117results about How to "Reduce heat flux" patented technology

A radiation shield and an assembly and a reactor including the radiation shield are disclosed. The radiation shield can be used to control heat flux from a susceptor heater assembly and thereby enable better control of temperatures across a surface of a substrate placed on a surface of the susceptor heater assembly.

A double temperature sensor is provided for measuring a near-surface temperature of the ambient air and the temperature of the skin surface (9). A heat flux insulation block (4) is made of an insulation material in one piece as a housing. Two temperature sensor elements (2, 3) with respective electric connections (6) belonging to them are arranged in the heat flux insulation block (4) one on top of another at spaced locations from one another and near the surface.

Light-weight, heat-managing structures feature open-cell lattice, honeycomb, and/or corrugated (prismatic) arrangements in their substructures, combined with heat pipe/heat plate arrangements for managing heat to which the structures are subjected. The structures are well suited to aerospace applications and may be employed in the leading edge of wings or other airfoil-shaped components; gas turbine engine components; rocket nozzles; and other high-heat, high-stress environments.

A method of reducing the amount of cooling energy required to heat and cool a building is provided. The method includes disposing a porous insulating material in the exterior walls and substantially covering the ceiling in the attic space of the building to a substantial depth. The porous insulating material includes a desiccant. The method further includes permitting the desiccant—bearing porous insulating material to adsorb water moisture from the attic space and then permitting the adsorbed water moisture to desorb from the desiccant—bearing porous insulating material into the enclosed room of the building, resulting in a reduction in the amount of energy required to heat and cool the building.

A mould for horizontal casting of molten metal comprising a mould body forming an open-ended mould cavity having an inlet end and an outlet end. An annular permeable wall member is mounted in the mould body adjacent the inlet end of the mould cavity with an inner face thereof forming an interior face of the mould. A refractory transition plate is mounted at the inlet end of the mould cavity, this transition plate providing a mould inlet opening having a cross-section less than that of the mould cavity. This provides an annular shoulder at the inlet end of the cavity. Means are provided for feeding molten aluminum through the inlet opening. Separate conduits are also provided for feeding a gas into the shoulder and via the permeable wall means for providing a layer of gas between the metal and the inner face of the mould. A gas that is more reactive with molten aluminum is fed into the shoulder and a less reactive gas is fed via the permeable wall. The reactions with the molten aluminum create a skin or shell on the aluminum which provides smooth passage through the mould and allows for more rapid secondary cooling of the emerging ingot.

A droplet dispensing device includes a reservoir for receiving a liquid material, an outlet nozzle in fluid communication with the reservoir and a piezoelectric actuating means acting on the liquid material at the outlet nozzle to exit the outlet nozzle in a sequence of droplets. A piezoelectric actuating means that includes a piston, which is actuated by a piezoelectric actuator at one end and dips the other, free end into the liquid material is provided just upstream of the outlet nozzle.

A heat transfer tube can comprise a tube body, and outer fins integrated with the tube body which are formed by allowing material on the tube body to extend along radial direction of the tube body and wind and extend around the tube outer surface in helical manner, wherein microscale channels are formed on at least one lateral surface of the outer fin. The invention has the advantage that the microscale channel is formed on at least one lateral surface of the outer fin to help increase the heat exchange area of the outer fin surface, improve the fluid disturbance, enhance the forced convention heat exchange out of tube, and significantly improve the heat transfer coefficient; when the enhanced heat transfer tube in the present invention is applied on an evaporator, the microscale channel can greatly increase the number of the nucleation sites, so as to enhance boiling heat exchange in condition of low heat flux density; when the enhanced heat transfer tube in the present invention is applied on a condenser, the microscale channel can improve distribution of liquid membrane thickness on outer fin surface to enhance condensing heat exchange.

The invention relates to a multiphase fluorescent ceramic and a preparation method thereof. The multiphase fluorescent ceramic comprises a high-thermal-conductivity dielectric ceramic matrix and fluorescent ceramic main bodies which are distributed in the high-thermal-conductivity dielectric ceramic matrix and are periodically arranged; the shortest distance L between the adjacent fluorescent ceramic main bodies is 200-1000 microns, and the volume fraction delta of the high-thermal-conductivity dielectric ceramic matrix in the multiphase fluorescent ceramic is 5-60%; the fluorescent ceramic main body is rare earth doped transparent ceramic; and the material of the high-thermal-conductivity dielectric ceramic matrix is selected from at least one of Al2O3, AlN, BeO, Sc2O3, Si3N4, BN, SiC andMgO.

The invention discloses an air-cooled module for heat transfer temperature uniformization of a fuel cell. The air-cooled module mainly consists of a fuel cell module, fins and a fan system; the fuel cell module comprises an end cap, a membrane electrode, an ultra-thin temperature uniformization plate, a plurality of membrane electrodes and a plurality of ultra-thin uniform temperature plates are alternately arranged, the two sides of each membrane electrode are respectively provided with an ultra-thin uniform temperature plate, and the ultra-thin uniform temperature plate comprises a shell, acavity, a liquid suction core and a working medium; The hollow cavity is arranged in the housing, the hollow cavity is at least protruded from one end of the housing, and the hollow cavity is providedwith a liquid suction core and a working medium; The upper surface or the lower surface of the shell is respectively provided with an air flow channel or a hydrogen flow channel; The overall thickness of the ultra-thin homogeneous temperature plate shall not exceed 3mm; A plurality of fins are installed on the condensing end of the ultra-thin uniform temperature plate. The evaporation end of theultra-thin uniform temperature plate of the invention can separate the reaction gas, collect and conduct the electric current; The heat flux concentrated on the surface of the bipolar plate is rapidlytransferred and diffused to the large area of the condensation surface, which has the effect of uniform temperature and heat dissipation.

The invention provides an integrated thermal protection structure for the leading edge of a hypersonic aircraft pneumatic rudder, which is integrally designed and comprises a heat protection skin, a heat pipe, a heat absorption device and a heat insulation layer, wherein the heat protection skin is arranged on the outer surface of the leading edge of the pneumatic rudder; the heat absorption device is arranged on the inner surface of the heat protection skin; the heat pipe is fixedly connected with the heat absorption device; the heat pipe is arranged on the inner surface of the heat absorption device; and the heat insulation layer is fixedly arranged on the inner surface of the heat pipe. The invention also provides a coolant circulating system and a hypersonic aircraft. According to theinvention, the deformation of the leading edge of the aircraft pneumatic rudder is small, the heat flow density is small, the aerodynamic characteristic of the aircraft with high lift-resistance ratioand the operability of the pneumatic rudder are kept, the problems of material failure caused by large heat flow of the leading edge of the aircraft pneumatic rudder and poor pneumatic load bearing capacity caused by high flying speed are solved, the extreme distribution of the temperature of the leading edge of the pneumatic rudder is avoided, and the long-time thermal insulation of the aircraftis achieved.

The invention provides a flat heat pipe, which comprises a flat shell, a liquid-filled pipe and a capillary core. Wherein, the interior of the flat shell is hollow, and the upper and lower inner surfaces of the flat shell are provided with a number of cross-distributed grooves, and there are protrusions between the adjacent grooves; There is a small hole communicating with its interior, and the liquid filling tube is fixedly connected to the flat shell through the small hole; the capillary core is arranged inside the flat shell, and the capillary core The upper and lower surfaces are respectively in contact with the protrusions on the upper and lower inner surfaces of the flat shell; the capillary core and the groove form a channel with a closed section. The flat heat pipe of the invention can effectively reduce the heat flux density of the heat source, has good temperature uniformity and high reliability, and can also realize excellent temperature uniformity performance under the condition of anti-gravity.

A bucket for a steam turbine includes an airfoil portion having a radially outer tip, the radially outer tip having a thermal barrier coating applied thereto, and wherein the thermal barrier coating is resurfaced to form at least one ridge along the radially outer tip.

The invention provides a boil cooling method, a boil cooling apparatus, a flow channel structure, and applied products thereof, by which noise and vibration attending on cooling by microbubble emission boiling can be effectively reduced, and efficient boil cooling can be realized.

A subcooled cooling liquid is caused to flow through a flow channel structure, which is formed by using a surface of an object 10 to be cooled as a surface 10A to be cooled and the surface 10A to be cooled as a tubular wall and has a tubular flow channel 16, through which the subcooled cooling liquid is caused to flow, and a structure that a group of rigid needles N1, N2, . . . Ni . . . is protruded within the tubular flow channel 16 from the tubular wall of the tubular flow channel, thereby conducting cooling by microbubble emission boiling.

The invention belongs to the technical field of nuclear reactor safety, and particularly relates to a reactor core fused mass catching device. The reactor core fused mass laying and spreading of the existing fused mass catching device is nonuniform; the process is slow; a kinetic component can easily fail in serious accidents; the laying and spreading temperature reduction operation on the reactor core fused mass is influenced, and great potential safety hazards are caused. The reactor core fused mass catching device provided by the invention comprises a fused mass retention compartment, wherein the fused mass retention compartment is provided with a fused mass guiding device and is positioned under the reactor; a fused mass blasting laying and spreading device is arranged in the fused mass retention compartment; the laying and the spreading on the reactor core fused mass are uniform and fast; a non-kinetic mode is used; the reliability during the occurrence of the serious accidents is high.

A method for improving the thermal barrier properties of silicone resin/glass fiber composites. Composites comprising a layer of polysiloxane (silicone resin) matrix with a glass or quartz fiber reinforcement embedded in such matrix and an organic polymeric layer were subjected to multi-cycle heat treatment, preferably with quartz lamps. The polysiloxane layer was pre-coated with graphite dispersion in order to ensure acceptable optical receptivity of the polysiloxane layer. As a result, the silicone resin was converted into a thick porous layer of silicone dioxide, the latter having the improved thermal barrier properties.