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 discloses an early-strength polycarboxylate water reducing agent for a component and a preparation method for the early-strength polycarboxylate water reducing agent, and belongs to the field of water reducing agent preparation. The water reducing agent is formed by polymerization of the following ingredients in percentage by weight: 80-85% of methyl alkene butyl polyoxyethylene polypropylene oxide monomer with the molecular weight more than 2400, 10-15% of unsaturated monocarboxylic acid and derivative monomer thereof and 0.5-5% of unsaturated alkenyl sulfoacid and sodium salt thereof; the preparation method comprises the following steps: under the temperature condition of 20-40 DEG C, all ingredients are enabled to be subjected to polymerization reaction in an aqueous solution by adopting a redox initiation system, after polymerization reaction is performed, neutralization is performed through a neutralizing agent, so that the polymer with low air entraining amount and good dispersibility is obtained; the early-strength performance of the polycarboxylate water reducing agent is reinforced with the increasing of the macromonomer molecular weight; the using requirements of early strength or super early strength of the component are met.

The invention discloses high-strength impervious concrete and a preparation method thereof. the high-strength impervious concrete comprises the following components in parts by weight: 320-350 parts of cement, 120-150 parts of fly ash, 65-95 parts of mineral powder, 850-900 parts of crushed stone, 820-850 parts of medium sand, 2-6 parts of a water reducing agent, 170-190 parts of water, 10-26 parts of an impervious composition, and 100-120 parts of a coarse aggregate, wherein the impervious composition comprises the following components in parts by weight: 10-25 parts of modified rubber particles, 15-25 parts of a fiber composition, 20-30 parts of steel slag, 10-15 parts of boron trioxide, 15-25 parts of gypsum, and 10-15 parts of superabsorbent resin, and the fiber composition comprises carbon fiber, polypropylene fiber, calcium formate and polyamide with a mass ratio of 1:0.7-1.4:0.4-0.8:1.5-2.5. The high-strength impervious concrete has the advantages of high strength, good impermeability and easy pumping.

The invention provides a cooling method and device for an engine core module. According to the method, cooling airflow in a fan cabin is reutilized and introduced into the core module so as to cool the core module. In the ground test state, ambient airflow enters the fan cabin for ventilation cooling through an exhaust port of the fan cabin in a free convection mode and is discharged through an air inlet of the fan cabin finally. In other flying states, ambient airflow enters through the air inlet of the fan cabin under the ram action, is divided into a left stream and a right stream for ventilation cooling of the fan cabin, and then is introduced into the core module through an air guiding pipe under the differential pressure of the fan cabin and the core module to conduct ventilation cooling on the core module, and meanwhile, the ambient airflow can conduct directional concentrated cooling on the local high-temperature region in the cabin under the guiding of the air guiding pipe. In this way, ventilation cooling of the core module is achieved, the air entraining content of an external duct is reduced, entraining loss of the external duct is reduced, and reutilization of ventilation cooling airflow of the fan cabin is achieved.

The invention discloses a method for mixing polyester-ether macromonomers for preparation of a polycarboxylic acid water reducer, and belongs to the field of a water reducer. According to the method, two macromonomers and maleic anhydride polyethylene glycol are taken as raw materials to produce the polycarboxylic acid water reducer through multiple polymerization in the presence of acrylic acid, a chain transfer agent and a reducing agent. By use of influence of the structure and performance of the polycarboxylic acid water reducer by structure difference of polyether macromonomers and ester macromonomers, water reducing ratio and slump retention property of the polycarboxylic acid water reducer can be balanced, and air entraining ratio of the polycarboxylic acid water reducer can be effectively reducted by use of ester ether mixed structure. The method has the advantages of simple process, convenient control, easy industrialization, low cost, safety and environmental protection.

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.

The invention discloses a g system for coupling aircraft membrane nitrogen making oil tank inerting and cockpit environment control, and belongs to the technical field of aviation systems. The systemis formed by coupling an aircraft fuel tank hollow fiber membrane nitrogen production inerting system with a cockpit environment control system, that is exhaust gas with high oxygen concentration in the inerting system is injected by an injection pump and is mixed with low-temperature gas at an outlet of a turbine cooler in an environmental control system, then the obtained mixture is sent to thecockpit, the temperature, the pressure, the oxygen concentration and the air cleanliness in the cockpit are adjusted, and the health and physiological needs of drivers and passengers are guaranteed. The engine air entraining amount of the cockpit environmental control system is effectively reduced, and the fuel oil compensation loss is reduced; the oxygen concentration level of the cockpit is increased, the pressure height of the cockpit is increased, and the structural weight of the cockpit is reduced; and exhaust pressure of a membrane nitrogen making device is reduced, internal and externalpressure difference of a separation membrane is increased, and separation efficiency of a membrane device is improved.

The invention discloses a high performance polycarboxylic acid slump retaining agent and a preparation method thereof. The slump retaining agent comprises, by weight, 300 to 350 parts of macromonomers, 45 to 60 parts of an agent A, 4.0 to 4.5 parts of an agent B, 3.5 to 7.0 parts of an agent C and 500 to 550 parts of deionized water. The macromonomers comprise one or two of isopentenyl alcohol polyoxyethylene ethers. The agent A is a mixture of a small monomer and a sustained-release small monomer. The small monomer is acrylic acid and the sustained-release small monomer comprises one or both of hydroxyethyl acrylate and hydroxypropyl acrylate. A mass ratio of the small monomer to the sustained-release small monomer is 1 to 1.2 to 2.5. The agent B comprises, by weight, 1.2 to 1.8 parts of a reducing agent and 2.2 to 3.5 parts of a chain transfer agent. The agent C is an initiator. The high performance polycarboxylic acid slump retaining agent has a high water reducing capacity and good slump retaining ability, has the air entraining amount lower than that of the commercial product, prevents heating in the whole process, saves energy, is environmentally friendly and has no pollution.

The present invention relates to an engine gas inlet pipe anti-icing system and an aircraft engine. The engine gas inlet pipe anti-icing system comprises a gas introduction structure, a heat exchange structure and a gas discharge structure, wherein a plurality of diversion devices are arranged inside the heat exchange structure, hot gas introduced by the gas introduction structure enters the heat exchange structure, diversion is performed through the diversion devices inside the heat exchange structure so as to make the hot gas helically advance in the heat exchange structure, and after the heat exchange, the obtained gas is discharged through the gas discharge structure. According to the present invention, the diversion devices are arranged to perform diversion on the introduced hot gas to adjust the hot gas flowing direction, such that the hot gas helically advances in the heat exchange structure so as to accelerate the heat exchange between the hot gas and the anti-icing surface, improve the heat exchange efficiency inside the heat exchange structure, and reduce the anti-icing gas introduction amount.

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 provides slump-loss-resistant and mud-resistant polycarboxylic acid with high performance and a preparation method of the polycarboxylic acid. The polycarboxylic acid is prepared from components in parts by mass as follows: 300-350 parts of a macromonomer, 45-60 parts of an agent A, 4.0-4.5 parts of an agent B, 3.5-7.0 parts of an agent C and 500-550 parts of deionized water. The polycarboxylic acid has high water reducing rate and good slump loss resistance and is energy-saving, environmentally friendly, green and pollution-free.

The invention discloses an aircraft fuel tank inerting system which comprises a fuel tank, a liquid outlet of the fuel tank is connected with a second control valve through a pipeline, a downstream pipeline of the second control valve is sequentially connected with a fuel pump, a fifth temperature sensor, a third flow sensor and an electronic equipment cabin, and finally, the downstream pipeline of the second control valve is connected to a liquid inlet of the fuel tank through a pipeline. The fuel oil serves as a cold source, the temperature of the fuel oil rises while airborne equipment is cooled, and the vapor pressure of the fuel oil increases along with the rising of the temperature such that the vapor concentration of the fuel oil in the gas-phase space of the fuel tank is increased,and a non-combustible state is achieved. Meanwhile, fuel oil heating is combined with an aircraft-borne nitrogen-making inerting technology for preparing nitrogen-rich gas by using a hollow fiber membrane such that the inerting effect of the fuel tank is further ensured.

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 discloses an anti-icing structure suitable for an aero-engine flow rectifing supporting plate and a wing. The anti-icing structure comprises an anti-icing part, a partition plate is arranged in the anti-icing part and divides the inner space of the anti-icing part into an air inlet cavity and an impact cavity, a jet hole is formed in the partition plate, the air inlet cavity and the impact cavity communicates through the jet hole, and convection-impact heat exchange of heat flow between the air inlet cavity and the impact cavity is formed; a flow dividing plate is vertically arranged in the air inlet cavity, an air inlet is formed in the top of the air inlet cavity on the right side of the flow dividing plate, and gaps are reserved between the two ends of the flow dividing plate and the top face and the bottom face of the anti-icing part to form a heat flow forward conveying channel; and a plurality of layers of porous medium fillers are laid in the impact cavity in the unfolding direction, and air outlet slits are formed in the surface of the impact cavity. Heat flow distribution away from the far end and the near end of a heat source can be regulated and controlled, non-uniform protection of the far end and the near end of a traditional heat exchange structure is reduced, the heat exchange effect of hot air flow and the front edge of a part can be enhanced, and hot air condition requirements needed by a conventional hot air anti-icing method are reduced.

The invention discloses a double-wall turbine guide blade with small air entrainment amount, and belongs to the technical field of aero-engines. The guide blade comprises a blade front edge, a middle chord blade basin, a blade back middle chord and a blade tail edge, the blade front edge is subjected to double-layer partition plate impact and film cooling, the middle chord blade basin and the blade back middle chord are subjected to double-wall impact and film cooling, and the blade tail edge is cooled by a radial turbulent flow column. The technology can be applied to the design of a high-cycle-parameter small-cold-air-capacity gas turbine guider, and a cooling system has the advantages of being small in heat exchange area, high in cooling effect, very suitable for a high-cycle-parameter aero-engine and a gas turbine and beneficial to heat management and cooling design optimization of the turbine guider. Small air entrainment amount can be achieved, engine performance is improved, micro-channel flowing and impacting are adopted, a higher heat exchange coefficient of an inner cavity can be achieved, the positions and angles of partition plate holes are adjusted, the temperatures of different positions of the blade are adjusted, and the metal temperature gradient of the blade is reduced.

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 belongs to an oxygen and nitrogen production technology, and relates to the improvement of a molecular sieve oxygen production separation device and a hollow fiber membrane nitrogen production separation device. The oxygen and nitrogen separation device with a molecular sieve and a hollow fiber membrane is characterized by comprising a filter (1), a flow adjusting device (2), a molecular sieve oxygen production device (3), an injector (4) and a hollow fiber membrane nitrogen production device (5). The oxygen and nitrogen separation device with the molecular sieve and the hollow fiber membrane has the advantages that exhaust gas of the molecular sieve oxygen production separation device can be used as feed gas of the nitrogen production separation device, so that the nitrogen production efficiency is improved; meanwhile, the air-entrainment quantity is reduced, the system structure is simplified, and the size and the weight are reduced.

The invention discloses a manufacturing method of high-performance concrete, relates to concrete, and mainly solves the technical problem of poor mechanical properties in the existing manufacturing method. The method comprises the following steps: S1, carrying out screening treatment, shaping treatment and water washing treatment on coarse aggregate, medium aggregate and fine aggregate; S2, selecting a high-performance polycarboxylic acid additive; S3, respectively weighing the cement, the active admixture, the fine aggregate, the water, the high-performance polycarboxylic acid admixture, themedium aggregate and the coarse aggregate according to the formula ratio; S4, sequentially adding the coarse aggregate, the medium aggregate, the fine aggregate, the cement, the active admixture, thewater and the high-performance polycarboxylic acid admixture into a forced stirrer, and uniformly stirring the mixture to obtain a concrete mixture; S5, separating the concrete mixture into two layersand loading the concrete mixture into a standard test mold, tamping the mixture by a tamping rodin an inserted manner, and demolding the cement mixture after standing treatment for 24 hours, thus preparing a concrete standard test piece; S6, transferring the concrete standard test piece into a standard curing chamber to be cured to the standard age. The mechanical property of the concrete can beimproved.

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 an air circulation system with controllable ejection heat dissipation and belongs to the field of helicopter environment control systems. High-temperature high-pressure gas passing through an absolute pressure regulator (1) further stretches to a channel air outlet where a cooling radiator (2) is located through a first pipeline, an ejector (10) is arranged at the tail end of the first pipeline, and the direction of a nozzle of the ejector (10) is consistent with the air direction of the air outlet. Outboard ambient air is firstly ejected through the ejector to the cooling radiator, the air temperature of an inlet of a turbine cooler is reduced, it can be guaranteed that the system can stably work when a helicopter hovers or no ram air exists in ground work, and the service life of the turbine cooler can be prolonged. As a fan is started and sucks the outboard air to be cooling radiator, the ejector is stopped to reduce the air entraining amount of an engine, and the power consumption of the engine is reduced.

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.

The invention belongs to the technical field of building materials and relates to an enhanced admixture for a municipal refuse recycled concrete as well as a preparation method thereof and the application thereof. The enhanced admixture comprises the following functional components for water reduction, enhancement, impurity shielding and the like in percentage by weight: 0-50% of polycarboxylic acid water reducer, 0-50% of highly efficient naphthalene water reducer, 0-50% of melamine resin water reducer, 0-50% of highly efficient aliphatic water reducer, 10-50% of lignosulfonate, 0.1-5% of sodium gluconate, 0.1-5% of sodium dodecyl sulfate, 0.1-10% of sodium silicate, 0.1-10% of potassium methyl silicate, 0.1-10% of sodium thiocyanate, 0.1-10% of sodium metaphosphate and 10-65% of water. In addition, the invention further discloses the preparation method and the application of the enhanced admixture. The enhanced admixture for the municipal refuse recycled concrete, provided by the invention, has the advantages of wide raw material source, simple production method, high production efficiency and obvious use effect and is suitable for large-scale industrial production.