37results about How to "Effective heat protection" patented technology

The invention discloses a double-layer-wall heat insulation screen used for an afterburner. Cooling protection is formed for the wall surface of the afterburner by using an inner convection cooling mode and a gas side air film cooling mode. The double-layer-wall heat insulation screen comprises a gas side gas film hole plate, a cool air side impacting plate and a trapezoidal reinforcing frame. The gas side air film hole plate serves as the inner wall of a cylinder body of the afterburner, the inner side of the gas side air film hole plate is provided with a main gas duct of the afterburner, the cool air side impacting plate and an outer wall surface form a cool air duct, and the trapezoidal reinforcing frame is arranged between the impacting plate and the air film hole plate. The double-layer-wall heat insulation screen is formed by the impacting plate, the air film hole plate and the trapezoidal reinforcing frame. Cooling air is made to form an air film on the gas side inner wall of the heat insulation screen, and heat load and gas flow losses are reduced. In addition, composite cooling is formed through inner convection cooling and outer air film cooling of a double-layer wall, incoming heat is brought away through convection heat exchange, and the cool air utilization rate is increased. Reduction is achieved after reflection, the effect of vibration prevention is achieved, the service life of the afterburner is prolonged, and the reliability of the afterburner is enhanced.

The invention relates to a thermal protection method of a porous medium jetting support plate leading edge nose cone. The thermal protection method comprises the following steps that firstly, a narrow seam is formed in the jetting support plate leading edge nose cone, a front cavity of a jetting support plate is communicated with one fuel pipe, and a back cavity of the jetting support plate is communicated with the other fuel pipe; secondly, most of low-temperature fuel is quickly sprayed out of the narrow seam through the fuel pipe arranged at the front cavity, and the rest part of fuel permeates to the surface of the front cavity in a sweating mode; thirdly, the fuel sprayed to the leading edge is collected through the narrow seam, and produced detached shock waves are pushed away from the leading edge nose cone; fourthly, a thick protection air film is formed at the leading edge nose cone through the fuel sprayed out of the narrow seam and under the action of high-speed main stream, the thick protection air film is fused with a compact air film formed on the surface of the jetting support plate in a sweating and cooling mode, and thermal protection for the jetting support plate is enhanced. According to the thermal protection method, due to the fact that the fuel is sprayed to the high-speed main stream through the narrow seam at the leading edge nose cone, the low-temperature fuel serves as coolant for reducing the temperature of the leading edge nose cone when sprayed out of the narrow seam, meanwhile the sprayed fuel can form the protection air film on the surface of the jetting support plate, and the protection air film can conduct effective thermal protection on the jetting support plate.

In the invention, a longitudinal corrugated impact pore plate and a flat plate type air film plate are used to constitute a double-wall cooling structure. Impact holes and air film holes are distributed in a staggered manner respectively; impact holes are formed in wave troughs of the corrugated impact hole plate and air film holes in the air film hole plate directly face wave peaks of the corrugated impact hole plate; and each of the corrugated impact pore plate and the air film hole plate is a plurality of unit period structures in the axial direction. A relatively small impact distance is formed between the wave trough and the air film hole plate, so that the heat exchange by impact may be increased; a relatively larger space may be formed between the wave peak and the air film hole plate, full development of cool air flowing is facilitated, outflowing is facilitated, the flow resistance may be reduced, the utilization ratio of cold air is increased and the contradiction between themethod of impact distance reduction for heat exchange enhancement and the method of impact distance increase for flow resistance reduction is solved; and meanwhile, the air film plate is a flat plate, so that air film attachment is facilitated to form effective heat protection, heat stress is reduced and the problem of uneven heat stress of a corrugated heat shield is solved.

An air / methane combustor for a high-temperature pure air heat accumulation type heating device is characterized by comprising a head portion and a body portion, wherein the head portion and the body portion are fixedly connected together to form an air / methane combustor integrated structure, a premixing cavity is formed in the head portion, a combustion chamber inner cavity is formed in the body portion, air in the head portion enters the premixing cavity in a rotational flow manner and is mixed with methane, with the flow being adjustable, jetted in the radial direction at the premixing cavity to form premixed gas, a sudden expansion face backflow area is formed at the connection portion between the head portion and the body portion, the air / methane premixed gas is ignited at the sudden expansion face backflow area, and a preheated heat source is provided for the heat accumulation type heating device. According to the air / methane combustor for the high-temperature pure air heat accumulation type heating device, a pintle structure is designed on the head portion, under drive of an actuator, the injection area of a methane spray nozzle is changed, it is guaranteed that gas media arealways mixed at the best momentum ratio, and ignition and efficient combustion of the premixed gas is ensured.

The invention relates to a preparation technology of a titanium alloy high-temperature protective coating and particularly relates to TiAl3 / Al2O3 composite powder as well as a preparation method and application thereof. The preparation method comprises the steps of firstly, carrying out thermal treatment after carrying out high-energy ball milling on pure Al and TiO2 nanopowder according to a certain ratio for a certain time to obtain the TiAl3 / Al2O3 composite powder; and then, spraying the prepared composite powder on a titanium alloy substrate at the temperature of 100-700 DEG C and the pressure of 0.3-5.0MPa by using a cold gas dynamic spraying method to form a TiAl3 / Al2O3 composite coating. The coating comprises the components of TiAl3 and Al2O3, wherein Al2O3 is uniformly distributed in the coating, and the coating is more than 10mu m thick. The preparation method disclosed by the invention is simple in operation, the components are easily controlled, the obtained coating is low in porosity, good in compatibility with matrix and binding force and relatively good in high-temperature oxidation resistance, the mutual diffusion between the coating and the matrix can be greatly reduced, and the problem of high-temperature oxidation of titanium alloy can be favorably solved.

The invention discloses a lower spraying laminar flow cooling device. The device comprises a plurality of groups of lower spraying devices, wherein each group of lower spraying device comprises a collecting pipe, two plunger pipes, two plungers and two U-shaped covers; the collecting pipe is fixedly arranged along a direction vertical to the operation direction of strip steel; a plurality of goose neck spray pipes are uniformly distributed on the collecting pipe along the axial direction; the two plunger pipes are fixedly arranged above the two ends of the collecting pipe respectively, pass through the plurality of goose neck spray pipes which are uniformly distributed at the two ends of the collecting pipe respectively, divide the goose neck spray pipes into upper nozzles and lower spraypipes, and are communicated with the upper nozzles and the lower spray pipes of the goose neck spray pipes through a plurality of through holes; the two plungers are arranged in the two plunger pipesrespectively; the two U-shaped covers are covered outside the two plungers in a mode that openings are downward; and the plungers are connected with driving devices through the U-shaped covers, so that movement in the axial direction is realized, the through holes are blocked, and cooling water quantity is adjusted.

The invention discloses a double-layer wall cooling structure composed of a transverse corrugated impact plate and a flat plate type gas film plate. According to the double-layer wall cooling structure, impact holes and gas film holes are distributed in a crossed mode, the impact holes are formed in wave troughs of the corrugated impact pore plate, the gas film holes in the gas film pore plate arearranged at wave peaks just opposite to the corrugated impact pore plate, and the corrugated impact pore plate and the gas film pore plate are in a plurality of unit cycle structures in the axial direction. Small impact distances are formed between the wave troughs and the gas film pore plate so that impact heat exchange can be enhanced, larger spaces can be formed between the wave peaks and thegas film pore plate, so that the cold gas flow can be fully developed, flowing out of the cold gas can be facilitated, the flow resistance can be reduced, the cold gas utilization rate can be improved, and the contradiction that the impact distances are reduced so as to enhance the heat exchange, but the impact distances need to be increased so as to reduce the flow resistance is solved. Meanwhile, the gas film plate is a flat plate, so that the adhesion of a gas film is facilitated, then effective heat protection is formed, the thermal stress is reduced, and the problem of non-uniform thermalstress of a corrugated heat insulation screen is solved.

An internal and external cooling combined launch platform is provided. A launch platform body is provided with a supporting frame and a guiding hole for guiding gas in gas flow, and the supporting frame is processed into a through hollow structure to form a built-in flow channel serving as a cooling water flow channel and a water supply channel. The upper surface of the supporting frame and the side wall of the supporting frame facing the guiding hole are provided with a water spraying hole array communicated with the built-in flow channel. The launch platform not only improves the thermal protection capability of the launch platform body structure but also reduces the installation complexity between systems. At the same time, the internal and external cooling of the launch platform is fully achieved by combining the external surface water spraying cooling mode.

The invention discloses a stable type aging furnace high-temperature-resistant axial flow fan which comprises a rectangular installation plate, a drive motor, a cooler, an impeller mechanism, a transmission shaft, an impeller shell, a cylindrical air flue, a toroidal base and a conical inner cover. According to the stable type aging furnace high-temperature-resistant axial flow fan, the conical inner cover can be matched with the cylindrical air flue so as to guide hot air, so that the air can be quickly discharged from an air outlet; the conical inner cover can be used for effectively heat-insulating and protecting the cooler; the cooler can be used for heat-insulating the transmission shaft, so that two bearings can be cooled and are prevented from being damaged by high temperature, andthe service life of each bearing is prolonged; and by utilizing a conical flow guiding cover, the front air resistance of the impeller mechanism can be reduced, the inlet air is prevented from causingthe shaking influence on the rotary stability of the impeller structure, so that the impeller mechanism is ensured to rotate stably.

The invention discloses a rotational flow torch igniter based on 3D printing forming. The rotational flow torch igniter comprises an electric spark plug rod, a torch ignition tube and a red copper sealing gasket, wherein the torch ignition tube comprises a head tube section, a body tube section, a throat nozzle section and a tail tube section which are integrally arranged in a 3D printing mode; amain working principle of the rotational flow torch igniter is as follows: ignition combustion is carried out in an ignition chamber in the head tube section, secondary combustion is carried out in asecondary combustion chamber of the body tube section, and tertiary blending combustion is carried out in the throat spray tube section, so that the ignition starting process is stable, the combustionprocess is sufficient, and the combustion working reliability of the igniter is greatly improved; and oxidizing agent rotational flow can be arranged on the head tube section to protect the electricspark plug rod, a rotational flow field is arranged in the secondary combustion chamber to form gas film protection on the body tube section, connecting and fastening parts with a thrust chamber are reasonably designed, the appearance structure of the torch igniter is simplified, the miniaturization design of the torch igniter is achieved, the process complexity and cost are reduced, and the manufacturing period is shortened.

The invention relates to a film cooling system with an ejector and a method. The film cooling system comprises a coolant storage container arranged inside an aircraft, a suction hole and a plurality of film cooling micropores which are formed in the surface of the aircraft and the ejector connected with the coolant storage container, the suction hole and the film cooling micropores. According to the method, a high-pressure coolant is adopted as working fluid of the ejector, low-pressure fluid outside the aircraft is sucked, fluid after being mixed is used as cooling fluid of film cooling, after the mixed fluid flows out of the outlet of the ejector and arrives at the plurality of film cooling micropores on the surface of the aircraft, a cooling film is formed in the surface of the aircraft, and thermal protection of the high-temperature surface of a hypersonic aircraft is achieved.

The invention provides a design method of a venturi flow channel of a double-swirl atomizing device, which comprises the following steps of: (1) calculating the air flow passing through the double-swirl atomizing device; (2) calculating the flow WIN of a primary swirler according to that the flow WIN of the primary swirler of the double-swirl atomizing device is equal to the air flow WO passing through the venturi; (3) calculating a throat diameter d0 of the venturi according to the principle that the air flow Mach number of the venturi throat section is 0.1; (4) determining an axial positiondimension L0 of the venturi throat,(5) determining an inlet dimension d1 of the venturi flow channel and an outlet dimension d2 of the venturi flow channel; (6) determining the profile modeling of theventuri flow channel. According to the invention, the design method is an important part in the design of the double-swirl atomizing device, ensures the spray quality of the atomizing device and theeffective thermal protection of a fuel nozzle, and provides a basis for the design work in the future.

The invention relates to a heat insulating device, belonging to the technical field of chemical experiment supplies. The heat insulating device mainly comprises an anti-explosion vessel including a cover, wherein a sand grains heat insulating layer is arranged in the anti-explosion vessel; a support base is arranged below the anti-explosion vessel; the support base comprises a bracket including a support net; plastic sleeves are arranged on the leg parts of the bracket; and a groove corresponding to the outer diameter of the anti-explosion vessel is arranged on the middle of the support net. According to the invention, an asbestos wire gauze is substituted; in a using procedure, the heat insulating device plays a role by dint of change of physical performance of the heat insulating device; in addition, the heat insulating device has safe, non-toxic, environmental-friendly, acid-resist, alkali-resist, moisture-resistant and the like performances and is characterized by low and easily-acquired material, energy saving and long service life.

The invention relates to an anode high temperature protection method and protection device. A positive charge is applied to a shell or a component, meanwhile, a negative charge is applied to a self-renewing or easy-to-replace sacrificial electrode or a substance most in need of heating, or electrons (the negative charge) are emitted to a place far away from a spacecraft by an electron gun, and thespacecraft loses part of the negative charge and gains the positive charge. Positive ions in a high-temperature plasma is repelled by applying the positive charge to the component or shell needing tobe protected, therefore the heating of the positive ions in the high-temperature plasma to the component or the shell is effectively reduced, and the purpose of high temperature protection is achieved. The anode high temperature protection method and protection device are suitable for protection for high temperature generated by friction between the spacecraft shell and atmosphere in the recoveryprocess of the spacecraft, and meanwhile is also suitable for high temperature protection of the inner parts of a rocket engine, a turbine engine and a high-temperature furnace.

The invention provides a thermal bridge suppression structure for equipment installation, wherein equipment is installed in a suspended mode through an adapter lug arranged on an equipment shell, the adapter lug is connected with the top of an installation supporting foot through a connecting screw, the installation supporting foot is installed in an equipment cabin shell thermal protection structure, and the bottom of the installation supporting foot is connected with the equipment cabin shell through an adapter gasket. The installation supporting feet are of a hollow thin-wall structure, and pyrolysis materials are arranged in the inner areas and the outer areas of the installation supporting feet. According to the thermal bridge suppression structure, the hollow structure is adopted for mounting the supporting legs and a suspended mounting mode is adopted, so that heat transferred into a cabin and an equipment shell through a thermal bridge is greatly reduced, and effective thermal protection is realized.