51results about How to "Reduce boost pressure" patented technology

The invention provides a multi-stage supercharging flexible air system with an electric supercharging function for an engine. The multistage supercharging flexible air system involves an electric supercharger, the engine, a turbocharger, an air storage tank and a controller, wherein an air inlet communicates with the air inlet end of a first air compressor of the electric supercharger through a pipeline, the air inlet communicates with the air inlet end of a second air compressor of the turbocharger through a pipeline, and a one-way valve is arranged on the pipeline; the air outlet end of thefirst air compressor communicates with the air inlet end of the second air compressor through a pipeline; the air outlet end of the second air compressor communicates with an air inlet pipe of the engine through a pipeline via an air inlet intercooler and an air inlet heater; an air outlet pipe of the engine communicates with a turbine air inlet end of the turbocharger; the output end of the controller is electrically connected with a motor of the electric supercharger; the motor is used for driving the first gas compressor to operate; and a turbine of the turbocharger drives the second air compressor to operate through exhaust energy of the air outlet pipe of the engine.

The invention discloses a spacecraft propellant in-orbit filling system and a spacecraft propellant in-orbit filling method. A technology of performing primary exhaust and then performing pressurized filling is adopted, a target conduit head and a filling conduit head do not need simultaneous connection of a gas path and a liquid path, and only a single liquid path is used for connection, so that a docking mechanism is simplified; a supplementary spacecraft is capable of performing pressurized filling without a mounting pump, not only can an attitude disturbing torque generated by rotation of a motor in the pump be avoided, but also the boost pressure during filling is reduced, and the task reliability is improved; before filling, a measure of performing pressure relief on the target spacecraft till reaching a pressure which is below a propellant saturated vapor pressure is adopted, thereby ensuring that the filling rate of the target spacecraft achieves a higher level; in addition, the system has a reusable characteristic; the supplementary spacecraft can be used for performing in-orbit supplement on multiple targets or one target for multiple times, so that a foundation for further implementing in-orbit filling service is laid.

The invention relates to a multiple-starting liquid oxygen kerosene engine of a gas driven preloading turbine. The multiple-starting liquid oxygen kerosene engine solves the problems that an oxygen-rich afterburning circulating liquid oxygen kerosene engine has no capacity of being started under low inlet pressure and can not being started for multiple times. The liquid oxygen kerosene engine comprises a gas system, a liquid oxygen system, a fuel supply system, an ignition agent supply system and a starting system. The ignition agent supply system comprises an ignition agent starting box, an ignition agent supply valve, a third one-way valve, a generator fuel valve and a fourth one-way valve. The generator fuel valve is a two-position three-way valve and comprises an inlet, an outlet A andan outlet B. The starting system comprises a high-pressure gas supply device, a high-pressure gas one-way valve, an oxygen preloading pump, an oxygen preloading turbine, a switching valve, a liquid oxygen one-way valve and a mixer. The ignition agent starting box of the liquid oxygen kerosene engine is relatively independent, an ignition agent is supplied to fuel gas generator and the thrust chamber for multiple times, and therefore the engine has the capacity of being started for multiple times.

A control device is applied to a hybrid vehicle on which an internal combustion engine equipped with a supercharger, and a motor generator that generates electric power while applying negative torque to the internal combustion engine, are installed. The control device drives a boost pressure varying mechanism so as to regulate a boost pressure developed by the supercharger, and drives a throttle valve of the engine so as to adjust its throttle opening. A controller of the control device drives the boost pressure varying mechanism to reduce the boost pressure of the supercharger, before driving the throttle valve to reduce the throttle opening, in order to reduce output torque of the engine, when the motor generator is in a. high-load condition while negative torque applied from the motor generator to the engine is adjusted so as to restrict the engine speed to a target value.

The invention discloses a double-channel air exhausting device of a double-flow channel turbocharger. The air exhausting device comprises a turbine volute, wherein two air inlet flow channels are formed in the turbine volute; the turbine volute is provided with an air exhausting channel which is communicated with the two air inlet flow channels respectively; and an air exhausting valve is arranged at the outlet of the air exhausting channel and is in transmission connection with an execution mechanism on the turbine volute. Mutual influence of exhaust pulses of the two air inlet flow channels of the double-flow channel turbine volute is restrained by a simple device and energy loss caused by the entrance of waste gas into the air exhausting channel when an engine runs at a low speed is reduced. The air exhausting device has a simple structure; an air exhausting port is molded in the casting process of the turbine volute; and compared with a double-air exhausting channel double-air exhausting valve device, the air exhausting device can effectively lower processing and assembly difficulty and cost and contributes to enhancing the sealing performance of the air exhausting valve and the reliability of a bypass air exhausting device of the turbocharger.

A method and a control device for raising and/or lowering an exhaust gas temperature of a combustion engine having an exhaust gas aftertreatment device arranged in an exhaust line sets the exhaust gas temperature for the exhaust gas aftertreatment using an electric-motor mode and/or a generator mode of an electrified exhaust turbocharger.

Methods and systems are provided for controlling boost pressure in a staged engine system comprising a turbocharger and an upstream electric supercharger. In one example, a method may include accelerating an electric supercharger to choke the flow of air to the engine in the event of turbocharger overboost.

A plastic material injection molding system includes a feeding nozzle, a forming mold having a cave therein, and a material-passing mold having a runner therein. The runner communicates both the feeding nozzle and the cave, and has two curved parts therein for slowing down the plastic material injected from the feeding nozzle in order.

The invention provides a multi-stage hybrid pressurizing system used for an engine and provided with an electric pressurizer arranged front. An air inlet communicates with the air input end of a firstair compressor of the electric pressurizer and the air input end of a second air compressor of a turbine pressurizer through a pipeline. The air output end of the first air compressor communicates with the air input end of the second air compressor through a pipeline. A one-way valve is arranged on the pipeline, communicating with the second air compressor, of the air inlet. The air output end ofan air storing tank communicates with the air input end of the first air compressor through a pipeline, and the pipeline is provided with a compressed air nozzle. The air output end of the second aircompressor communicates with an air input pipe of the engine. An air output pipe of the engine communicates with a turbine air input end of the turbine pressurizer. The air output end of the turbinepressurizer communicates with external air. A pressure sensor is arranged in the air input pipe of the engine.

The invention relates to a high-thrust liquid rocket engine and a low-power-consumption semi-self-starting method thereof, and aims to solve the problems that an existing liquid rocket engine starting mode is poor in starting quality, the required swirling power is large, and the repeated use of the engine cannot be achieved. The engine comprises a gas system, an oxidant supply system, a fuel supply system and a starting system, wherein the starting system comprises a first high-pressure gas driving pipeline and a second high-pressure gas driving pipeline, an inlet of the the first high-pressure gas driving pipeline is connected with a high-pressure air source, an outlet of the first high-pressure gas driving pipeline is connected with an inlet of a first main turbine, an inlet of the the second high-pressure gas driving pipeline is connected with the high-pressure air source, an outlet of the second high-pressure gas driving pipeline is connected with an inlet of a second main turbine, an outlet of an oxygen pump is connected with an inlet of an oxygen preloading turbine, an outlet of the oxygen preloading turbine is connected with an inlet of the oxygen pump, an outlet of a fuel pump or an outlet of a thrust chamber cooling pipeline is connected with an inlet of a fuel preloading turbine, and an outlet of the fuel preloading turbine is connected with an inlet of the fuel pump.

The invention relates to a method for the floatation-clarification of difficult water, in particular heavily polluted surface water, urban or industrial wastewater, rainwater or any type of water thatfloats with difficulty, particularly water which contains a high percentage of mineral matter or requires the injection of a flocculation aid and which originates from filters or membrane technologies such as ultrafiltration, said method comprising: a coagulation step (A1) in which a dose of coagulant (1) is injected into the water to be treated; a flocculation step (B) in which flocculant (2) isinjected (B1) into the water after the coagulation step, in order to agglomerate the suspended particles in the form of flocs; and subsequently a floatation step (C) in which the flocculated water ismixed with an emulsion of air micro-bubbles in a floatation apparatus. A second coagulant injection step (A2) is performed downstream of the flocculant injection (B1) and upstream of the floatation (C).

The invention provides an oil transportation heat management integrated system for controlling fuel oil temperature rise of a high-speed aircraft. The oil transportation heat management integrated system comprises a main oil tank, a built-in oil tank, an oil pump, a first oil pipe, a second oil pipe, a supporting frame and an air inlet pipe. Oil tank pressurized gas enters the main oil tank from the gas inlet pipe to provide pressure for fuel oil in the main oil tank, so that the fuel oil is conveyed to the built-in oil tank from the main oil tank through the first oil pipe, then is conveyed to the oil pump through the second oil pipe, and finally is supplied to an engine through the oil pump. According to the technical scheme, the built-in oil tank is arranged in the main oil tank, the temperature of fuel oil at the flight tail section of the long-endurance high-speed aircraft can be effectively reduced, and the effects of reducing the cavitation risk of a fuel oil pump, reducing thepressurization pressure of a fuel oil tank, reducing the design difficulty of oil passing equipment, increasing available fuel oil heat sinks of an engine and the like can be achieved. The method canbe applied to high-speed aircrafts such as high-speed aircrafts and aerospace aircrafts.

The invention provides an oil transportation heat management system design method for controlling the temperature rise of fuel oil of a high-speed aircraft, and the method comprises the steps: building a main oil tank heat transfer model without a built-in oil tank based on a main oil tank structure model; based on the fuel temperature rise curve of the main oil tank heat transfer model without the built-in oil tank, determining the fuel consumption at the fuel target temperature; determining the initial volume of the built-in oil tank based on the fuel consumption at the target fuel temperature; based on the main oil tank structure model and the initial volume of the built-in oil tank, establishing a main oil tank heat transfer model of the built-in oil tank; and determining the final volume of the built-in oil tank based on the highest temperature of the fuel oil temperature rise curve of the main oil tank heat transfer model with the built-in oil tank, the fuel oil target temperature and the initial volume of the built-in oil tank. The method can effectively reduce the temperature of the fuel at the flight tail section of the long-endurance high-speed aircraft, and can achieve the effects of reducing the cavitation risk of a fuel pump, reducing the pressurization pressure of a fuel tank, reducing the design difficulty of fuel passing equipment, increasing the available fuelheat sink of an engine and the like.

The invention discloses a diesel engine pressurized air bypass device comprising an air filter, a pressure reducing valve, a compressed air inlet pipe and a by-pass valve. The compressed air inlet pipe is connected to the air filter and the pressure reducing valve in sequence, and the upper end of the by-pass valve is connected to a scavenge box cover plate of a diesel engine. The by-pass valve comprises a by-pass valve body, a valve core, a spring and a valve rod, and the output end of the pressure reducing valve communicates with a lower end cover of the by-pass valve through a compressed air outlet pipe. The valve core is embedded in a longitudinal pipe of the by-pass valve body, and a central through hole of a horizontal pore plate is closed by the top end of the valve core. One end ofthe valve rod extends into the longitudinal pipe, and the other end of the valve rod is in threaded connection with the lower end cover, and extends out of the lower end cover; and the upper and lower ends of the spring are supported between the top of the longitudinal pipe and the inner side of the lower end cover separately. The diesel engine pressurized air bypass device has the advantages ofsimple structure, low manufacturing cost, less parts, firmness and durability, easy maintenance and low cost, and the boosting pressure of the diesel engine is reduced effectively so that the operating cost of the diesel engine is reduced; and the working efficiency is improved.

The invention belongs to the field of internal combustion engines, and relates to an adjustment method of worm gear pressurization of an internal combustion engine, in particular to an intake and exhaust end double-throttle-valve control method of an amount adjusting type supercharged engine and a realization mechanism of the intake and exhaust end double-throttle-valve control method of the amount adjusting type supercharged engine. The realization mechanism mainly comprises a gas compressor arranged in an intake system, wherein the gas compressor is connected with a gas inlet of the internal combustion engine, a gas outlet of the internal combustion engine is connected with an exhaust pipe, the exhaust pipe is connected with a worm gear supercharger in series, the worm gear supercharger drives the gas compressor, and the exhaust pipe of the internal combustion engine is provided with an exhaust pipe throttle valve; the exhaust pipe throttle valve and the worm gear supercharger are connected in parallel, and waste gas entering a worm gear front exhaust pipe can be discharged in a bypass mode; the exhaust pipe throttle valve is connected with and controlled by an ECU. The invention further provides a control and adjustment method, the gas loss of the internal combustion engine can be effectively reduced, and economy of fuel is improved.