61 results about "Fuel spray" patented technology

A gas turbine engine for an aircraft includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the chamber. The nozzles include a first and second subset. The combustor is operable so each of the first subset is supplied with fuel at a greater rate than each of the second subset. A ratio of nozzles in the first subset to nozzles in the second subset is 1:3 to 1:6. A thrust nvPM emissions index ratio is EImaxTO / FmaxTO / EIidle / Fidle. EIidle is system loss corrected nvPM emissions index in mg / kg of the engine operating at around 7% available thrust. EImaxTO is system loss corrected nvPM emissions index in mg / kg of the engine at around 100% available thrust. FmaxTO is thrust of the engine at around 100% available thrust. Fidle is thrust at around 7% available thrust. The thrust nvPM emissions index ratio is between 0.0009 and 0.02.

A gas turbine engine for an aircraft includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the chamber. The nozzles include a first and second subset. The combustor is operable so each of the first subset is supplied with fuel at a greater rate than each of the second subset. A ratio of nozzles in the first subset to the second subset is 1:3 to 1:6. A fuel-flow nvPM emissions index ratio isEIidle × Wf,idleEImaxTO × Wf,maxTO.EIidle is the system loss corrected nvPM emissions index in mg / kg of the engine at around 7% available thrust. EImaxTO is the index at around 100% available thrust. Wf,idle is the rate of fuel to the nozzles in kg / s at around 7% available thrust. Wf,maxTO is the rate of fuel to the nozzles in kg / s at around 100% available thrust. The index ratio is between 0.357 and 8.

A gas turbine engine has a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. A combustor is operable with the first subset of fuel spray nozzles supplied with fuel at a greater fuel flow rate than each the second subset of fuel spray nozzles. A a ratio of the first subset of fuel spray nozzles to the second subset of fuel spray nozzles is 1:2 to 1:5. A first idle-MTO nvPM emissions index ratio is:EIidleEImaxTOwhere: EIidle is the system loss corrected nvPM emissions index in mg / kg operating at around 7% available thrust; and EImaxTO is the system loss corrected nvPM emissions index in mg / kg operating at around 100% available thrust; and the first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 60. A sustainable aviation fuel (SAF) can be provided to the fuel spray nozzles.

The invention discloses a combustion chamber fuel injection and oil-gas mixing system suitable for a low-temperature environment, and belongs to the field of combustion chambers of gas turbines, the combustion chamber fuel injection and oil-gas mixing system comprises a flame tube, a centrifugal nozzle and a two-stage cyclone which are coaxially arranged, after fuel is atomized through the centrifugal nozzle and enters, the fuel is further atomized through rotational flow of an inner ring of the two-stage cyclone and enters the flame tube, and the fuel is injected into the combustion chamber through the centrifugal nozzle. External high-pressure air is swirled through the outer ring of the two-stage swirler to form swirling air, and internal fuel spray is crushed, atomized and mixed; a venturi tube is arranged at the end, close to the flame tube, of the inner ring of the two-stage cyclone, vortex generators are evenly arranged on the inner wall of the expansion section of the venturi tube in the circumferential direction, and oil mist with the small and even particle size is formed after the atomized mist is acted. Through multi-stage rotational flow, oil mist with fine and uniform granularity is formed, the atomization effect is optimized, and the fuel oil atomization quality and combustion stability in a low-temperature environment are improved.

A gas turbine engine has a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. A combustor is operable with the first subset of fuel spray nozzles supplied with fuel at a greater flow rate than each of the second subset of fuel spray nozzles. A ratio of the first subset of fuel spray nozzles to the second subset of fuel spray nozzles is 1:2 to 1:5. A first idle-MTO nvPM emissions index ratio is:EIidleEImax⁢TO,where: EIidle is the nvPM emissions index in mg / kg operating at around 7% available thrust; EImaxTO is the nvPM emissions index in mg / kg of the gas turbine engine operating at around 100% available thrust; and the first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 60. A sustainable aviation fuel (SAF) can be provided to the fuel spray nozzles.

The invention discloses a multifunctional catalyst for a diesel vehicle and a preparation method, and relates to the field of catalyst preparation, the multifunctional catalyst for the diesel vehicle comprises a precious metal coating and an SCR coating which are arranged in a layered mode, and the SCR coating is located above the precious metal coating; the SCR coating is of a sectional structure and comprises an SCR coating front section and an SCR coating rear section. The problems that an existing catalyst is low in NOx efficiency during cold start, coating regeneration after HC / SO2 poisoning cannot be achieved at the same time, low N2O selectivity cannot be ensured, and unreacted NH3 cannot be treated at the same time are solved, by means of the layered and sectional type coating structure design, diesel oil or other hydrocarbon fuel sprayed backwards by a system can be rapidly oxidized through the bottom layer precious metal coating, reaction heat is generated, and the catalyst can be recycled. The temperature of the whole catalyst is increased, adsorbed HC and sulfide are oxidized and removed, and the SCR activity is recovered. And unreacted NH3 can be treated, so that the arrangement space of a post-treatment catalyst is saved. The upper-layer sectional type coating structure not only can efficiently convert NOx at a low temperature, but also can keep relatively low N2O selectivity.

A gas turbine engine for an aircraft is disclosed. The gas turbine engine comprises: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:3 to 1:6. A MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles. Also disclosed are methods of operating the gas turbine engine.

A piston and injector system designed to minimize thermal loading on the cylinder head of an internal combustion engine. The piston features a profiled upper surface that defines an annular piston bowl with a primary bowl configuration and an asymmetric bowl sector. The asymmetric bowl sector is configured to receive the fuel spray from the injector, directing combustion to reduce heat concentration on certain areas of the cylinder head. This design helps prevent overheating, thereby enhancing engine durability and performance.

This invention provides a test method for determining injection fusion in multiple injections of a high-pressure common rail system, comprising the following steps: S1. Constructing a high-pressure common rail system injection pattern test system to test the injection pattern of two injections: pre-injection + main injection; S2. Constructing a high-speed photography direct-view test system for the injection process of the high-pressure common rail system to test the spray development characteristics under injection intervals; S3. Processing the images of the spray development process of multiple injections of the high-pressure common rail system, and repeating the spray development characteristic test until the fuel sprays of the two injections merge. The test method for determining injection fusion in multiple injections of a high-pressure common rail system described in this invention employs a spray visualization test method, obtaining the actual development process of real fuel spray in the cylinder, which can accurately determine whether actual fuel spray fusion has occurred in the cylinder, solving the problem of misjudgment of injection fusion based on control signals and injection pattern curves.

The device is arranged in the combustion chamber, a flame tube is arranged in the combustion chamber, and the device comprises a high-pressure fuel spray pipe and a concentric-square-shaped evaporation pipe; the high-pressure fuel spray pipe penetrates through the side wall of the combustion chamber and is connected with a high-voltage power supply to serve as an anode; the concentric-square-shaped evaporation pipe penetrates through the side wall of the flame tube to serve as a cathode; an anode oil spraying opening of the high-pressure fuel oil spraying pipe and a cathode expanding type fuel oil opening of the concentric-square-shaped evaporation pipe are coaxially arranged, and the end of the anode oil spraying opening extends into the cathode expanding type fuel oil opening. Through high-voltage arc discharge, fuel oil is physically promoted to be split into tiny liquid drops, and macromolecular fuel oil is partially split into micromolecular fuel with higher chemical activity, so that the chemical reaction rate is greatly increased, and rapid and sufficient combustion of the fuel oil is realized.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the fuel spray nozzles. Also disclosed is a method of operating a gas turbine engine.

The low-speed combustion-supporting device is installed between an outlet of a fuel oil injection pump and an oil injection nozzle and comprises a high-pressure storage tank, a three-way connector and a high-pressure one-way valve, and the high-pressure one-way valve comprises a piston seat, a piston, a spring and a spring force regulator; when the spring is compressed, the piston is separated from the piston seat, and the high-pressure one-way valve is opened; when the spring is not compressed, the piston is matched with the piston seat, and the high-pressure one-way valve is closed; the inner diameter of the piston seat is equal to or larger than that of the fuel injection pump piston. When the diesel engine runs at an idle speed, the closed high-pressure one-way valve introduces fuel oil flowing out of the injection pump into the high-pressure oil storage tank for temporary storage, and when slow-flow fuel enters the high-pressure oil storage tank, air in the high-pressure oil storage tank is converted into compressed air. When the pressure exceeds the preset spring force, the high-pressure one-way valve is opened, and the fuel stored in the high-pressure oil storage tank and the entering slow-flow fuel flow out of the nozzle at higher speed and higher pressure. The fuel oil spraying quality of the diesel engine in idle speed operation can be improved, the structure is simple, and the cost is low.

The utility model relates to the technical field of lime shaft kilns, in particular to a double-hearth kiln fuel spray gun which comprises a gas pipeline, a pulverized coal pipeline, an inlet sleeve and an outlet sleeve. The coal gas pipeline and the pulverized coal pipeline are both in an L shape, the inlet end of the coal gas pipeline is fixed to the outer wall of the inlet sleeve and communicated with an inner cavity of the inlet sleeve, the inlet sleeve is arranged on the horizontal portion of the pulverized coal pipeline in a sleeved mode, and the two ends of the inlet sleeve are connected with the outer wall of the pulverized coal pipeline in a sealed mode. A coal gas inlet pipe is arranged on the inlet sleeve; the outlet end of the gas pipeline is fixed on the outer wall of the outlet sleeve and communicated with the outlet sleeve, the lower portion of the pulverized coal pipeline is arranged in the outlet sleeve in a penetrating mode in the axial direction of the outlet sleeve, and the top end of the outlet sleeve is connected with the outer wall of the pulverized coal pipeline in a sealed mode. The utility model provides the double-hearth kiln fuel spray gun which not only realizes the diversification of fuel, but also does not limit the use of single fuel.

The application discloses a kind of based on full light scattering fuel spray aerosol measurement method, device and system, belong to internal combustion engine laser detection field, the measurement method includes: control light source generates preset light beam and is irradiated the distribution area where oil fog aerosol particle is located, the light path area that the preset light beam passes through the distribution area is evenly divided into multiple lattices;Utilize multiple distribution in the measurement region outside photoelectric sensor receives scattering light intensity;The scattering light intensity is brought into the preset equation that characterizes the relationship between scattering characteristic and aerosol particle distribution and is solved, obtains the distribution parameter of oil fog aerosol particle in each lattice.The application can extract the distribution parameter of oil fog aerosol particle from the scattering characteristic of accurately captured oil fog aerosol, realizes the real-time monitoring of concentration and particle size distribution;The method has the advantages of strong real-time, wide measurement range and high accuracy.

A piston (38) for an engine is disclosed. The engine (20) comprises a cylinder head (22) with a cylinder (28) that defines a combustion chamber (30) and carries a fuel injection device (32) configured to deliver a fuel spray jet (34, 36) into the combustion chamber (30). The piston (38) is configured to move back and forth within the cylinder (28) and compress a mixture of air and fuel within the combustion chamber (30). Furthermore, the piston (38) comprises the following: a piston head (40) with a profiled upper surface (42) extending radially around a center line (44) and defining an annular piston bowl (46), wherein the annular piston bowl (46) has a primary bowl (48) with a first bowl configuration (50) and an asymmetric bowl sector (52) with a second bowl configuration (54) that differs from the first bowl configuration (50),wherein the primary bowl (48) extends around the centerline (44) near a circumference of the piston head (40) to each side of the asymmetric bowl sector (52), wherein the primary bowl (48) is defined by a pivot of a radial line extending from the centerline (44) of the piston head (40) through a first angle (58) and the asymmetric bowl sector (52) is defined by a pivot of the radial line extending from the centerline (44) of the piston head (40) through a second angle (60) that is smaller than the first angle (58), wherein the second angle (60) is dimensioned such that the fuel spray jet (34, 36) from the fuel injection device (32) is received within the asymmetric bowl sector (52) and not the primary bowl (48).

The rotary detonation combustion device comprises a combustion chamber outer ring, a combustion chamber head, a combustion chamber center body, a high-temperature-resistant sealing ring, a circular seam width adjusting shaft sleeve, an axial positioning ring and a fixed cylinder barrel. Wherein the combustion chamber center body comprises a combustion chamber center body front section, a combustion chamber center body rear section, a fuel cavity and a fuel spray hole; and the circular seam width adjusting shaft sleeve comprises a shaft sleeve main body, a shaft sleeve axial positioning boss and a shaft sleeve external telescopic arm. When the device works, the cylinder barrel drives the shaft sleeve to be externally connected with the telescopic arm to enable the circular seam width adjusting shaft sleeve to move in the axial direction, the width of an air injection circular seam jointly formed by the shaft sleeve body tail end molded surface and the front end of the combustion chamber center body rear section is adjusted to the optimal value, the detonation wave propagation stability can be enhanced, and active regulation and control over the working mode of the combustion chamber are achieved; and the stable working range of the rotary detonation combustion chamber is widened. The method can be used in the fields of detonation propulsion and the like.

The application discloses a variable cross-section small furnace and a glass melting furnace, and relates to the technical field of float glass melting furnaces. The small furnace comprises a supporting refractory brick, side walls, a small furnace arch and a bottom plate assembly; the two side walls are respectively stacked on the two sides of the supporting refractory brick; the two ends of the small furnace arch are respectively connected with the two side walls; the bottom plate assembly is arranged on the supporting refractory brick and surrounded by the side walls and the small furnace arch to form a gas passage; and at least one end of the bottom plate assembly is movable in the direction close to the small furnace arch to change the cross-sectional area of the gas passage. The application improves the structure of the small furnace of the glass melting furnace, changes the downward inclination angle of the bottom of the small furnace by adjusting the position of the bottom plate of the small furnace, changes the contact position of the combustion-supporting air and the fuel sprayed by the small furnace, thereby realizing the control of the flame length; and the cross-sectional area of the gas passage of the small furnace is changed, the different requirements of different fuel amounts of the lower spray gun of the small furnace on the combustion-supporting air amount are matched, the combustion sufficiency is effectively improved, and the fuel waste is reduced.

An engine system includes an engine housing including a plurality of intake valve openings, an intake port extending to the plurality of intake valve openings and an injector bore extending to the intake port. The engine system also includes a fuel system having a port fuel injector, and a fuel distributor having a baffle wall. The baffle wall extends into the intake port and extends at least partially around a fuel spray axis, forming a fuel channel and having at least one of a circumferentially varied porosity or an axially varied cross sectional area. The baffle wall shields fuel spray of an injected fuel such as methanol to limit a bias in distribution of fuel among the plurality of intake valve openings.

The invention relates to the technical field of engine combustion chambers, and discloses a combustion chamber hydrogen supply device and a hydrogen combustion chamber with the same. The combustion chamber hydrogen supply device comprises an inner cylinder and an outer cylinder which are sleeved inside and outside, a fuel channel is formed between the inner cylinder and the outer cylinder, the fuel channel comprises a rotational flow gas distribution section, a circulation cavity is communicated with a gas inlet pipeline, and the outlet end of the gas inlet pipeline is tangent to the circulation cavity; the axial injection section is arranged on the downstream of the rotational flow gas distribution section, an axial flow cavity is formed in the axial injection section, a pressure dividing plate is arranged between the axial flow cavity and the circular flow cavity, and a plurality of flow guide holes are formed in the pressure dividing plate; a plurality of fuel spray holes are formed in the inner cylinder in the circumferential direction. Through the combined action of a serial flow channel combining rotational flow gas distribution, flow guide of the pressure dividing plate and the axial cavity, hydrogen obtains good circumferential and radial distribution uniformity before being sprayed into the combustion chamber. And a uniform fuel concentration field can be formed in the combustion chamber, so that high-temperature hot spots generated due to over-thick local fuel are relieved.

The invention relates to a concentric loose coupling partition combustion chamber and a combustion organization method thereof. The concentric loose coupling partition combustion chamber comprises a diffuser, a combustion shell, a combustion assembly and a flame tube. The combustion assembly comprises an auxiliary mold nozzle, a main mold nozzle, an auxiliary mold swirler and a main mold swirler. An annular non-rotation air channel is defined between the inner wall of the main mold swirler and the outer wall of the main mold nozzle. A preset included angle is formed between the direction of main mold fuel sprayed by the main mold nozzle and the central axis of the combustion shell, the non-rotation air channel can form an annular air barrier, and under the medium and low working conditions, the air barrier can prevent the main mold fuel from entering a main mold combustion area so that the main mold fuel can enter an auxiliary mold combustion area, and under the high working condition, the main mold fuel can be prevented from entering an auxiliary mold combustion area. The primary mold fuel can pass through the air barrier and into the primary mold combustion zone. Therefore, partitioned combustion under different working conditions can be realized, the reliability of ignition and the stability of combustion under medium and low working conditions are ensured, the combustion efficiency under high working conditions is improved, and the condition of smoking is avoided.

The invention relates to the technical field of combustion ignition devices of gas turbine engines using liquid fuel, in particular to a multi-fuel torch igniter with regenerative cooling. The igniter is characterized by comprising an igniter shell, a semiconductor ignition electric nozzle, an oxygen connecting nozzle, a fuel connecting nozzle and a pressure connecting nozzle are arranged on the igniter shell, an igniter combustion chamber is arranged in the igniter shell, and a fuel spraying hole and a liquid collecting cavity are formed in the igniter shell corresponding to the igniter combustion chamber. A regeneration cooling channel is arranged in the wall of the igniter shell; according to the torch igniter, the igniter shell with the regenerative cooling structure is adopted, the fuel temperature is increased while the fuel is used for cooling the igniter shell, oil-gas mixed combustion in the torch igniter is facilitated, and the torch igniter can be repeatedly used for a long time. And the ignition performance of the combustion chamber of the gas turbine engine is improved, so that the gas turbine engine is quickly and reliably ignited and started, and the ignition boundary of the engine is improved.

The application discloses a zirconium-based amorphous alloy-titanium alloy composite coating and a preparation method thereof, and belongs to the technical field of preparation of wear-resistant and corrosion-resistant materials.The preparation method comprises the following steps: (1) pretreating a substrate; (2) performing layer-by-layer cladding on the substrate by adopting a laser cladding process to form a gradient-coupled titanium alloy layer; and (3) layer-by-layer spraying a zirconium-based amorphous alloy coating on the surface of the titanium alloy layer by adopting a high-velocity oxygen fuel spraying technology.The load material coating with the gradient structure of the crystal and the amorphous crystal is prepared by adopting the preparation method, so that the titanium alloy layer and the zirconium-based amorphous alloy layer have high interface bonding strength, and the composite coating with more comprehensive performance and excellent performance is obtained.

A gas turbine engine 10 for an aircraft comprising a rich burn quick quench, lean burn (RQL) combustor 16 having a number of spray nozzles 403, 404, in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range of 2-6, with the engine configured to provide fuel comprising sustainable aviation fuel to the spray nozzles. The engine operation is characterised by specific non-volatile particulate emission ratio beign related to the bypass ratio. The fuel spray nozzles may comprise one or more duplex nozzles and one more single flow nozzles and preferably the combustor comprises 10-14 duplex fuel spray nozzles and 4-8 signle flow fuel spray nozzles. The duplex fuel spray nozzles are arranged in groups about the circumference of the combustor and optionally wherein the groups duplex fuel spray nozzles comprise at least two groups arraned dimametrically opposite each other. A corresponding method is also claimed. Fig 6

The invention provides a rotary detonation combustion chamber injection device with an air mixing circular seam. The rotary detonation combustion chamber injection device comprises an oxidizing agent circular seam, a fuel injection hole and the air mixing circular seam. The application object of the device is a rotary detonation combustion chamber, and the device is arranged at one end of an annular flow channel of the rotary detonation combustion chamber. In a working state, the air mixing circular seam starts supplying while the oxidizing agent circular seam and the fuel spraying hole supply normally. When rotating detonation waves propagate in the combustion chamber, the detonation waves are locally decoupled in the radial direction of the combustion chamber due to the fact that no fuel exists in the downstream position of the air mixing circular seam, and the pressure and the temperature are both reduced; the air and detonation wave combustion products are mixed at the head of the combustion chamber, and the temperature of the products is further reduced. Under the condition that the supply conditions of an oxidizing agent, fuel and mixed air are fixed, the rotating detonation wave propagation process and the air mixing process reach dynamic balance, the pressure and temperature of combustion products near an outer ring and an inner ring of a combustion chamber are reduced, and the uniformity of fuel gas parameters at an outlet of the combustion chamber is improved.

A gas turbine engine for an aircraft includes a rich burn, quick quench, lean burn combustor having 14-22 fuel spray nozzles or 2-6 fuel spray nozzles per unit engine core size. A thrust nvPM emissions index ratio isEImaxTO / FmaxTOEIidle / Fi⁢d⁢l⁢e.EIidle is the nvPM emissions index in mg / kg of the gas turbine engine operating at around 7% available thrust for given operating conditions. EImaxTO is the nvPM emissions index in mg / kg of the gas turbine engine operating at around 100% available thrust for the given operating conditions. FmaxTO is the thrust of the gas turbine engine at around 100% available thrust in kN. Fidle is the thrust of the gas turbine engine at around 7% available thrust in kN. The thrust nvPM emissions index ratio is greater than 0.09. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel to the fuel spray nozzles.

The invention relates to a method for preparing a thermal barrier coating interface three-dimensional texture with the assistance of a mask plate, and the method comprises the following steps: depositing a texture layer on the surface of a bonding layer by adopting a metal mask plate auxiliary spraying technology: placing a metal mask plate, and then carrying out plasma spraying or high velocity oxy-fuel spraying on the surface of the bonding layer to obtain the thermal barrier coating interface three-dimensional texture with the assistance of the metal mask plate; and a texture layer is prepared on the surface of the bonding layer through spraying, and after the metal mask plate is removed, the three-dimensional texture of the needed structure is obtained. Compared with the prior art, in the spraying process of the bonding layer, a layer of metal mask plate is added on the surface of the bonding layer, rapid and simple three-dimensional texture construction is achieved in a continuous spraying mode, and therefore the stability of the coating is improved, and the service life of the coating is prolonged.

The utility model discloses a direct injection type blowout ignition device, which relates to the technical field of oil and gas exploitation equipment and comprises a main fuel spray pipe, an electronic ignition component, a fuel supply cabinet and a control cabinet, a horizontal fuel pump and an oil tank are arranged in the fuel supply cabinet, and the main fuel spray pipe is connected with the horizontal fuel pump through an oil pipe. The electronic ignition assembly is connected with the control cabinet through an ignition wire, the control cabinet is in control connection with the horizontal fuel pump, the horizontal fuel pump is an oil pump with the working pressure being the output pressure not smaller than 1 MPa, a nozzle is installed at the other end of the main fuel spray pipe, and the hole diameter of the nozzle is 1.2-4.0 mm. According to the ignition device, an air compressor is not adopted for fuel atomization any more, and the ignition efficiency is improved. Pipelines and cables involved in the ignition device are reduced, and the ignition device is more convenient to disassemble, assemble and carry.

The utility model discloses an oil spraying bottle, which relates to the technical field of oil bottles and comprises a bottle body, the outer surface of the bottle body is in threaded connection with a lower cover, the outer surface of the lower cover is fixedly connected with a rotating handle, a clamping block and a clamping groove, an upper cover is arranged above the lower cover, the outer surface of the upper cover is fixedly connected with a connecting block and two fixing blocks, and the clamping block is matched with the connecting block. A rotating rod rotationally connected with the clamping groove is fixedly connected between the two fixing blocks, and an oil pouring and discharging assembly and an oil spraying assembly which are used for edible oil to flow out are arranged outside the bottle body. The oil bottle has the functions of pouring out oil and spraying oil at the same time, the oil bottle cap is arranged in a split mode, when the handle of the oil bottle is difficult to screw due to oil viscosity after the oil bottle is used for a long time, the oil bottle cap can be turned and separated, and therefore a user can conveniently add edible oil and overhaul the internal structure of the oil bottle cap, and the oil bottle cap is convenient to use. Therefore, the user experience is improved, and the cooking efficiency of the user is ensured.

The utility model discloses a fuel nozzle with an adjustable diffusion range, which comprises a shell, a swirler and a nozzle are arranged at the outlet end of the shell, a rotating shaft is coaxially arranged in the shell corresponding to the swirler, the rotating shaft divides the interior of the shell into a first cavity and a second cavity, an adjusting disc is arranged at one end of the rotating shaft close to the swirler, and the adjusting disc is connected with the nozzle. A plurality of through-flow holes are distributed in the adjusting disc along circumferential paths with different diameters, swirling flow channels with different swirling flow diameters are arranged on the swirler corresponding to the through-flow holes in the different circumferential paths, and the outlet ends of the swirling flow channels are arranged corresponding to the nozzles; oil inlets are formed in the inlet ends of the first cavity and the second cavity, and the outlet ends of the first cavity and the second cavity are connected with the inlet end of the adjusting disc; the fuel oil supply quantity and the diffusion range of fuel oil sprayed into the combustion chamber can be adjusted according to the fuel oil supply quantity requirements of the aero-engine in different working states, the appropriate fuel oil supply quantity of the aero-engine is further guaranteed, and it can also be guaranteed that the fuel oil has the good combustion efficiency.

The invention relates to an engine cold start improving device for fuel heating. The engine cold start improving device comprises an oil tank, a fuel nozzle and a fuel heater connected with a thermocouple. A high-pressure fuel inlet pipe and a high-pressure fuel return pipe are arranged on the oil tank, and a fuel pump is arranged on the high-pressure fuel inlet pipe; the high-pressure fuel inlet pipe and the high-pressure fuel return pipe are connected through two fuel common-rail pipes, and a plurality of fuel nozzles are arranged on the fuel common-rail pipes; the fuel heater is arranged at the end, close to the high-pressure fuel inlet pipe, of the fuel common rail pipe. A pressure release valve is arranged between the fuel common rail pipe and the high-pressure fuel oil return pipe; the pressure release valve and the fuel heater are controlled by a controller; the invention further discloses a control method using the device. The temperature of methanol injected into the gas inlet channel and in the cylinder is increased through the fuel heater, so that the quality of gaseous methanol in the cylinder is improved; oil inlets of the fuel common-rail pipes are formed in the positions, close to each other, of the two common-rail pipes, and pressure relief valves are arranged at the far ends, so that the temperatures of fuel sprayed out of the fuel nozzles on the two sides are consistent.