39 results about "Inlet cone" patented technology

The invention provides an air inlet cone with a noise reduction effect and an aero-engine comprising the air inlet cone. An acoustic liner is laid on the surface of the air inlet cone, and the acoustic liner avoids the tip part of the air inlet cone; the acoustic liner comprises a perforated plate, at least one honeycomb interlayer and a back plate, the honeycomb interlayer is installed between the perforated plate and the back plate, and the back plate is fixed to the surface of the air inlet cone. On the premise that the appearance of the air inlet cone is guaranteed, the acoustic liner is arranged on the surface of the air inlet cone, meanwhile, the acoustic liner is arranged away from the tip part, the honeycomb laying space of the acoustic liner and the strength of the air inlet cone are guaranteed, and forward noise of a fan can be effectively reduced.

The invention relates to turbofan-driven unmanned aerial vehicle ground auxiliary equipment which meets the actual requirements of supplying power to an unmanned aerial vehicle, providing high-speed large-air-volume cooling air flow for hot parts of the unmanned aerial vehicle and providing high-temperature large-air-volume air flow for heating starting of a power system of the unmanned aerial vehicle in a low-temperature environment. Comprising a casing, a turbofan engine and a power supply system, a transmission rotating shaft is arranged in the center of the turbofan engine, an air inlet cone, a fan blade disc, a supercharging blade disc, a turbine blade disc and a generator are sequentially and fixedly connected to the transmission rotating shaft, and the casing in the turbofan engine wraps part of the transmission rotating shaft, the supercharging blade disc, the turbine blade disc and the power supply system. An annular inner duct and an annular combustion area are formed between the turbofan engine outer casing and the turbofan engine inner casing, the turbofan engine is fixed to the auxiliary equipment casing through a rectification partition plate, a fuel pipeline extends into the combustion area from the outside of the casing, and a starting generator and a storage battery in the power supply system are connected with the power distribution management system. The power supply cable is connected with the power distribution management system and extends out of the casing.

An inlet cone (20) for an aircraft turbine engine (1) is configured to be rotated about an axis (X). The inlet cone comprises a frustoconical body (22) and a tip (21) made of elastically deformable material fixed to a smaller-diameter end (221) of said body. The body comprises through-housings (222) distributed around the axis, and parts (23) made of elastically deformable material located in the through-housings. Each of the parts (23) made of elastically deformable material comprises at least one peripheral flange (230) for retaining the part in the corresponding through-housing (222). The peripheral flange bears against an internal surface (22a) of the body.

The present application belongs to the field of centrifugal pump, and particularly relates to a mounting method of a slurry pump, which comprises seven steps, i.e. firstly fixing a bearing body assembly to a bracket body and installing an adjusting screw, then fixing a pump body to the bracket body, then measuring the round run-out of an inner hole and an end face of the pump body and requiring to meet the requirements, then opening two positioning pin holes at a connecting part, then installing a sealing assembly, a secondary impeller and a rear backplate, then installing a primary impeller, then installing a sheath and a front backplate, then installing an inlet cone pipe outside a pump cover and connecting and fixing by fastening bolts, and finally adjusting the gap between the primary impeller and the front backplate, fastening the sealing assembly, fastening the primary impeller, and performing disc checking without friction; the present application correctly installs the slurry pump, improves the qualified rate of one-time trial, and thus improves the service life of the pump.

A high-adaptability sensor structure belongs to the technical field of automobile exhaust system sensors and is characterized by comprising a catalyst and an air inlet cone end connected to the circle center of the left side surface of the catalyst, a pressure difference pipeline is inserted in the outer edge of the left side surface of the air inlet cone end, and an exhaust cone end is connected to the circle center of the right side surface of the catalyst. An exhaust pipeline is connected to the circle center of the right side surface of the exhaust cone end, a protective jacket is welded to the outer edge of the right side surface of the exhaust cone end, a sensor probe is inserted into the circle center of the outer side surface of the protective jacket, and an over-high adaptive sensor mounting surface is changed into an oblique angle design, so that the sensor can be adaptive to mounting surfaces with different angles and different directions; and the welding accessibility can be well met.

The invention discloses a signal transmission equipment isolation sealing structure and a dynamic stress measuring device with the same. The signal transmission equipment isolation sealing structure comprises an air inlet cone, an engine support, an electricity guiding device, an electricity guiding device mounting seat and a sealing connecting shaft group. An inner cavity of the engine support forms an engine lubricating oil cavity, and the electricity guiding device installation base is located in the engine lubricating oil cavity and connected with the engine support in a sealed mode. The electricity leading device is arranged in the electricity leading device mounting seat, and the front end of the electricity leading device extends into the mounting seat inner shaft cavity of the electricity leading device mounting seat. The sealing connecting shaft set is located in the engine lubricating oil cavity, the first end of the sealing connecting shaft set is fixedly connected with an engine rotor shaft of the engine, and the second end of the sealing connecting shaft set penetrates through the installation base inner shaft cavity in a sealed mode in the axial direction to be connected with the electricity guiding device floating shaft of the electricity guiding device. The electric conduction device can effectively prevent the electric conduction device front bearing from being overheated to cause normal work, does not need to be filled with a cooling medium, and does not cause oil leakage and gas leakage of an engine due to the fact that cooling gas enters an engine lubricating oil cavity.

The utility model relates to the field of heat exchangers, in particular to an air preheater which comprises a preheater body, a flue gas inlet cone, a flue gas outlet cone, an air inlet cone and an air outlet cone are arranged on the preheater body, and a mounting frame is detachably mounted between the flue gas inlet cone and the preheater body through a mounting mechanism. And a filter screen is mounted in the mounting frame. Flue gas is filtered through the filter screen before entering the preheater body, solid particles in the flue gas are screened out, the possibility that the solid particles are attached to a pipeline in the preheater body is reduced, the heat exchange efficiency between the flue gas and air is improved, the preheating effect of the air is enhanced, and after the filtering effect of an old filter screen is reduced, the heat exchange efficiency between the flue gas and the air is improved. A new filter screen is mounted through the mounting mechanism, so that the filtering effect of the filter screen is effectively maintained.

The invention discloses a high-speed wind tunnel air inlet test operation and flow field control method, and relates to the technical field of high-speed wind tunnel tests. Communication signals and corresponding simple and clear interaction logics of various systems such as a wind tunnel operation control system, a model attitude control system, an air inlet channel cone position operation control system and a measurement and acquisition system are designed and standardized, and full adaptation of various air inlet channel test working conditions and ordered control of various interaction systems are achieved. According to the method, the test data can be smoothly acquired, the unexpected action of the system and the interactive response abnormity of each system caused by complex interaction of various systems can be avoided, the test data can be smoothly acquired, the test target can be effectively achieved, and the generation of scrapped vehicles in the actual wind tunnel test can be greatly reduced.

The invention discloses a composite mixed-flow turbine, which belongs to the technical field of turbines, and mainly comprises a volute, a flow guide plate and a flow guide plate, the air inlet cone is mounted in the volute casing; the rotating piece is mounted on the air inlet cone; the impeller is installed on the rotating piece, multiple layers of blades are arranged on the impeller, the blades in part of layers are composite blades, the blades in part of layers are axial flow blades, and the blade layers with the axial flow blades are arranged adjacently; the length of the projection of a blade root chord D of each axial flow blade on the axis of the impeller is the projection length H, and the distance between adjacent layers with the axial flow blades is 1 / 5H-1 / 3H; and the tail cone is mounted in the volute casing, and the tail cone corresponds to the impeller. The turbine solves the problems that when fluid passes through an existing turbine, large air volume and high air pressure cannot be provided at the same time in a small space size, and turbulent flow and too large noise are generated at the same time.

The invention relates to an inlet cone (9) for an aircraft turbomachine fan comprising a rotation-locking device including a pusher (3) slidably mounted in an orifice (20), said main portion (30) carrying first rotation-locking means (31) of said cone adapted to engage against second rotation-locking means (12), said first rotation-locking means (31) being movable between at least: an engaged position between the first (31) and second (12) rotation-locking means; and a disengaged position between the first (31) and second (12) rotation-locking means. The transition from the engaged position to the disengaged position is effected by translation of said pusher (3) from an initial position in which one end (300) is flush with an external surface of said inlet cone (9) to a retracted position in which said end (300) is pushed into said orifice (20). Figure 3.

The present invention relates to an inlet cone (2) for an aircraft turbomachine (1), said cone (2) comprising: - a conical or frustoconical body (20) having through-holes (202) distributed around the axis (X), and - parts (23) of elastically deformable material located in said through-holes (202), each of the parts (23) of elastically deformable material having at least one peripheral rim (230) for retaining said part (23) in the corresponding through-hole (202), said at least one peripheral rim (230) bearing against an internal surface (20a) of said body (20), wherein the cone (2) further comprises an annular flange (90) attached and fixed inside the body (20), said flange (90) extending radially inside the parts (23) of elastically deformable material to close said holes (202) through-holes in case of loss of said parts (23) during operation. Figure for the abbreviation: Figure 6

The invention provides an aero-engine air inlet cone dismounting device, and relates to the technical field of aero-engine part dismounting equipment, and the aero-engine air inlet cone dismounting device comprises a hooking assembly, a clamping assembly, a clamping assembly and a clamping assembly, and the hooking assembly comprises a flexible fixed pulling claw, a centering expansion sleeve and a contraction sleeve; the telescopic sleeve is movably arranged outside the pipe wall of the flexible fixed pulling claw in a sleeving mode so as to extrude and contract the flexible fixed pulling claw, and the centering expansion sleeve is arranged in the pipe wall of the flexible fixed pulling claw in a sleeving mode and used for expanding the contracted flexible fixed pulling claw so that the flexible fixed pulling claw can be stably fixed to the air inlet cone. The supporting assembly comprises a supporting end cover and a force application rod, the supporting end cover is fixed to the top end of the flexible fixed pulling claw, and the force application rod penetrates through the supporting end cover and the interior of the centering expansion sleeve; a threaded section is arranged on the force application rod, and the supporting end cover is in threaded connection with the force application rod on the threaded section, so that the supporting end cover and the flexible fixed pulling claw are driven to move upwards by rotating the force application rod, and the air inlet cone of the engine is pulled out. The disassembly efficiency of the air inlet cone is improved, and the disassembly risk is reduced.

This invention discloses a method for proportioning ultra-fine copper wire drawing dies, relating to the field of wire plastic compression technology. The method includes: collecting and preprocessing copper plasticity data; generating a compression decreasing sequence by combining the initial copper wire diameter and the activation energy of the slip system; extracting the compression diameter and compression gradient value from the compression decreasing sequence; calculating the initial curvature of the die inlet cone surface and the cone surface exit curvature using a matching algorithm; determining the sizing band gap size based on the initial curvature of the die inlet cone surface and the cone surface exit curvature; associating the initial curvature of the die inlet cone surface, the cone surface exit curvature, and the sizing band gap size as a three-dimensional reference for the die, generating a three-dimensional manufacturing reference drawing for the die; manufacturing a solid die assembly using the three-dimensional manufacturing reference drawing; and judging the die proportioning result. This invention achieves cross-scale precise coordination of ultra-fine copper wire drawing die proportioning through the synergistic effect of generating the compression decreasing sequence and calculating the die cone surface curvature.

The invention discloses a working procedure combination machining method for an air inlet cone part, belongs to the field of stamping machining of automobile parts, and aims to solve the problems that a traditional air inlet cone stamping process is numerous in working procedure, accumulated in positioning error, low in product percent of pass, high in welding leakage risk and the like. The process is designed by four continuous composite procedures, all the procedures are accurately butted through a unified reference positioning pin, and special equipment does not need to be newly added. The method specifically comprises the steps that in the blanking process, differential edge lapping and precise blanking are adopted; drawing and shaping procedures are integrated in the same module, and continuous forming is achieved through hot plasticity after drawing; the three functions of shaping, trimming and flanging are integrated, and the curvature error of the molded surface after finishing is determined; and the punching and hole flanging processes are coaxially processed at one time. According to the technology, the number of devices is reduced to four, the production takt of a single piece is improved by 35%, meanwhile, the maintenance cost of the devices is reduced by 58%, efficiency, quality and economical efficiency are considered, and the large-scale continuous production requirements of automobile parts are met.

The application discloses a high-speed wind tunnel inlet test operation and flow field control method, relates to the technical field of high-speed wind tunnel test, and designs and specifies communication signals of a wind tunnel operation control system, a model posture control system, an inlet cone position operation control system and a measurement and collection system and corresponding simple and clear interaction logic, realizes full adaptation of various inlet test working conditions and orderly control of various interaction systems, ensures smooth collection of test data, avoids system unexpected actions and system interaction response abnormalities caused by complex interaction of various systems, ensures smooth acquisition of test data and effective achievement of test targets, and can greatly reduce scrapped train sets in actual wind tunnel tests.

The application discloses a double-sleeve structure rapid heat exchange pipe bundle welding positioning tool and a welding method. In the operation process, the inner pipe bears high temperature, the inner pipe is elongated and bent, the gap between the sleeves is reduced, the flow of the cooling water is reduced, and the inner pipe is easily unevenly heated; the inlet cone is subjected to heat treatment after being welded with the lower connecting piece, and the inlet cone is easily cracked by heat. The application is composed of a supporting base (1), a traveling track (2) and a plurality of boosting trolleys (3). The boosting trolleys are arranged in the traveling track, the traveling track is supported by the supporting base, and a side positioning support frame (4) is fixed to the supporting base. The application is used for welding the double-sleeve structure rapid heat exchange pipe bundle.

The present invention relates to an inlet cone (2) for an aircraft turbomachine (1). The cone comprises a conical or frustoconical body (20) having through-cavities (202) distributed about an axis (X), and parts (23) made of elastically deformable material located in the through-cavities. Each of the parts made of elastically deformable material comprises at least one peripheral rim (230) that retains the part in the corresponding through-cavity. The at least one peripheral rim bears against an inner surface (20a) of the body. The cone further comprises an annular flange (90) mounted and secured inside the body. The flange extends radially inside the parts made of elastically deformable material in order to close the through-cavities in the event of loss of the parts during operation. The present invention also relates an aircraft turbomachine (1) comprising the inlet cone (2).

The invention belongs to a mass spectrometry technology, and particularly provides an ionization device and method based on airflow hedging assistance, the ionization device comprises a vacuum cavity, a first electrospray ion source and a sample introduction cone, the first electrospray ion source and the sample introduction cone are respectively arranged in the vacuum cavity; the exhaust pipe is arranged in the vacuum cavity; the central axis of a nozzle of the first electrospray ion source is perpendicular to the central axis of the sample injection cone, the central axis of the sample injection cone penetrates through an exhaust port of the exhaust pipe, and the exhaust port, the central axis of the nozzle and a sample injection port of the sample injection cone are sequentially arranged; the air inlet pipe is arranged in the vacuum cavity, and the nozzle and an outlet of the air inlet pipe are symmetrical about the central axis of the sampling cone; the power supply applies different voltages to the spray ion source, the air inlet pipe, the exhaust port and the sample injection cone to form an electric field, and the electric field pushes sample ions to pass through the sample injection port. The invention has the advantages of high atomization efficiency, strong anti-pollution capability and the like.

The invention provides an inner cavity air entraining type axisymmetric rocket-based combined engine. The inner cavity air entraining type axisymmetric rocket-based combined engine comprises a cone, a rocket engine, a shell and an air entraining component. The cone is divided into a cone part and a containing part in the axis direction, and the end, away from the cone part, of the containing cavity is an open end. A bent part is arranged at the joint of the cone part and the accommodating part; the rocket engine is provided with an injection part and a body part, and a flow guide gap is formed between the body part and the containing part at the opening end. One end of the shell sleeves the accommodating part, and an air inlet channel is formed between the shell and the accommodating part; the air entraining component is arranged in the containing part, one end of the air entraining component communicates with the outside at the position of the bent part, and the other end communicates with the shell through the flow guide gap. The additional air flow is introduced near the outlet of the spray pipe, so that the speed and pressure distribution of the convergent flow beam are improved, the shock wave intensity is weakened, and the total pressure loss is further reduced. The interference between shock waves and a boundary layer is reduced through the suction effect of the air entraining guide pipe on the boundary layer of the air inlet cone, so that the flow stability of the air inlet channel is improved.

The present invention relates to a roll profile of a three-roll skew rolling tube mill (referred to as an Assel tube mill), belonging to the field of hot-rolling steel pipe rolling process in the iron and steel metallurgy industry. The present invention is used to solve the pain point problem of serious spiral channel defects on the inner and outer surfaces of the steel pipe after Assel rolling: the shape of the roll is a truncated cone, the value range of the roll diameter D is 280-1100 mm, and the value range of the roll body length L is 300-800 mm. The conical surface of the roll consists of four major parts: an inlet cone, a roll shoulder, an sizing section, and an outlet cone. The roll profile provided by the present invention can significantly reduce the additional deformation during Assel rolling, reduce the non-uniformity of deformation, and can control the depth of the spiral channels on the inner and outer surfaces of the steel pipe after Assel rolling within 0.3 mm, thereby achieving high-quality production.

An inlet cone (20) for an aircraft turbine engine (1) is configured to be driven in rotation about an axis (X). The inlet cone comprises a body (22) in the shape of a frustoconical shape and a tip (21) made of an elastically deformable material fixed to an end (221) of the body having a smaller diameter. The body comprises a through housing (222) distributed about the axis and a component (23) made of an elastically deformable material located in the through housing. Each of the parts (23) made of an elastically deformable material comprises at least one peripheral edge (230) for retaining the part in a corresponding through housing (222). The outer peripheral edge is supported on an inner surface (22a) of the main body.

The invention belongs to the technical field of aircraft hybrid power system design, and particularly relates to an aircraft hybrid power system hydrogen energy acceleration ducted fan which comprises an outer casing, a spray pipe, an air inlet cone, an inner casing, a tail cone, an electric fan, a motor, a rectification supporting plate, a hydrogen injection rod and an ignition electric nozzle. The spray pipe is connected to the rear end of the outer casing, and the air inlet cone, the inner casing and the tail cone are sequentially arranged in the outer casing. An annular gap exists between the rear end of the air inlet cone and the front end of the inner casing. The electric fan is arranged in the outer casing and located at the annular gap. The motor is arranged in the inner casing, and a rotor is connected with the electric fan; the rectifying support plates are supported between the outer casing and the inner casing in the circumferential direction; the hydrogen injection rods penetrate through the outer casing and extend into the rectification support plates, and nozzles on the hydrogen injection rods are aligned with the hydrogen injection holes in the side walls of the two sides of the rectification support plates; and the ignition electric nozzle penetrates through the outer casing and extends between the rear edges of the two adjacent rectification support plates.

The application relates to the technical field of aero-engines, and provides a rotary detonation combustion chamber with a supercritical combined injection structure, which comprises an inner cylinder and an outer cylinder, the inner cylinder and the outer cylinder are respectively provided with cooling cavities and injection oil cavities, and high-efficiency heat management is realized through multistage regenerative cooling microchannels. The space between the inner cylinder and the outer cylinder forms a combustion cavity, a throat and an air inlet cavity, and the injection hole group is designed to make fuel mixing more uniform, improve combustion efficiency and stability. An opening and closing piece controls the opening and closing of the injection hole, thereby ensuring accurate oil supply under different working conditions. In addition, the air inlet cone and the variable cross-section design optimize the gas flow characteristics, and further improve the overall performance. The application achieves the effects of significantly improving combustion efficiency, reducing temperature distribution unevenness and improving system stability.

The invention relates to the technical field of wind power generation, and discloses a wind driven generator steering mechanism which comprises a main tower body and a cabin, the cabin is rotationally arranged at the top of the main tower body, a supporting beam is arranged in the cabin and sleeved with a supporting cylinder, and a hydraulic motor for driving the cabin to rotate is arranged in the middle of the cabin. The device is characterized in that an air inlet cone is arranged at the tail end of the supporting beam, air inlets are formed in the two sides of the air inlet cone, airflow channels are formed in the two sides of the supporting cylinder, a cover plate capable of overturning up and down is hinged to the communicating position of the air inlets and the airflow channels, an equipment cabin is arranged in the center in the supporting cylinder, and a reversing rotary valve and a linkage assembly for connecting the cover plate and the reversing rotary valve are arranged in the equipment cabin. Compared with the prior art, the device has the advantages that the device is not influenced by eddy current generated by fan blades of a generator, the judgment on the wind direction is more accurate, sensors such as a wind indicator and an encoder are omitted, electronic faults caused by the high-humidity and high-salt environment on the sea are avoided, and mechanical linkage signal transmission and feedback delay are lower.

A fan rotor assembly (10) for a turbomachine, the rotor assembly (10) comprising an inlet cone (14) and a fan disc (12) arranged around a longitudinal axis (A) of the rotor assembly (10), wherein the inlet cone (14) comprises a first end portion (27) and the fan disc (12) comprises a first complementary end portion (25), the first end portion (27) and the first complementary end portion (25) being substantially annular, wherein said first end portion (27) and the first complementary end portion (25) are mounted tightly together. Abstract figure: Figure 1

Inlet cone formed of several parts Aircraft turbomachine (1) comprising an air inlet cone (10) and a rotor (7) driven in rotation about an axis (X) by a turbine (5), said rotor (7) being connected to the air inlet cone (10) to drive it in rotation. The turbomachine (1) comprises a speed reduction module (8) connected to the rotor (7). The air inlet cone (10) has two distinct parts: a tip (11) and a ferrule (12). The tip (11) is located upstream of the ferrule (12). The ferrule (12) is fixed to the rotor (7) and driven by it to rotate at a speed Vv during turbine (5) operation. The tip (11) is connected to the speed reduction module (8) and, via the module, is driven by the rotor (7) to rotate at a speed Vp different from the speed Vv. Figure to be published with the abbreviation: Figure 1

The invention relates to an inlet cone (9) for an aircraft turbomachine fan mounted to rotate about an axis of rotation (R), comprising an upstream cone (1) fixed by at least one first fixing screw (4) to a downstream ferrule (2), said first fixing screw (4) being configured to fit into a first threaded orifice (40) formed partly in said upstream cone (1) and in said downstream ferrule (2), and opening into a channel (39) machined on said upstream cone (1). According to the invention, the inlet cone (9) also comprises a cover (3) configured to fit onto said upstream cone (1) so as to close said channel (39), the upstream cone (1), the downstream ferrule (2), and said cover (3) together forming a substantially continuous external surface of said inlet cone (9). Figure 5

A gas inlet cone assembly is used on a tail gas after-treatment device and comprises an inner metal shell, an outer metal shell and heat insulation cotton clamped between the inner metal shell and the outer metal shell. The outer metal shell is provided with a first main body part; and the inner metal shell is provided with a second main body part. And the first main body part and the second main body part are fixed together in a plug welding manner. According to the arrangement, the structural rigidity of the air inlet cone assembly is improved, the modal frequency is improved, and the problems of resonance and noise are effectively avoided.

The present invention relates to an inlet cone (2) for an aircraft turbomachine (1), said cone (2) comprising: - a conical or frustoconical body (20) having through-holes (202) distributed around the axis (X), and - parts (23) of elastically deformable material located in said through-holes (202), each of the parts (23) of elastically deformable material having at least one peripheral rim (230) for retaining said part (23) in the corresponding through-hole (202), said at least one peripheral rim (230) bearing against an internal surface (20a) of said body (20), wherein the cone (2) further comprises an annular flange (90) attached and fixed inside the body (20), said flange (90) extending radially inside the parts (23) of elastically deformable material to close said holes (202) through-holes in case of loss of said parts (23) during operation. Figure for the abbreviation: Figure 6

The invention discloses a motor-stamping combined engine which comprises a casing, an exhaust nozzle, an air inlet channel, an edge hollowed-out flame stabilizing baffle, an air inlet cone, a diffuser, a motor fixing shell, a motor fixing support, an impeller, a motor, an oil conveying pipe, a J-shaped evaporation pipe, a motor wire, a battery pack, an accelerator, an electronic control unit, an igniter, a fuel valve and a fuel pump. And fuel oil. The motor-ramjet engine is a hybrid aero-engine which is flexible in design, high in total efficiency, simple in structure, low in manufacturing cost, wide in working range, energy-saving, emission-reducing and low-carbon, four strokes are jointly completed through combination of the motor and the ramjet engine, and the problems that the ramjet engine is started independently, depends on external power, is low in low-speed domain thrust, low in combustion stability, low in energy consumption and the like are solved. The requirement for the design of an air inlet channel is extremely high; and the independent endurance mileage of a motor is short. The ECU can adjust the motor power and the fuel pump power in real time so as to achieve the optimal air-fuel ratio as much as possible.