Patent ID: 12249433

In the drawings:1. fusion device;2. isolation valve;3. piezoelectric valve;4. pressure stabilizing tank;5. fuel cylinder;6. Laval nozzle;7. solenoid valve;8. gas distribution box;9. diffusion chamber;10. vacuum pumping unit;11. pellet injector;12. propellant gas cylinder;13. divertor;14. plasma;15. thousand-second plasma density;16. gas puffing system;17. supersonic molecular beam injection system; and18. ice pellet injection system.

DETAILED DESCRIPTION OF EMBODIMENTS

The technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the accompanying drawings of the present disclosure. Obviously, described below are merely some embodiments of the present disclosure, rather than all embodiments. Based on the embodiments provided herein, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of the present disclosure.

As shown inFIGS.1-2, a coordinated fueling system satisfying thousand-second pulsed plasma discharge is provided, which includes a gas puffing system16, a supersonic molecular beam injection system17, an ice pellet injection system18, a fusion device1, a gas puffing port of a wave antenna, a divertor13and a plasma14.

The gas puffing system16is provided with a piezoelectric valve3for gas flow adjustment. The supersonic molecular beam injection system17is provided with a Laval nozzle6for gas injection. The ice pellet injection system18is configured for pellet preparation, acceleration and propulsion. The fusion device1is a magnetic confinement fusion reaction device. The gas puffing port of the wave antenna is arranged near a low hybrid wave and ion cyclotron wave antenna. The divertor13is configured to discharge a fusion ash. The plasma14is electrically neutral as a whole. The divertor13is a key component in a vacuum chamber of the fusion device1. The plasma14is operated in the fusion device1. The divertor13can be strongly interacted with the plasma14. The gas puffing system16, the supersonic molecular beam injection system17, the ice pellet injection system18and the fusion device1are each provided with an isolation valve2. The isolation valve2is configured to control a pulse time and an injection rate of an injected gas. A pressure stabilizing tank4is arranged in the pipeline of the gas puffing system16. The gas puffing system16, the supersonic molecular beam injection system17and the ice pellet injection system18are each provided with a fuel cylinder5, which is configured to provide fuel gas. The Laval nozzle6, a solenoid valve7and a gas distribution box8are main components of the supersonic molecular beam injection system17, and are arranged on a pipeline of the supersonic molecular beam injection system17. A diffusion chamber9, a vacuum pumping unit10, a pellet injector11and a propellant gas cylinder12are main components of the ice pellet injection system18, and are arranged in a pipeline of the ice pellet injection system18.

During a thousand-second pulsed plasma discharge process of the fusion device1, the plasma14is established by the gas puffing system16provided at a mid-plane of the fusion device1. Parameters of the plasma14in a scrape-off layer near the wave antenna are adjusted by the gas puffing system16provided near the wave antenna thereby improving a coupling efficiency. A feedback control on a density of the plasma14is performed by the supersonic molecular beam injection system17. A core fueling on the plasma14is performed by the ice pellet injection system18. A feedback control of a heat flux of the divertor13is performed by the gas puffing system16provided at the divertor13and the supersonic molecular beam injection system17. The coordinated fueling is achieved through coordination of different fueling methods at different positions and different moments, so as to achieve stable thousand-second density control of the fusion device1, effective coupling of a low hybrid wave and an ion cyclotron wave and effective control of the heat flux of the divertor13.

As shown inFIG.2, a coordinated fueling method satisfying thousand-second pulsed plasma discharge is provided, which includes the following steps. A density15of a thousand-second plasma is obtained. The gas puffing is performed by the gas puffing system16. The supersonic molecular beam injection is performed by the supersonic molecular beam injection system17. An ice pellet injection is performed by the ice pellet injection system18. The density15of the thousand-second plasma is obtained by pre-gas puffing breakdown of the gas puffing system16before the discharge of the plasma14. A feedback control on a density of the plasma14is performed through the supersonic molecular beam injection system17. A core fueling is performed through the ice pellet injection system18, thereby improving a fueling efficiency and the density of the plasma and establishing a higher plasma density than the initial thousand-second plasma density. The plasma14is operated in the fusion device1. The divertor13is a key component of an interaction between the fusion device1and the plasma14. The gas puffing system16includes a pre-gas fueling system for plasma discharge at the mid-plane of the fusion device1, a gas fueling system for the gas puffing port of the wave antenna, an upper gas fueling system of the divertor, a lower gas fueling system of the divertor. The upper gas fueling system and the lower gas fueling system are each mainly composed of the isolation valve2, the piezoelectric valve3, the pressure stabilizing tank4and the fuel cylinder5. The supersonic molecular beam injection system17includes a first portion and a second portion. The first portion is arranged at the mid-plane of the fusion device1. The second portion is arranged at the divertor13. The first portion and the second portion are each mainly composed of the isolation valve2, the fuel cylinder5, the Laval nozzle6, the solenoid valve7and the gas distribution box8. The ice pellet injection system18is arranged at the mid-plane of the fusion device1, and is composed of the isolation valve2, the fuel cylinder5, the diffusion chamber9, the vacuum pumping unit10, the pellet injector11and the propellant gas cylinder12.

The gas puffing system16involved in the first fueling method is operated as follows. The injected gas is injected into the pressure stabilizing tank4from the fuel cylinder5. A pulse time and an injection rate of the injected gas is controlled through the piezoelectric valve3. The first injected gas enters the fusion device1after the isolation valve2is opened to complete the gas supply. Systems for realizing the gas puffing are respectively arranged at the mid-plane of the fusion device1, near the wave antenna of the fusion device1and at the upper and lower divertor, so as to realize the pre-gas puffing of the plasma14, the adjustment of boundary parameters of the plasma14to improve wave coupling efficiency and the control of the heat flux of the divertor13.

The supersonic molecular beam injection system17involved in the second fueling method is operated as follows. The injected gas is injected into the gas distribution box8through the fuel cylinder5. A pulse time and an injection frequency are regulated through the solenoid valve7. The injected gas is accelerated through the Laval nozzle6to enter the plasma14inside the fusion device1through the isolation valve2. The supersonic molecular beam injection system17includes a first portion and a second portion. The first portion is arranged at the mid-plane of the fusion device1, and the second portion is arranged at the divertor13, so as to satisfy requirements of feedback control of the plasma density and alleviation of the heat flux of the divertor13.

The ice pellet injection system18involved in the third fueling method is operated as follows. The fuel gas enters the pellet injector11through the fuel cylinder5, and is condensed into ice and cut to form a cylindrical ice pellet. The ice pellet is accelerated by the propellant gas cylinder12to enter the diffusion chamber9. The propellant gas is pumped out of the diffusion chamber9through the vacuum pumping unit10. The ice pellet enters the plasma14through the isolation valve2to achieve core fueling and establish a high-density plasma.

A top of the fusion device1and a bottom of the fusion device1are each provided with the divertor13as a region where particles of the plasma14are strongly interacted with the heat flux. An ablation of the divertor13may be easily caused, such that an ablated material enters the plasma14, resulting in the degrading of the performance of the plasma14. The gas puffing system16and the supersonic molecular beam injection system17arranged at the divertor13can alleviate the interaction between the plasma14and the divertor13, reduce the heat flux of the divertor13and facilitate the maintenance of a long-pulse plasma discharge.

The coordinated fueling method at different positions and in different ways which can realize the coordinated fueling of plasma discharge has the following operating process. The plasma is established through gas puffing. Parameters of the plasma in a scrape-off layer near the wave antenna to improve a coupling efficiency between a lower hybrid wave and an ion-cyclotron wave. After the plasma is established, the feedback control on the density of the plasma is performed through supersonic molecular beam injection. The core fueling on the plasma is performed through ice pellet injection to satisfy the requirements for plasma operation. The feedback control of the heat flux of the divertor is performed through gas puffing and supersonic molecular beam injection at the divertor. The coordination of different fueling methods can achieve stable thousand-second density control of the fusion device, boundary parameter adjustment of the plasma required for wave coupling and effective control of the heat flux of the divertor.

The embodiments mentioned above are intended to facilitate understanding of the present disclosure rather than limiting the scope of the disclosure. For those of ordinary skill in the art, various modifications made without departing from the spirit and scope of the present disclosure shall fall within the scope of the present disclosure defined by the appended claims.