CN112199811B - Method and device for determining reactor core parameters of nuclear thermal propulsion reactor - Google Patents

Abstract

The invention provides a method and device for determining core parameters of a nuclear thermal propulsion reactor, relating to the technical field of nuclear thermal propulsion. The method includes: obtaining a fluid-solid coupling heat transfer model of a nuclear thermal propulsion reactor; obtaining a target that satisfies the performance constraints of an aircraft Dynamic parameters, and based on the target dynamic parameters, conduct heat transfer calculations on the fluid-solid coupling heat transfer model, and obtain multiple sets of design parameters that meet thermal constraints; where, each set of design parameters includes geometric parameters and thermal parameters; based on multiple sets of design parameters The neutronics modeling and physical analysis are carried out to obtain the target geometric parameters and target thermal parameters satisfying the neutron physical constraints; the target dynamic parameters, target thermal parameters and target geometric parameters are used as the core design parameters of the nuclear thermal reactor. The invention can improve the reliability of core parameter design in low-enrichment uranium nuclear thermal propulsion reactor.

Description

Method and device for determining core parameters of nuclear thermal propulsion reactor

technical field

The invention relates to the technical field of nuclear thermal propulsion, in particular to a method and device for determining core parameters of a nuclear thermal propulsion reactor.

Background technique

Thermonuclear propulsion refers to the use of nuclear fission energy to heat the working medium, and then directional ejection of the heated high-temperature and high-pressure working medium to obtain thrust. Nuclear thermal propulsion reactors usually use high-enrichment (>90%) enriched uranium as nuclear fuel since the 1950s and 1960s. In order to reduce the risk of nuclear proliferation and reduce research and development costs, researchers are designing low-enrichment enrichment uranium in recent years. Uranium (<20%) nuclear thermal propulsion reactors. However, for nuclear thermal propulsion reactor low-enrichment enriched uranium core parameter design, at present, researchers only make appropriate modifications on the basis of referring to high-enrichment enriched uranium core design parameters, therefore, the existing low-enrichment There is also the problem of low reliability in the core parameter design method in the intensively enriched uranium nuclear thermal propulsion reactor.

Contents of the invention

In view of this, the object of the present invention is to provide a method and device for determining core parameters of a nuclear thermal propulsion reactor, which can improve the reliability of core parameter design in a low-enrichment uranium nuclear thermal propulsion reactor.

In order to achieve the above object, the technical solution adopted in the embodiment of the present invention is as follows:

In the first aspect, an embodiment of the present invention provides a method for determining core parameters of a nuclear thermal propulsion reactor, including: obtaining a fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor; obtaining target dynamic parameters satisfying aircraft performance constraints, And based on the target dynamic parameters, heat transfer calculations are performed on the fluid-solid coupling heat transfer model to obtain multiple sets of design parameters that meet thermal constraints; wherein, each set of design parameters includes geometric parameters and thermal parameters; based on Perform neutronics modeling and physical analysis on multiple sets of design parameters to obtain target geometric parameters and target thermal parameters satisfying neutron physical constraints; The parameters are used as the core design parameters of the nuclear thermal reactor.

Further, the embodiment of the present invention provides the first possible implementation of the first aspect, wherein the geometric parameters include the core height, core radius and coolant flow path diameter; The step of the solid coupling heat transfer model, comprising: based on the height of the core, the radius of the core and the diameter of the coolant flow channel, respectively determining the structure of the fuel assembly and the structure of the moderator assembly in the nuclear thermal reactor; based on the structure of the fuel assembly , the structure of the moderator component and the flow direction of the coolant to obtain a fluid-solid coupling heat transfer model of the nuclear thermal reactor.

Furthermore, the embodiment of the present invention provides a second possible implementation of the first aspect, wherein both the fuel assembly structure and the moderation assembly structure are prism structures, and the fuel assembly structure and the moderation assembly The structure has the same height and cross-sectional shape, the fuel assembly structure includes a plurality of coolant flow channels, the moderator assembly structure includes a second coolant flow channel, and the flow direction of the coolant is from the second coolant The flow channels flow to first coolant flow channels, which are respective coolant flow channels in the fuel assembly structure.

Further, the embodiment of the present invention provides a third possible implementation manner of the first aspect, wherein the thermal parameters include the core outlet temperature; The step of performing heat transfer calculations to obtain multiple sets of design parameters satisfying thermal constraints includes: performing axial heat transfer calculations and radial heat transfer calculations on the fluid-solid coupling heat transfer model based on the target dynamic parameters to obtain the obtained The wall temperature of the coolant flow channel, the fuel center temperature, the mainstream temperature at any axial position, the core outlet temperature, and the geometric parameters corresponding to the core outlet temperature; repeat the above axial heat transfer calculation and radial heat transfer calculation. Thermal calculation, until the first preset condition is reached, to obtain multiple sets of the design parameters.

Further, the embodiment of the present invention provides a fourth possible implementation manner of the first aspect, wherein the first preset condition includes: the temperature of the fuel center reaches the maximum temperature of the fuel, and/or the structure of the moderator component slows down The temperature of the moderator reaches the maximum temperature of the moderator.

Further, the embodiment of the present invention provides a fifth possible implementation of the first aspect, wherein the geometric parameters include core height, core radius, and coolant flow channel diameter; the design parameters are based on multiple sets of The steps of performing neutronics modeling and physical analysis to obtain target geometric parameters and target thermal parameters satisfying neutron physical constraints include: selecting any set of design parameters from multiple sets of design parameters to obtain the first design parameters , performing neutronics modeling based on the geometric parameters in the first design parameters to obtain a target model; performing reactor physics analysis on the target model to obtain physical parameters of the target model; judging whether the physical parameters meet the first requirement Two preset conditions, if yes, using the geometric parameters and thermal parameters in the first design parameters as the target geometric parameters and target thermal parameters respectively.

Further, the embodiment of the present invention provides a sixth possible implementation manner of the first aspect, wherein the physical parameters include the effective multiplication coefficient of the core; the step of judging whether the physical parameters meet the second preset condition includes: Judging whether the effective multiplication coefficient is greater than 1, and if so, determining that the physical parameter satisfies the second preset condition.

Further, the embodiment of the present invention provides a seventh possible implementation manner of the first aspect, wherein the method further includes: if the physical parameters do not meet the second preset condition, selecting from multiple groups of the design parameters Select any set of design parameters except the first design parameters in the first design parameters to obtain new first design parameters; perform neutronics modeling and physical analysis based on the geometric parameters in the new first design parameters, until The target geometric parameters and target thermal parameters are obtained.

In the second aspect, the embodiment of the present invention also provides a nuclear thermal propulsion reactor core parameter determination device, including: an acquisition module, used to acquire the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor; a calculation module, used Obtaining target dynamic parameters satisfying aircraft performance constraints, and performing heat transfer calculations on the fluid-solid coupling heat transfer model based on the target dynamic parameters, to obtain multiple sets of design parameters satisfying thermal constraints; wherein, each set of design parameters The parameters include geometric parameters and thermal parameters; the analysis module is used to perform neutronics modeling and physical analysis based on multiple sets of design parameters, and obtain target geometric parameters and target thermal parameters that meet neutron physical constraints; parameter determination A module for using the target power parameter, the target thermal parameter and the target geometric parameter as core design parameters of the nuclear thermal reactor.

In a third aspect, an embodiment of the present invention provides a computer-readable storage medium, where a computer program is stored on the computer-readable storage medium, and when the computer program is run by a processor, it executes any one of the above-mentioned first aspects. steps of the method.

Embodiments of the present invention provide a method and device for determining core parameters of a nuclear thermal propulsion reactor. The method includes: first obtaining a fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor; obtaining target dynamic parameters that meet the performance constraints of the aircraft, and Based on the target dynamic parameters, the heat transfer calculation of the fluid-solid coupling heat transfer model is carried out to obtain multiple sets of design parameters that meet the thermal constraints (each set of design parameters includes geometric parameters and thermal parameters); based on multiple sets of design parameters, the neutron science construction Through model and physical analysis, the target geometric parameters and target thermal parameters satisfying the neutron physical constraints are obtained; the target dynamic parameters, target thermal parameters and target geometric parameters are used as the core design parameters of the nuclear thermal reactor. In this method, based on the target dynamic parameters that satisfy the performance constraints of the aircraft, the heat transfer calculation is performed on the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor, and neutronics modeling and physical analysis are performed to obtain Constraints, thermal constraints, and neutron physical constraints ensure the effectiveness of core design parameters. This method can be applied to the determination of core design parameters for low-enrichment Reliability of Core Parameter Design in Intensively Enriched Uranium Nuclear Thermal Propulsion Reactors.

Other features and advantages of the embodiments of the present invention will be described in the following descriptions, or some of the features and advantages can be inferred or unambiguously determined from the descriptions, or can be known by implementing the above-mentioned techniques of the embodiments of the present invention.

In order to make the above-mentioned objects, features and advantages of the present invention more comprehensible, preferred embodiments will be described in detail below together with the accompanying drawings.

Description of drawings

In order to more clearly illustrate the specific implementation of the present invention or the technical solutions in the prior art, the following will briefly introduce the accompanying drawings that need to be used in the specific implementation or description of the prior art. Obviously, the accompanying drawings in the following description The drawings show some implementations of the present invention, and those skilled in the art can obtain other drawings based on these drawings without any creative work.

Fig. 1 shows a flow chart of a method for determining core parameters of a nuclear thermal propulsion reactor provided by an embodiment of the present invention;

Fig. 2 shows a top view of a fluid-solid coupling heat transfer model provided by an embodiment of the present invention;

Fig. 3 shows a side cut view of a fluid-solid coupling heat transfer model provided by an embodiment of the present invention;

Fig. 4 shows a kind of low-enrichment enriched uranium core parameter design flowchart provided by the embodiment of the present invention;

Fig. 5 shows a schematic structural diagram of a nuclear thermal propulsion reactor core parameter determination device provided by an embodiment of the present invention;

Fig. 6 shows a schematic structural diagram of an electronic device provided by an embodiment of the present invention.

icon:

011-first coolant channel; 012-second coolant channel; 013-third coolant channel; 014-zirconium hydride material; 015-zirconium-4 material; 016-zirconium carbide material; 017-graphite material ; 018-tungsten-uranium dioxide material; 021-core entrance; 022-core exit.

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them.

At present, considering the core parameter design method of the existing nuclear thermal propulsion reactor, there is still a problem of low reliability. In order to improve this problem, a method for determining the core parameter of the nuclear thermal propulsion reactor provided by the embodiment of the present invention And devices, this technology can be applied to improve the reliability of core parameter determination for low-enrichment enriched uranium. The following describes the embodiments of the present invention in detail.

This embodiment provides a method for determining the core parameters of a nuclear thermal propulsion reactor, which can be applied to the parameter design of a low-enrichment uranium nuclear thermal propulsion reactor, see the nuclear thermal propulsion reactor stack shown in Figure 1 A flowchart of a method for determining core parameters, the method mainly includes the following steps S102 to S106:

Step S102, obtaining a fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor.

Since there are two different components in the nuclear thermal propulsion reactor core: the fuel assembly and the moderator assembly, by determining the geometric parameters of the core (that is, the size and shape of the fuel assembly and the moderator assembly), and analyzing the internal nuclear thermal propulsion reactor The fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor can be established based on the flow law of the coolant. Through the fluid-solid coupling heat transfer model, the heat transfer process of the coolant, the fuel assembly and the moderator assembly in the core of the nuclear thermal propulsion reactor can be simulated and calculated.

Step S104, obtaining target dynamic parameters satisfying the performance constraints of the aircraft, and performing heat transfer calculation on the fluid-structure coupling heat transfer model based on the target dynamic parameters, and obtaining multiple sets of design parameters satisfying thermal constraints.

The above dynamic parameters include parameters such as specific impulse and thrust. According to the value range of the dynamic parameters, the dynamic parameter values that meet the performance constraints of the aircraft are determined to obtain the target dynamic parameters. Usually, the specific impulse value in the nuclear thermal propulsion system should be as high as possible. The value of the specific impulse (also called the specific impulse, which is the impulse generated by the unit amount of propellant) may be around 900s.

Each set of design parameters above includes a geometric parameter and a thermal parameter, the thermal parameter may be the core outlet temperature, and the geometric parameter may be the core height, radius, and coolant channel diameter. In the process of heat transfer calculation of the fluid-solid coupling heat transfer model, each round of iterative calculation can obtain a set of design parameter values (core outlet temperature, and corresponding geometric parameter values), when the above iterative calculation meets the thermal convergence When conditions are met, multiple sets of design parameters that satisfy thermal constraints can be obtained.

In step S106, neutronics modeling and physical analysis are performed based on multiple sets of design parameters to obtain target geometric parameters and target thermal parameters satisfying neutron physical constraints.

From the multiple sets of design parameters obtained in the above step S104, obtain any set of design parameters for secondary modeling, and perform physical analysis on the obtained model, so as to screen out the geometry that meets the neutron physical constraints from the above multiple sets of design parameters. parameters and thermal parameters to obtain the target geometric parameters and target thermal parameters.

Step S108, using the target dynamic parameters, target thermal parameters and target geometric parameters as core design parameters of the nuclear thermal reactor.

The target dynamic parameters, target thermal parameters and target geometric parameters calculated above are the design parameters that satisfy the performance constraints, thermal constraints and neutron physical constraints of the aircraft. The values of the target dynamic parameters, target thermal parameters and target geometric parameters of physical constraints are used as the core design parameters of the nuclear thermal propulsion reactor.

The method for determining the core parameters of the above-mentioned nuclear thermal propulsion reactor provided in this embodiment is to calculate the heat transfer of the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor based on the target dynamic parameters satisfying the performance constraints of the aircraft, and conduct neutronics Modeling and physical analysis can obtain core design parameters that simultaneously satisfy aircraft performance constraints, thermal constraints, and neutron physical constraints, ensuring the validity of core design parameters. This method can be applied to low-enrichment enriched uranium The determination of the core design parameters improves the reliability of core parameter design in low-enrichment uranium nuclear thermal propulsion reactors.

In order to accurately obtain the fluid-solid coupling heat transfer model, this embodiment provides a specific implementation method for obtaining the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor: based on the core height, core radius and coolant flow channel diameter, respectively determine Fuel assembly structure and moderator assembly structure in nuclear thermal reactor. Based on the structure of the fuel assembly, the structure of the moderator assembly and the flow direction of the coolant, the fluid-solid coupling heat transfer model of the nuclear thermal reactor is obtained. The above-mentioned core height, core radius and coolant flow path diameter are the geometric parameters of the nuclear thermal propulsion reactor core. Since the core includes fuel assemblies and moderator assemblies, the above-mentioned core height includes the height of the fuel assemblies and the moderator assemblies. The above-mentioned core radius includes the radius of the cross-section of the fuel assembly and the radius of the cross-section of the moderator assembly, and the diameter of the coolant flow channel includes the diameter of the coolant flow channel in the fuel assembly structure and the diameter of the cooling channel in the moderator assembly structure.

In a specific embodiment, the above-mentioned fuel assembly structure and moderator assembly structure are both prism structures, and the height and cross-sectional shape of the above-mentioned fuel assembly structure and moderator assembly structure are the same, see the fluid-solid coupling as shown in Figure 2 The top view of the heat transfer model, the hexagonal prism on the left in Figure 2 is the structure of the fuel assembly, and the hexagonal prism on the right is the structure of the moderator assembly, as shown in Figure 2, the above-mentioned fuel assembly structure is a hexagonal prism-shaped tungsten-uranium dioxide material 018, there are a plurality of cylindrical coolant flow passages evenly distributed in the prism structure (multiple circles are used to represent the cross section of the flow passage in Figure 2), which can be represented by the first coolant flow passage 011, each flow in the fuel assembly structure All channels can be used as the first coolant flow channel 011. The moderator assembly structure includes the second coolant flow channel 012 and the third coolant flow channel 013. The third coolant flow channel 013 is a cylindrical channel located in the moderator In the center of the component structure, the second coolant flow channel 012 is a circular channel, and the space between the second coolant flow channel 012 and the third coolant flow channel 013 is filled with zirconium hydride material 014 and zirconium-4 material 015. The periphery of the coolant channel 012 is sequentially composed of zirconium-4 material 015, zirconium carbide material 016 and graphite material 017, wherein the ring width values of various materials can be set according to actual conditions. Referring to the side cut view of the fluid-solid coupling heat transfer model shown in Figure 3, the coolant flows and heats from the core inlet 021 into the third coolant flow channel 013 (also called flow channel 3), and then from the third cooling The coolant flow channel 013 to the second coolant flow channel 012 (also called flow channel two) to the first coolant flow channel 011 (also called flow channel one), flows out from the core outlet 022 (as shown in Fig. 3 In practical application, the flow direction of the coolant can be simplified as entering the second coolant flow channel 012 from the core inlet 021 to the first coolant flow channel 011 (each coolant flow in the fuel assembly Both channels can be used as flow channels 1), flowing out from the core outlet 022 (as shown in the right figure in Figure 3), that is, the flow direction of the coolant is from the second coolant flow channel 012 to the first coolant flow channel 011 , the first coolant flow channel 011 is each coolant flow channel in the fuel assembly structure.

In order to obtain design parameters satisfying thermal constraints, this embodiment provides an implementation method of performing heat transfer calculation on the fluid-solid coupling heat transfer model based on target dynamic parameters to obtain multiple sets of design parameters satisfying thermal constraints. For details, refer to the following steps ( 1) ~ step (2) execution:

Step (1): Calculate the axial heat transfer and radial heat transfer of the fluid-solid coupling heat transfer model based on the target dynamic parameters, and obtain the wall temperature of the coolant channel, the temperature of the fuel center, the mainstream temperature at any axial position, The core outlet temperature and the geometric parameters corresponding to the core outlet temperature.

As shown in FIG. 3 , T _M in the left figure is the wall surface temperature of the second coolant flow channel 012 away from the fuel assembly, and _Tw is the wall surface temperature of the second coolant flow channel 012 near the fuel assembly side. T _Mn in the figure on the right is the discrete value of the wall temperature on the side away from the fuel assembly in the second coolant channel 012 in the axial direction (the highest temperature of the moderator is the maximum value of T _Mn ), and T _Fn is A discrete value of the temperature of the wall surface of the second coolant channel 012 near the side of the fuel assembly in the axial direction (the highest temperature of the fuel center is the maximum value of T _Fn ).

Axial (Z direction in Figure 3) heat transfer calculations are performed on the fluid-solid coupling heat transfer model, a small part of the coolant flows in from the third coolant flow channel 013 of the moderator component, and finally flows into the fuel through the second coolant flow channel 012 Most of the coolant passes through the first coolant flow channel 011 of the fuel assembly FE from top to bottom at one time.

为流量分配系统分配给堆芯内全部慢化组件的冷却剂质量流量，

为流量分配系统分配给堆芯内全部燃料组件的冷却剂质量流量，由于慢化组件内的冷却剂将回流到燃料组件进行二次冷却，如图3所示，因此流经全部燃料组件的质量流量

等于

与

二者之和。

is the coolant mass flow distributed by the flow distribution system to all moderating components in the core,

is the mass flow rate of coolant distributed to all fuel assemblies in the core by the flow distribution system, since the coolant in the moderator assembly will flow back to the fuel assemblies for secondary cooling, as shown in Figure 3, the mass flow through all fuel assemblies flow

equal

and

sum of both.

与推力和比冲的关系如下公式total mass flow in the core

The relationship with thrust and specific impulse is as follows

Among them, I _sp is the specific impulse of the dynamic parameter of the aircraft, F is the thrust of the dynamic parameter of the aircraft, g ₀ is the acceleration of gravity, and the specific impulse I _sp and the core outlet temperature T _e (thermal parameters) satisfy the following relationship:

γ in the above formula is the ratio of heat capacity at constant pressure to heat capacity at constant volume, which is called specific heat capacity ratio. R is the Boltzmann constant, and M is the relative molecular mass of the coolant.

为：Coolant mass flow through individual moderator components

for:

α is the proportion of the mass flow rate of coolant flowing through all moderator components in the total mass flow rate of the core, expressed by the following formula:

N _ME is the number of moderator components in the core, let N _FE be the number of fuel components in the core, there are:

N _FE +N _ME =N ₀

N ₀ is the total number of components in the core, and the calculation formula of N ₀ is as follows:

N ₀ ≈πr ² /S ₀

where r is the radius of the active area of the core, and S ₀ is the cross-sectional area of the hexagonal component.

Introducing the number ratio β ₀ of moderator components to fuel components, we have:

β ₀ =N _ME /N _FE

The size of _β0 can be adjusted according to the different arrangement rules of components in the stack.

出口温度为T₂的冷却剂经第二冷却剂流道012流出，与质量流量为

温度为T₁的冷却剂混合进入第二冷却剂流道011，则混合后冷却剂的入口温度T₀满足下面的关系式：According to energy conservation, the mass flow rate is

The coolant whose outlet temperature is _T2 flows out through the second coolant channel 012, and the mass flow rate is

The coolant at temperature _T1 is mixed into the second coolant channel 011, then the inlet temperature _T0 of the mixed coolant satisfies the following relationship:

In order to accurately calculate the maximum temperature of the fuel and the maximum temperature of the moderator in the axial direction, n nodes are divided on the axial Z, as shown in Fig. 3 . The inner wall surface temperature and mainstream temperature of each node of each flow channel satisfy:

-q=h(T _w -T _b )

In the above formula, q is the heat flux density, _Tw is the wall temperature, h is the convective heat transfer coefficient, and the mainstream temperature _Tb of adjacent nodes satisfies the following relationship:

同时功率分布呈现余弦分布，那流动方向上任意轴向位置z处的主流温度可以根据下面的公式计算：q _n is the heat generated by the flow at node n (that is, the heat obtained by the product of the heat flux at node n and the heat transfer area), c _p is the specific heat capacity, assuming that the linear power density of the coolant channel is q _l , the length of the channel is L, the mass flow rate is

At the same time, the power distribution presents a cosine distribution, so the mainstream temperature at any axial position z in the flow direction can be calculated according to the following formula:

The radial (X direction in Figure 3) heat transfer calculation is performed on the fluid-solid coupling heat transfer model, and the radial direction mainly focuses on the heat transfer from FE (fuel assembly) to ME (moderation assembly). The heat transfer from T _Fn (fuel center temperature) to T _Mn (moderator surface temperature) can be regarded as the heat conduction of a multi-layer flat plate without internal heat source, then the heat flow Φ ₂ of FE to ME:

为T_Fn与T_Mn之间材料的热阻，d_i为第i层材料的厚度，λ_i为第i层材料的热导率，A₀为两个组件的接触导热面积，A₀＝L*H，L是六边形组件截面的边长，H是堆芯活性区高度。若单个燃料组件冷却剂通道带走的热量为Φ₁，则有

is the thermal resistance of the material between T _Fn and T _Mn , d _i is the thickness of the i-th layer material, λ _i is the thermal conductivity of the i-th layer material, A ₀ is the contact heat transfer area of the two components, A ₀ =L *H, L is the side length of the cross-section of the hexagonal component, and H is the height of the active area of the core. If the heat taken away by the coolant channel of a single fuel assembly is Φ ₁ , then there is

p＝Φ ₁ +β ₁ Φ ₂

_β1 represents the average number of fuel assemblies adjacent to each moderator assembly in the core, and p is the power emitted by a single fuel assembly. According to the power p emitted by the fuel assembly, the linear power density q _l and the fuel center temperature in the axial heat transfer calculation can be further determined.

Under the premise of given initial aircraft performance parameters such as thrust (25kN～75kN) and thermal initial parameters such as core inlet temperature (about 120K), the thermal parameters of the reactor can be obtained by simultaneously programming and iteratively solving the above equations (core outlet temperature) and core geometric parameters (core height, radius and coolant flow channel diameter). The convergence criteria in the above iterative calculation include: the maximum temperature of the fuel center max(T _Fn )<3000K, and the maximum temperature of the moderator surface max(T _Mn )<773K. In each round of iterative calculation, a set of design parameters (ie core outlet temperature and corresponding core geometric parameters) satisfying thermal constraints can be obtained.

Step (2): The above-mentioned axial heat transfer calculation and radial heat transfer calculation are repeatedly performed until the first preset condition is reached, and multiple sets of design parameters are obtained.

The above-mentioned first preset condition includes: the temperature of the fuel center reaches the maximum temperature of the fuel, and/or the temperature of the moderator in the structure of the moderator component reaches the maximum temperature of the moderator. The above-mentioned first preset condition is the end sign of the above-mentioned heat transfer calculation. Repeat the axial heat transfer calculation and radial heat transfer calculation in the above step (1), when the fuel center temperature and/or the moderator in the moderator assembly When the temperature of the agent satisfies the above-mentioned first preset condition, the convergence condition is reached, and the above-mentioned heat transfer calculation ends, that is, when the fuel center temperature in the above-mentioned fluid-solid coupling heat transfer model reaches the maximum temperature of the fuel, or when the above-mentioned moderator component structure When the temperature of the moderator reaches the maximum temperature of the moderator, it is determined that the above heat transfer calculation has reached the thermal convergence condition, and the above heat transfer calculation is stopped so that the fuel center temperature (including the maximum value of the fuel center temperature) reaches the maximum fuel temperature and and/or the moderator temperature in the moderator assembly (including the maximum in moderator temperature) reaches the moderator maximum temperature. Since a set of design parameters can be obtained in each heat transfer calculation, multiple sets of design parameters can be obtained after multiple rounds of heat transfer calculations. In practical application, the maximum temperature of the above-mentioned fuel is less than 3000K, and the maximum temperature of the above-mentioned moderator is less than 773K. The temperature of the moderator mentioned above may be the temperature T _M of the wall surface of the second coolant channel 012 away from the fuel assembly. When the maximum value of the discrete values T _Mn in the axial direction reaches the highest temperature of the moderator, the above heat transfer rate is determined. The calculation has reached the thermal convergence condition. The above-mentioned fuel center temperature is the wall surface temperature of the second coolant flow channel 012 near the fuel assembly side. When the maximum value of the discrete value T _Fn in the axial direction reaches the maximum temperature of the fuel, it is determined that the above-mentioned heat transfer calculation has reached thermal convergence condition.

In order to obtain design parameters satisfying neutron physical constraints, this embodiment provides an implementation mode in which neutronics modeling and physical analysis are performed based on multiple sets of design parameters, and target geometric parameters and target thermal parameters satisfying neutron physical constraints are obtained. For details, please refer to the following steps 1 to 3:

Step 1: Select any set of design parameters from multiple sets of design parameters to obtain the first design parameters, and perform neutronics modeling based on the geometric parameters in the first design parameters to obtain the target model.

Since each set of design parameters above includes geometric parameters and thermal parameters, the geometric parameters include core height, core radius and coolant flow path diameter, neutronics modeling is performed based on the geometric parameters in any set of design parameters , the target model corresponding to the geometric parameters can be obtained.

Step 2: Perform reactor physics analysis on the target model to obtain the physical parameters of the target model.

By performing reactor physical analysis on the target model obtained from the above-mentioned neutronics modeling, the physical parameters of the target model can be analyzed, such as the effective multiplication coefficient of the core and the like.

Step 3: judging whether the physical parameters satisfy the second preset condition, if yes, using the geometric parameters and thermal parameters in the first design parameters as target geometric parameters and target thermal parameters respectively.

According to the size of the effective multiplication coefficient of the above-mentioned core, it is judged whether the above-mentioned physical parameters meet the second preset condition, specifically, it can be judged whether the above-mentioned effective multiplication coefficient is greater than 1, and if the above-mentioned effective multiplication coefficient is greater than 1, it is determined that the physical parameters meet the second preset condition condition. When the above physical parameters meet the second preset condition, it indicates that the target model obtained by modeling the geometric parameters in the first design parameters meets the neutron physical constraints, that is, the first design parameters meet the neutron physical constraints, and the first The geometric parameters in the design parameters are used as the target geometric parameters, and the thermal parameters in the same group as the target geometric parameters are used as the target thermal parameters.

Considering that when the above physical parameters do not meet the above second preset condition, the method provided in this embodiment further includes: if the physical parameter does not meet the second preset condition, selecting one of the multiple groups of design parameters except the first design parameter Based on any set of design parameters outside the new first design parameters, new first design parameters are obtained; neutronics modeling and physical analysis are performed based on the geometric parameters in the new first design parameters until the target geometric parameters and target thermal parameters are obtained. When the above-mentioned physical parameters do not meet the second preset condition, select any set of design parameters from the above-mentioned multiple sets of design parameters except the above-mentioned first design parameters as a new first design parameter, or combine the above-mentioned multiple sets of design parameters The parameters are successively used as new first design parameters, and the above steps 1 to 3 are repeated based on the new first design parameters until the target geometric parameters and target thermal parameters satisfying neutron physical constraints are obtained.

The core parameter determination method of the above-mentioned nuclear thermal propulsion reactor provided in this embodiment provides a complete calculation idea for the parameter design of the low-enrichment enriched uranium core of the nuclear thermal propulsion reactor. Using a reasonably established simplified heat transfer model, it is suitable for The different number distribution and arrangement rules of fuel assemblies and moderator assemblies in the core are also applicable to the different distribution of coolant mass flow in the two assemblies, which can be conveniently and flexibly tailored to different assembly arrangements and The flow distribution is optimally designed, and the effectiveness of the design parameters is guaranteed through three constraints: aircraft performance constraints, thermal hydraulic constraints, and neutron physical constraints.

On the basis of the above-mentioned embodiments, this embodiment provides an example of applying the core parameter determination method of the aforementioned nuclear thermal propulsion reactor to design the parameters of the low-enrichment enriched uranium core. For details, please refer to the following steps a to steps d execute:

Step a: Determine the target power parameters that satisfy the performance constraints of the aircraft in the nuclear thermal propulsion reactor, and determine the value ranges of the geometric parameters and thermal parameters in the nuclear thermal propulsion reactor.

The aforementioned dynamic parameters include parameters such as specific impulse and thrust, the aforementioned geometric parameters include core height, radius, coolant flow path diameter, etc., and the aforementioned thermal parameters include core outlet temperature, etc. Referring to the flow chart of core parameter design for low-enrichment enriched uranium shown in Fig. 4, firstly, according to the initial performance of the aircraft, the target power parameters satisfying the constraints of the aircraft are determined, and then the selection of geometric parameters and thermal parameters in the nuclear thermal propulsion reactor is set. range of values.

Step b: Determine the fluid-solid coupling heat transfer model based on the flow law of the coolant inside the nuclear thermal propulsion reactor.

The above fluid-solid coupling heat transfer model satisfies the following conditions: 1) There are two different components in the core: the fuel component and the moderator component. The structure inside the moderator component is relatively complicated. The materials and structures of the two components are shown in Figure 2; 2) Between the highest temperature point S1 of the fuel and the temperature point S2 on the inner wall surface of the second coolant channel 012 of the moderator component 3) The coolant flow heat exchange from the third coolant flow channel 013 to the second coolant flow channel 012 and then to the first coolant flow channel 011 is simplified to flow from the second coolant flow Channel 012 to the first coolant flow channel 011; 4) The core heat obeys the cosine distribution in the axial direction.

Step c: Perform heat transfer calculations on the fluid-solid coupling heat transfer model above to obtain multiple sets of design parameters that satisfy thermal constraints.

The above multiple sets of design parameters (including geometric parameters and thermal parameters) can constitute the value range of the design parameters. Through the above heat transfer calculation, the mainstream temperature, wall surface temperature and fuel center temperature of the corresponding coolant flow channel can be obtained, and the thermal convergence condition can be set by using the limit temperature of the fuel and the tolerance temperature of the moderator. When the above design parameters do not satisfy the thermal convergence Conditions, update the geometric parameters and thermal parameter values in the heat transfer calculation according to the above geometric parameters and thermal parameter ranges, and obtain multiple sets of design parameters that meet the thermal constraints.

Step d: Carry out neutronics modeling for each set of design parameters in the above multiple sets of design parameters in turn, and perform physical analysis on the obtained model to judge whether each set of design parameters satisfies neutron physics constraints.

When the design parameters satisfying the neutron physical constraints are obtained, the target thermal parameters and the target geometric parameters satisfying the neutron physical constraints are taken as the core design parameters, and the core design parameters calculated by the above target dynamic parameters can be further judged ( Including whether the target dynamic parameters, target thermal parameters and target geometric parameters) meet the requirements (or whether the above-mentioned core design parameters are satisfied), if the requirements are met, the low-enrichment uranium core design parameters are obtained, if the requirements are not met, The initial target power parameters (thrust and specific impulse) can be modified by returning to step a above to recalculate the design parameters until satisfactory reactor design parameters satisfying the three constraints are obtained.

Corresponding to the nuclear thermal propulsion reactor core parameter determination method provided by the above embodiments, the embodiment of the present invention provides a nuclear thermal propulsion reactor core parameter determination device, see Figure 5 for a nuclear thermal propulsion reactor Schematic diagram of the structure of the core parameter determination device, which includes the following modules:

The obtaining module 51 is used to obtain the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor.

The calculation module 52 is used to obtain the target dynamic parameters satisfying the performance constraints of the aircraft, and perform heat transfer calculation on the fluid-solid coupling heat transfer model based on the target dynamic parameters, and obtain multiple sets of design parameters satisfying the thermal constraints; wherein, in each set of design parameters Including geometric parameters and thermal parameters.

The analysis module 53 is used to perform neutronics modeling and physical analysis based on multiple sets of design parameters, and obtain target geometric parameters and target thermal parameters satisfying neutron physical constraints.

The parameter determination module 54 is used to use the target dynamic parameters, target thermal parameters and target geometric parameters as core design parameters of the nuclear thermal reactor.

The nuclear thermal propulsion reactor core parameter determination device provided in this embodiment performs heat transfer calculation on the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor based on the target dynamic parameters satisfying the performance constraints of the aircraft, and performs neutronics Modeling and physical analysis can obtain core design parameters that simultaneously satisfy aircraft performance constraints, thermal constraints, and neutron physical constraints, ensuring the validity of core design parameters. This method can be applied to low-enrichment enriched uranium The determination of the core design parameters improves the reliability of core parameter design in low-enrichment uranium nuclear thermal propulsion reactors.

In one embodiment, the above-mentioned geometric parameters include core height, core radius and coolant flow channel diameter; the acquisition module 51 is further used to determine respectively based on the core height, core radius and coolant flow channel diameter Fuel assembly structure and moderator assembly structure in nuclear thermal reactor; Based on the fuel assembly structure, moderator assembly structure and coolant flow direction, the fluid-solid coupling heat transfer model of nuclear thermal reactor is obtained.

In one embodiment, the above-mentioned fuel assembly structure and moderator assembly structure are both prismatic structures, the height and cross-sectional shape of the fuel assembly structure and the moderation assembly structure are the same, the fuel assembly structure includes a plurality of coolant channels, and the moderator The assembly structure includes a second coolant flow channel, and the flow direction of the coolant is from the second coolant flow channel to the first coolant flow channel, and the first coolant flow channel is each coolant flow channel in the fuel assembly structure.

In one embodiment, the above-mentioned thermal parameters include the core outlet temperature; the above-mentioned calculation module 52 is further used to perform axial heat transfer calculation and radial heat transfer calculation on the fluid-solid coupling heat transfer model based on the target dynamic parameters to obtain cooling The wall temperature of the agent flow channel, the temperature of the fuel center, the mainstream temperature at any axial position, the core outlet temperature, and the geometric parameters corresponding to the core outlet temperature; repeat the above axial heat transfer calculation and radial heat transfer calculation until When the first preset condition is reached, multiple sets of design parameters are obtained.

In one embodiment, the above-mentioned first preset condition includes: the temperature of the fuel center reaches the maximum temperature of the fuel, and/or the temperature of the moderator in the moderator assembly structure reaches the maximum temperature of the moderator.

In one embodiment, the above-mentioned geometric parameters include the core height, the core radius and the diameter of the coolant flow channel; the above-mentioned analysis module 53 is further used to select any set of design parameters from multiple sets of design parameters to obtain the first design Parameters, based on the geometric parameters in the first design parameters, neutronics modeling is carried out to obtain the target model; the reactor physics analysis is performed on the target model to obtain the physical parameters of the target model; whether the physical parameters meet the second preset condition is judged, if yes , taking the geometric parameter and the thermal parameter in the first design parameter as the target geometric parameter and the target thermal parameter respectively.

In one embodiment, the above-mentioned physical parameters include the effective multiplication coefficient of the core; the above-mentioned analysis module 53 is further configured to determine whether the effective multiplication coefficient is greater than 1, and if so, determine that the physical parameters meet the second preset condition.

In one embodiment, the above-mentioned device also includes:

The repeated analysis module is used to select any set of design parameters except the first design parameters from multiple sets of design parameters when the physical parameters do not meet the second preset condition to obtain new first design parameters; based on the new The geometric parameters in the first design parameters are subjected to neutronics modeling and physical analysis until the target geometric parameters and target thermal parameters are obtained.

The nuclear thermal propulsion reactor core parameter determination device provided in this embodiment provides a complete calculation idea for the parameter design of the low-enrichment enriched uranium core of the nuclear thermal propulsion reactor. Using a reasonably established simplified heat transfer model, it is suitable for The different number distribution and arrangement rules of fuel assemblies and moderator assemblies in the core are also applicable to the different distribution of coolant mass flow in the two assemblies, which can be conveniently and flexibly tailored to different assembly arrangements and The flow distribution is optimally designed, and the effectiveness of the design parameters is guaranteed through three constraints: aircraft performance constraints, thermal hydraulic constraints, and neutron physical constraints.

The implementation principle and technical effects of the device provided in this embodiment are the same as those of the foregoing embodiments. For brief description, for the parts not mentioned in the device embodiments, reference may be made to the corresponding content in the foregoing method embodiments.

An embodiment of the present invention provides an electronic device. As shown in FIG. 6 , the electronic device includes a processor 61 and a memory 62, and the memory stores a computer program that can run on the processor. When the processor executes the computer program, the steps of the methods provided in the foregoing embodiments are implemented.

Referring to FIG. 6 , the electronic device further includes: a bus 64 and a communication interface 63 , and the processor 61 , the communication interface 63 and the memory 62 are connected through the bus 64 . The processor 61 is used to execute executable modules, such as computer programs, stored in the memory 62 .

Wherein, the memory 62 may include a high-speed random access memory (RAM, Random Access Memory), and may also include a non-volatile memory (non-volatile memory), such as at least one disk memory. The communication connection between the system network element and at least one other network element is realized through at least one communication interface 63 (which may be wired or wireless), and the Internet, wide area network, local network, metropolitan area network, etc. can be used.

The bus 64 may be an ISA (Industry Standard Architecture, industry standard architecture) bus, a PCI (Peripheral Component Interconnect, peripheral component interconnect standard) bus, or an EISA (Extended Industry Standard Architecture, extended industry standard architecture) bus, etc. The bus can be divided into address bus, data bus, control bus and so on. For ease of representation, only one double-headed arrow is used in FIG. 6 , but it does not mean that there is only one bus or one type of bus.

Wherein, the memory 62 is used to store the program, and the processor 61 executes the program after receiving the execution instruction, and the method performed by the flow process definition device disclosed in any embodiment of the above-mentioned embodiments of the present invention can be applied to processing In the device 61, or implemented by the processor 61.

The processor 61 may be an integrated circuit chip with signal processing capability. During implementation, each step of the above method may be completed by an integrated logic circuit of hardware in the processor 61 or instructions in the form of software. The aforementioned processor 61 may be a general-purpose processor, including a central processing unit (Central Processing Unit, CPU for short), a network processor (Network Processor, NP for short), and the like. It can also be a digital signal processor (Digital Signal Processing, referred to as DSP), an application specific integrated circuit (Application Specific Integrated Circuit, referred to as ASIC), a ready-made programmable gate array (Field-Programmable Gate Array, referred to as FPGA) or other programmable logic devices, Discrete gate or transistor logic devices, discrete hardware components. Various methods, steps and logic block diagrams disclosed in the embodiments of the present invention may be implemented or executed. A general-purpose processor may be a microprocessor, or the processor may be any conventional processor, or the like. The steps of the methods disclosed in connection with the embodiments of the present invention may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software module can be located in a mature storage medium in the field such as random access memory, flash memory, read-only memory, programmable read-only memory or electrically erasable programmable memory, register. The storage medium is located in the memory 62, and the processor 61 reads the information in the memory 62, and completes the steps of the above method in combination with its hardware.

An embodiment of the present invention provides a computer-readable medium, wherein the computer-readable medium stores computer-executable instructions, and when the computer-executable instructions are invoked and executed by a processor, the computer-executable instructions cause The processor implements the methods described in the foregoing embodiments.

Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working process of the system described above can refer to the corresponding process in the foregoing embodiments, and details are not repeated here.

The computer program product of the method and device for determining core parameters of a nuclear thermal propulsion reactor provided by the embodiments of the present invention includes a computer-readable storage medium storing program codes, and the instructions included in the program codes can be used to execute the foregoing method embodiments The specific implementation of the method described in may refer to the method embodiments, and details are not repeated here.

In addition, in the description of the embodiments of the present invention, unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection , or integrally connected; it may be mechanically connected or electrically connected; it may be directly connected or indirectly connected through an intermediary, and it may be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

If the functions described above are realized in the form of software function units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the essence of the technical solution of the present invention or the part that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including Several instructions are used to make a computer device (which may be a personal computer, a server, or a network device, etc.) execute all or part of the steps of the methods described in various embodiments of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), magnetic disk or optical disk and other media that can store program codes. .

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, or in a specific orientation. construction and operation, therefore, should not be construed as limiting the invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and should not be construed as indicating or implying relative importance.

Finally, it should be noted that: the above-described embodiments are only specific implementations of the present invention, used to illustrate the technical solutions of the present invention, rather than limiting them, and the scope of protection of the present invention is not limited thereto, although referring to the foregoing The embodiment has described the present invention in detail, and those skilled in the art should understand that any person familiar with the technical field can still modify the technical solutions described in the foregoing embodiments within the technical scope disclosed in the present invention Changes can be easily thought of, or equivalent replacements are made to some of the technical features; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be covered by the scope of the present invention. within the scope of protection. Therefore, the protection scope of the present invention should be determined by the protection scope of the claims.

Claims (8)

1. A method for determining core parameters of a nuclear thermal propulsion reactor, characterized in that it is applied to a low-enrichment enriched uranium nuclear thermal propulsion reactor, and the method for determining core parameters of the nuclear thermal propulsion reactor comprises: Obtain the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor; Obtaining target dynamic parameters that meet the performance constraints of the aircraft, and performing heat transfer calculations on the fluid-solid coupling heat transfer model based on the target dynamic parameters, to obtain multiple sets of design parameters that meet thermal constraints; wherein, each set of design parameters Including geometric parameters and thermal parameters; Perform neutronics modeling and physical analysis based on multiple sets of design parameters, and obtain target geometric parameters and target thermal parameters that meet neutron physical constraints; Using the target dynamic parameters, the target thermal parameters and the target geometric parameters as core design parameters of the nuclear thermal reactor; The thermal parameters include the core outlet temperature; the step of performing heat transfer calculation on the fluid-solid coupling heat transfer model based on the target dynamic parameters to obtain multiple sets of design parameters satisfying thermal constraints includes: Perform axial heat transfer calculation and radial heat transfer calculation on the fluid-solid coupling heat transfer model based on the target dynamic parameters, and obtain the wall surface temperature of the coolant channel, the fuel center temperature, the mainstream temperature at any axial position, Core outlet temperature and geometric parameters corresponding to the core outlet temperature; Repeating the above axial heat transfer calculation and radial heat transfer calculation until the first preset condition is reached, and multiple sets of the design parameters are obtained; The geometric parameters include core height, core radius and coolant flow channel diameter; The step of performing neutronics modeling and physical analysis based on multiple sets of design parameters to obtain target geometric parameters and target thermal parameters satisfying neutron physical constraints includes: selecting any set of design parameters from multiple sets of design parameters to obtain first design parameters, and performing neutronics modeling based on geometric parameters in the first design parameters to obtain a target model; Performing reactor physics analysis on the target model to obtain physical parameters of the target model; It is judged whether the physical parameters meet the second preset condition, and if yes, the geometric parameters and thermal parameters in the first design parameters are used as target geometric parameters and target thermal parameters respectively. 2. The method according to claim 1, wherein the geometric parameters include core height, core radius and coolant flow channel diameter; The step of obtaining the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor includes: Based on the core height, core radius and coolant flow channel diameter, respectively determine the fuel assembly structure and the moderator assembly structure in the nuclear thermal reactor; Based on the structure of the fuel assembly, the structure of the moderator assembly and the flow direction of the coolant, a fluid-solid coupling heat transfer model of the nuclear thermal reactor is obtained. 3. The method according to claim 2, wherein the fuel assembly structure and the moderating assembly structure are both prism structures, and the height and cross-sectional shape of the fuel assembly structure and the moderating assembly structure are Similarly, the fuel assembly structure includes a plurality of coolant flow channels, the moderator assembly structure includes a second coolant flow channel, and the flow direction of the coolant is from the second coolant flow channel to the first coolant flow channel. The first coolant flow channel is each coolant flow channel in the fuel assembly structure. 4. The method according to claim 1, wherein the first preset condition comprises: the temperature of the fuel center reaches the maximum temperature of the fuel, and/or the temperature of the moderator in the moderator assembly structure reaches the moderator The maximum temperature of the agent. 5. The method according to claim 1, wherein the physical parameter comprises an effective multiplication coefficient of the core; The step of judging whether the physical parameter meets the second preset condition includes: Judging whether the effective multiplication coefficient is greater than 1, and if so, determining that the physical parameter satisfies the second preset condition. 6. The method according to claim 1, further comprising: If the physical parameter does not satisfy the second preset condition, selecting any set of design parameters except the first design parameter from multiple sets of design parameters to obtain a new first design parameter; Based on the geometric parameters in the new first design parameters, neutronics modeling and physical analysis are performed until the target geometric parameters and target thermal parameters are obtained. 7. A nuclear thermal propulsion reactor core parameter determination device, characterized in that it is applied to a low-enrichment uranium nuclear thermal propulsion reactor, and the nuclear thermal propulsion reactor core parameter determination device comprises: An acquisition module, configured to acquire the fluid-solid coupling heat transfer model of the nuclear thermal propulsion reactor; The calculation module is used to obtain target dynamic parameters that meet the performance constraints of the aircraft, and perform heat transfer calculations on the fluid-structure coupling heat transfer model based on the target dynamic parameters to obtain multiple sets of design parameters that meet thermal constraints; wherein, each The set of design parameters includes geometric parameters and thermal parameters; The analysis module is used to perform neutronics modeling and physical analysis based on multiple sets of design parameters, and obtain target geometric parameters and target thermal parameters satisfying neutron physical constraints; A parameter determination module, configured to use the target dynamic parameters, the target thermal parameters and the target geometric parameters as the core design parameters of the nuclear thermal reactor; The thermal parameters include core outlet temperature; the calculation module is used to perform axial heat transfer calculation and radial heat transfer calculation on the fluid-solid coupling heat transfer model based on the target dynamic parameters to obtain coolant flow The wall temperature of the channel, the fuel center temperature, the mainstream temperature at any axial position, the core outlet temperature, and the geometric parameters corresponding to the core outlet temperature; repeat the above axial heat transfer calculation and radial heat transfer calculation until The first preset condition is met, and multiple sets of the design parameters are obtained; The geometric parameters include core height, core radius and coolant flow path diameter; the analysis module is used to select any set of design parameters from multiple sets of design parameters to obtain the first design parameters, based on the Perform neutronics modeling on the geometric parameters in the first design parameters to obtain a target model; perform reactor physics analysis on the target model to obtain physical parameters of the target model; determine whether the physical parameters meet the second preset condition , if yes, using the geometric parameters and thermal parameters in the first design parameters as target geometric parameters and target thermal parameters respectively. 8. A computer-readable storage medium, with a computer program stored on the computer-readable storage medium, characterized in that, when the computer program is executed by a processor, the method according to any one of claims 1 to 6 is executed A step of.

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