32 results about "Helium temperature" patented technology

The invention discloses a thermal hydraulic characteristic testing device and method for tritium blowing helium of a breeding blanket pebble bed of a fusion reactor. The thermal hydraulic characteristic testing device for the tritium blowing helium of the breeding blanket pebble bed of the fusion reactor is mainly used for researching the flow and heat transfer characteristics of the tritium blowing helium of the solid breeding blanket layer of the fusion reactor between breeding agent pebbles of the pebble bed. The thermal hydraulic characteristic testing method includes that using a non-contact type high-frequency induction power to heat quasi metal breeding agent pebbles to simulate high-power density nuclear heat generated by the breeding agent pebbles in the pebble bed, researching the thermal hydraulic characteristics of the pebble bed under changed tritium blowing helium temperature, speed and pressure, breeding agent pebble arrangement mode, size and power density and the like, measuring the temperature distribution of the breeding agent pebbles and pebble bed wall surface, and obtaining a convection heat transfer correlation equation and a flow resistance relation to provide supports for testing and demonstrating the nuclear heat transmission of the neutron deposition in the pebble bed on the breeding agent pebbles and the tritium blowing helium flow and heat transfer characteristics under laboratory conditions, verifying the feasibility of a solid breeding blanket designing scheme and the correctness of a numerical method and data, and researching and developing Chinese solid experiment blanket modules of ITER.

The invention discloses a control method and system of high temperature gas cooled reactor power, relating to the technical field of nuclear energy science and engineering, wherein the method includes the steps as follows: S1, setting a nuclear power controller parameter and a reactor core outlet hot helium temperature controller parameter; S2, the reactor core outlet hot helium temperature controller calculating the deviation between the reactor core outlet hot helium temperature measuring value and the core outlet hot helium temperature reference value to obtain the modification of the relative nuclear power reference value; the nuclear power controller calculating the deviation between the reactor core relative neutron flux density measuring value and the relative neutron flux density reference value and obtaining a rod speed signal that drives the control rod to move. The invention real-time obtains and calculates the core outlet hot helium temperature measuring value and the reactor core relative neutron flux density measuring value of the high temperature gas cooled reactor, obtains the rod speed signal for driving the control rod and controls the high temperature gas cooled reactor power.

The invention discloses a liquid nitrogen and cold helium double media coupling heat sink for space environment simulation. The heat sink is a sealed cylinder which comprises a liquid nitrogen cooling pipe network, a cold air helium cooling pipe network, copper fins and electric heaters, wherein the copper fins are connected with the liquid nitrogen cooling pipe network and the cold air helium cooling pipe network and forms a barrel of the liquid nitrogen and cold helium double media coupling heat sink with the liquid nitrogen cooling pipe network and the cold air helium cooling pipe network. The electric heaters are uniformly distributed on the copper fins. According to the heat sink disclosed by the invention, the liquid nitrogen cooling pipe network and the cold air helium cooling pipe network are embedded and coupled, so that refrigerating media liquid nitrogen and cold helium work independently to switch in function smoothly, thereby, realizing transition from a liquid nitrogen temperature area to a low temperature gas helium temperature area. In addition, according to design of two parallel and staggered medium pipelines with two runners, conditions of complex flow, reduced safety, discontinuous transition of the temperature area and waste of cooling capacity caused by emptying switch of a single runner can be avoided. The heat sink disclosed by the invention is simple in operational flow and safe and reliable.

The invention provides a liquid helium and superflow helium temperature zone insulating material high-voltage electrical performance test experiment platform. The platform comprises a vacuum chamber,a first-stage test chamber and a second-stage test chamber which are nested layer by layer from outside to inside. A refrigerator is used for providing cold energy for a liquid helium temperature zonetest platform in the first-stage test chamber, so that the test requirement of the insulating material under the 4.2 K temperature zone use condition can be met; and the second-stage test chamber isin contact with a liquid helium temperature zone test platform, helium is introduced, and the cooling capacity is provided for the liquid helium temperature zone test platform by adopting the refrigerator, helium introduced into the helium condensation cavity is liquefied under the action of the refrigerator; liquefied helium is converted into superfluid helium through a throttle valve and an airexhaust pressure reduction pipeline, and the superfluid helium is output into the superfluid helium cavity to provide cold energy for a superfluid helium zone test platform in the secondary test chamber, so that the test requirement of the insulating material under the 1.8 K temperature area use condition can be met.

The invention provides a method for producing an indium phosphide back hole. The method comprises the following steps: step (1), producing a metal barrier layer at a position of the front of a indium phosphide wafer where the back hole needs to be configured, and finishing a front process; step (2), bonding the front of the wafer to a temporary slide sapphire, and thinning and polishing the back of the wafer; step (3), photoetching a back hole figure at the back of the wafer, ensuring that the back hole position is consistent with the front metal barrier layer, and forming an etching mask; step (4), rising the back helium temperature of an STS ICP dry etching machine to 190 DEG C, using the combined gas of chlorine (C12) and argon Ar to perform dry etching, until etching to the front metal barrier layer; step (5), removing the etching mask; and step (6), sputtering a seed layer at the back, electroplating a back gold and filling the back hole, and then finishing the back hole production. The method for producing the indium phosphide back hole provided by the invention has the following advantages that the problem of etching an indium phosphide deep hole has been solved; the back hole morphology, the etching repeatability and the coherence are all very good; and meanwhile, the process is simple and can be compatible with the GaAs process, thus the method is suitable for large-scale popularization and application.

In a cryocooler for developing coldness of 4 K or lower by expanding helium, an expander expands high-pressure helium. A compressor compresses low-pressure helium returned from the expander, to generate high-pressure helium, and supplies the high-pressure helium to the expander. When helium temperature in the expander is 2.17 K or lower, the pressure of the low-pressure helium is equal to or higher than pressure given by a curve, in a helium state diagram in which the horizontal axis is temperature and the vertical axis is pressure, along which helium's volumetric thermal expansion coefficient is 0.

The invention discloses a pressure monitor, a superconducting magnet and an MRI system. The pressure monitor comprises a temperature sensing unit for sensing the helium temperature of the superconducting magnet and providing representative data, a determining unit for comparing the representative data with a threshold and obtaining a determination result, and a control unit for controlling a refrigeration part of the superconducting magnet according to the determination result, wherein the determining unit is electrically connected with the temperature sensing unit and the control unit. The pressure monitoring monitor of the superconducting magnet can control the pressure of the superconducting magnet accurately and greatly reduces the cost of an absolute pressure sensor.

The invention discloses a high-pressure-helium obtaining method for a liquid-hydrogen temperature zone and the method is mainly used for providing low-temperature helium for a ground test system of a carrier-rocket cold-helium pressurization system. An applied device mainly includes a liquid-nitrogen heat exchanger, an upper volute, titanium bottles, a lower volute and a liquid-hydrogen dewar. Each titanium bottle is provided with an upper opening and a lower opening, which are connected to the upper and lower volute respectively. The liquid-hydrogen dewar is a vacuum powder heat insulation structure. A preparation process of the low-temperature helium is as follows: firstly, the titanium bottles are filled with normal-temperature helium to XMPa and then liquid nitrogen and liquid hydrogen are injected to the liquid-nitrogen heat exchanger and the liquid-hydrogen dewar and then the titanium bottles are filled with helium which undergoes temperature reduction by the liquid-nitrogen heat exchanger so that the pressures of the titanium bottles rise to be slightly higher than XXMPa; the inflation is stopped and the helium is made to stand so as to reduce temperature and reduce pressure and then the titanium bottle inflation and standing processes are repeated until the pressures in the titanium bottles are stabilized to XXMPa without an obvious lowering trend; and if a needed helium temperature is lower than 21K, deflation of the titanium bottles can be carried out firstly after preparation of the XXMPa helium is completed and the helium can be used after the temperature is reduced to a needed value. The titanium bottle inflation and deflation structure is high in reliability and the titanium bottles can be used for a plurality of times and consumption of liquid hydrogen and helium in a test process is reduced so that an objective of reducing test cost and improving test security is achieved.

The invention relates to a sleeve type helium temperature-control sediment sampling device applied to a high-temperature gas cooled reactor. The sampling device is characterized by comprising a sleeve, a core rod which is fixed inside the sleeve and extends along the axial direction, a plurality of temperature control units which are sequentially fixed on the outer wall of the sleeve at intervals along the axial direction, a plurality of water delivery pipe sections for communicating every two adjacent temperature control units, as well as a water inlet and a water outlet which are respectively connected with the two temperature control units at the outmost sides. The temperature-control sediment sampling device is capable of implementing the certain temperature control on a high-temperature helium environment generated by a steam generator in the whole sedimentation length, so that during the continuous cooling process of high-temperature helium, sedimentable fission product particles with different types, and graphite dust within different particle size ranges, which are carried in the high temperature helium, are gradually sedimented and adsorbed onto the sleeve and the core rod through a certain temperature gradient, and therefore, the follow-up measurement and analysis can be effectively implemented.

The invention discloses a one-dimensional pneumatic design method for a helium compressor, and belongs to the technical field of pneumatic design of compressors. The problem that the pneumatic designof an existing helium compressor cannot meet the requirement for the design efficiency of the helium compressor is solved. According to the invention, the sum of the adiabatic work amounts of all stages of the helium compressor is reasonably designed and reasonably distributed; the temperature rise of each stage of a helium compressor, the total helium temperature before each stage, the pressure ratio of each stage and the front total pressure of each stage are calculated to obtain the total supercharging ratio, the adiabatic power and the power consumption power of the helium compressor, thefirst-stage geometric dimension and the last-stage geometric dimension of the helium compressor along the uniform-diameter pneumatic direction are determined, and further the through-flow dimension ofthe helium compressor is solved, so that the design of the one-dimensional pneumatic direction of the helium compressor is completed. Compared with the prior art, the method has the advantages that the efficiency of the helium compressor designed by the aid of the method can be improved by 2%-3%, and the method can be applied to the technical field of helium compressor pneumatic design.

The invention discloses a high-temperature gas cooled reactor helium flow control system and method with an incremental adjusting function. The high-temperature gas cooled reactor helium flow controlmethod comprises the following steps: 1) calculating a hot helium temperature correction value for hot helium temperature PID adjustment; 2) calculating a power correction value for power PID adjustment of a unit; 3) calculating a helium flow correction value for helium flow PID adjustment; and 4) performing three-impulse control according to the hot helium temperature correction value for hot helium temperature PID adjustment, the power correction value for unit power PID adjustment and the helium flow correction value for helium flow PID adjustment, and then controlling the reactor accordingto the result of the three-impulse control. The system and method can rapidly tract and control the change trend of a variable, correct and control the output of the variable to meet the functional requirements of peak regulation and frequency modulation of the reactor tracking power grid load.

The invention discloses a freely-detachable gold wire sealing connection device for a superfluid helium temperature zone and an implementation method. The freely-detachable gold wire sealing connection device is composed of a sealing connection base, a sealing connection nut, a gold wire sealing ring and a sealing connection screw. The sealing of a fluid working medium in the superfluid helium temperature zone is realized in a gold wire sealing manner, and a gas inlet pipe and a gas outlet pipe can be freely separated by designing three independent components, namely the base, the nut and the screw, so that the mounting and dismounting of a low-temperature fluid pipeline are greatly simplified, and the device and the implementation method have very positive significance in application of a low-temperature throttling refrigerating machine working in the superfluid helium temperature zone in the special fields of aerospace and the like.

The invention provides a primary loop humidity measuring device for a high temperature gas cooled reactor, which comprises a sampling chamber, an air cooling temperature adjusting device, a filter assembly and a flow adjusting assembly, a temperature sensor and a hygrograph sensor are arranged in the sampling chamber, and the air cooling temperature adjusting device is used for adjusting the temperature of gas entering the sampling chamber; the flow adjusting assembly adjusts the flow of gas entering the sampling chamber. The device has the beneficial effects that the efficiency of the heat exchanger does not need to be manually adjusted and controlled, and the temperature of helium entering the sampling chamber can be automatically adjusted; and a water-cooling coil pipe is omitted, so that a pressure test is not needed.

The invention discloses a stratospheric airship with full-motion front wings and a mobile counterweight. The front wings are symmetrically arranged on both sides of the front portion of a hull, and the front wings can be rotated relative to the hull. Horizontal tails are symmetrically disposed on both sides of the rear portion of the hull. The hull includes a main capsule and two side capsules, and the main capsule is disposed in the middle of the two side capsules. The head portion of the main capsule protrudes from the head portions of the side capsules on both sides, and the horizontal position of the main capsule is higher than the side capsules on both sides. Vertical tails are arranged on the upper portions of the tail portions of the side capsules, and the front wings and the horizontal tails are symmetrically disposed on both sides of the longest weft of the side capsules. The full-motion front wings have more remarkable adjustment effect on the airship, and the buoyant weightbalance problem caused by the helium temperature difference of the stratospheric airship is comprehensively and effectively solved by adjusting the pitch angle of the airship, controlling a power device in a vector mode and the like.

The invention discloses an airship with front wings and a mobile counterweight. The airship includes a hull, the front wings, horizontal tails and vertical tails. The front wings are symmetrically arranged on both sides of the front portion of the hull, and the horizontal tails are symmetrically disposed on both sides of the rear portion of the hull. The hull includes a main capsule and two side capsules, and the main capsule is disposed in the middle of the two side capsules. The head portion of the main capsule protrudes from the head portions of the side capsules on both sides, and the horizontal position of the main capsule is higher than the side capsules on both sides. The vertical tails are arranged on the upper portions of the tail portions of the side capsules, and the front wingsand the horizontal tails are symmetrically disposed on both sides of the horizontal meridians of the side capsules. According to the buoyancy variation of the airship, the rudder yaw-angles of the front wings are controlled, and the buoyant weight balance problem caused by the helium temperature difference of a stratospheric airship is comprehensively and effectively solved by adjusting the pitchangle of the airship, controlling a power device in a vector mode and the like.

The invention relates to the technical field of superfluid helium low-temperature throttling refrigerators, and discloses an extremely-low-temperature cold head evaporator capable of inhibiting anti-gravity climbing of a superfluid helium liquid film, which comprises a base, an evaporator main body, a top cover, a first connecting pipe, a second connecting pipe and a porous sintering interlayer, according to the ultra-low-temperature cold head evaporator, conventional liquid helium and super-flow liquid helium are separated through the porous sintering interlayer, the temperature before throttling can be effectively controlled through the top cover with the good heat insulation effect and the special structural design of the top cover, anti-gravity climbing of a super-flow helium liquid film can be restrained, and therefore the stability of the pressure and the temperature in the ultra-low-temperature cold head evaporator is guaranteed, and the service life of the ultra-low-temperature cold head evaporator is prolonged. And the device has very positive significance in practical application of the extremely low temperature throttling refrigerating machine working in the superfluid helium temperature region.