CN115691852A - Hundred-kilowatt-level supercritical carbon dioxide Brayton cycle direct cooling space reactor system - Google Patents
Hundred-kilowatt-level supercritical carbon dioxide Brayton cycle direct cooling space reactor system Download PDFInfo
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- CN115691852A CN115691852A CN202211370103.8A CN202211370103A CN115691852A CN 115691852 A CN115691852 A CN 115691852A CN 202211370103 A CN202211370103 A CN 202211370103A CN 115691852 A CN115691852 A CN 115691852A
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Abstract
The invention discloses a Brayton cycle direct cooling space reactor system for hundred kilowatts of supercritical carbon dioxide, which comprises a supercritical carbon dioxide direct cooling reactor, wherein the output end of the supercritical carbon dioxide direct cooling reactor is connected with the fuel inlet end of a gas turbine, the gas turbine is coaxially connected with a compressor and a generator, the gas outlet end of the compressor is connected with the input end of the supercritical carbon dioxide direct cooling reactor through the cold side of a heat regenerator, and the gas outlet end of the gas turbine is connected with the gas inlet end of the compressor after passing through the hot side of the heat regenerator and the hot side of a precooler; the cold side outlet of the precooler is connected with the cold side inlet of the precooler through the radiant panel radiator. The invention has compact structure and low emission cost.
Description
Technical Field
The invention belongs to the technical field of nuclear reactors, and particularly relates to a hectowatt-level supercritical carbon dioxide Brayton cycle direct cooling space reactor system.
Background
The direct Brayton cycle system coupled with the gas-cooled fast reactor adopts inert gas or supercritical fluid as a coolant, can avoid corrosion to structural materials, provides higher thermoelectric conversion efficiency and has good economical efficiency. An intermediate heat exchanger is not needed between the reactor and the energy conversion system, the system is simple in arrangement and compact in structure, the lower mass-power ratio is favorably realized, and the construction and emission cost of the space nuclear power system can be reduced.
The existing space nuclear power system design mainly adopts helium-xenon mixed gas as a coolant, the helium-xenon cooled reactor usually needs about 900 ℃ of reactor core outlet temperature, the overhigh operating temperature puts high requirements on material performance, and the engineering difficulty is increased. The supercritical carbon dioxide brayton cycle can relatively reduce the core exit temperature while reducing the size of the heat exchanger and the turbomachinery. The research on the direct cooling of the space reactor by the supercritical carbon dioxide Brayton cycle is of great significance.
The research of the current supercritical carbon dioxide Brayton cycle as a direct cooling system is mainly oriented to high-power ground application, and is represented by a fast reactor design with the thermal power of 2400MWt proposed by American Massachusetts university. Ground applications are more focused on achieving high thermal efficiency and system quality considerations are not applicable to space stack designs.
It is therefore desirable to develop a supercritical carbon dioxide brayton cycle direct cooled spacestack system design that takes into account system mass.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a hundred-kilowatt-level supercritical carbon dioxide brayton cycle direct cooling space reactor system aiming at the defects in the prior art, and the system is used for solving the technical problem that the conventional space reactor concept design has few schemes in working medium selection and quality optimization.
The invention adopts the following technical scheme:
the space reactor system is characterized by comprising a supercritical carbon dioxide direct cooling reactor, wherein the output end of the supercritical carbon dioxide direct cooling reactor is connected with the fuel inlet end of a gas turbine, the gas turbine is coaxially connected with a compressor and a generator, the gas outlet end of the compressor is connected with the input end of the supercritical carbon dioxide direct cooling reactor through the cold side of a heat regenerator, and the gas outlet end of the gas turbine is connected with the gas inlet end of the compressor through the hot side of the heat regenerator and the hot side of a precooler; the cold side outlet of the precooler is connected with the cold side inlet of the precooler through a radiation plate radiator.
Specifically, the supercritical carbon dioxide direct cooling reactor comprises a reactor core, wherein the reactor core is arranged in a pressure vessel, and a radial and axial reflecting layer is arranged between the reactor core and the pressure vessel.
Further, the core is composed of several TID type fuel assemblies.
Still further, the TID-type fuel assembly includes an assembly wall having an interior portion provided with a fuel zone directly cooled by supercritical carbon dioxide.
Still further, the module walls are in a hexagonal configuration.
Still further, a dispersed UO is arranged in the fuel area 2 BeO matrix of the particles.
Further, the length-diameter ratio of the core is 1.
Furthermore, a plurality of coolant channels are uniformly distributed in the reactor core.
Further, the coolant channel comprises a cooling flow channel, a cladding and an air gap from inside to outside in sequence.
Specifically, the energy conversion efficiency of the supercritical carbon dioxide brayton cycle direct cooled space reactor system is 21.74%.
Compared with the prior art, the invention has at least the following beneficial effects:
the hundred-kilowatt-level supercritical carbon dioxide Brayton cycle direct cooling space reactor system has high working medium density and good heat transfer performance, and can greatly reduce the sizes of a compressor, a heat exchanger and the like; the heat regenerator adopts a printed circuit board type heat exchanger, has compact structure and wide application range, can meet the heat exchange requirement of the supercritical carbon dioxide Brayton cycle in a limited volume, heats the compressed gas by utilizing the heat of exhaust gas and can improve the cycle heat efficiency; the working medium is further cooled in the precooler, the precooler is connected with the radiation plate radiator, the radiation plate consists of a plurality of heat pipe radiators, waste heat is discharged into a space environment, the heat transfer performance of the heat pipes is good, and single fault of a heat extraction system can be effectively prevented.
Furthermore, the supercritical carbon dioxide directly cools the pressure vessel of the reactor to contain the reactor core and the reflecting layer and ensures that the reactor core operates in a high-pressure state; the uranium dioxide pellets in the reactor core generate energy through fission to serve as a heat source, and the radial and axial reflecting layers can shield neutrons so as to prolong the service life of the pressure vessel.
Furthermore, the TID type fuel assembly is adopted in the reactor core, compared with the traditional rod-shaped fuel, the TID type fuel assembly has higher fuel share, is favorable for reducing the positive coolant cavitation reactivity feedback effect of the air-cooled fast reactor, and improves the safety performance of the system; helps to reduce fuel temperature; the need for spacer grids is eliminated, thereby reducing the core pressure drop of the reactor.
Furthermore, the fuel area directly cooled by the supercritical carbon dioxide is arranged in the component, an intermediate heat exchanger is not needed, and the system arrangement can be simplified.
Furthermore, the assembly wall is arranged in a hexagonal structure, so that the influence of foreign matters on the operation of the fuel assembly in the stack can be reduced, and the grid structure is simplified.
Further, UO 2 The fuel has stable performance, is not easy to deform after being irradiated, has unchanged structure at high temperature, and does not interact with supercritical carbon dioxide.
Further, the aspect ratio of the core is 1, and the selection of this value is limited by the critical calculation of the reactor physics, i.e. the relationship between the fuel fraction and the critical core diameter.
Furthermore, a plurality of coolant channels are uniformly distributed in the reactor core, flow distribution of the flow channels is balanced, and the reactor core of the reactor is fully cooled.
Further, the cladding acts as an isolation barrier between the fuel and the coolant, preventing fission products from escaping and efficiently conducting heat away; an air gap is arranged between the fuel area and the cladding and filled with carbon dioxide for compensating possible thermal expansion and swelling of the fuel, accommodating a part of fission gas, balancing the pressure difference inside and outside the cladding tube and preventing the cladding from deforming.
Furthermore, the energy conversion efficiency of the supercritical carbon dioxide Brayton cycle direct cooling space reactor system is 21.7 percent, so that the system has the minimum mass under the target operation working conditions (low pressure of 8MPa, high pressure of 16MPa and reactor core outlet temperature of 600 ℃) and the emission cost is reduced.
In conclusion, the system for directly cooling the space reactor by the aid of the Brayton cycle of the hundred-kilowatt-level supercritical carbon dioxide has the advantages of high thermoelectric conversion efficiency, simple system arrangement, compact structure, capability of reducing construction and emission costs of a space nuclear power system, and good economical efficiency and safety.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
Figure 1 is a schematic cross-sectional view of a TID type fuel assembly.
Fig. 2 is a schematic cross-sectional view of a coolant channel.
Fig. 3 is a schematic cross-sectional view of a supercritical carbon dioxide direct cooled reactor.
FIG. 4 is a schematic diagram of a supercritical carbon dioxide Brayton cycle direct cooling space stack system.
Wherein: 1. a fuel zone; 2. a component wall; 3. a cooling flow channel; 4. cladding; 5. an air gap; 6. a core; 7. radial and axial reflective layers; 8. a pressure vessel; 9. a compressor; 10. a heat regenerator; 11. directly cooling the reactor by supercritical carbon dioxide; 12. a gas turbine; 13. a generator; 14. a precooler; 15. a radiant panel heat sink.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "one side", "one end", "one side", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. In addition, in the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
It will be understood that the terms "comprises" and/or "comprising," when used in this specification and the appended claims, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.
It is also to be understood that the terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the specification of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
It should be further understood that the term "and/or" as used in this specification and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items.
Various structural schematics according to the disclosed embodiments of the invention are shown in the drawings. The figures are not drawn to scale, wherein certain details are exaggerated and possibly omitted for clarity of presentation. The shapes of the various regions, layers and their relative sizes, positional relationships are shown in the drawings as examples only, and in practice deviations due to manufacturing tolerances or technical limitations are possible, and a person skilled in the art may additionally design regions/layers with different shapes, sizes, relative positions, according to the actual needs.
Referring to fig. 4, the brayton cycle direct cooling space reactor system for hundred kilowatts of supercritical carbon dioxide of the present invention includes a brayton cycle energy conversion system and a supercritical carbon dioxide direct cooling reactor 11.
The brayton cycle energy conversion system includes a compressor 9, a regenerator 10, a gas turbine 12, a generator 13, a precooler 14, and a radiant panel radiator 15.
The output end of the supercritical carbon dioxide direct cooling reactor 11 is connected with the fuel inlet end of a gas turbine 12, the gas turbine 12 is coaxially connected with a compressor 9 and a generator 13, the gas outlet end of the compressor 9 is connected with the input end of the supercritical carbon dioxide direct cooling reactor 11 through the cold side of a heat regenerator 10, and the gas outlet end of the gas turbine 12 is connected with the gas inlet end of the compressor 9 through the hot side of the heat regenerator 10 and the hot side of a precooler 14; the cold side outlet of the precooler 14 is connected to the cold side inlet of the precooler 14 via a radiant panel radiator 15.
Wherein the compressor 9, the gas turbine 12 and the generator 13 are coaxially arranged and have the same rotational speed.
The efficiency of the compressor 9 was 91%, the pressure ratio was 2, the inlet pressure was 8MPa, and the inlet temperature was 232.57 ℃.
The heat regenerator 10 adopts a printed circuit plate heat exchanger, the heat regeneration capacity is 55.5kW/K, the mass is 133.645kg, and the minimum temperature difference between the cold side and the hot side is 10.2 ℃.
The efficiency of the gas turbine 12 was 94%, the pressure ratio was 2 and the inlet pressure was 16MPa.
The power of the generator 13 is 100kWe.
The radiator 15 adopts a heat pipe radiator, the temperature of a heat trap is 200K, and the area of a radiation plate is 120m 2 The mass was 810kg.
Referring to fig. 3, the main structure of the supercritical carbon dioxide direct cooling reactor 11 includes a pressure vessel 8, a radial and axial reflector 7 and a core 6, the core 6 is sleeved in the pressure vessel 8, the radial and axial reflector 7 is disposed between the core 6 and the pressure vessel 8, and the core 6 is a TID fuel assembly.
The ratio of the height to the diameter of the active zone of the core 6 is 1, and on the basis of this, the correspondence between the critical core diameter and the volume fraction of fuel is investigated. According to the method, the maximum temperature of the fuel is limited as a constraint condition, a plurality of groups of reactor core structures and system operation parameters meeting the constraint condition under the input condition are calculated and obtained, the quality minimum value is obtained by comparing the system quality, and finally the corresponding reactor structure and system operation parameters are obtained.
Referring to fig. 1, the tid fuel assembly is hexagonal and comprises two layers from inside to outside, namely a fuel zone 1 directly cooled by supercritical carbon dioxide and an assembly wall 2.
The material of the fuel region 1 is dispersed UO 2 BeO matrix of the particles.
The material of the module wall 2 is 304 stainless steel.
Referring to fig. 2, the coolant passage includes a cooling flow passage 3, a cladding 4, and an air gap 5.
The material of the envelope 4 is 304 stainless steel.
The gas filled in the air gap 5 is carbon dioxide.
The material of the reflective layer 7 is graphite.
The material of the pressure vessel 8 is 304 stainless steel.
The energy conversion efficiency of the supercritical carbon dioxide Brayton cycle direct cooling space reactor system is 21.74 percent, and the mass is 1082.072kg.
The working principle of the supercritical carbon dioxide Brayton cycle direct cooling space reactor system is as follows:
when the system operates, carbon dioxide is compressed and pressurized by the compressor 9, then enters the cold side of the heat regenerator 10 to absorb a part of heat, enters the reactor 11 to further absorb the heat through directly cooling a fuel area, flows to the gas turbine 12 after reaching 600 ℃, pushes the shaft to rotate to enable the generator 13 to generate electricity, the working medium with reduced pressure and higher temperature enters the hot side of the heat regenerator 10 to transfer the heat to the working medium at the cold side, then is radiated to the space environment by the radiation plate radiator 15 through the precooler 14, and the cooled working medium flows to the compressor to complete one thermal cycle.
In conclusion, the hundred-kilowatt-level supercritical carbon dioxide Brayton cycle direct cooling space reactor system has the characteristics that the electric power is 100kWe, the thermal power of the reactor is 460kWt, the thermal efficiency of the system is 21.74%, the outlet temperature of the reactor core is 600 ℃, the lowest cycle pressure is 8MPa, the highest cycle pressure is 16MPa, and the system mass is 1082.072kg, and the system has the advantages of being simple, compact in structure and low in emission cost.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (10)
1. The Baikwatt-level supercritical carbon dioxide Brayton cycle direct cooling space reactor system is characterized by comprising a supercritical carbon dioxide direct cooling reactor (11), wherein the output end of the supercritical carbon dioxide direct cooling reactor (11) is connected with the fuel inlet end of a gas turbine (12), the gas turbine (12) is coaxially connected with a compressor (9) and a generator (13), the gas outlet end of the compressor (9) is connected with the input end of the supercritical carbon dioxide direct cooling reactor (11) through the cold side of a heat regenerator (10), and the gas outlet end of the gas turbine (12) is connected with the gas inlet end of the compressor (9) through the hot side of the heat regenerator (10) and the hot side of a precooler (14); the cold side outlet of the precooler (14) is connected with the cold side inlet of the precooler (14) through a radiation plate radiator (15).
2. The hundred kilowatt-class supercritical carbon dioxide brayton cycle direct cooled spacereactor system of claim 1 wherein the supercritical carbon dioxide direct cooled reactor (11) comprises a core (6), the core (6) is disposed within a pressure vessel (8), and radial and axial reflectors (7) are disposed between the core (6) and the pressure vessel (8).
3. The hundred kilowatt-level supercritical carbon dioxide brayton cycle direct cooled space reactor system according to claim 2, characterized in that the core (6) is composed of several TID-type fuel assemblies.
4. A hundred kilowatt-class supercritical carbon dioxide brayton cycle direct cooled space stack system according to claim 3, characterized in that the TID type fuel assembly comprises an assembly wall (2), the inside of the assembly wall (2) being provided with a fuel zone (1) directly cooled by supercritical carbon dioxide.
5. The hundred kilowatt-class supercritical carbon dioxide brayton cycle direct cooled space stack system according to claim 4, characterized in that the module walls (2) are of hexagonal structure.
6. Hundred kilowatt-class supercritical carbon dioxide brayton cycle direct cooled spacestack system according to claim 4, characterized in that dispersed UO is located in fuel zone (1) 2 BeO matrix of the particles.
7. The hundred kilowatt-class supercritical carbon dioxide brayton cycle direct cooled spacestack system of claim 2 wherein the length to diameter ratio of the core (6) is 1.
8. The hundred-kilowatt-level supercritical carbon dioxide brayton cycle direct cooled space reactor system according to claim 2, characterized in that a plurality of coolant channels are uniformly distributed in the core (6).
9. The hundred-kilowatt-level supercritical carbon dioxide brayton cycle direct cooling space stack system according to claim 7, characterized in that the coolant channel comprises a cooling flow channel (3), a cladding (4) and an air gap (5) in sequence from inside to outside.
10. The hundred kilowatt-class supercritical carbon dioxide brayton cycle direct cooled spacestack system of any one of claims 1-9 wherein the energy conversion efficiency of the supercritical carbon dioxide brayton cycle direct cooled spacestack system is 21.74%.
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| CN202211370103.8A CN115691852A (en) | 2022-11-03 | 2022-11-03 | Hundred-kilowatt-level supercritical carbon dioxide Brayton cycle direct cooling space reactor system |
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| CN202211370103.8A CN115691852A (en) | 2022-11-03 | 2022-11-03 | Hundred-kilowatt-level supercritical carbon dioxide Brayton cycle direct cooling space reactor system |
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