62 results about "Rotor design" patented technology

The invention discloses a device and a method for simulating heat exchange and friction resistance measurement of an aviation high-speed motor under different working conditions, and relates to the field of heat management of high-speed rotating equipment. An additional heating sheet is attached to the outer surface of the inner rotor, and different surface structures are detachably assembled on the outer rotor to form a stator and rotor slit flow channel boundary; cooling liquid forms one-inlet and one-outlet forced convection through the radial through hole of the end cover. The rotating speed larger than or equal to 20,000 rpm, runner pressure drop and temperature data are synchronously collected through an axle load type sensor, and the heat exchange coefficient, the flow resistance coefficient and the friction resistance coefficient are calculated in real time based on energy conservation, a Darcy formula and a torque empirical formula. A real rotor surface structure is reproduced under the condition of high-speed rotation, working medium leakage is restrained through mechanical sealing, and runner blockage caused by centrifugal deformation of the surface structure is prevented through the outer rotor designed in an integrally-formed mode; the obtained convective heat transfer-resistance coefficient-friction resistance coefficient all-parameter curved surface database can guide optimization of the cooling flow channel of the aviation motor.

The utility model belongs to the technical field of agricultural unmanned aerial vehicles, and particularly relates to a bionic agricultural pesticide spraying aircraft. Comprising a fuselage and n supporting legs evenly distributed around the fuselage, n is an even number larger than or equal to 4, and each supporting leg is provided with a set of propellers driven by a motor; a plurality of independent pesticide bins are arranged in the machine body, an outlet of each pesticide bin is connected with a mixing box in the machine body through a water path, a metering pump is connected into the water path, a stirring device is arranged in the mixing box, a plurality of nozzles are evenly distributed on the periphery of the machine body, an outlet pipeline of the mixing box is divided into branches with the same number as the nozzles, and the branches are connected with the nozzles in a one-to-one mode. A booster pump is mounted on the branch; depth cameras are distributed outside the fuselage and used for acquiring environment images, and the aircraft controls a flight path according to the environment images; the unmanned aerial vehicle adopts a partitioned pesticide bin and octopus bionic eight-rotor design, and has high pesticide mixing capacity and stable flight control performance.

The application discloses a small airship device and a control method for automatic modeling of indoor three-dimensional objects, and belongs to the field of indoor aircraft intelligent inspection and three-dimensional perception systems. The airship adopts a four-rotor design arranged in layers. The upper vertical rotors control horizontal forward and backward movement and turning, and the lower horizontal rotors adjust the lifting force to realize lifting and hovering, thereby realizing multi-degree-of-freedom decoupling control. Attitude data are collected through an attitude sensor, and a PID algorithm is combined to realize automatic height maintenance. A communication module is used to build a WiFi local area network and run a Web control page, thereby realizing remote flight control of an intelligent terminal. On this basis, a preset flying-around program is executed to control the airship to automatically cruise at a constant radius and height around a target object, the rudders are synchronously adjusted to drive the camera to take multi-angle photographs, and image acquisition required for three-dimensional modeling is completed. The method combines manual and automatic control modes, and improves flight stability and modeling efficiency.

The invention belongs to the field of aero-engine rotor design, and provides an aero-engine two-dimensional thrust vectoring nozzle heat shield fixing and restraining structure which adopts a high-flexibility space curve notch design to actively control the rigidity of two dimensions of a bolt so as to release thermal deformation and avoid thermal damage to the structure caused by local overlarge thermal stress. And meanwhile, the material characteristics of metal rubber are used for improving the vibration absorption capacity of the aero-engine fixing and restraining structure, the problem that the vibration reduction capacity of an existing connecting structure is insufficient under airflow pulsation excitation is solved, and meanwhile the pulsation frequency band in the engine working condition is widened.

A rotating electric machine (100) in an internal rotor design for converting mechanical energy into electrical energy or vice versa, comprising: - a stator (2), - a rotor (4) inside the machine (100) which is enclosed by the stator (2) and is or can be arranged non-rotatably on or attached to a rotatably mounted drive / output shaft (5) such that the drive / output shaft (5) including the rotor is rotatable about an axis of rotation R, and - a rotor cooling device designed to guide cooling medium along at least a part of the inner surface and / or through at least a part of the interior of the rotor (4) for heat dissipation mainly by thermal convection or to bring it close to the inner surface of the rotor (4) for heat dissipation by thermal radiation, wherein the drive / output shaft (5) has a free shaft end (5a) and the rotor (4) is or can be fitted onto the free shaft end (5a) and the rotor (4) is cup-shaped.wherein the rotor cooling device further comprises a stationary hollow cooling nozzle (3) extending in the direction of the rotational axis R of the rotor (4) from the open side of the cup-shaped rotor (4) into the interior of the cup and having, at its end (3a) facing away from the rotor (4), connected or connectable to a cooling medium source for supplying cooling medium, and having a cooling medium outlet (19) for discharging the cooling medium to the outside of the machine, wherein the end (3b) of the cooling nozzle (3) facing the rotor (4) is open and rib- or blade-like projections (7) and a vane (8) for forced cooling are located on the outside (3c) of the cooling nozzle (3).

The invention discloses a reluctance rotor design method based on a streamline magnetic barrier and a motor, and belongs to the field of synchronous reluctance motors, a reluctance rotor comprises a magnetic barrier main body, a low-magnetic-conductance tail part and a separated magnetic island, and the design method comprises the following steps: drawing the streamline magnetic barrier main body according to the direction of a magnetic line of force of a d-axis magnetic field by taking increase of d-axis inductance and reduction of q-axis inductance as targets; in order to reduce the magnetic flux leakage of the rotor and reduce the influence on a d-axis magnetic circuit at the same time, the tail part of the magnetic barrier is subjected to narrow opening design, and the endpoint of the magnetic barrier main body and the endpoint of the magnetic barrier tail part are connected through a straight line or an arc to form a low-magnetic-permeability magnetic barrier tail curve; taking all design parameters of the rotor as optimization variables, selecting proper optimization targets and constraint conditions, establishing an optimization problem, and solving the optimization problem to obtain optimal design parameters; and selecting a new material or process mode to realize the integrity of the rotor, and completing the design of the reluctance motor based on the streamline magnetic barrier. According to the invention, the dq-axis reluctance difference can be increased, the salient pole ratio is improved, and the torque output capability of the synchronous reluctance motor is improved.

The utility model relates to a motor stator rotation direction testing device, which comprises a computer, a main control board, a testing cable, a signal cable and a magnetic sensor group, the computer is connected with the main control board, one end of the testing cable and one end of the signal cable are both connected with the main control board, the other end of the testing cable is connected with a stator UVW lead, and the magnetic sensor group is connected with the testing cable. The other end of the signal cable is connected with the magnetic sensor, the magnetic sensor group is arranged in the stator, and the magnetic sensor group comprises two vertically arranged magnetic sensors. The magnetic sensor is small in size and wide in adaptive motor stator diameter range, does not need to be matched with a plurality of testing devices for different stators, cancels the design of a false rotor, does not have a rotating device, cannot fly out to hurt people, and is safe and relieved.

The invention relates to the technical field of high-temperature gas cooled reactors, and discloses a verification system and method for high-temperature gas cooled reactor fuel choke flow passage, and the verification system comprises a reaction section, a lifting section, a ball falling section, a gas supply assembly and a choke; the downstream of the lifting section is communicated with the upstream of the reaction section; the upstream of the ball falling section is communicated with the downstream of the reaction section; the air supply assembly is communicated with the upstream of the lifting section; the upstream of the flow plug is communicated with the downstream of the ball falling section, the downstream of the flow plug is communicated with the upstream of the lifting section, and a rotor of the flow plug is detachably mounted in the main body part; in the first state, the rotor is installed in the main body part, and the air supply assembly only supplies air to the lifting section, and in the second state, the rotor is detached from the main body part, and the air supply assembly supplies air to the lifting section and the ball falling section at the same time. According to the invention, through the design of the detachable rotor, rapid switching between flow choking and flow passing of the flow choking device is realized, the gas flow direction difference in the two states is determined, and a stable and reliable hardware basis is provided for verifying the feasibility of cancelling the flow choking device.

This invention provides a steering pump rotor designed to prevent detachment, belonging to the field of automotive parts technology. It solves the problem of existing steering pump rotors easily detaching. This anti-detachment steering pump rotor includes a stator and a rotor. The rotor surface has several slots, and blades are slidably connected to the inner cavity of each slot. Annular grooves are formed at the top and bottom of the rotor, and limiting rings are placed inside the inner cavities of these grooves. Sliding grooves that match the limiting rings are formed at the top and bottom of each blade. Several adjusting bolts are threaded through the inner wall of the limiting rings. This invention has the advantages of constraining the blades, preventing them from detaching, and allowing for fine adjustment of the blade positions according to actual usage.

The invention discloses a small airship device for indoor three-dimensional object automatic modeling and a control method, and belongs to the field of indoor aircraft intelligent inspection and three-dimensional sensing systems. The airship adopts a layered four-rotor design, an upper-layer vertical rotor controls horizontal advancing, retreating and steering, a lower-layer horizontal rotor adjusts lift force to realize lifting and hovering, and multi-degree-of-freedom decoupling control is realized. Attitude data are collected through an attitude sensor, and height automatic holding is achieved in combination with a PID algorithm. And a WiFi local area network is constructed by using the communication module, and a Web control page is operated, so that remote control of the intelligent terminal on flight is realized. On the basis, a preset flying-around program is executed, the airship is controlled to conduct fixed-radius and fixed-height automatic cruise around the target object, a steering engine is synchronously adjusted to drive a camera to conduct multi-angle shooting, and image collection needed by three-dimensional modeling is completed. According to the method, manual and automatic control modes are fused, and the flight stability and the modeling efficiency are improved.

The invention relates to the technical field of motors, in particular to a multifunctional disc type motor integrated system, application thereof and mobile terminal equipment. The disc type motor integrated system comprises a disc-shaped shell, a power component and functional components, the functional components comprise an eccentric wheel, a linear driving arm and a cooling fan, and the power component adopts a double-rotor design; the motor integrated system not only integrates multiple functions of vibration feedback, lens driving, heat dissipation and the like, but also can efficiently utilize the internal space of the mobile terminal equipment and improve the integration, is flexible in function switching, and can meet the use requirements of users. Functions originally required to be realized by three independent motors are integrated into one disc-type double-rotor motor, and more flexibility is provided for layout of other parts of the mobile terminal equipment. And meanwhile, the system also has the advantages of reduced energy loss, prolonged endurance time of mobile terminal equipment, low motor failure rate, high reliability, more accurate and efficient control, more simplified production process, higher assembly efficiency and the like.

The switching valve comprises a driving part, a valve body part and a control detection device, the driving part comprises a motor, the output end of the motor is connected with a coupler, the coupler is sleeved with a first deep groove ball bearing, the end, away from the motor, of the coupler is provided with a butt joint end, and the butt joint end is provided with a second deep groove ball bearing. The valve body part comprises a valve shell and a valve head, a valve rod is arranged in the valve shell in a penetrating mode, butt joint ends of the valve rod are correspondingly connected, the valve rod is sleeved with a spring assembly, the valve rod is detachably connected with a rotor through a first connecting piece, the rotor is provided with a plurality of flow channels, the valve head is detachably connected with a stator through a second connecting piece, and the stator is provided with a plurality of flow paths. According to the utility model, the stator and the rotor are designed to be detachably connected, so that the valve rod has the advantages of simplicity in maintenance and low maintenance cost, and the effect of prolonging the service life of a product and the effect of enhancing the competitiveness of the product are achieved by arranging the spring assembly between the coupler and the rotor on the valve rod correspondingly.

This invention belongs to the field of aero-engine rotor design and provides a distributed support and constraint structure for high-temperature thin-walled components. The structure includes a thin-walled component for an afterburner, a thin-walled nozzle component mounted on the tail end of the afterburner thin-walled component, and a component hinge assembly installed between the outer surface of the tail nozzle thin-walled component and the tail end of the afterburner thin-walled component. An electrically controlled telescopic assembly for the thin-walled component is provided between the outer surface of the afterburner thin-walled component and the outer ring surface of the tail nozzle thin-walled component. In this invention, with the assistance of the electrically controlled telescopic assembly and the hinge assembly, the thin-walled components can be supported and constrained while simultaneously improving their fatigue resistance by reducing friction. Furthermore, the structure of the thin-walled components is non-uniformly distributed along the axial / circumferential directions, achieving a non-coordinated design effect through environmental excitation and the thin-walled components.

The present invention relates to a three-phase asynchronous motor having a passive rotor and a stator, comprising a laminated core having slots, wherein the slots can accommodate a plurality of molded winding coils made of solid copper material using hairpin technology, the rotor is designed as a copper rotor, and the winding head of the stator can preferably be realized by layer-by-layer additive coating and locally selective solidification of a conductive material, particularly copper material. According to the present invention, the three-phase asynchronous motor has distributed pitch-free hairpin windings with a number of strand windings in the range of 100 or more, with 10 to 16 hairpins installed in each slot, and can achieve a limiting efficiency factor of IE4 or higher, particularly IE5 or higher, in accordance with IEC-60034-02, in a speed range of at least up to 2000 rpm.

The present application relates to the field of variable displacement fluid machinery, and particularly relates to an asymmetric three-claw rotor and a claw type fluid machinery with the three-claw rotor, wherein the asymmetric three-claw rotor comprises a first three-claw rotor and a second three-claw rotor capable of synchronous and opposite double-rotation movement around respective rotation centers; the cross-sectional profiles of the first three-claw rotor and the second three-claw rotor are not completely identical, but each is composed of three single-claw outline curves of the same shape connected in sequence to form a planar rotationally symmetric figure. The single-claw outline curves of the first three-claw rotor and the second three-claw rotor in the present application are composed of only four curves, the outline profile is simple, the number of curves contained is less, the independent geometric parameters are less, the rotor design process is simple, and the design and manufacturing difficulty is lower.

An improved desiccant rotor is provided that uses a three-dimensional printed joule heating structure to heat the desiccant directly, thereby improving its efficiency. The heating structure is printed as the substrate itself using additive manufacturing techniques, allowing for unique rotor configurations and better performance in a smaller size. The desiccant is coated on and within the porous heating structure and is in direct contact with it. The heating structure generates heat that is transferred directly to the desiccant, resulting in better moisture removal. The porosity and configuration of the heating structure can be varied to achieve different heating levels and rotor designs. In one embodiment, the desiccant is mixed directly into the conductive ink used to print the heating structure for even greater heat flux. The desiccant rotor may also include sensors and controllers to monitor humidity and adjust heating levels accordingly to maintain consistent dehumidification.

The invention discloses a molded line design method for a corrosion-resistant multi-cavity plum pump. The molded line design method comprises the following steps that S1, molded line parameters are designed; s2, designing an outer rotor; and S3, designing an inner rotor. The design method is simple in step, the molded lines of the inner rotor and the outer rotor can be accurately meshed in the whole running process, a suction cavity and a discharge cavity can be separated through meshing points, stable running and high efficiency of the pump are ensured, the inner rotor and the outer rotor rotate around the centers of the inner rotor and the outer rotor, a closed cavity is formed through molded line combination, and gas compression is achieved; meanwhile, the molded line overcomes the defects that a traditional circular rotor air cylinder molded line is simple, the area utilization rate is low, flow fluctuation is too large, and the defect that an asymmetric structure needs dynamic balance is overcome.

A turbomolecular vacuum pump including a stator and a rotor designed to rotate in the stator. The rotor includes a hub and at least one blade stage including blades distributed regularly about the periphery of the hub. The blades of at least one blade stage of the rotor are hollow.

The invention relates to an electric motor for an aircraft, the electric motor comprising a stator for generating variable magnetic fields, and a rotor that is rotatable with respect to the stator and designed to carry out a rotational movement when the magnetic fields generated by the stator change, wherein the stator has a plurality of, preferably at least three, electrical coils which are each designed to generate a variable magnetic field independently of one another, wherein each of the coils is connected in series between two electrical half-bridges independently of the other coils and can be connected to a current source via the two electrical half-bridges.

Systems and methods form induction rotors by performing isostatic pressing (HIP) to weld clad to a shaft, which allows for scaling the manufacturing of solid steel rotors, as compared to conventional techniques. In examples, the rotors are designed for high-speed motors and may include recessed short circuit rings and / or end rings. An exemplary process molds an alloy powder into cladding such that heretofore unachievable rotor designs are achievable according to systems and methods described herein. In examples, a thin source-layer is introduced to welding zones, thereby enriching and strengthening the resulting joint at welding zones. The source-layer may be introduced by adding an intermediate layer comprising the source material between the materials being welded. The reduced alloy-depletion welding disclosed herein strengthens the welding area joints and provides for the manufacture of component designs, which were previously unachievable due to alloy-depletion weaknesses and environmental constraints.

To address the problem of insufficient design margin caused by the inability to obtain design boundaries in existing turbopump seal-rotor design methods, this invention discloses a liquid rocket engine turbopump seal-rotor design method comprising the following steps: Step S1, establishing a deterministic dynamic model of the seal-rotor; Step S2, setting the optimization parameters, optimization constraints, and objective function of the engine turbopump seal-rotor; Step S3, sampling the dimension and range of the uncertainty parameters to generate a sample library; Step S4, constructing a polynomial surrogate model of the seal-rotor dynamic characteristics; Step S5, determining the boundaries of the seal-rotor dynamic characteristics; Step S6, screening and optimizing the deterministic dynamic model of the seal-rotor to determine the final seal-rotor model result. This invention optimizes the seal-rotor design by combining uncertainty with rotor design, improving the reliability and safety of the rotor, and is simple, efficient, and easy to operate.

The invention discloses a rotor structure of a biphase magnetic material embedded motor, a preparation method and an assembly method, and belongs to the field of motor design. The rotor structure comprises a magnetic conductive block, a magnetic barrier structure and a sleeve structure, the magnetic conductive block is of a segmented structure; the sleeve structure is made of a biphase magnetic material, comprises an outer sheath arranged on the outer side of the rotor and an embedded support body embedded into a rotor pole center shaft, and is connected with the outer sheath; the sleeve structure is T-shaped under the single pole; the contact area of the sleeve structure and the magnetic barrier structure is set as a non-magnetic phase, and the rest area is set as a magnetic phase. The problem of mutual restriction of high strength and low flux leakage requirements in motor rotor design is solved, the peak rotating speed and torque output capability of the motor are improved, and the power density of the motor is improved.

The invention relates to a radial flux machine (10) with a stator (12) and with a rotor (14) which can be driven by means of the stator (12) and is thereby rotatable about an axis of rotation (16) relative to the stator (12), which is designed as a double rotor, which has an outer rotor (20) arranged radially outside the stator (12) and an inner rotor (22) which is arranged radially inside the stator (12) and radially inside the outer rotor (20), wherein the stator (12) has two axially spaced stator parts (44, 46) between which a web (50) is arranged, via which the outer rotor (20) and the inner rotor (22) are connected to each other.

The invention relates to an electronically commutated electric motor (10; 10a; 10b) of internal rotor design, in particular as a component of a windshield wiper motor, with a motor housing (12; 12a; 12b) which has an insertion opening (14) for inserting a stator (16; 16a; 16b) into an interior space (18) of the motor housing (12; 12a; 12b), wherein the stator (16; 16a; 16b) has a longitudinal axis (26), wherein the stator (16; 16a; 16b) is positioned in the interior space (18) in an end position in an axial direction and in a rotational angular position with respect to its longitudinal axis (26).

The utility model relates to a blade root structure for reducing rotor thermal stress belongs to steam turbine rotor design technical field. The utility model solves the technical problem that the existing blade root structure is easy to be damaged and injured due to stress concentration on the slotting of the gap strip at the bottom of the blade root groove on the rotor because of the structure, the middle body, the blade root neck and the blade root lower part are arranged from top to bottom, the gap strip slot is arranged in the center of the blade root bottom, and the cross section shape of the gap strip slot is circular arc; the blade root structure for reducing rotor thermal stress further includes a blade root groove, the blade root groove is sleeved on the outside of the blade root middle body, the blade root neck and the blade root lower part, the blade root groove includes a blade root groove middle body, a blade root groove neck and a blade root groove lower part arranged from top to bottom, the longitudinal section contour shape of the blade root groove lower part is the isosceles trapezoid of wide top and narrow bottom, and four internal angles of the isosceles trapezoid all use circular arc transition. The gap strip slot thermal stress is reduced. The utility model is used for steam turbine rotor.

The invention relates to electric machines, in particular the structural nature of laminated rotor cores and the incorporation of magnetic material in laminated rotor cores for a rotor of an electric machine. A corresponding laminated rotor core for an electric machine comprises a magnetic pocket with magnetic material, which has radially outwardly and inwardly directed regions. Structural integration allows mechanical force deflection by directly abutting surfaces of the magnetic material and the regions of the laminated rotor core, wherein intermediate spaces separate the laminated rotor core from the magnetic material.

The invention relates to the field of gas turbines, in particular to a marine gas turbine elastic support centering design and test method.The method comprises the steps that a rotor geometric model containing design parameters is established on the basis of a rotor design drawing, and according to a rotor global temperature field distribution result and a rotor mechanical constraint and load applying result, a rotor geometric model is established; calculating a rotor support radial component force; constructing an elastic support geometric model according to the design drawing of the elastic support, and applying the radial component force of the rotor support as a load to the elastic support grid model; and the maximum radial deformation and the minimum radial deformation in the extraction area are obtained, the eccentric distance is calculated based on the maximum radial deformation and the minimum radial deformation, and supporting centering design is completed. Through the centering design test, the accuracy of the centering design can be detected, the actual deformation condition of the elastic support under the action of the gravity of the rotor can be obtained, the loaded support plate and the loading force arm can be replaced according to the bearing seats of different sizes, and the good engineering application value is achieved.