by the radial bearing, the support ring being located between the compressor vane and the turbine inlet runner, one end of the support ring being fixedly connected with the compressor vane, the other end being fixedly connected with the turbine inlet runner.
In some embodiments, the turbomachine further comprises a thrust bearing disposed between the compressor wheel and the support ring.
In some embodiments, the multi-layer flow sleeve assembly comprises a high temperature inlet flow sleeve, a high temperature exhaust flow sleeve, a regenerative flow inner sleeve, a regenerative flow outer sleeve, an exhaust flow tail cover, and an isolating ring;
the high-temperature air inlet guide sleeve comprises an inner sleeve and an outer sleeve, one end of the inner sleeve is connected with one end of the outer sleeve to form a closed end, the other end of the inner sleeve is an open end, the outer sleeve at the open end of the high-temperature air inlet guide sleeve is connected with the turbine air inlet flow passage, the inner sleeve is connected with the turbine air outlet flow passage, and the areas surrounded by the inner sleeve, the outer sleeve and the turbine air inlet flow passage form the high-temperature air inlet chamber;
the first end of the high-temperature exhaust flow guiding sleeve is arranged in the inner sleeve and is connected with the turbine exhaust runner, and the second end of the high-temperature exhaust flow guiding sleeve extends out of the inner sleeve along the axial direction;
the heat-return flow-guiding inner sleeve is sleeved outside the outer sleeve and the turbine air inlet flow passage, the first end of the heat-return flow-guiding inner sleeve is connected with the compressor air inlet flow passage in a sealing way, and the second end of the heat-return flow-guiding inner sleeve is connected with the second end of the high-temperature exhaust flow-guiding sleeve;
the exhaust guide tail cover is sleeved outside the regenerative guide inner sleeve, the first end of the regenerative guide outer sleeve is connected with the first end of the regenerative guide inner sleeve in a sealing mode, and the exhaust guide tail cover seals the second end of the regenerative guide outer sleeve; the turbine exhaust runner, the high-temperature exhaust guide sleeve, the regenerative guide inner sleeve, the regenerative guide outer sleeve and the exhaust guide tail cover form an exhaust regenerative chamber in the surrounding area;
the isolating ring is arranged between the turbine air inlet channel and the regenerative diversion inner sleeve, one end of the isolating ring is in sealing connection with the regenerative diversion inner sleeve, and the other end of the isolating ring is in sealing connection with the turbine air inlet channel; the area surrounded by the backheating diversion inner sleeve, the compressor air inlet flow passage, the turbine air inlet flow passage, the supporting ring and the isolating ring forms the low-temperature exhaust chamber.
In some embodiments, the inner sleeve is spaced from the high temperature exhaust gas flow sleeve, and the outer sleeve is spaced from the regeneration flow inner sleeve, such that a thermal insulation chamber is formed between the exhaust gas regeneration chamber and the high temperature intake chamber;
the heat insulation chamber is formed by an area surrounded by the isolation ring, the turbine inlet air flow, the high-temperature exhaust flow guide sleeve, the turbine exhaust flow channel, the high-temperature inlet flow guide sleeve and the regenerative flow guide inner sleeve.
In some embodiments, the multilayer flow sleeve assembly further comprises a corrugated sleeve having one end connected to the exhaust gas flow sleeve and the other end connected to the high temperature exhaust gas flow sleeve, the heating tube passing through the corrugated sleeve.
In some embodiments, the heating tube assembly further comprises a plurality of heating tube fins, the heating tube fins being evenly distributed over the heating tube.
In some embodiments, the cooling tube assembly further comprises a plurality of cooling tube fins, the cooling tube fins being evenly distributed over the cooling tube.
The invention has the technical effects that: the invention adopts a multilayer flow guide sleeve structure, realizes the functions of collecting, bidirectionally guiding and conveying working media in the sleeve structure, greatly reduces the working media conveying pipelines, reduces the flow pressure drop loss of the working media, and is beneficial to the improvement of the performance of a closed cycle power generation system; in addition, the working medium heat regeneration process in the flow guide sleeve is realized, the configuration of an external independent heat regenerator is reduced, the arrangement of the existing closed cycle power generation system is simplified, the system volume is reduced, the compactness is improved, and the device is suitable for various scenes such as mobile carrier power generation, space nuclear power generation and the like.
Drawings
The invention is described in further detail below with reference to the attached drawings and detailed description:
fig. 1 is a schematic structural diagram of a closed brayton cycle power generation device with a multilayer flow sleeve structure according to an embodiment of the present application;
fig. 2 is a schematic diagram of an operating principle of a closed brayton cycle power generation device with a multilayer flow guiding sleeve structure according to an embodiment of the present application;
FIG. 3 is a schematic structural view of a core engine assembly according to an embodiment of the present application;
FIG. 4 is a schematic illustration of a multi-layer flow sleeve assembly provided in accordance with an embodiment of the present application;
FIG. 5 is a schematic view of a high temperature inlet guide sleeve according to an embodiment of the present disclosure;
FIG. 6 is a schematic view of a high temperature exhaust gas flow sleeve according to an embodiment of the present disclosure;
fig. 7 is a schematic partial structure of a regenerative diversion inner sleeve according to an embodiment of the present application;
fig. 8 is a schematic partial structure of a regenerative diversion outer sleeve according to an embodiment of the present application;
FIG. 9 is a schematic view of an exhaust gas flow guiding tail cover according to an embodiment of the present disclosure;
FIG. 10 is a schematic structural view of an isolating ring according to an embodiment of the present application;
FIG. 11 is a schematic longitudinal cross-sectional view of a cooling tube assembly provided in an embodiment of the present application;
FIG. 12 is a schematic cross-sectional view of a cooling tube assembly provided in accordance with an embodiment of the present application;
FIG. 13 is a schematic view of a longitudinal cross-sectional configuration of a heating tube assembly provided in an embodiment of the present application;
FIG. 14 is a schematic cross-sectional view of a heating tube assembly provided in an embodiment of the present application.
Reference numerals illustrate:
1. a core machine assembly; 2. a multi-layer flow sleeve assembly; 3. a heating tube assembly; 4. a cooling tube assembly; 5. a motor housing; 6. a motor cooling member; 7. a motor body; 8. a compressor inlet flow path; 9. a compressor vane; 10. a compressor wheel; 11. a support ring; 12. turbine inlet flow path; 13. a thrust bearing; 14. a radial bearing; 15. a high-speed shaft; 16. a turbine wheel; 17. turbine exhaust flow passages; 18. a lock nut; 19. a cooling tube; 20. cooling tube fins; 21. heating pipes; 22. heating the tube fin; 23. a high temperature inlet flow sleeve; 231. an inner sleeve; 232. an outer sleeve; 24. a high temperature exhaust flow sleeve; 25. backheating the diversion inner sleeve; 26. a heat return diversion outer sleeve; 27. an exhaust air guide tail cover; 28. a spacer ring; 29. a corrugated sleeve; 30. a low temperature air intake chamber; 31. a low temperature exhaust chamber; 32. a high temperature air intake chamber; 33. an exhaust backheating chamber; 34. an insulated chamber.
Detailed Description
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
For the sake of simplicity of the drawing, the parts relevant to the present invention are shown only schematically in the figures, which do not represent the actual structure thereof as a product. Additionally, in order to simplify the drawing for ease of understanding, components having the same structure or function in some of the drawings are shown schematically with only one of them, or only one of them is labeled. Herein, "a" means not only "only this one" but also "more than one" case.
It should be further understood that the term "and/or" as used in this specification and the appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes such combinations.
In this context, it should be noted that the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, unless explicitly stated or limited otherwise; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In addition, in the description of the present application, the terms "first," "second," and the like are used merely to distinguish between descriptions and are not to be construed as indicating or implying relative importance.
In one embodiment of the present application, as shown in fig. 1 and 2, a closed brayton cycle power generation device with a multi-layer flow sleeve structure comprises a core machine assembly 1, a multi-layer flow sleeve assembly 2, a heating pipe assembly 3 and a cooling pipe assembly 4, wherein the core machine assembly 1 comprises a motor group, a high-speed shaft 15, a compressor group and a turbine group, a rotating shaft of the motor group is in transmission connection with the high-speed shaft 15, the compressor group and the turbine group are respectively installed on the high-speed shaft 15, the motor group comprises a low-temperature air inlet chamber 30, and the low-temperature air inlet chamber 30 is communicated with an air inlet of the compressor group; the multi-layer flow guiding sleeve assembly 2 comprises a low-temperature exhaust chamber 31, a high-temperature air inlet chamber 32 and an exhaust backheating chamber 33, wherein the low-temperature exhaust chamber 31 is communicated with an exhaust port of a compressor unit, the high-temperature air inlet chamber 32 is communicated with an air inlet of a turbine unit, and the exhaust backheating chamber 33 is communicated with the exhaust port of the turbine unit; the heating pipe assembly 3 comprises a plurality of heating pipes 21 which are arranged at intervals along the circumferential direction and are used for exchanging heat with an external heat source, one end of each heating pipe 21 is positioned in the exhaust backheating chamber 33 and is communicated with the low-temperature exhaust chamber 31, the other end of each heating pipe 21 is communicated with the high-temperature air inlet chamber 32, and at least one part of each heating pipe 21 is positioned in the exhaust backheating chamber 33; the cooling pipe assembly 4 comprises a plurality of cooling pipes 19 which are arranged at intervals along the circumferential direction and are used for exchanging heat with an external cold source, one end of each cooling pipe 19 is communicated with the exhaust heat recovery chamber 33, and the other end of each cooling pipe is communicated with the low-temperature air inlet chamber 30 and is used for cooling the motor group.
In this embodiment, the core engine component 1 is used for pressurizing and expanding the circulating working medium to realize power generation. The multi-layer flow guiding sleeve assembly 2 is arranged outside the core assembly 1 and is used for collecting, guiding and conveying the circulating working medium. The heating pipe assembly 3 is arranged on the other side of the multi-layer flow guiding sleeve assembly 2 and is used for heating the circulating working medium. The cooling pipe assembly 4 is arranged on one side of the multi-layer flow guiding sleeve assembly 2 and is used for cooling the circulating working medium. In this embodiment, inert gases such as carbon dioxide, nitrogen, argon, or a combination of inert gases may be used as the working medium.
The core machine assembly 1 comprises a motor group, a high-speed shaft 15, a compressor group and a turbine group, wherein a rotating shaft of the motor group is connected with the high-speed shaft 15 and used for transmitting torque so as to realize rotation of the high-speed shaft 15. The compressor unit and the turbine unit are both arranged on the high-speed shaft 15, an air inlet of the compressor unit is communicated with the low-temperature air inlet chamber 30 and used for pressurizing low-temperature working media, low-temperature high-pressure working media discharged by the compressor unit enter the low-temperature air outlet chamber 31 and then enter the heating pipe 21 to exchange heat with exhaust waste heat in the air exhaust back-heating chamber 33, so that the temperature of the working media in the heating pipe 21 is increased to form high-temperature high-pressure working media and enter the high-temperature air inlet chamber 32, an air inlet of the turbine unit is communicated with the high-temperature air inlet chamber 32, and the working media in the high-temperature air inlet chamber 32 can push the turbine unit to rotate for doing work, thereby realizing power generation.
As shown in fig. 2, in operation, the compressor unit works to suck the low-temperature low-pressure working medium in the low-temperature air inlet chamber 30, the compressor unit pressurizes the working medium, the working medium pressure rises and enters the low-temperature air outlet chamber 31, the low-temperature high-pressure working medium in the low-temperature air outlet chamber 31 enters the heating pipe 21, heat exchange is performed between the low-temperature high-pressure working medium in the heating pipe 21 and the exhaust waste heat in the exhaust heat return chamber 33 and an external high-temperature heat source, the working medium temperature in the heating pipe 21 rises to form the high-temperature high-pressure working medium, finally, the high-temperature high-pressure working medium enters the high-temperature air inlet chamber 32 through the heating pipe 21 and enters the turbine unit through the air inlet of the turbine unit, the high-temperature high-pressure working medium pushes the turbine unit to rotate for doing work, one part of the working power is used for power consumption required by the rotation of the compressor unit, and the other part of the working power is used for driving the coaxial motor unit, so that electric energy is generated, and power generation is realized. After the turboset performs work, the pressure and the temperature of the working medium are reduced, the working medium enters the exhaust backheating chamber 33 through the exhaust port of the turboset, after the working medium exchanges heat with the low-temperature low-pressure working medium in the heating pipe 21, the temperature of the working medium in the exhaust backheating chamber 33 is further reduced, the working medium enters the cooling pipe 19, the working medium exchanges heat with an external low-temperature cold source in the cooling pipe 19, and the temperature is further reduced to form a low-temperature low-pressure working medium and enters the low-temperature air inlet chamber 30, so that the whole cycle is formed.
The invention adopts a multilayer flow guide sleeve structure, realizes the functions of collecting, bidirectionally guiding and conveying working media in the sleeve structure, greatly reduces the working media conveying pipelines, reduces the flow pressure drop loss of the working media, and is beneficial to the improvement of the performance of a closed cycle power generation system. The heat recovery process of the working medium in the flow guide sleeve is realized, so that the configuration of an external independent heat regenerator is reduced, the arrangement of the existing closed cycle power generation system is simplified, the system volume is reduced, the compactness is improved, and the heat recovery device is suitable for various scenes such as mobile carrier power generation, space nuclear power generation and the like.
Further, as shown in fig. 3, the motor unit includes a motor housing 5, a motor cooling member 6 and a motor body 7, a low-temperature air inlet chamber 30 is provided in the motor housing 5, the motor body 7 and the motor cooling member 6 are respectively provided in the motor housing 5, and the motor cooling member 6 is provided outside the motor body and is communicated with the low-temperature air inlet chamber 30 for cooling the motor body 7.
In this embodiment, the motor body 7 may adopt a permanent magnet synchronous heuristic motor, and the rotating shaft of the motor body 7 is connected with the high-speed shaft 15. The motor cooling piece 6 can be annular spoke metal structure, and the motor cooling piece 6 is arranged outside the motor body 7, and low-temperature low-pressure working medium in the cooling pipe 19 can enter the motor cooling piece 6 to cool down the motor body 7, take away the heat generated by the operation of the motor body 7, so as to realize long-time stable operation of the motor body 7. The motor shell 5 is a cylindrical pressure-resistant component and is arranged outside the motor cooling piece 6 and connected with the compressor unit, and small holes are arranged at the bottom of the motor shell 5 and used for penetrating the cooling pipes 19 so as to realize that working media in the cooling pipes 19 are conveyed into the low-temperature air inlet chamber 30 of the motor shell 5.
Further, as shown in fig. 3, the compressor unit includes a compressor intake runner 8, a compressor guide vane 9 and a compressor impeller 10, the compressor intake runner 8 is fixedly connected with the motor housing 5 and is communicated with the low-temperature air intake chamber 30, the compressor impeller 10 is mounted on the high-speed shaft 15 and rotates along with the high-speed shaft 15, and the compressor guide vane 9 is disposed on the outer side of the compressor impeller 10 and is fixedly connected with the other side of the compressor intake runner 8, so as to recompress and convey the working medium compressed by the compressor impeller 10 to the low-temperature air exhaust chamber 31.
In this embodiment, the compressor inlet flow channel 8 is disposed in the air inlet direction of the compressor impeller 10 and has an annular sleeve structure, so as to improve the inlet speed and compression efficiency of the working medium entering the compressor impeller 10. One side of the compressor air inlet runner 8 is fixedly connected with the motor shell 5, and the other side is fixedly connected with the compressor guide vane 9. The compressor wheel 10 may be constructed as a radial flow centrifugal impeller, fabricated from cast aluminum material, and mounted to the high speed shaft 15. The compressor guide vane 9 is installed outside the compressor impeller 10 and fixedly connected with the compressor air inlet runner 8, the air inlet of the compressor guide vane 9 is communicated with the air outlet of the compressor impeller 10, the air outlet of the compressor guide vane 9 is communicated with the low-temperature exhaust chamber 31, and the working medium compressed by the compressor impeller 10 enters the compressor guide vane 9 for further compression and is then conveyed to the low-temperature exhaust chamber 31.
Further, as shown in fig. 3, the turbo-set includes a turbine wheel 16, a turbine intake runner 12, and a turbine exhaust runner 17, the turbine wheel 16 is fixedly mounted on the high speed shaft 15, the turbine intake runner 12 is fixedly connected with the compressor vane 9, the turbine exhaust runner 17 is fixedly connected with the turbine intake runner 12, the high temperature intake chamber 32 is communicated with the turbine intake runner 12, and the turbine exhaust runner 17 is communicated with the exhaust heat recovery chamber 33.
Further, as shown in fig. 3, the turbomachine further comprises a support ring 11 and a radial bearing 14, the support ring 11 is connected with the high speed shaft 15 through the radial bearing 14, the support ring 11 is located between the compressor guide vane 9 and the turbine inlet runner 12, one end of the support ring 11 is fixedly connected with the compressor guide vane 9, and the other end is fixedly connected with the turbine inlet runner 12.
The turbine wheel 16 is made of a radial flow centrifugal impeller structure and made of a nickel-based superalloy material and is mounted on the high-speed shaft 15, and a lock nut 18 is mounted on the outer side of the turbine wheel 16 to prevent the turbine wheel from loosening and flying out during operation. The turbine inlet runner 12 is installed on the inlet side of the turbine wheel 16, and the turbine inlet runner 12 is of an L-shaped structure and is installed on the support ring 11 so as to guide the inlet air of the turbine wheel 16. The outlet side of the turbine wheel 16 is provided with a turbine exhaust runner 17, and the turbine exhaust runner 17 is of an annular sleeve structure and is arranged on the support ring 11 so as to realize further diffusion of working medium at the outlet of the turbine wheel 16. The turbine intake runner 12 has an outer diameter larger than that of the turbine exhaust runner 17, and the turbine exhaust runner 17 is provided inside the turbine intake runner 12. One end of the supporting ring 11 is fixedly connected with the compressor guide vane 9 and the compressor air inlet runner 8, and the other end is fixedly connected with the turbine air inlet runner 12 and the turbine exhaust runner 17. The compressor wheel 10, turbine wheel 16 are mounted on the high speed shaft 15 in a back-to-back arrangement. The radial bearing 14 is mounted in the inner bore of the support ring 11, and in this embodiment the radial bearing 14 may be a pneumatic suspension bearing for effecting movement between the support ring 11 and the high speed shaft 15.
As shown in fig. 3, the turbomachine further comprises a thrust bearing 13, the thrust bearing 13 being arranged between the compressor wheel 10 and the support ring 11. The thrust bearing 13 is located on the compressor side for achieving circumferential thrust balance of the high speed shaft 15.
In some embodiments, as shown in fig. 1 and 4, the multi-layer flow sleeve assembly 2 includes a high temperature inlet flow sleeve 23, a high temperature exhaust flow sleeve 24, a regenerative flow inner sleeve 25, a regenerative flow outer sleeve 26, an exhaust flow tail cover 27, and a spacer ring 28; the high temperature air intake guide sleeve 23 comprises an inner sleeve 231 and an outer sleeve 232, wherein one end of the inner sleeve 231 is connected with one end of the outer sleeve 232 to form a closed end, the other end is an open end, the outer sleeve 232 at the open end of the high temperature air intake guide sleeve 23 is connected with the turbine air intake runner 12, the inner sleeve 231 is connected with the turbine air exhaust runner 17, and the areas surrounded by the inner sleeve 231, the outer sleeve 232 and the turbine air intake runner 12 form a high temperature air intake chamber 32.
The high temperature exhaust gas flow sleeve 24 is disposed at a first end within the inner sleeve 231 and is connected to the turbine exhaust runner 17 and at a second end extending axially out of the inner sleeve 231.
The inner regenerative diversion sleeve 25 is sleeved outside the outer sleeve 232 and the turbine inlet runner 12, the first end of the inner regenerative diversion sleeve 25 is connected with the compressor inlet runner 8 in a sealing way, and the second end of the inner regenerative diversion sleeve 25 is connected with the second end of the high-temperature exhaust diversion sleeve 24.
The regenerative diversion outer sleeve 26 is sleeved outside the regenerative diversion inner sleeve 25, the first end of the regenerative diversion outer sleeve 26 is in sealing connection with the first end of the regenerative diversion inner sleeve 25, and the exhaust diversion tail cover 27 seals the second end of the regenerative diversion outer sleeve 26; the areas enclosed by the turbine exhaust runner 17, the high-temperature exhaust guide sleeve 24, the regenerative guide inner sleeve 25, the regenerative guide outer sleeve 26 and the exhaust guide tail cover 27 form an exhaust regenerative chamber 33.
The isolating ring 28 is arranged between the turbine air inlet channel 12 and the regenerative diversion inner sleeve 25, one end of the isolating ring 28 is in sealing connection with the regenerative diversion inner sleeve 25, and the other end of the isolating ring 28 is in sealing connection with the turbine air inlet channel 12; the areas surrounded by the backheating diversion inner sleeve 25, the compressor air inlet runner 8, the turbine air inlet runner 12, the supporting ring 11 and the isolating ring 28 form a low-temperature exhaust chamber 31.
The inner sleeve 231 and the high-temperature exhaust guide sleeve 24 are arranged at intervals, and the outer sleeve 232 and the backheating guide inner sleeve 25 are arranged at intervals, so that a heat insulation chamber 34 is formed between the exhaust backheating chamber 33 and the high-temperature air inlet chamber 32; the insulating chamber 34 is formed by the area enclosed by the spacer ring 28, the turbine inlet flow passage 12, the high temperature inlet flow sleeve 23, the turbine exhaust flow passage 17, the high temperature exhaust flow sleeve 24 and the regenerative flow sleeve 25.
The multi-layer flow sleeve assembly 2 further comprises a bellows 29, one end of the bellows 29 being connected to the exhaust gas flow cap 27 and the other end being connected to the high temperature exhaust gas flow sleeve 24, the heating tube 21 passing through the bellows 29.
Specifically, as shown in fig. 5, a half of the longitudinal section of the high-temperature air intake guide sleeve 23 is of a U-shaped structure, an inner sleeve 231 at the side of the U-shaped opening is connected with the turbine exhaust runner 17, an outer sleeve 232 is connected with the turbine intake runner 12, a plurality of holes are uniformly distributed in the circumferential direction at the bottom of the U-shaped structure for installing the heating pipe 21, and the inside of the high-temperature air intake guide sleeve 23 is communicated with the space inside the heating pipe 21. The high-temperature air inlet guide sleeve 23 is used for collecting and conveying working media in the heating pipe 21 to the turbine air inlet flow passage 12.
As shown in fig. 6, the longitudinal section of the high-temperature exhaust guide sleeve 24 is of an L-shaped structure, one end of the high-temperature exhaust guide sleeve 24 is located inside the inner sleeve 231 and connected with the turbine exhaust runner 17, the other end extends axially out of the inner sleeve 231 and is connected with the regenerative guide inner sleeve 25, and holes are uniformly arranged in the circumferential direction of the L-shaped bottom for mounting the corrugated sleeve 29. The high temperature exhaust flow sleeve 24 is used to deliver the working fluid of the turbine exhaust runner 17 to the exhaust flow cap 27.
As shown in fig. 7, the inner regenerative guide sleeve 25 is in a cylindrical structure, one end of the inner regenerative guide sleeve is connected with the high-temperature exhaust guide sleeve 24, the other end of the inner regenerative guide sleeve is connected with the outer regenerative guide sleeve 26 and the air inlet channel 8 of the compressor, and holes are uniformly arranged on the circumferential wall surface, close to the compressor unit, of the inner regenerative guide sleeve 25 for installing the heating pipe 21. The heat-return diversion inner sleeve 25 is used for forming a heat-insulating chamber 34 on one hand so as to reduce heat exchange between working medium in the high-temperature air inlet chamber 32 and working medium in the exhaust heat-return chamber 33, and is used for forming the exhaust heat-return chamber 33 with the heat-return diversion outer sleeve 26 on the other hand so as to realize heat exchange between turbine exhaust waste heat and working medium in the heating pipe 21.
As shown in fig. 8, half of the longitudinal section of the regenerative diversion outer sleeve 26 is in an L-shaped structure, one end of the regenerative diversion outer sleeve 26 is connected with one end of the regenerative diversion inner sleeve 25 close to the compressor air inlet flow channel 8, the other end is connected with the exhaust diversion tail cover 27, and holes are uniformly distributed in the circumferential direction of the bottom of the regenerative diversion outer sleeve 26 and used for installing the cooling pipes 19, so that working media in the exhaust regenerative chamber 33 can be conveyed into the cooling pipes 19.
As shown in fig. 9, the exhaust guide tail cover 27 is a generally elliptical or butterfly-shaped metal end enclosure, is installed on the opening side of the L-shaped structure of the heat recovery guide outer sleeve 26, and is used for changing the flow direction of the working medium in the high-temperature exhaust guide sleeve 24, and is conveyed to the pipeline portion of the heating pipe 21 in the exhaust heat recovery chamber 33, and exchanges heat with the pipeline portion, so that the temperature of the working medium in the heating pipe 21 is increased by using exhaust waste heat, and the performance of the whole system is improved. Holes are uniformly arranged on the exhaust guide tail cover 27 for installing the heating pipe 21 and the corrugated sleeve 29. The corrugated sleeve 29 is in the form of corrugated metal pipes and is respectively connected with the high-temperature exhaust guide sleeve 24 and the exhaust guide tail cover 27, so that heat exchange between working media in the high-temperature exhaust guide sleeve 24 and the heating pipe 21 is reduced, and displacement compensation of dimensional change caused by temperature change of a connecting part is realized.
As shown in fig. 10, the isolating ring 28 has an annular bell mouth structure, one side is connected with the backheating diversion inner sleeve 25, and the other side is connected with the turbine exhaust runner 17, so as to isolate the low-temperature exhaust chamber 31 from the heat insulation chamber 34.
In this embodiment, as shown in fig. 1 and 4, the high-temperature air intake chamber 32 is a closed space formed by the high-temperature air intake guide sleeve 23, the turbine air intake runner 12, and the turbine air exhaust runner 17, and is used for collecting and conveying the working medium in the heating pipe 21 to the inlet of the turbine wheel 16.
The exhaust heat regeneration chamber 33 is a closed space formed by the high-temperature exhaust guide sleeve 24, the turbine exhaust runner 17, the exhaust guide tail cover 27, the heat regeneration guide inner sleeve 25 and the heat regeneration guide outer sleeve 26, and is used for exchanging heat between the exhaust of the turbine impeller 16 and the heating pipe 21 to increase the temperature of working medium in the heating pipe 21, and is used for collecting and conveying the exhaust working medium into the cooling pipe 19.
The low-temperature exhaust chamber 31 is a closed space formed by the backheating diversion inner sleeve 25, the compressor air inlet runner 8, the supporting ring 11, the turbine air inlet runner 12 and the isolating ring 28, and is used for collecting and conveying the working medium after the pressurization of the compressor impeller 10 into the heating pipe 21.
The low-temperature air intake chamber 30 is a space formed by the motor housing 5 and the compressor air intake runner 8, and is used for collecting and conveying the cooled working medium in the cooling pipe 19 to the inlet of the compressor impeller 10.
The heat insulation chamber 34 is a closed space formed by the isolating ring 28, the turbine inlet runner 12, the high-temperature inlet flow guide sleeve 23, the turbine exhaust runner 17, the high-temperature exhaust flow guide sleeve 24 and the regenerative flow guide inner sleeve 25, and is used for isolating the high-temperature inlet chamber 32 and the exhaust regenerative chamber 33 and reducing the heat transfer quantity of the high-temperature inlet chamber and the exhaust regenerative chamber.
In some embodiments, as shown in fig. 11 and 12, the heating tube assembly 3 further includes a plurality of heating tube fins 22, the heating tube fins 22 being uniformly distributed over the heating tube 21. As shown in fig. 13 and 14, the cooling tube assembly 4 further includes a plurality of cooling tube fins 20, and the cooling tube fins 20 are uniformly distributed on the cooling tube 19.
The heating pipe 21 may generally take the form of a U-shaped pipe, a coiled pipe or a spiral pipe, etc., one end of the heating pipe 21 is installed on the backheating inner sleeve 25, and penetrates the exhaust guide tail cover 27 along the pipe direction, and penetrates the exhaust guide tail cover 27, the corrugated sleeve 29 and the high-temperature exhaust guide sleeve 24 again after absorbing heat, and then is connected to the high-temperature air inlet guide sleeve 23, so as to convey the working medium of the low-temperature exhaust chamber 31 to the high-temperature air inlet chamber 32. The heating pipe fins 22 are made of metal sheets and are uniformly arranged on the heating pipe 21, so that the heat exchange area is increased, and the heat exchange efficiency of the heating pipe 21 and a high-temperature heat source is improved. The cooling tube 19 is generally in the form of a U-shaped tube, a coiled tube or a spiral tube, and the like, and the cooling tube fins 20 are made of metal sheets and are uniformly distributed on the cooling tube 19 so as to increase the heat exchange area and improve the heat exchange efficiency of the cooling tube 19 and the low-temperature cold source.
As shown in fig. 2, the specific working process of the closed brayton cycle power generation device with the multilayer flow guiding sleeve structure is as follows: during operation, the compressor impeller 10 rotates, the working medium in the low-temperature air inlet chamber 30 is sucked, the working medium is pressurized, the working medium pressure is increased and enters the compressor guide vane 9 to be further pressurized and then enters the low-temperature air outlet chamber 31, the working medium in the low-temperature air outlet chamber 31 is conveyed to the heating pipe 21 due to the air pressure difference, the heating pipe 21 exchanges heat with the exhaust waste heat in the exhaust air back-heating chamber 33 in the exhaust back-heating chamber 33, the temperature of the working medium in the heating pipe 21 is increased, the heat exchange is carried out between the heating pipe fins 22 and an external high-temperature heat source, the temperature of the working medium in the heating pipe 21 is further increased, the final high-temperature high-pressure working medium flows back into the high-temperature air inlet chamber 32 through the heating pipe 21 and is conveyed to the turbine impeller 16 through the turbine air inlet channel 12, the turbine impeller 16 is pushed to rotate to do work, the working medium temperature and the pressure are reduced after the working medium is subjected to work done on the turbine impeller 16, the working medium enters the exhaust back-heating chamber 33 through the turbine air outlet channel 17 and enters the cooling pipe 19 after the heat exchange is carried out with the heating pipe 21, the working medium temperature is reduced through the cooling pipe fins 20 and the external low-temperature heat source, the working medium temperature in the cooling pipe 19 is reduced, and enters the motor housing 5, the motor body 7 is cooled through the motor cooling element 6, and finally, the motor body 7 is returned to the low-temperature inlet side of the compressor impeller 10, and the low-temperature air inlet chamber is formed.
The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which are intended to be comprehended within the scope of the present invention.
Claims (13)
1. A closed brayton cycle power plant of a multilayer flow sleeve structure comprising:
the core machine assembly comprises a motor group, a high-speed shaft, a compressor group and a turbine group, wherein a rotating shaft of the motor group is in transmission connection with the high-speed shaft, the compressor group and the turbine group are respectively arranged on the high-speed shaft, the motor group comprises a low-temperature air inlet chamber, and the low-temperature air inlet chamber is communicated with an air inlet of the compressor group;
the multi-layer flow guide sleeve assembly comprises a low-temperature exhaust chamber, a high-temperature air inlet chamber and an exhaust backheating chamber, wherein the low-temperature exhaust chamber is communicated with an exhaust port of the compressor unit, the high-temperature air inlet chamber is communicated with an air inlet of the turbine unit, and the exhaust backheating chamber is communicated with the exhaust port of the turbine unit;
the heating pipe assembly comprises a plurality of heating pipes which are arranged at intervals along the circumferential direction and used for exchanging heat with an external heat source, one end of each heating pipe is positioned in the exhaust backheating cavity and communicated with the low-temperature exhaust cavity, and the other end of each heating pipe is communicated with the high-temperature air inlet cavity;
the cooling pipe assembly comprises a plurality of cooling pipes which are arranged at intervals along the circumferential direction and used for exchanging heat with an external cold source, one end of each cooling pipe is communicated with the exhaust heat recovery chamber, and the other end of each cooling pipe is communicated with the low-temperature air inlet chamber.
2. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 1, wherein,
when the compressor unit works, the low-temperature low-pressure working medium in the low-temperature air inlet cavity is sucked, and the low-temperature low-pressure working medium enters the low-temperature air outlet cavity after being pressurized by the compressor unit;
the low-temperature high-pressure working medium in the low-temperature exhaust cavity enters the heating pipe to exchange heat with the waste heat in the exhaust heat recovery cavity and an external heat source to form a high-temperature high-pressure working medium which enters the high-temperature air inlet cavity;
after the high-temperature high-pressure working medium in the Gao Wenjin air cavity enters the turbine group and pushes the turbine group to rotate to do work, the temperature and the pressure of the working medium are reduced and enter an exhaust heat recovery cavity to exchange heat with the low-temperature low-pressure working medium in the heating pipe and then enter the cooling pipe, and the working medium exchanges heat with an external cold source in the cooling pipe to form a low-temperature low-pressure working medium and enters the low-temperature air inlet cavity.
3. A multi-layer flow sleeve structured closed Brayton cycle power plant as claimed in claim 1 or 2, wherein,
the motor unit comprises a motor shell, a motor cooling part and a motor body, wherein the motor shell is internally provided with a low-temperature air inlet cavity, the motor cooling part and the motor body are respectively arranged in the motor shell, and the motor cooling part is arranged outside the motor body and is communicated with the low-temperature air inlet cavity and used for cooling the motor body.
4. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 3, wherein,
the compressor unit comprises a compressor air inlet flow passage, a compressor impeller and a compressor guide vane, wherein one side of the compressor air inlet flow passage is fixedly connected with the motor shell and communicated with the low-temperature air inlet chamber, the compressor impeller is installed on the high-speed shaft, and the compressor guide vane is arranged on the outer side of the compressor impeller and fixedly connected with the other side of the compressor air inlet flow passage and is used for recompressing and conveying working media compressed by the compressor impeller to the low-temperature air outlet chamber.
5. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 4, wherein,
the turbine set comprises a turbine impeller, a turbine air inlet runner and a turbine air outlet runner, wherein the turbine impeller is fixedly arranged on the high-speed shaft, the turbine air inlet runner is fixedly connected with the compressor guide vane, the turbine air outlet runner is fixedly connected with the turbine air inlet runner, the high-temperature air inlet chamber is communicated with the turbine air inlet runner, and the turbine air outlet runner is communicated with the exhaust heat regeneration chamber.
6. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 5, wherein,
the outer diameter of the turbine inlet runner is larger than that of the turbine outlet runner, and the turbine outlet runner is arranged on the inner side of the turbine inlet runner.
7. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 5, wherein,
the turbine group further comprises a supporting ring and a radial bearing, the supporting ring is connected with the high-speed shaft through the radial bearing, the supporting ring is located between the compressor guide vane and the turbine air inlet runner, one end of the supporting ring is fixedly connected with the compressor guide vane, and the other end of the supporting ring is fixedly connected with the turbine air inlet runner.
8. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 7, wherein,
the turbomachine further includes a thrust bearing disposed between the compressor wheel and the support ring.
9. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 7, wherein,
the multi-layer flow guide sleeve assembly comprises a high-temperature air inlet flow guide sleeve, a high-temperature air exhaust flow guide sleeve, a back-heating flow guide inner sleeve, a back-heating flow guide outer sleeve, an air exhaust flow guide tail cover and an isolating ring;
the high-temperature air inlet guide sleeve comprises an inner sleeve and an outer sleeve, one end of the inner sleeve is connected with one end of the outer sleeve to form a closed end, the other end of the inner sleeve is an open end, the outer sleeve at the open end of the high-temperature air inlet guide sleeve is connected with the turbine air inlet flow passage, the inner sleeve is connected with the turbine air outlet flow passage, and the areas surrounded by the inner sleeve, the outer sleeve and the turbine air inlet flow passage form the high-temperature air inlet chamber;
the first end of the high-temperature exhaust flow guiding sleeve is arranged in the inner sleeve and is connected with the turbine exhaust runner, and the second end of the high-temperature exhaust flow guiding sleeve extends out of the inner sleeve along the axial direction;
the heat-return flow-guiding inner sleeve is sleeved outside the outer sleeve and the turbine air inlet flow passage, the first end of the heat-return flow-guiding inner sleeve is connected with the compressor air inlet flow passage in a sealing way, and the second end of the heat-return flow-guiding inner sleeve is connected with the second end of the high-temperature exhaust flow-guiding sleeve;
the exhaust guide tail cover is sleeved outside the regenerative guide inner sleeve, the first end of the regenerative guide outer sleeve is connected with the first end of the regenerative guide inner sleeve in a sealing mode, and the exhaust guide tail cover seals the second end of the regenerative guide outer sleeve; the turbine exhaust runner, the high-temperature exhaust guide sleeve, the regenerative guide inner sleeve, the regenerative guide outer sleeve and the exhaust guide tail cover form an exhaust regenerative chamber in the surrounding area;
the isolating ring is arranged between the turbine air inlet channel and the regenerative diversion inner sleeve, one end of the isolating ring is in sealing connection with the regenerative diversion inner sleeve, and the other end of the isolating ring is in sealing connection with the turbine air inlet channel; the area surrounded by the backheating diversion inner sleeve, the compressor air inlet flow passage, the turbine air inlet flow passage, the supporting ring and the isolating ring forms the low-temperature exhaust chamber.
10. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 9, wherein,
the inner sleeve and the high-temperature exhaust guide sleeve are arranged at intervals, and the outer sleeve and the backheating guide inner sleeve are arranged at intervals, so that a heat insulation chamber is formed between the exhaust backheating chamber and the high-temperature air inlet chamber;
the heat insulation chamber is formed by an area surrounded by the isolation ring, the turbine inlet air flow, the high-temperature exhaust flow guide sleeve, the turbine exhaust flow channel, the high-temperature inlet flow guide sleeve and the regenerative flow guide inner sleeve.
11. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 9, wherein,
the multi-layer flow guiding sleeve assembly further comprises a corrugated sleeve, one end of the corrugated sleeve is connected with the exhaust flow guiding tail cover, the other end of the corrugated sleeve is connected with the high-temperature exhaust flow guiding sleeve, and the heating pipe penetrates through the corrugated sleeve.
12. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 1, wherein,
the heating pipe assembly further comprises a plurality of heating pipe fins, and the heating pipe fins are uniformly distributed on the heating pipe.
13. A multi-layer flow sleeve structured closed Brayton cycle power plant as defined in claim 1, wherein,
the cooling tube assembly further comprises a plurality of cooling tube fins which are uniformly distributed on the cooling tubes.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311228710.5A CN117365689A (en) | 2023-09-22 | 2023-09-22 | Closed brayton cycle power generation device with multilayer flow guide sleeve structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311228710.5A CN117365689A (en) | 2023-09-22 | 2023-09-22 | Closed brayton cycle power generation device with multilayer flow guide sleeve structure |
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| CN117365689A true CN117365689A (en) | 2024-01-09 |
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| CN202311228710.5A Pending CN117365689A (en) | 2023-09-22 | 2023-09-22 | Closed brayton cycle power generation device with multilayer flow guide sleeve structure |
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- 2023-09-22 CN CN202311228710.5A patent/CN117365689A/en active Pending
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