89 results about "Combustion chamber" patented technology

The invention relates to a counter-flow flame combustion chamber which has a monocyclic cavity structure. The counter-flow flame combustion chamber is designed by adopting a concept of staged combustion, and combustion gas is supplied from a pre-combustion stage and a main combustion stage, wherein the pre-combustion stage adopts a diffusion combustion structural mode with stable whirlblast, and the main combustion stage adopts a combustion structural mode of combining premixing and pre-evaporation with counter-flow flame. The counter-flow flame combustion chamber mainly comprises a shunt diffuser, an external combustion chamber case shell, an internal combustion chamber case shell, a fuel nozzle, a head pre-combustion stage, a flame tube external wall main combustion stage, a flame tube internal wall main combustion stage, a flame tube external wall and a flame tube internal wall, wherein the head pre-combustion stage utilizes stable flame in a low-speed backflow area, which is generated by whirlblast air entering the combustion chamber from a pre-combustion stage whirlblast assembly; the main combustion stage comprises the flame tube internal wall main combustion stage and the flame tube external wall main combustion stage, and uniform oil-gas mixture jetted from the main combustion stage counters in a flame tube to form a counter jet flow which forms counter-flow flame under the ignition of pre-combustion flame. The invention has simple structure, and can effectively reduce disposal of pollutants besides ensuring the normal work condition of an aeroengine.

A combustion chamber assembly for use in a combustion tool including a combustion chamber, at least one combustion chamber plate disposed in the chamber, the at least one combustion chamber plate and the chamber members being configured for relative reciprocal movement, the combustion chamber assembly having at least one latch member associated with control of movement of at least one plate within the combustion chamber to divide the chamber into multiple volumes. The combustion chamber assembly further has a release for the latch member for permitting relative movement of the at least one combustion chamber plate and the combustion chamber.

The present invention discloses a novel apparatus and way for controlling combustion dynamics in a premix combustion system. The apparatus comprises a hemispherical dome assembly with a plurality of dome dampers having a predetermined damper volume and air supply with the damper in fluid communication with the combustion chamber. The dome dampers are pressurized with a volume of air to dampen pressure waves received from the combustion chamber. One or more combustor frequencies can be targeted through use of the present invention.

The invention discloses a gas water heater provided with a cold water inlet pipe and a hot water outlet pipe. The gas water heater comprises a shell, a catalysis combustor, a preheating combustor anda heat exchanger. A combustion chamber is formed in the shell. The catalysis combustor is arranged in the combustion chamber. The preheating combustor is arranged in the combustion chamber and is adjacent to the catalysis combustor. When the preheating combustor conducts combustion, the preheating combustor acts on the catalysis combustor, and the catalysis combustor is heated. One end of the heatexchanger communicates with the cold water inlet pipe, and the other end of the heat exchanger communicates with the hot water outlet pipe. The heat exchanger is used for absorbing heat generated dueto combustion of the preheating combustor and combustion of the catalysis combustor and conducting heat exchange on the absorbed heat and water in the heat exchanger. The gas water heater is simple and compact in structure, the energy utilization rate can be sufficiently improved, and harmful substance emission is reduced.

A spark plug which includes an end at its combustion chamber end, and an end at its connecting end, as well as a housing and an insulator situated in the housing. The insulator has a longitudinal bore having a longitudinal axis, a center electrode situated in the longitudinal bore of the insulator, a first ground electrode which extends into the region of the longitudinal axis of the insulator, and a second ground electrode which is situated at a distance from the longitudinal axis of the insulator laterally next to the center electrode. The insulator has a front section, facing the first ground electrode, which has an end face. The insulator has an outside diameter d and an inside diameter c, d−c, that is, the difference between outside diameter d and inside diameter c, in the front section of the insulator being not greater than 1.9 mm.

A head part of an annular combustion chamber for a gas turbine, the head part comprising: an end wall with a passage opening for accommodating a burner, the end wall comprising a back side which faces towards the combustion chamber; a burner collar adapted to fit within the passage opening and receive the burner, the burner collar comprising a protruding portion radially protruding from an outer surface of the burner collar; and a ring member for receiving the protruding portion of the burner collar; wherein the head part of the annular combustion chamber is configured such that in an installed configuration a radially outer portion of the ring member engages with the end wall and a radially inner portion of the ring member receives the protruding portion of the burner collar.

The invention discloses a reverse flow combustor and a double-wall elbow structure thereof and relates to the field of aero-engines. The double-wall elbow structure comprises an inner elbow wall and an outer elbow wall; in the flowing direction of fuel gas, the inner elbow wall is divided into an upper inner elbow wall section and a lower inner elbow wall section, cooling structures of the two regions are different, the upper inner elbow wall section is provided with multiple rows of diverging holes, besides the fact that certain included angles are formed between the diverging holes and the wall of the upper inner elbow wall section, certain deflection included angles are formed between the diverging holes and the flowing direction of the fuel gas, and compound angles are formed; the lower inner elbow wall section is provided with a plurality of rows of diverging holes, certain included angles are formed between the diverging holes and the wall of the lower inner elbow wall section, and deflection included angles are not formed; and the inner elbow wall is sleeved with the outer elbow wall, a middle cavity is formed between the inner elbow wall and the outer elbow wall, and impactholes are formed in a shell of the outer elbow wall. By means of the elbow structure, the peak wall temperature at the start section of the inner elbow wall and the wall temperature gradient of an elbow can be effectively reduced, and therefore the strength of the elbow is improved, and the service life of the elbow is prolonged.

The invention discloses a straw carbonization furnace with high thermal conversion efficiency. The straw carbonization furnace comprises a furnace body, a large furnace door and a small furnace door, wherein the large furnace door and the small furnace door are arranged at one side of the furnace body; the large furnace door is connected with the furnace body through a large furnace door sealing compression bar and a large furnace door hinge; the small furnace door is connected with the large furnace door through a small furnace door sealing compression bar and a small furnace door hinge; the furnace body is internally provided with a combustion chamber; the furnace body surrounding the combustion chamber is provided with a water interlayer; the upper end of the water interlayer is provided with an exhaust port and a water inlet; the upper end of the combustion chamber is provided with a smoke outlet pipe; the lower end of the furnace body is provided with a hot water outlet pipe and a hot water pump which are connected with the water interlayer; the combustion chamber is internally provided with a temperature detecting probe; the furnace body is provided with a control device connected with the temperature detecting probe.

The invention relates to a central grading lean oil premixed low-pollution combustion chamber. A duty stage is located in the center and consists of a film-forming air atomizing nozzle and a two-stagecyclone, the two-stage cyclone forms a reasonable central backflow area at the downstream, in addition, an oil film improves the atomizing effect under the shearing action of the two-stage cyclone, the flame stability characteristic under a small working condition is effectively improved, and the working boundary of the duty stage is widened. A main combustion stage is composed of a plurality ofdirect injection nozzles with annular air and a main combustion stage cyclone, the annular air effectively controls jet flows to have a reasonable penetration depth within a full working condition range, swirling air and the multiple jet flows are premixed in a main combustion stage straight channel and a convergent channel in advance, the formed uniform combustible mixed gas is premixed and combusted in the combustion chamber, the pollution emission of the combustion chamber under a large working condition can be remarkably reduced, and the problem of spontaneous combustion can be effectivelyavoided. Therefore, the problems of flame stability under the small working condition and pollution emission under the large working condition can be effectively solved.

The invention relates to a fast virtual numerical value test method for the aerodynamic performance of a baffled combustor, and relates to the technical field of small turbine engine tests. Accordingto the method, the problem that an aerodynamic model of the combustor is needed in a virtual numerical value test is solved by building a fast, simple and applicable one-dimensional aerodynamic modelof the baffled combustor of a small turbine engine, then the fast virtual numerical value test method for the aerodynamic performance of the baffled combustor of the small turbine engine is formed, and the aim that tests for the aerodynamic performance of the combustor are quickly conducted on a computer platform to obtain the aerodynamic performance of the combustor is achieved. The method is high in computing speed, under the condition that the model is verified, real object tests of the baffled combustor can be partly replaced, the combustor testing cost is reduced, the development period is shortened, and the combustor development efficiency is improved.

An internal combustion engine has a plurality of cylinders having combustion chambers and each being associated with a spark plug designed for igniting a mixture of air and fuel in the combustion chamber, and at least two adjusting devices for adjusting the air supply to the combustion chambers of the different cylinders. To control the internal combustion engine, an individual ignition angle is detected for each group of cylinders to which the same air mass per working cycle is respectively supplied and during the respective working cycles of which the same loss torque is decisive. The decisive loss torque is the one associated with the cylinder that is in its intake cycle during the respective working cycle of the respective cylinder of the respective group. The individual ignition angle for each group is detected as a function of the decisive loss torque for the respective group.

A system for controlling a continuous variable valve lift actuator of a diesel engine and a method thereof stabilize exhaust gas and improve performance by variably controlling lift and timing of intake and exhaust valves based on combustion state and driving purpose. The method may include, recognizing a driving purpose and combustion state by detecting driving conditions, temperature of exhaust gas at predetermined locations on an exhaust pipe, and NOx concentration contained in the exhaust gas, determining target position and timing of intake and exhaust valves by applying the driving purpose and the combustion state to a predetermined map table, controlling position and timing of the intake and exhaust valves by actuating a CVVA, detecting combustion pressure in a combustion chamber, and modifying fuel injection amount according to the combustion pressure.

The invention aims to provide a multifunctional compound supercharging test system. The multifunctional compound supercharging test system comprises an air compressor, turbines, a combustion chamber, a motor and a dynamometer, wherein the air compressor comprises a first air compressor and a turbocharger air compressor; the turbines comprise a first turbine working together with the first air compressor and a turbocharger turbine working together with the turbocharger air compressor. Through reasonable valve control and testboard control, independent pneumatic performance test can be carried out on key components, a centrifugal compressor and the turbine, of a turbocharger, and matching test research can be conducted on a single-stage turbocharger and compound supercharging systems such as a two-stage turbo-charging system. The multifunctional compound supercharging test system can also achieve pneumatic characteristic tests of both a high-pressure supercharger centrifugal compressor and a high-pressure supercharger turbine for two-stage supercharging.

The invention discloses a dual-layer mechanical grate type garbage gasifying incinerator and a dual-boiler power generation system thereof. The dual-layer mechanical grate type garbage gasifying incinerator comprises a dual-layer garbage gasifying incinerator, a boiler system and a circulating air supply system, wherein the dual-layer garbage gasifying incinerator comprises a feeding hopper, a gasification furnace and a burnout furnace; the burnout furnace is positioned directly under the gasification furnace; the feeding direction of the burnout furnace is opposite to the feeding direction of the gasification furnace, and flue gas outlets are formed in the upper end of the gasification furnace and the upper end of the burnout furnace; the boiler system comprises a boiler body a, and a boiler body b, wherein the boiler body a is provided with a cyclone-combustion chamber, a furnace chamber a, and a furnace chamber b; a flue gas inlet of the cyclone-combustion chamber is connected with a flue gas outlet of the gasification furnace; the boiler body b is provided with evaporators b, superheaters b, and water-cooled walls b, which are arranged on a flue gas pipeline in a sleeving manner, wherein the superheaters are arranged in the furnace chamber a, the evaporators are arranged in the furnace chamber b, and the superheaters and the evaporators are arranged in a furnace chamber d; steam drums are arranged at the top ends of the two boiler bodies.

The invention discloses a system and a method for oxidizing and thermally propelling by an active metal wire. The system for oxidizing and thermally propelling by the active metal wire comprises an air cylinder, a piston, an arc generating device, a first active metal wire supplier, and a power supplier; the air cylinder is provided with a cylinder body, an air inlet valve and an air exhaust valve, wherein a combustor is defined by the cylinder body; the piston is arranged in the cylinder body; the arc generating device is provided with a first electrode and a second electrode penetrates through the cylinder body, wherein a small gap for generating an electric arc existes between the first electrode and the second electrode; the first active metal wire supplier supplies a first active metal wire and feeds the active metal wire in the combustor as the first electrode; the power supplier is electrically connected with the first electrode and the second electrode to generate the electric arc, so that the first active metal is vaporized.

The invention aims at providing a high-pressure metal powder supply system based on pressure difference control. The system is suitable for a metal engine and can be used for stably supplying metal powder to a combustion chamber of the metal engine. Air passes a porous board to evenly blow metal powder, meanwhile, the air pressure of a metal powder region and the air pressure of an upper air region are monitored, the air pressure of the upper air region is controlled through a regulating valve on an exhausting pipeline, the pressure different of the upper portion and the lower portion is equal to 0.2 of the atmospheric pressure, and at this moment, the metal powder at the lower portion is blown by air to become gas-solid two-phase flow and is in a stable and even state. The metal powder obtained at this moment is supplied to the combustion chamber so that stable combustion in the combustion chamber can be guaranteed. A pressure sensor is arranged in the combustion chamber to monitor the pressure intensity in the combustion chamber, and it is kept that the pressure intensity in the combustion chamber is smaller than that of the metal powder region all the time. By the adoption of the high-pressure metal powder supply system, the better combustion state can be achieved and the work efficiency of the engine is improved.

The invention provides an air cylinder cover of a miniature type engine precast with a cooling water jacket, which is provided with an air cylinder cover body, wherein a cooling water jacket is precast between two exhaust ducts of the air cylinder cover body and positioned at a position above a combustion chamber, and a water jacket hole which is communicated with a cooling water channel of a cylinder body is machined inside the cooling water jacket. The water jacket hole is arranged between two exhaust doors of each cylinder of an engine on the air cylinder cover body, is arranged at the upper right part of a combustion chamber and is close to the exhaust ducts, and an included angle C1 is formed between the axis of the hole center of the water jacket hole and the bottom plane of the air cylinder cover and the included angle is 30-50 degrees. By arranging the cooling water jacket between the two exhaust ducts of the air cylinder cover additionally, the invention can quickly take away superfluous heat transmitted by high-temperature waste gas and improve the power property, the durability and the combustion property of the engine. In order to prevent the local position from becoming the flowing dead area of cooling water, the cooling water between the cylinder body and the cylinder cover is also further communicated by machining holes to take away the heat, thus preventing the occurrence of a dead water area.

A combustion apparatus includes a combustion chamber, a pre-chamber and a first device for mixing a fuel with an oxidant, the first device being located upstream of the pre-chamber. The combustion chamber and the pre-chamber share a common first and second wall spaced to each other building a cavity. The first wall exhibits at least one first opening in the area of the combustion chamber for introducing a coolant into the cavity. Further, the combustion apparatus has a channel for feeding the oxidant to the first device, whereby the channel is formed by a housing element of the combustion apparatus and the common first wall of the combustion chamber and the pre-chamber. The at least one first opening is located in the area of the combustion chamber. The first wall exhibits at least one second opening, located in the area of the pre-chamber, for introducing the coolant into the cavity.

The invention discloses an integrated aerodynamic layout method for a hypersonic aircraft forebody, an air inlet duct and a supporting plate. A combined standard flow field combining an inner core flow field, an isentropic flow field and a truncation Busemann flow field is adopted, a streamline tracer technology is used, based on a free incoming flow capture size and a downstream combustion chamber inlet size given by the overall configuration of an aircraft, a forebody compression face, an air inlet duct compression face and a supporting plate lateral compression face are constructed with traced streamline clusters starting from an outlet of the downstream air inlet duct, and the forebody, the air inlet duct and the supporting plate are smoothly connected to achieve integrated aerodynamic layout configuration. The three-dimensional space structure of the aircraft forebody and the air inlet duct is improved, the disturbing influence of the supporting plate is eliminated in a side face compression mode, adverse factors are converted into favorable compensation, the forebody, the air inlet duct and the supporting plate are reasonably laid out from the space three-dimension perspective, and flowing is kept to be isentropic flowing to the maximum extent, which is beneficial for reducing flowing loss and improving overall performance of the aircraft.

The present invention discloses a smelting complete equipment for ferrotitanium line products and relates to the technology field of titanium ferroalloy for metallurgy. Said equipment comprises a feed position, a buttjunction position connected with the feed position, a rapid heating mechanism connected with the buttjunction position, a mixing mechanism and a smelting mechanism, wherein said rapid heating mechanism comprises a rotating furnace having one end connected to the buttjunction position, said rotary furnace is equipped with a driving mechanism for driving the rotary furnace rotating and a heating stove for heating the rotary furnace, a burning compartment is mounted at the other end of the rotary furnace and is equipped with a gas generator connected through gas barrel at its outer portion, a warm-blast apparatus is connected with the burning compartment through the gas barrel outer layer endless tube. Said rapid heating mechanism in the complete equipment exhibits short heat-up time to materials and high efficiency, and then greatly enhances accumulating efficiency of raw material, wherein the materials is heated homogeneously in the rotary furnace.

The invention discloses a jet engine, which comprises a shell with exhaust holes, a rotor which is arranged in the shell and can be rotated, and at least one jet device, wherein the rotor is fixedly arranged on an output shaft supported by a bearing; the jet device is arranged on the periphery of the rotor and generates propulsion by combusting fuel gas to cause the rotor to rotate; and the jet device comprises a combustion chamber with a jet exhaust, an ignition device, an oxygen therapy trachea and a hydrogen therapy trachea. Compared with the prior piston type engine, the jet engine has the characteristics of simple structure, small volume, light weight, few components, easy processing and manufacture, low fault rate, low manufacturing and using cost, fast starting, high rotating speed, high efficiency of heat engine, high power, stable running, small noise, no air pollution, small abrasion of accessories, long service life and so on, and is suitable for various vehicles or power generating machines.

Provided in the invention is a steady-state-temperature-field-included simulation test bench of an aero-engine combustor. The simulation test bench comprises a box body, a combustion chamber simulation device, a test device, an air supply system, a ventilation system, a cooling system and a control system. The ventilation system includes an air suction type exhaust hood installed inside the lowerbox body and a wall-mounted industrial ventilation fan installed at the top of the box body. The air supply system and the cooling system are installed inside the lower box body. The control system includes a controller installed inside the lower box body and a human-machine interaction device installed on the outer side of the box body; and the controller is connected with the wall-mounted industrial ventilation fan, the human-machine interaction device, the combustion chamber simulation device, the test device, the air supply system, and the cooling system respectively. The simulation test bench can be used for simulating the actual working condition of the aero-engine combustion chamber; and the enabling performance of the thermal barrier coating material is studied preliminarily beforerun trial examination of the ground track. The steady-state-temperature-field-included simulation test bench has advantages of low cost, short cycle and low risk and the like.

The combustor has a laser ignitor mounted to the casing, remotely from the liner of the combustion chamber. The laser ignitor has an igniter beam path for igniting the fuel and air mixture in the combustion chamber, the igniter beam path extending at least partially across the air plenum surrounding the liner and into the combustion chamber through a corresponding beam path aperture provided in the liner.

The inventive combustion method consists in: dividing a hearth into a fuel chamber and a combustion chamber; storing the main comburant in the fuel chamber and the secondary combustible material in the combustion chamber and forming annular intake passage in the air intake of the combustion chamber. One way of the blower through the top of the connected stove forms the annular intake passage, and the combustion chamber is formed among the top air intake disposed at the bottom of the top, a fire-separating plate on the fire-separating ring. The other way through the air-vent at the bottom of the connected stove realizes the secondary combustion, and meanwhile joins pushing, ash-removing and ventilating together.

The invention discloses an oxygen-deficiency pyrolyzing circular sludge incinerator. The sludge incinerator comprises a incinerator body (02), a hearth bottom (28), a condenser (19) and a fan (21), wherein an incinerator cover (01) is arranged at the top of the incinerator body, a ventilation and smoke discharging hole (06) is arranged on the incinerator body, a circular combustion chamber (05) is arranged at the periphery of the upper middle part of the incinerator body, an air supply tuyere (15) is arranged at the outer wall of the circular combustion chamber, and the fan is connected with the air supply tuyere (15) through an air supply pipe (16); the hearth bottom comprises a circular ventilation room (08) and a barrel-shaped ventilation chamber (11), an incinerator thermal insulating layer (04) is arranged at the upper part of the incinerator body and the peripheries of the circular combustion chamber, the circular ventilation chamber and the barrel-shaped ventilation chamber; the upper part of the condenser is communicated with the upper part of the incinerator body through pipelines, and the condenser is connected with the fan through an air return pipe (24); and a condenser water outlet (20) is arranged at the bottom of the condenser. The oxygen-deficiency pyrolyzing circular sludge incinerator has the advantages of waste minimization, pollution-free disposal, waste recycling and the like.