25 results about "Inlet cone" patented technology

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 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 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

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 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.

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 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.

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

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.

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 the operation of the turbine (5). 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 discloses a drilling fracture zone magnetic type grouting device and method.The drilling fracture zone magnetic type grouting device comprises a barrel, a magnetic type floating ball valve structure and a rope magnetic control system, and the barrel comprises an outer shell of a tubular structure, a hanging ring structure arranged at the top of the outer shell and a double-cone structure arranged at the bottom of the outer shell; the double-cone structure comprises an inlet cone and an outlet cone which are both of a conical shell structure, and the small-diameter ends of the inlet cone and the outlet cone are oppositely connected. The magnetic attraction type floating ball valve structure comprises a floating ball made of ferromagnetic materials and magnetic strips circumferentially arranged at the small-diameter end of the inlet cone. The floating ball is limited in the inlet cone under the action of magnetic attraction force and gravity of the magnetic strip to block the small-diameter end of the inlet cone; the rope magnetic control system comprises a rope and a magnetic chuck fixed at one end of the rope, the rope penetrates through the hanging ring structure to suspend the magnetic chuck below the hanging ring structure, and the rope is lowered to enable the magnetic chuck to attract the floating ball for releasing the small-diameter end of the inlet cone from being blocked by the floating ball. According to the invention, lightweight and efficient small-scale drilling grouting operation within the hole depth of 300m can be realized.

The invention provides a heat pipe system for heat dissipation and ice prevention of a gear fan engine and the engine thereof.The heat pipe system comprises a heat pipe assembly, a plurality of spiral return pipes, an air inlet cone, an air inlet cone heating partition plate assembly and a plurality of partition plate ribs, the air inlet cone heating partition plate assembly is installed in the air inlet cone to form an umbrella-shaped cavity, and the spiral return pipes are arranged in the air inlet cone; the partition plate ribs are arranged in the umbrella-shaped cavity; an outlet of the spiral backflow pipe is connected with the heat pipe assembly, and an inlet of the spiral backflow pipe is connected with the high-radius position of the partition plate rib. The GTF heat dissipation requirement can be met, heat is fully used for an anti-icing area, comprehensive utilization of heat dissipation and heat consumption is met, and the GTF large-amount heat dissipation requirement is met. And 1% of mainstream acting gas is expected to be reduced, and heat management is more efficient. The umbrella-shaped spiral structure can achieve backflow of liquid in the heat pipe, and heat transfer is accelerated. The heat needing to be dissipated of the gearbox is used for the anti-icing area of the front section of the air inlet cone, and waste heat is used for preventing icing.

The invention relates to the technical field of pump model tests, and discloses an efficient guide vane type mixed-flow pump section model test device, which comprises a sectional type pump section group and an adjusting mechanism, and is characterized in that the sectional type pump section group comprises a water inlet taper pipe, a guide vane body, an impeller chamber, a water outlet elbow pipe and a support ring which are detachably connected; the impeller chamber is of a sectioning structure, two blade observation windows are symmetrically arranged on the two sides of the impeller chamber, and the length of the blade observation windows in the downstream direction is larger than that of blades at all angles in the downstream direction. According to the efficient pump section model test device for the guide vane type mixed-flow pump, disassembly and assembly convenience, observation comprehensiveness, adjustment precision and operation stability are achieved, and high relevance between test data and actual working conditions is guaranteed; the problems that an existing pump section model test device of the mixed-flow pump is tedious to disassemble and assemble, incomplete in observation, low in adjustment precision, poor in test data reliability and insufficient in operation stability are solved.

An air inlet cone shell is provided with an air inlet part corresponding to an air inlet and a shell part connected with the air inlet part. The shell part is provided with a plate-shaped part and a bent part extending from the periphery of the plate-shaped part. And the plate-shaped part is circular. The plate-shaped part comprises a center part located in the center, a first circular-ring-shaped protruding part arranged on the periphery of the center part in a surrounding mode and a first circular-ring-shaped concave part connected between the center part and the first circular-ring-shaped protruding part in the radial direction of the plate-shaped part. The protruding direction of the first circular-ring-shaped protruding part is opposite to the concave direction of the first circular-ring-shaped concave part. By means of the arrangement, the rigidity of the air inlet cone shell can be improved through the first circular-ring-shaped protruding part and the first circular-ring-shaped concave part, and therefore the noise phenomenon caused by resonance is avoided.

The invention relates to the technical field of gas turbine engine anti-icing design, and discloses an anti-icing flexible air inlet cone structure which comprises an air inlet cone front section with a cone tip part and an air inlet cone rear section fixedly connected to the air inlet cone front section. The front section of the air inlet cone is made of a flexible rubber material, and the rear section of the air inlet cone is made of a hard material; according to the air inlet cone, ice blocks of the front section of the air inlet cone can be automatically thrown out to a fan flow channel under the action of centrifugal force through flexible deformation of the front section of the air inlet cone, rapid deicing and anti-icing of the air inlet cone are achieved, and automatic deicing and anti-icing of the air inlet cone of an aero-engine can be achieved without introducing a complex electric heating device or high-temperature gas for heat exchange in the process; safe operation of the aero-engine is guaranteed; in addition, the inner wall of the rotation section of the front section of the air inlet cone is of a double-step structure, the double-step structure can reduce the rigidity of the cone tip, the deicing effect is enhanced through flexible deformation of the cone tip, and meanwhile the weight of an engine can be reduced.