1011 results about "Heat shield" patented technology

The invention discloses a flat heat shield wall temperature calculation method based on air system network automatic numbering and hole row partitioning, and the method comprises the steps: carrying out the geometric discrete grid division of a wall surface for a flat heat shield in a binary convergent-divergent nozzle in order to accurately calculate the wall surface temperature of the flat heat shield, i.e., dividing a continuous calculation region into a plurality of calculation control bodies, calculating points in all the calculating areas are determined, and heat exchange parameters are calculated through the flow parameters; then, the wall surface temperature is updated through the heat exchange parameters, and the flow heat exchange parameters of the next step are calculated through the new wall surface temperature till the calculation result converges. According to the method, the calculation precision and speed are greatly improved, the wall temperature of the heat insulation screen can be calculated more efficiently and accurately, and then more reliable data support is provided for optimization of a cooling system.

The disclosure provides an air fryer, including a main body and an inner pot. A heat shield of the main body has a first accommodating chamber, a second accommodating chamber and a bottom opening that are sequentially arranged from top to bottom and are in communication with each other. A caliber of the second accommodating chamber is greater than a caliber of the first accommodating chamber. The first accommodating chamber is equipped with blades of a fan inside. The second accommodating chamber is equipped with a heating member inside. A side wall of the second accommodating chamber is a vertical side wall. Cooking efficiency is effectively improved.

The invention relates to the technical field of thermal protection of hypersonic aircrafts, in particular to a multi-scale prediction method for an ablation behavior of a thermal protection structure based on data driving, which comprises the following steps: performing molecular dynamics simulation on a gas-solid interface of an ablation type thermal protection material to obtain simulation calculation activation energy; obtaining the experimental activation energy of the material; performing Bayesian optimization on the simulation calculation activation energy and the experiment measured activation energy to obtain optimized activation energy; performing macroscopic wall surface ablation simulation by taking the optimized activation energy as a boundary condition to obtain an ablation parameter database recording ablation wall surface temperatures, ablation rates and ablation depths corresponding to different flow rates, altitudes and time; training a radial basis function neural network based on the ablation parameter database, and establishing an ablation prediction model; obtaining a prediction result; the calculation efficiency and accuracy of the thermal protection structure ablation behavior multi-scale prediction method can be improved.

A thermal shade for an automobile having a panoramic roof includes an elongated jacket sized to overlay a vehicle's panoramic roof and a thermally insulating layer sandwiched within the jacket. Magnetic tape strips or individual magnets are located along the perimeter of the jacket and provide means for securing the thermal shade to the automobile. The thermal shade has a streamlined appearance and does not obscure the automobile's doors or door windows and does not interfere with the vehicle's security camera.

The invention provides a method for improving COP defects based on crystal bar temperature gradient control, and relates to the technical field of monocrystalline silicon production, the method comprises the following steps: collecting temperature distribution data of a crystal bar growth interface and surface in real time, and reading a crystal bar pulling speed in real time; calculating an instantaneous V / G value according to the temperature distribution data and the pulling speed of the crystal bar; comparing the instantaneous V / G value with a preset V / G critical value; and according to the comparison result, adjusting the inward or outward opening angle of the scales on the scale type radiation adjusting device arranged between the crystal bar and the heat shield, so as to adjust the crystal bar temperature gradient G by adjusting the heat radiation reflected to different positions of the crystal bar, and further adjust the V / G value. According to the scheme, the thermal radiation reflection path can be dynamically changed according to the actual condition of the single crystal growth stage, so that the temperature gradient distribution of the single crystal growth stage is adjusted, the V / G value is further adjusted to reduce the generation of COP defects, and the quality of the single crystal is improved.

The application relates to a fixing mechanism of a combustion chamber tile and a combustion chamber heat shield device, wherein the circumferential side edge of the tile is provided with a stepped installation slot, the stepped surface of which constitutes an anchoring surface; the shell is provided with a shell ventilation hole and a containing through hole; the fixing mechanism comprises a pressing disc and a connecting bolt, the pressing disc comprises a middle connecting part, a limiting side plate and a pressing plate, the limiting side plate is located outside the middle connecting part, the lower end of the limiting side plate is connected with the lower end of the middle connecting part, and a cooling cavity is arranged between the two, the pressing plate is connected with the upper end of the limiting side plate and extends outward, the lower end of the middle connecting part is provided with a cooling groove and an abutting surface, a disc-in-plate ventilation hole and a connecting through hole are arranged in the middle connecting part and are connected with the cooling groove and the cooling cavity, one end of the connecting bolt is provided with a pressing head, and the other end is a fixed end; during installation, the limiting side plate of the pressing disc is located in the lower slot part, the connecting bolt passes through the connecting through hole and the containing through hole, the middle connecting part is pressed on the shell by the pressing head, the cooling groove is aligned with the shell ventilation hole, and the pressing plate is pressed on the anchoring surface.

An aircraft engine, has: a turbine including a turbine rotor rotatable about a central axis; a scroll case having an inlet connected to a source of combustion gases and an outlet fluidly connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet; a bearing housing; a turbine support case secured to the bearing housing, the scroll case disposed axially between the turbine support case and the bearing housing, the turbine support case having spokes extending through the scroll case and radially supported by the bearing housing; and heat shields distributed around the central axis in circumferential alignment with the spokes and extending axially through the scroll case for thermally shielding the spokes, a heat shield of the heat shields disposed around a spoke of the spokes, the heat shield defining an air gap surrounding the spoke inside the scroll case.

The invention relates to the technical field of heater performance testing, in particular to an all-copper quick-heating heater assembly performance testing device and method.The device comprises a water tank, a containing base, a heat insulation cover, a temperature measuring mechanism and an upper connecting piece moving up and down, and the water tank is divided into two parts through a partition plate and used for containing water and a calcium carbonate solution; the placing seat comprises a door-shaped bracket, a lower connecting piece and an auxiliary bearing piece, and the heater is fixed by the upper connecting piece and the lower connecting piece; water pressure resistance detection and thermal efficiency detection are integrated, so that the heater does not need to be disassembled and assembled back and forth during different detections, and the operation convenience is improved; when the thermal performance of the heater is evaluated, besides the conventional thermal efficiency, the heating rate, the heating uniformity and the heat storage capacity of the heater are evaluated by performing multi-point temperature measurement on the surface of the heater, in addition, the influence of scale on the thermal efficiency and the heat storage capacity is simulated by heating a calcium carbonate solution, and multiple detection functions are integrated; and the performance of the heater is evaluated from multiple aspects.

A Czochralski round silicon core growth furnace, comprising a furnace body, a pulling and rotating device, a multi-axis pulling disc device and a heat shield lifting device, wherein the furnace body comprises a main furnace chamber and an auxiliary furnace chamber, and the auxiliary furnace chamber is detachably connected to the main furnace chamber; the pulling and rotating device comprises a crystal pulling and lifting mechanism and a rotating mechanism; the multi-axis pulling disc device comprises a housing and a gear transmission mechanism located in the housing; the crystal pulling and lifting mechanism is connected to the housing; the rotating mechanism is connected to the gear transmission mechanism; the gear transmission mechanism is connected to a plurality of sets of seed crystals; and the heat shield lifting device comprises a lifting drive device and a perforated water-cooled jacket connected to the lifting drive device. The perforated water-cooled jacket is lifted by means of the lifting device to move up and down, and the auxiliary furnace chamber is detachably connected to the main furnace chamber, such that the function of cleaning ash without furnace shutdown is achieved, thereby effectively preventing impurities from falling, and ensuring the purity of a silicon melt.

The invention discloses an anti-oxidation and anti-scouring heat prevention and insulation composite material, a preparation method and application, and belongs to the technical field of high-temperature thermal protection materials. According to the method, a two-step in-situ modification method is adopted, hydrolyzed organosilane reacts with phenolic resin to prepare silicon modified phenolic resin, then the silicon modified phenolic resin is bonded with an organoboron compound to obtain boron-silicon co-modified phenolic resin, a curing agent is added, then the boron-silicon co-modified phenolic resin is injected into a fiber reinforcement mold, and a finished product is obtained through a sol-gel reaction and normal-pressure drying. According to the invention, boron and silicon elements are embedded into phenolic aldehyde molecular chains through covalent bonds to form a boron-silicon-carbon hybrid network, a nano ceramic phase and a compact glassy protective layer are generated at high temperature, and the coating has excellent anti-scouring property, thermal stability and heat insulation property. The preparation process is simple and controllable, is suitable for large-scale production, can accurately regulate and control the performance, and is suitable for thermal protection parts of supersonic aircrafts.

A printing device 11 includes a printing section 16 that performs printing by ejecting a liquid onto a transported medium 99, a support section 21 facing the printing section and having a support surface 22 for supporting the medium, a holding section 26 for holding the medium spanning across from the support section, a heating section 31 that is located downstream of the support section in the transport direction of the medium and that heats the printed medium, and a heat shield section 41 facing the heating section, wherein the heat shield section has a facing surface 43 that faces the heating section and that is separated from the medium extending across from the support section to the holding section, and a protruding section 46 that protrudes from the facing surface toward the heating section at an end portion on a downstream side in the transport direction.

Embodiments include thermal covers to help drain fluids away from dangerous environments, e.g., in an engine bay in a vehicle. Thermal covers can comprise a hat portion extending between two distal edges, support straps beneath the hat portion and extending between the distal edges, and thermal insulation disposed between the hat portion and the support straps. These can be coupled to the floor so as to allow space below for the flow of fluid. This allows the fluid to flow to holes in the floor of the engine bay, allowing the fluid (which could be flammable) to be drained away from potentially dangerous environments in the engine bay which may involve high temperatures.

The invention relates to a wall (11) for a leaktight and thermally insulating vessel for storing a liquefied gas, said wall (11) comprising, in succession in a thickness direction from the outside to the inside of the vessel, a leaktight outer barrier (13), a thermally insulating barrier (14) and a leaktight inner barrier (15), the thermally insulating barrier (14) having a gas phase at an absolute pressure of less than 1 Pa and comprising:—a radiative multilayer insulation cover (47) which extends at right angles to the thickness direction, said radiative multilayer insulation cover (47) comprising a stack of a plurality of sheets which are made of metal or polymer material coated with a metal and which are separated from one another by a textile layer; and-insulating elements (51) which have an open-celled porous structure and are arranged between the radiative multilayer insulation cover (47) and the leaktight outer barrier (13).

The invention discloses an air suspension dryer, and aims to solve the problems that the sealing effect is poor in the heating process of a traditional dryer, and the sealing performance and the heating effect of the dryer are affected. The air suspension dryer comprises a dryer body, a heating assembly and a heat insulation cover, and the dryer body and the heating assembly are located in the heat insulation cover; the heating assembly comprises a first insulating layer, a heating resistance layer and a second insulating layer, the first insulating layer, the heating resistance layer and the second insulating layer are sequentially arranged on the outer side of the dryer body, the heating resistance layer is connected with an external circuit, and a gap is formed between the second insulating layer and the heat insulation cover. The heating assembly is directly sintered or attached to the outer side of the dryer body, and the heating function and the drying function are highly integrated. The external heating assembly can prevent the initial structure of the dryer body from being changed, and the sealing performance of the dryer body is ensured. The general arrangement design is facilitated, and meanwhile, the production and assembly cost can be reduced.

Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

A protective container for a surfboard is disclosed, wherein the protective carrying case includes a bag including one or more retaining elements, wherein the retaining elements include a plurality of microbeads and at least one vacuum port. A vacuum pump is able to withdraw air from within the retaining elements to compress the microbeads around the surfboard within the container, creating a conforming and protective fit around the board.

A fuel injector includes a mount, a stem, a nozzle, and a heat shield. The stem extends from the mount. The nozzle is at a distal end of the stem opposite the mount and configured to discharge an oxidant-fuel mixture along a nozzle axis. The heat shield extends from the mount towards the nozzle. The heat shield includes a stem segment surrounding the stem and at least a portion of the nozzle and a compliant segment extending from the stem segment to the nozzle, a lip extending from the nozzle, or a cap surrounding the nozzle.

A heat shield for protecting a part of an aircraft is disclosed including superposed layers providing thermal protection, and one or more layers providing fire protection. The heat shield also may include other layers implementing other functions.

The present disclosure provides a connector assembly comprising a shielding cage and a liquid cooling cabin. The shielding cage has an insertion space and a window in communication with the insertion space. The liquid cooling cabin is configured to allow a cooling liquid to circulate and flow inside, the liquid cooling cabin comprises a shell having an opening, a thermal coupling cover provided at the opening of the shell, and an elastic sealing unit sealing a gap between the thermal coupling cover and the shell, the thermal coupling cover having a thermal coupling plate entering into the insertion space via the window of the shielding cage, the thermal coupling plate being capable of elastically moving in a direction close to the shell and elastically restoring in a direction away from the shell by a function of the elastic sealing unit.

The invention relates to the technical field of aviation equipment, in particular to an electric gas compressor system and a cooling method thereof.The electric gas compressor system comprises a heat insulation cover and further comprises a gas compressor, a motor, a turbine, a first heat exchanger and a second heat exchanger which are fixed in the heat insulation cover; the outlet is communicated with a hot side runner inlet of the second heat exchanger; a hot side runner outlet of the second heat exchanger is communicated with an inner cavity of a shell of the motor through a cooling air channel, and the cavity is communicated with an airflow inlet of the turbine; the air compressor, the motor, the turbine and the two-stage heat exchanger are integrated in the heat insulation cover, open type cooling circulation without an external cold source is constructed, self-cooling of the motor and a bearing is achieved, a relatively low-temperature environment is built in the heat insulation cover, and the problem that an existing electric air compressor generally lacks effective self-cooling capacity, and the service life of the air compressor is prolonged is solved. And active heat management cannot be carried out on heat-sensitive parts such as motor windings and bearings by utilizing own airflow.

The invention discloses a halogen-free low-smoke flame-retardant polyolefin cable which comprises a composite cable core, a first flame-retardant wrapping tape layer, an inner sheath, a second flame-retardant wrapping tape layer, a waterproof layer, a metal sheath layer and an outer sheath which are sequentially arranged from inside to outside. The outer sheath is made of a ceramic polyolefin material which is extruded and covered on the metal sheath layer. According to the low-smoke halogen-free cable, the ceramic polyolefin outer sheath is introduced into the cable structure, so that the problems of sheath softening, insulating layer stripping, structure collapse and the like of a traditional low-smoke halogen-free cable during high-temperature combustion are effectively solved. The ceramic polyolefin material can be converted into a compact ceramic layer under the action of flame to form a firm heat insulation barrier, so that the integral structure of the cable is kept complete, flame spreading and conductor short circuit are prevented, and the fire resistance and continuous power supply performance are remarkably improved.

A turbocharger heat management structure relates to the technical field of internal combustion engine supercharging devices and comprises a radial flow turbine, a centrifugal compressor and a bearing system which are connected, and the heat management structure is arranged between the radial flow turbine and the bearing system. The heat management structure comprises a first heat insulation cover, a second heat insulation cover and a third heat insulation cover which are in a revolving body metal sheet shape and arranged at the turbine back disc, a first heat insulation cavity is formed between the first heat insulation cover and the second heat insulation cover, a second heat insulation cavity is formed between the second heat insulation cover and the third heat insulation cover, and a third heat insulation cavity is formed between the third heat insulation cover and the annular cooling groove. The first heat insulation cavity communicates with a gap in the turbine back disc, and the third heat insulation cavity is connected with a cold air hole. The third heat insulation cavity, the second heat insulation cavity and the first heat insulation cavity are sequentially communicated through an air guide structure. On the premise that the weight and the size are not greatly increased, the heat insulation efficiency is greatly improved, and the purpose of actively and efficiently cooling a key area is achieved.

This invention provides a valve actuation device and a valve assembly for controlling fluid flow. The valve actuation device comprises: a linear actuator including a shaft operatively coupled to an electric motor; a fluid-sealed enclosure housing the shaft and a rotor of the electric motor; a control unit located outside the enclosure; and a housing containing the linear actuator, the enclosure, and the control unit. According to the invention, the housing has a heat shield between the enclosure and the control unit. The heat shield may have a wall portion molded or mounted on the inner side of the housing, wherein the wall portion may circumferentially surround a front closed end of the enclosure.

The refrigerant circuit for hydrocarbon refrigerants is isolated from heat-generating elements within the vehicle body. [Solution] The on-board air conditioning system comprises a refrigerant circuit R and first and second coolant circuits C1 and C2. The refrigerant circuit R has a compressor 20, a condenser for heat dissipation, an expansion valve 24a, and an evaporator for heat absorption, through which a hydrocarbon refrigerant circulates. A first heat exchanger 30 is integrally configured with the condenser of the refrigerant circuit R and transfers heat from the refrigerant in the condenser to the coolant of the first coolant circuit C1. The first coolant circuit C1 has a radiator. A second heat exchanger 40 is integrally configured with the evaporator of the refrigerant circuit R and cools the coolant of the second coolant circuit C2 with the refrigerant in the evaporator. The second coolant circuit C2 has a cooler core located in the air conditioning unit. The on-board air conditioning system comprises a heat shield plate 100 positioned between the refrigerant circuit R and the first and second heat exchangers 30 and 40 and a heat-generating element 14 mounted on the vehicle.

An actively-cooled heat shield system includes a heat shield, a tank, a pump, a heat exchanger, and a turbine. The heat shield defines a windward side of a vehicle. The tank stores a coolant. The pump receives the coolant from the tank and outputs a pressurized coolant. The heat exchanger is integrally connected with the heat shield. The heat exchanger receives the pressurized coolant from the pump, transfers heat from the heat shield to the pressurized coolant to generate a heated fluid, and outputs the heated fluid. The turbine includes an inlet, a shaft, and an outlet. The inlet receives the heated fluid output from the heat exchanger. The shaft is coupled to the pump and includes turbine blades. The shaft rotates and powers the pump when the heated fluid received from the heat exchanger acts on the turbine blades. The outlet outputs the heated fluid.

A battery cell having a can including a bottom member and a sidewall member, and a cap covering an opening of the can, and an electrode assembly accommodated inside the can is provided. A current collection plate is connected to an electrode tab provided at an open end of the can located at an axial side of the electrode assembly. The current collection plate includes an electrode tab connection portion that electrically connects to the electrode tab. A can connection portion is provided outside the electrode tab connection portion in a radial direction that electrically connects to the can. A conductive connection portion electrically connects the can connection portion and the electrode tab connection portion. A periphery the sidewall member and the cap are seam-welded along a peripheral direction, and part of an insulating member is interposed between the current collection plate and the electrode assembly in the axial direction.

The present application relates to a kind of double-layer cable protection sleeve and its preparation method and application, the double-layer cable protection sleeve includes gas production inner layer and carbon formation outer layer;The gas production inner layer includes resin matrix A, metal hydrate flame retardant and sheet nano filler A;The carbon formation outer layer includes resin matrix B, intumescent flame retardant and sheet nano filler B.The present application is structured and formula design to cable protection sleeve, utilize the difference of two layers of material decomposition temperature realizes combustion timing cooperation, to dynamically construct thick porous heat shield, solve the problem that traditional single-layer high filling flame-retardant sheath carbon layer is easy to peel off, gas dissipation direction is uncontrollable, and the problem of low flame-retardant efficiency, realizes the self-reinforced flame-retardant protection of combustion trigger type under the premise of not relying on superhigh filling amount.

The invention provides a cryogenic system and a vacuum processing method, which can improve the maintaining precision of the exhaust speed in a cryopump. The height of the heat shield (11) is a first height (H11). Among the regions defined by the heat shield case (11) and the baffle (13), a region extending from the opening (11A) of the heat shield case (11) to 1 / 2 of the first height (H11) is a temperature adjustment region (10S). At least one of a portion of the heat shield (11) included in the temperature adjustment region (10S) and the baffle (13) is a portion to be heated. A cryogenic system (1) is provided with: a temperature sensor (15) positioned within a temperature adjustment region (10S); a heating unit (16) that heats the portion to be heated; and a control unit (20) that controls the driving of the heating unit (16). The control unit (20) controls the driving of the heating unit (16) on the basis of the value detected by the temperature sensor (15) so that the temperature of the shutter (13) becomes a prescribed value.

A thin film deposition apparatus includes: a chamber configured to process a plurality of substrates; a plurality of heater members disposed to correspond to the substrates to heat the substrates, respectively; a plurality of lift pins configured to support lower surfaces of the substrates while elevating through the heater members, respectively; a plurality of heat shield plates, having a heat shield function between the heater members, on which lower ends of the lift pins are configured to be seated; and a plurality of support columns coupled with and supporting the heater members.

The invention relates to a device (1) for attaching a heat shield (2) to an aircraft panel (3), comprising a first attachment element (4) associated with the heat shield (2), a second attachment element (5) associated with the aircraft panel, and a metal wire (6) forming a loop (7). At least one of the attachment elements is provided with means (10, 11) for holding the ring which is closed by a braking member (12) at the end (9) of the ring in order to gather the attachment elements together; the ring abuts one of the attachment elements in its middle portion (8) and abuts the other of the attachment elements in the braking member (12), respectively. The ring is arranged separate from the heat shield (2) and the aircraft panel (3), and the ring passes through the outside of the heat shield (2) and the aircraft panel (3).