61123 results about "Nozzle" patented technology

A nozzle for a laser processing system is provided. A primary passage extends between the proximal end and the distal end of the nozzle body along a central longitudinal axis. At least one auxiliary passage is located within the body of the nozzle adjacent to the primary passage while substantially fluidly isolated from the primary passage. At least one conduit is located proximate the distal end of the body and in fluid communication with the at least one auxiliary passage. The at least one auxiliary passage is configured to flow a secondary fluid through the body of the nozzle in a first direction to impinge on a surface of the at least one conduit that is proximate the primary passage. The at least one conduit is configured to redirect the secondary fluid toward an exterior surface of the body in a second direction.

The invention discloses a rotational flow micro-mixing nozzle with built-in plasma combustion supporting and a micro-mixing combustor. The rotational flow micro-mixing nozzle comprises a tangential rotational flow part, a fuel pipe and a mixing pipe which are coaxially arranged, and plasma combustion supporting exciters arranged on the fuel pipe and the mixing pipe. The plasma combustion-supporting exciter is integrated in the nozzle, the structural design of the micro-mixing combustor can be simplified, and the size and complexity of the micro-mixing combustor are reduced; the plasma combustion-supporting exciter is installed at the top of the mixed gas channel of the rotational flow micro-mixing nozzle, stable adjustment of the combustion process under the variable working conditions can be achieved by controlling opening and closing and the discharge intensity of the plasma combustion-supporting exciter when the load changes, and meanwhile the response speed under the different working conditions is increased; air or an oxidizing agent can be fully mixed with fuel at a specific rotational flow degree through rotational flow air flow generated by the tangential rotational flow component, the combustion range can be widened, and the stable combustion effect under the extreme working condition is enhanced.

A bubble producing device including a shaft with two ends, wherein a housing is connected to the first end and bubble producing solution reservoir is connectable to the second end. The housing contains control circuitry to wirelessly activate the device and at least one bubble engine containing a motor, a pump and an air producing device. An air duct is connected to the air producing device on one end and connected on the other end to a nozzle containing a wiper. A channel with a tubular structure is submerged within the solution reservoir and connected on another end to the nozzle. A converter is secured within the channel and the diameter of the channel between the first end of the channel and the converter is larger than the diameter of the channel between the converter and the second end of the channel.

To perform efficient surface treatment on a surface to be treated which is positioned on a lower surface side of a structure.SOLUTION: A surface treatment system jets jetted material to a surface to be treated which is set on a lower surface of a structure. The system includes: a surface treatment device which has a nozzle head provided with a jetting nozzle which is inserted in a base end opening part and jets the jetted material, and having a tip end opening part arranged opposite to the surface to be treated; and a nozzle head support device for supporting the nozzle head. The nozzle head support device includes: a pillar arranged in a periphery of the surface to be treated; an arm mechanism which has an arm main body of which a base end is connected to the pillar and rotates around the pillar, and includes a rotation shaft parallel to the pillar and arranged on a joint of a link; and a nozzle head mounting member which is connected to a tip end of the arm mechanism and on which the nozzle head is mounted.SELECTED DRAWING: Figure 1

The invention relates to the technical field of valve body machining, and discloses valve body pipe orifice and flange welding equipment which comprises a bottom plate and supporting legs, a rotating mechanism is arranged above the bottom plate and comprises a first mounting plate, a double-end motor, a first rotating rod, a second mounting plate and a first gear, and the inner wall of the first mounting plate is connected with the outer wall of the double-end motor; the output end of the double-end motor is connected with one end of a first rotating rod. A valve body can be rapidly and conveniently clamped and fixed through the rotating mechanism, the valve body rotates, a flange can be rapidly and conveniently clamped and fixed through the clamping mechanism, the flange can synchronously rotate along with rotation of the valve body, and the problem that the valve body and the flange can only be relatively moved and aligned only through an adjusting assembly, and the machining efficiency is high is solved. The problem that the position of a welding gun needs to be continuously adjusted for welding due to the fact that the valve body and the flange cannot be rotated in the welding process is solved, and the working efficiency of welding equipment is improved.

A method of operating a gas turbine engine having a combustor having a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The fuel spray nozzles have a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. 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 1:2 to 1:5. The method includes providing a fuel to the plurality of fuel spray nozzles having a calorific value of at least 43.5 MJ / kg. A gas turbine engine can be for an aircraft.

The invention is suitable for the technical field of performance detection, and provides a method for detecting the ablation resistance of a burning-resistant nozzle and an arc contact, and the method comprises the steps: collecting a temperature field matrix, an arc image sequence, an electrical parameter time sequence and a surface displacement curve of an ablation region, and generating a multi-modal data set; based on the data set, extracting spatial features of the ablation core region through a cavity convolution layer and a channel attention mechanism; inputting a preset bidirectional LSTM network, fusing thermal stress data of the COMSOL simulation model to drive gating weight update, and extracting time sequence evolution characteristics; generating a space-time fusion feature vector containing the temperature field gradient, the arc form change rate and the surface roughness evolution feature; inputting the space-time fusion feature vector, the thermal stress distribution data and the material phase change threshold parameter into a constructed ablation prediction model for training; the ablation prediction model after training is completed is optimized; and a performance prediction result is generated in real time by using the optimized ablation prediction model, so that the detection accuracy is effectively improved.

A fuel cavity, an air cavity and a combustion cavity are sequentially and coaxially arranged at intervals in a sealed mode from bottom to top, a plurality of nozzle assemblies are fixedly arranged in the air cavity, and the nozzle assemblies are symmetrically arranged relative to the center of the air cavity to form an annular multi-layer array structure; the nozzle assembly comprises an air flow guide component, a tangential rotational flow component, a fuel pipe and a mixing pipe which are coaxially arranged. Through a combined adjusting mechanism of the air flow guide component and the tangential rotational flow component, different rotational flow degrees of a single nozzle can be realized, so that the nozzle adapts to fuels with different properties; according to different working conditions, different air rotational flow degrees can be set for the nozzle assemblies on different layers in a staggered mode, or different air rotational flow degrees can be set for the multiple nozzle assemblies on the same layer in a staggered mode, so that staged coupling combustion of the multiple nozzle assemblies in a large space is achieved, and the purposes of enhancing combustion stability and improving temperature uniformity are achieved.

The utility model relates to the technical field of waste gas treatment, in particular to a waste gas spray tower device for waste gas treatment, which comprises a tower body and a liquid tank, the circumferential surface of the rear end of the tower body is fixedly connected with a gas inlet pipe, the circumferential surface of the right end of the tower body is provided with a plurality of material holes, and the liquid inlet end of a water pump is fixedly connected with a liquid inlet pipe. The upper ends of the plurality of latticed carrying plates are connected with push plates through driving mechanisms, the bottom ends of the plurality of flow dividing shells are fixedly connected with a plurality of atomizing nozzles, the plurality of connecting pipes extend rightwards into the tower body and are fixedly connected with the plurality of flow dividing shells, and the plurality of flow dividing shells are located at the right upper ends of the corresponding push plates. According to the utility model, the driving mechanism is controlled to operate to simultaneously drive the plurality of push plates to rotate, at the moment, the filler positioned on the latticed loading plate is pushed by the push plates, and under the action of the push plates, the filler positioned deep in the tower body can be driven to gradually get close to the maintenance channel; and therefore, a worker can take out and replace the filler in the tower body more conveniently.

A gas turbine has a core turbine engine, and a fan having a plurality of fan blades. A nacelle surrounds the fan and at least a portion of the core turbine engine. The nacelle defines an inlet arranged upstream of the fan, and a bypass flow passage downstream of the fan defined between the nacelle and the core turbine engine. The gas turbine also includes a bypass flow passage water injection system that includes (a) at least one water injection nozzle assembly arranged to inject water into at least one of the inlet of the nacelle, or into the bypass flow passage, and (b) a water injection supply system arranged to supply water from a storage tank to the at least one water injection nozzle assembly. Water is provided by the bypass flow passage water injection system during a high power operating states of the gas turbine to augment thrust.

The present invention relates to the field of automated apparatuses. Disclosed is a robot capable of automatically climbing, wherein the robot capable of automatically climbing comprises a main body and climbing mechanisms, each of the climbing mechanisms comprising a telescopic linkage. An inner lifting sliding rail moves vertically along a fixed sliding rail, a middle lifting sliding rail moves vertically along the inner lifting sliding rail, and an outer lifting sliding rail moves vertically along the middle lifting sliding rail. An instant adhesive storage tank and a numerical control nozzle are provided at the top end of each of the inner, middle and outer lifting sliding rails, the numerical control nozzle spraying an instant adhesive to a climbing surface to form a load-bearing plate. A climbing assembly is provided on each of the inner, middle and outer lifting sliding rails, and the climbing assembly moves vertically along its corresponding inner, middle and outer lifting sliding rails and is configured to be supported on the load-bearing plate. A central processing unit is in communication connection with the telescopic linkage, the inner, middle and outer lifting sliding rails, the climbing assembly and the numerical control nozzle.

Provided are: an aircraft that can fly stably even when water is discharged from a hose installed on the airframe thereof; and an aircraft system that uses the aircraft. This aircraft system comprises: a master aircraft 10; three slave aircrafts 20; and a remote control device 30 that is for making the aircraft fly as a unit. Each slave aircraft 20 has: four rotary blade portions that have propellers 221; and a suspending means 23 that is for suspending a prescribed part of a hose 50 that is for discharging water. The master aircraft has: four first rotary blade portions that have first propellers 121 that have been arranged to rotate in a horizontal plane; four second rotary blade portions that have second propellers 131 that have been arranged to rotate in a vertical plane; and a nozzle 15 on which a tip end part of the hose 50 is installed. The direction of the center axis of the nozzle 15 is parallel to the direction of the rotational axes of the second propellers 131.

An atomizer includes: an aerosol-forming article having formed therein an accommodating cavity for accommodating an aerosol-forming substrate; and a suction nozzle assembly engaged with the aerosol-forming article, the suction nozzle assembly having an air inlet passage and an air outlet passage respectively in communication with the accommodating cavity and an assistance air passage directly or indirectly communicating the air outlet passage with external air.

Apparatus for cleaning a horizontally extending floor surface. In some embodiments, a flat surface cleaning machine has an inverted cup-shaped deck and a swivel coupled to a source of pressurized liquid such as water. A rotatable spray bar assembly extends from the swivel and includes an elongated hub member, an arm member threadingly coupled to the hub member, and a nozzle threadingly coupled to the arm member. Shoulder limit surfaces set the rotational position of the arm member relative to the hub member to position the nozzle at a desired operational angle such as from 5-30 degrees. Interior channels along the hub and arm members are shaped to efficiently convey the pressurized fluid to the nozzle. Multiple hub and arm members may form a T, X, Y or star-shaped pattern. The spray bar has an aerodynamically shaped outer surface profile to reduce weight, vibration and turbulence during operation.

The invention relates to an all-dimensional automatic spraying production line, which is characterized in that a spray head assembly can perform multi-degree-of-freedom movement in different planes through rotation driving of a cross beam around a central fixed shaft and combination of a vertical and horizontal state switching function of a swinging cross rod; through the swing hinging design of the spray head assembly and the transmission assembly of the sliding rod, the angle of the spray head can be dynamically adjusted in the spraying process, a composite motion trail is formed, dead-corner-free covering on the surface of the workpiece is achieved, and the spraying uniformity is remarkably improved; due to the linkage design of the sliding rod and the transmission assembly, when the cross beam rotates, the reciprocating driving assembly can synchronously drive the sliding rod to slide along the swing cross rod, and the spray head assembly is forced to swing back and forth through the transmission assembly; due to the dynamic adjusting mechanism, the nozzle can simulate manual spraying, and the spraying effect is further improved; in addition, due to the design of mechanical linkage, response delay caused by traditional motor or pneumatic independent control can be reduced, and it is ensured that actions of all the nozzles are highly synchronous.

An aircraft gas turbine engine includes a combustor, with a combustion chamber and fuel spray nozzles to inject fuel into the chamber. The nozzles include first and second subsets. The first subset of nozzles 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 lean cruise nvPM emissions index ratio isEIcruise⁡(lean),SAFEIcruise⁡(lean),FF,where EIcruise(lean),SAF isEImaxTO,SAF+EIclimb,SAF2and EIcruise(lean),FF isEImaxTO,FF+EIclimb,FF2.EImaxTO,SAF is nvPM emissions index operating at 100% available thrust and EIclimb,SAF is the nvPM emissions index operating at 85% available thrust if fuel includes sustainable aviation fuel. EImaxTO,FF is the nvPM emissions index operating at 100% available thrust and EIclimb,FF is the nvPM emissions index at 85% available thrust if fuel is a fossil-based hydrocarbon. The lean cruise nvPM emissions index ratio is less than 1.

The invention relates to the technical field of tool changing, in particular to a numerical control machine tool tool changing mechanism which comprises a first mounting plate, a second mounting plate and two L-shaped plates which are fixedly arranged in a machine tool and further comprises a controller, a tool taking device, a wiping device, an anti-rust device and a rotating device. The wiping device comprises a collecting box, a pushing assembly and two sponges, the anti-rust device comprises a storage cylinder, an extrusion assembly, a conveying assembly and a plurality of atomizing nozzles, and the rotating device comprises a rotating disc, a driving assembly and a tool to be replaced. And the two sponges can be used for wiping the surface of the operation tool in time after the operation tool is replaced, cleaning of the operation tool after replacement is achieved, and it is guaranteed that the machining precision and machining quality of the tool are not affected when the operation tool is used next time.

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 1:2 to 1:5. A thrust nvPM emissions index ratio is defined as:EImaxTO / FmaxTOEIidle / Fidlewhere: EIidle is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 7% available thrust for given operating conditions; EImaxTO is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if 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 for the given operating conditions; and Fidle is the thrust of the gas turbine engine at around 7% available thrust in kN for the given operating conditions. The thrust nvPM emissions index ratio is greater than 0.001. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the plurality of fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

The invention discloses a vacuum cup laser welding device, and belongs to the technical field of laser welding, the vacuum cup laser welding device comprises a processing table, the top of the processing table is connected with a base box, and the top of the base box is provided with a synchronous clamping assembly. According to the device, the air curtain assembly is arranged, a continuous and uniform annular laminar flow air curtain is formed by means of the nozzle array evenly distributed in the circumferential direction, a stable inert gas protection environment is formed in a welding area, the oxidation probability of a molten pool is remarkably reduced, meanwhile, the air curtain structure optimally designed through fluid dynamics can effectively disperse welding smoke dust, and the welding quality is improved. By means of a mechanical structure, the angle of the direction adjusting pipe can be accurately adjusted, the coverage range of the air curtain can be flexibly adjusted, accordingly, the vacuum cup body with different specifications can be adapted, possible protection blind areas are eliminated, and the service life of the vacuum cup body is prolonged. And the optimal action angle between the welding protection airflow and the workpiece surface is always kept.

The invention relates to the technical field of smashing, and discloses a cerium oxide airflow smashing device and a production technology.The cerium oxide airflow smashing device comprises a base, four supporting legs arranged at equal angles are arranged on the base, a first tank is connected to the supporting legs, and an air injection mechanism used for spraying high-pressure airflow and driving materials to collide with one another to be smashed is installed in the first tank; a feeding pipeline positioned above the air injection mechanism is mounted on the first tank body; the inner wall of the first tank body is provided with four cooling assemblies which are arranged at equal angles, the upper port of the first tank body is connected with a second tank body through a flange, the second tank body is provided with a grading mechanism and a discharging pipeline corresponding to the grading mechanism, and the upper port of the second tank body is provided with a top cover; according to the device, efficient production is achieved through multi-dimensional innovation, a double-layer S-shaped cooling flow channel dissipates heat quickly, and high-temperature agglomeration of materials is avoided so as to guarantee stable physicochemical properties; and the four groups of opposed nozzles form a vortex field, so that the particle size refining rate of the material is more than 90%, and the energy consumption is reduced by 35%.

A full-plastic trigger spray pump, wherein a lower part of the pump body is connected to a locking cover, a liquid spray channel is in the pump body, a nozzle is provided at an outlet of the liquid spray channel, a liquid outlet channel is communicated with the liquid spray channel, a liquid guide chamber is provided on the liquid outlet channel and a liquid inlet channel, the upper part of the liquid guide chamber is in communication with the liquid outlet channel by a normally open port, a pumping piston is in the liquid guide chamber, a trigger capable of driving the pumping piston is hinged onto the pump body, an elastic arm capable of driving the trigger is provided thereon, a lateral one-way valve adapted to open during the return movement of the pumping piston enables the liquid guide chamber to communicate with the liquid inlet channel.

Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.

An anti-icing system for a gas turbine system includes a plurality of nozzles and a bypass conduit. Each nozzle of the plurality of nozzles includes one or more outlets that are configured to inject a first portion of a heated fluid into an airflow within an air intake conduit of the gas turbine system upstream of a filter. The bypass conduit is configured to direct a second portion of the heated fluid into the airflow within the air intake conduit downstream of the filter.

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 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 plurality of 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 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.

Disclosed are a press-type cup lid and a nozzle cup. The press-type cup lid includes a lid body, a press button movably mounted on the lid body, a suction nozzle fixed to the press button, and a suction pipe fixed to the lid body. The press button includes a first position and a second position. When the press button is in the first position, a channel of the suction nozzle communicates with a channel of the suction pipe. When the press button is in the second position, the channel of the suction nozzle is disconnected from the channel of the suction pipe.

The utility model relates to the technical field of gas guiding of gas shielded welding guns, in particular to a gas guiding assembly of a gas shielded welding gun, which comprises a gas inlet pipe, a contact tube arranged at one end of the gas inlet pipe and gas dispersing holes arranged on the side wall of the gas inlet pipe. The side wall of the flow dividing sleeve is provided with a plurality of flow dividing holes, the inner wall of the flow dividing sleeve is provided with a vent groove, the flow dividing holes are communicated with the vent hole through the vent groove, the air inlet pipe is sleeved with an insulating cylinder, one side of the insulating cylinder is provided with a spray pipe, a spiral blade is sleeved with the spray pipe, and the spiral blade is arranged on the air inlet pipe in a sleeved mode. And the shunting hole and the contact tube are positioned in the spiral blade. The utility model provides a gas guide assembly of a gas shielded welding gun, which can reduce turbulent flow formed in a welding area, improve the welding quality and conveniently clean welding slag, and is used for overcoming the defects in the prior art.

A gas turbine engine for an aircraft. The gas turbine engine comprising: 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 1:2 to 1:5. An MTO nvPM emissions index ratio-modified fuel flow is defined as:EImaxTO,SAFEImaxTO,FF×Wf,maxTOwhere: 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 plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); 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 plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and Wf,maxTO is the mass flow rate of fuel provided to the plurality of fuel spray nozzles in kg / s when the gas turbine engine is operating at around 100% available thrust for the given operating conditions. The MTO nvPM emissions index ratio-modified fuel flow of the gas turbine engine in kg / s is less than 2. The gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

A gas turbine engine includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the combustion chamber. The nozzles include a first and second subset. Each of the nozzles 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 from 1:3 to 1:6. A fuel-flow nvPM emissions index ratio isEIidle×Wf,idleRImaxTO×Wf,maxTO.EIidle and EImaxTO are the system loss corrected nvPM emissions index in mg / kg operating at around 7% and 100% available thrust for the given operating conditions, respectively. Wf,idle and Wf,maxTO are the rate of fuel flow to the fuel spray nozzles in kg / s at around 7% and 100% available thrust for the given operating conditions, respectively. The fuel-flow nvPM emissions index ratio of the gas turbine engine is less than 0.3.

The invention discloses a low-temperature minimal quantity lubrication cooling method in aluminum alloy precision machining, and relates to the field of aluminum alloy precision machining. Machining parameters such as the cutting speed and the feeding amount are determined according to the aluminum alloy material, the machining requirement and the tool performance, and finite element simulation optimization is carried out; high-purity vegetable oil-based lubricating oil is selected, a nano anti-wear agent and an antioxidant are added, and cooling liquid is prepared by mixing compressed air through vortex tube refrigeration; spraying to a processing area through a special multi-channel nozzle, and dynamically adjusting the flow; multiple sensors are used for monitoring the temperature, the tool abrasion and the surface quality, and adjustment is conducted when threshold values are exceeded; and the cooling liquid is recycled after being subjected to centrifugation and membrane filtration treatment, and the metal filing is classified, recycled and reused. The cooling and lubricating effects are good, cutting heat and tool abrasion are reduced, the machining precision is improved, and the tool service life is prolonged; environment-friendly lubricating oil is recycled, so that pollution and cost are reduced; real-time monitoring and adjustment guarantee stable machining quality, machining efficiency is improved, and high-end manufacturing requirements are met.

A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in the range 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An nvPM emissions index ratio is defined as:EIidle×Wf,idleEImaxTO×Wf,maxTOwhere: EIidle and EImaxTO are respectively the nvPM emissions index in mg / kg of gas turbine engine if operating at around 7% or 100% available thrust for given operating conditions; Wf,idle and Wf,maxTO are respectively the rate of fuel flow to fuel spray nozzles in kg / s at around 7% or 100% available thrust for given operating conditions. The fuel-flow nvPM emissions index ratio is less than 0.08. The gas turbine engine is configured to provide fuel including sustainable aviation fuel to fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.