54results about How to "Reduce bleed air" patented technology

The invention discloses an anti-icing and deicing method for a civil aircraft adopting loop heat pipes, which comprises the following steps: 1, determining an icing protection range for parts of the civil aircraft needing anti-icing and deicing, and calculating the maximum anti-icing and deicing heat load Q required by the anti-icing and deicing parts; 2, arranging a heat exchange device to determine a heat source for anti-icing and deicing; 3, selecting loop heat pipes to determine the number of the loop heat pipes; and 4, arranging condensers and evaporators of the loop heat pipes on the civil aircraft. The method improves the heat utilization rate of the civil aircraft, reduces the bleed air from a compressor of an engine, improves the available thrust of the engine, reduces the weight of some structural parts used for anti-icing, deicing and bleed air cooling of the civil aircraft, and improves the flight performance of the civil aircraft and the economical efficiency focused by the civil aircraft.

The invention belongs to the technical field of aircraft thermal management, and relates to an energy-optimized aircraft electromechanical system thermal management method. The method comprises the steps: introducing a part of ram air absorbing heat of a heat source into a fuel tank and airborne nitrogen making equipment through a first pipeline to serve as a fuel tank pressurization air source and an airborne nitrogen making supplementary air source; leading out air from the rear end of the engine outer culvert fan to serve as a cold source to be led into the cold fuel tank heat exchanger, and soaking the cold oil tank heat exchanger in fuel oil of the fuel tank. The use mode of ram air is optimized, the air source serves as an air source of an oil tank pressurization and airborne nitrogen generation system, the air entraining amount of the engine is effectively reduced, the cold fuel tank is designed, air is led out from the rear portion of an outer culvert fan of the engine to serveas a cold source, fuel oil is cooled, the temperature of the fuel oil is reduced, and the heat sink capacity of the fuel oil is improved.

An anti-icing passage system with functions of precooling and backheating relates to the anti-icing operation of a passage of an engine with higher entraining temperature, comprises a anti-icing pipeline (10), a valve (11), a regulator (12) and a sensor (13), wherein the valve (11) is arranged on the anti-icing pipeline; the regulator (12) is used for regulating air pressure in the anti-icing pipeline; and the sensor (13) is used for monitoring pressure at an outlet of the regulator. The anti-icing passage system is characterized by comprising an inner-side anti-icing cavity (7) and an outer-side anti-icing cavity (6), wherein the inner-side anti-icing cavity (7) is formed by a clapboard (1) and an inner envelop (2), and the outer-side anti-icing cavity (6) is formed by the inner envelop (2) and an outer envelop (3); an air let (5), connected with the anti-icing pipeline (10), is left at the inner-side anti-icing cavity (7); a communicating hole (9) is arranged between the inner-side anti-icing cavity and the outer-side anti-icing cavity; and a vent (4) is left at the outer-side anti-icing cavity (6). The passage anti-icing system has a simple structure, high reliability and a low cost, is especially suitable for anti-icing passage systems of engines of turbine type and the like with higher entraining temperature, and is capable of reducing the entraining quantity of the system and the influence on the performances on the engine.

The invention discloses a low air-entraining type maleic anhydride poly carboxylic acid water reducing agent and a preparation method thereof. The low air-entraining type maleic anhydride poly carboxylic acid water reducing agent is prepared from the following components in parts by weight: 200 parts of TPEG, 15-22 parts of maleic anhydride, 3.5-6.0 parts of a functional monomer A, 0.5-1.2 parts of a functional monomer B, 1.9-3.0 parts of oxidant, 0.2-0.42 part of reducing agent, 0.5-1.5 parts of chain transfer agent and 345-360 parts of deionized water; and a pH value is regulated with liquid alkali to 6-7. The low air-entraining type maleic anhydride poly carboxylic acid water reducing agent is applied to high grade concrete and has the actions of low air entraining and viscosity reduction, so that the concrete has easy compaction ability and better gas exhausting ability, fair-faced concrete with good apparent effect can be obtained, and the technical problems of large viscosity, difficult exhaust and poor apparent effect of the high grade concrete are effectively solved. Meanwhile, the preparation technology is simple with normal temperature condition only needed, saves energy, is environmental-friendly and is liable in industrialization.

The invention discloses a cabin pressurizing oxygen supply system based on aerodynamic turbine driving. The cabin pressurizing oxygen supply system comprises a temperature sensor, a first electric control valve, a first heat exchanger, a water separator, a Venturi pressure stabilizer, a pressure sensor, a first flow sensor, an aerodynamic turbine, a second electric control valve, a hollow fiber membrane separator, a centrifugal compressor, a second flow sensor, a second heat exchanger, a third flow sensor and a controller. According to the invention, the centrifugal compressor driven by the aerodynamic turbine is used for recycling the oxygen-enriched gas of the hollow fiber membrane separator. The oxygen content of the cabin is increased, the pressure height of the cabin is conveniently increased, and the requirement for the structural strength of the cabin is effectively reduced; the air entraining amount of an engine air compressor is reduced, and the compensation loss of an airplane is reduced; the system has no motor drive and is feasible to manufacture; the aerodynamic turbine has the advantages of being high in rotating speed, small in size and large in flow and meets the technical requirement for cabin pressurization and oxygen supply.

The invention relates to a turbofan engine air intake duct anti-icing structure and an anti-icing method. The turbofan engine air intake duct anti-icing structure is characterized by comprising an air-entrainment total pipe of an engine core machine, a collector box connected with the air-entrainment total pipe, several heating branch pipes divided from the collector box, and several anti-icing ring chamber arranged in an anti-icing part of an air intake duct port, branch pipe valves are arranged on the heating branch pipes, anti-icing hot gas is introduced into the air-entrainment total pipe and flows to the collector box, then is optionally distributed to at least a part of the heating branch pipes according to the opening condition from the collector box, then is conveyed to the corresponding anti-icing ring chamber through the heating branch pipe, and is discharged from an air exhaust port of the anti-icing ring chamber.

The invention relates to a core engine and a turbine engine. The turbine engine comprises a gas compressor, a combustion chamber and a turbine; the turbine comprises a turbine first-grade movable blade; the turbine first-grade movable blade is provided with a front cooling cavity near the combustion chamber, and a back cooling cavity far from the combustion chamber; and the front cooling cavity and the back cooling cavity are independently arranged. The core engine further comprises a first cooling flow way and a second cooling flow way; the first cooling flow way can lead final-stage compressed gas of the gas compressor into the front cooling cavity; and the second cooling flow way can lead non-final-stage compressed gas of the gas compressor into the back cooling cavity. The core engine respectively leads the gas from two different positions of the gas compressor for cooling the turbine first-grade movable blade; the final-stage compressed gas and the non-final-stage compressed gas are used for cooling the turbine first-grade movable blade; the total flow needed by cold gas of the turbine first-grade movable blade is totally reduced; the heat efficiency of the engine is improved; and the oil consumption rate is reduced.

The invention provides a low air-entrained and viscosity-reduced slow-release polycarboxylate water reducer and a preparation method thereof. The low air-entrained and viscosity-reduced slow-release polycarboxylate water reducer is obtained by carrying out copolymerization reaction on a polyether monomer, a viscosity reducer, an unsaturated acid monomer and an unsaturated acid hydroxyl alkyl ester under the action of an initiator and a molecular weight modifier and adding an alkaline solution for neutralization until the pH value is 6-7. The low air-entrained and viscosity-reduced slow-release polycarboxylate water reducer has an excellent slow-release performance and a significant effect of delaying concrete coagulation time; the mobility of concrete is improved; meanwhile, the slump loss resistance and the water-reducing property of the polycarboxylate water reducer are also ensured; the durability and the later strength of the concrete are improved; the production technology is simple and the production cost is low; and the low air-entrained and viscosity-reduced slow-release polycarboxylate water reducer has good economic benefits and social benefits.

The invention discloses a hot air anti-icing structure of an aero-engine rectifying support plate. The hot air anti-icing structure comprises an anti-icing component, a hot air inlet is formed in the middle of the upper end surface of the anti-icing component and extends to the lower end of the anti-icing component along the uniform section in the spanwise direction of the rectifying support plate to form a hot air cavity; the anti-icing part is provided with a third hot air outlet along the lower end surface; a support plate front cavity is formed in the front end in the anti-icing part, and hot air flow in the hot air cavity is injected into the support plate front cavity in the tangential direction through the upper row of fine channels and flows into the rear end air collection cavity through the lower row of fine channels; the upper row of fine channels are a channel set which is uniformly arranged at intervals in the spanwise direction of the rectifying support plate, and the lower row of fine channels and the upper row of fine channels are correspondingly arranged according to a sequence or staggered arrangement mode; a plurality of splitter plates are arranged in the middle of the gas collecting cavity in the vertical direction, and a plurality of gas outlet holes are formed in the wall surfaces of the rear sections of the splitter plates; the supporting plate front cavity extends from the upper end face to the lower end face in the spanwise direction of the rectifying supporting plate, the upper end face forms a first hot air outlet, and the lower end face forms a second hot air outlet.

The invention provides a helicopter air inlet channel anti-icing and cabin heating comprehensive heat utilization system. The helicopter air inlet channel anti-icing and cabin heating comprehensive heat utilization system comprises a shut-off valve (1), an air entraining pipeline (2), an air suction fan (3), a ventilation pipeline (4), a heat exchanger (5), an anti-icing control valve (7), a heating control valve (8) and an ejector (9). The air entraining pipeline (2) entrains air from an air inlet (A) of a helicopter engine, sends the air to the heat exchanger (5), and respectively sends the air to the air inlet channel anti-icing cavity (C) and the ejector (9) through the heat exchanger (5); the ventilation pipeline (4) is connected with the atmosphere/air in the cabin, the air suction fan (3) is arranged on the ventilation pipeline (4), air is sucked into the ventilation pipeline (4) to flow to the heat exchanger (5), the air passing through the heat exchanger (5) is mixed with bleed air output by the ejector (9), and the mixed air is conveyed to the noise reduction mixing cavity (D) and then enters the helicopter cabin. Anti-icing of an air inlet channel of the engine and warming of the cabin are integrated, and the air entraining amount of the engine is reduced.

The invention discloses a preparation method of monomer-terminated amine ether for synthesizing an early-strength polycarboxylate superplasticizer. The method comprises the following steps: (1) synthesizing block monomer amine ether; (2) refining the block amine ether; and (3) preparing monomer-terminated amine ether. The method provided by the invention has simple process control, stable productstructure and excellent product performance. In the method, a one-step synthesis method different from conventional synthesis methods of alcohols, amine initiators and epoxides is adopted, and throughsynthesis and refining of EO-PO-EO type specific block amine ether and a key technology for terminating amine ether, nitrogen element is introduced into a final polycarboxylate superplasticizer and aprimary hydroxyl group is eliminated through terminating. The polycarboxylate superplasticizer synthesized by the method not only improves an early strength function, but also appropriately reduces an air entraining content, thus further expanding the application of the polycarboxylate superplasticizer in the field of concrete.

The invention belongs to the technical field of aviation, and relates to an air blowing rain removal system based on a supersonic flow ejection effect, which mainly comprises a first air path and a second air path through which airflow passes, and the first air path and the second air path are sequentially provided with an air source, a pressure regulating valve, a pressure sensor and a nozzle along the airflow direction; the first gas path and the second gas path are connected at the gas source outlet through a third gas path, the third gas path is provided with a cross air-entraining valve, the pressure sensor, the pressure regulating valve and the cross air-entraining valve are all connected with a control device, and the nozzle with the diagonal plane can enable the speed of the sprayed gas flow to reach supersonic speed and does not generate shock waves. The rain removal effect is better, and the air entrainment amount from the air source system can be reduced by injecting air in the surrounding environment.