10results about How to "Reduce wall temperature" patented technology

The invention is suitable for the technical field of aero-engines, and provides a venturi tube structure, a swirler and a combustion chamber, the venturi tube structure comprises a venturi tube outer layer and a venturi tube inner layer, the venturi tube outer layer is provided with a containing cavity, a plurality of first protrusions are arranged on one side of the venturi tube inner layer in the circumferential direction at intervals, and a plurality of second protrusions are arranged on the other side of the venturi tube inner layer in the circumferential direction at intervals; the venturi tube inner layer is embedded in the containing cavity, the multiple first protrusions abut against the inner wall of the containing cavity so that a first cavity can be formed between the venturi tube outer layer and the venturi tube inner layer, and the multiple second protrusions abut against the inner wall of the containing cavity so that a second cavity can be formed between the venturi tube outer layer and the venturi tube inner layer; the first cavity and the second cavity are mutually independent and are used for preventing high temperature from being directly transmitted to the inner layer of the venturi tube. By means of the core structure design of the double-layer tube body and the independent cavities, the first cavity and the second cavity which are independent of each other are formed between the two tubes, direct conduction of high temperature from the outer layer of the venturi tube to the inner layer of the venturi tube is blocked by means of the air heat insulation characteristic, and the carbon deposition restraining effect is remarkable.

This invention relates to a microribbed jet impact cooling channel for hot-end components of aircraft. It is an integral structure comprising 1 to 100 sub-channels arranged side-by-side, with adjacent sub-channels sharing sidewalls. Each sub-channel includes a main channel, microribs, and jet holes. Fuel enters the main channel from one end and through the jet holes, exiting from the other end. The main channel has a rectangular cross-section. Microribs are arranged at the bottom of the main channel, forming an array of microribs. Jet holes are arranged at the top of the main channel, with uniform or non-uniform distribution. The sidewalls of the main channel are smooth planes. This invention, with its arrayed microribs and jet holes, couples the effects of the microribs and the jet impact, effectively reducing the wall temperature of the scramjet engine combustion chamber without adding extra mass, effectively suppressing the temperature rise of high-heat components in the aircraft, thereby achieving higher Mach numbers.

The invention provides a thermal barrier coating exhaust passage with an anti-tempering function and an installation method, and relates to the technical field of thermal barrier coatings and diesel engine exhaust passages, the thermal barrier coating exhaust passage comprises an exhaust passage body, the exhaust passage body is coated with a thermal barrier coating, and the thermal barrier coating comprises a first bonding layer, a ceramic layer and a second bonding layer from outside to inside; the first bonding layer and the second bonding layer are made of the same material, an exhaust passage heat exchanger is installed on the exhaust passage body, and a spiral static mixer is installed on the inner side of the exhaust passage body, the exhaust passage with a spiral mixing structure is designed, mixing of incomplete combustion tail gas can be effectively promoted, in addition, a heat exchange channel is arranged on the outer side of the exhaust passage, and the heat exchange efficiency is improved. According to the design, heat transferred to the exhaust passage from the high-temperature cylinder cover can be reduced, heat on the high-temperature wall surface of the exhaust passage can be taken away, and the heat exchange passage and the exhaust passage are combined, so that the temperature of the wall surface of the exhaust passage is effectively reduced, and meanwhile, the situation that the local gas concentration is too high is avoided.

The invention aims at providing a combustion chamber and a combustion chamber interstage section, the combustion chamber interstage section comprises an inner wall body and an outer disc body, the inner wall body is arranged on the upstream of the outer disc body in the incoming flow direction, the inner wall body and the outer disc body are annular, the inner wall body is connected with the outer disc body through a connecting ring part, and the outer disc body is connected with the inner wall body. An outer ring cooling hole, an inner ring cooling hole and a middle cooling hole are formed in the combustion chamber interstage section, the outer ring cooling hole is formed in the outer edge of the inner wall body in the circumferential direction of the inner wall body, and the inner ring cooling hole penetrates through the inner edge of the inner wall body, the connecting ring part and the inner edge of the outer disc body. The middle cooling holes are formed in the inner wall body between the outer ring cooling holes and the inner ring cooling holes and face the outer disc body. An acute included angle is formed between the forming direction of the outer ring cooling holes and the central axis of the combustion chamber interstage section. According to the combustion chamber and the combustion chamber interstage section, interstage section ablation can be avoided.

The application provides a combustion chamber wall surface with locally encrypted cooling holes and a swirl combustion chamber, and comprises a combustion chamber wall surface; a plurality of cooling holes are arranged on the combustion chamber wall surface, and the cooling holes are distributed according to a temperature distribution curve of the combustion chamber wall surface. According to the application, the plurality of cooling holes are distributed according to the temperature distribution curve of the combustion chamber wall surface, the spacing between the cooling holes and adjacent holes is directly related to the local temperature, the cooling holes are denser in the place with higher temperature, the cooling effect is improved, the wall surface temperature is reduced, and the generation of local high temperature is avoided.

The present application relates to a kind of double-wall heat shields with baffle sandwich structure, double-wall heat shield is gas film orifice plate and impact orifice plate and turbulence baffle structure jointly constitutes the double-wall heat shield described;Turbulence baffle structure includes first helical baffle and second helical baffle vertically arranged on gas film orifice plate, and multiple separate turbulence spaces are enclosed by two baffle plates crossing each other;Gas film orifice is arranged at the multiple intersection points formed by the first helical baffle and the second helical baffle on the gas film orifice plate;The present application also provides the heat shield gas film forming method, airflow flows out through multiple fan-shaped holes to form gas film outflow and main flow gas mixing, and forms gas film cover layer on wall surface;The present application can not only strengthen the heat exchange inside heat shield, but also improve gas film cold efficiency, in addition, the impact orifice plate-gas film orifice plate double-wall structure with baffle turbulence fixed has good mechanical properties.

The application discloses a mixing hopper which is arranged on the wall of a flame tube, and comprises an inner cone part, an outer ring part arranged outside the inner cone part, and a hopper cap used for connecting the wall of the flame tube. The inner cone part and the hopper cap enclose a mixing cavity used for mixing high-temperature gas and cooling gas flow. The inner cone part and the outer ring part enclose a cooling gap used for the flow of the cooling gas flow. Cooling holes are arranged on the inner cone part and are respectively communicated with the mixing cavity and the cooling gap, and are used for introducing the cooling gas flow into the cooling gap to impact cool the outer ring part and form a cooling gas film on the inner cone part. The outer ring part actively uses a small amount of cooling gas flow in cooperation with the cooling holes to effectively reduce the wall temperature of the mixing hopper and prevent the mixing hopper from ablation. Meanwhile, the outer ring part can also shield part of the wall of the inner cone part to prevent the inner cone part from ablation as much as possible, and the cooling effect is good, the service life of the mixing hopper is prolonged, and the mixing hopper can be used in the flame tube for a long time. In addition, the application further discloses a combustion chamber. In addition, the application further discloses an aero-engine.

The present invention relates to a supercritical carbon dioxide boiler system with a high-safety furnace heating surface, and belongs to the technical field of boiler equipment. It includes a supercritical carbon dioxide boiler, a turbine, a high-temperature regenerator, a low-temperature regenerator, a cooler, a compressor, a recirculation fan, a recirculation flue gas heater, a burner, an air preheater and a chimney; the present invention reduces the overall temperature level of the flue gas in the furnace by introducing a flue gas recirculation setting, thereby reducing the average heat load and the peak heat load of the radiation heat transfer in the furnace, so as to achieve the reduction of the furnace heating surface temperature. The present invention can effectively achieve the purpose of reducing the wall temperature of the furnace heating surface, thereby avoiding the possibility of overheating of the boiler furnace heating surface, significantly extending the service life of the boiler heating surface and increasing the safety of the boiler furnace heating surface.

The invention relates to the technical field of aero-engines, and discloses an S-shaped spray pipe self-air-entraining wall surface cooling infrared suppression structure and a design method thereof.Outer culvert airflow of a mixer at the front section of an S-shaped spray pipe is guided into the outlet end of the S-shaped spray pipe through an air entraining pipe, the temperature of the wall surface of the outlet section of the S-shaped spray pipe is reduced, and therefore the purpose of reducing infrared radiation signals is achieved; the cooling effect on the wall surface of the outlet of the S-shaped spray pipe can be improved, the pertinence on cooling of the outlet of the spray pipe is high, full-wall-surface cooling of the S-shaped spray pipe is not needed, the problem that the middle section of the S-shaped spray pipe with small contribution to infrared signals is easily overcooled due to the fact that a sleeve is adopted for cooling the whole-course wall surface of the S-shaped spray pipe traditionally is solved, the cost is low, and the service life is long. Therefore, the thrust performance of the engine is ensured.