286 results about "Turbomachinery" patented technology

The invention relates to the technical field of PIV (particle image velocimetry) flow field testing devices, in particular to an internal peeping type PIV testing device and method for an internal flow field of turbomachinery, and the device comprises the turbomachinery, a testing assembly and a connecting assembly. The testing assembly comprises a lighting mechanism, a camera shooting mechanism, a laser mounting pipe arranged on the air inlet pipe, a mounting base arranged on the laser mounting pipe and a camera shooting mounting mechanism arranged on the air inlet pipe, and the connecting assembly comprises an inserting mechanism arranged on the laser mounting pipe and a connecting mechanism arranged on the camera shooting mechanism. Through the arrangement of the mounting base and the camera mounting mechanism, a laser light source emitter and a camera are quickly mounted, the camera can adapt to various special-shaped shells such as volutes, the angle of a sheet light source emitted by the laser light source emitter is quickly adjusted through the arrangement of a rotating pipe, and the angle of the sheet light source is adjusted through the arrangement of a connecting mechanism and an inserting mechanism. And the sheet light source emitted by the laser light source emitter is quickly perpendicular to the shooting direction of the camera mechanism again.

The invention belongs to the field of aero-engines and turbines, and provides a quick prediction method, system and device for a two-dimensional viscous compressible flow field of a gas compressor and a medium, and the method comprises the steps: obtaining CFD simulation data of a two-dimensional blade profile of the gas compressor under multiple working conditions, and carrying out the preprocessing to obtain a standardized training data set; on the basis of the data set, constructing a hybrid neural network model which takes a blade profile geometric parameter and an operation condition parameter as input and takes a two-dimensional viscous compressible flow field as output; combining mean square error, gradient loss and physical consistency loss based on RANS equation residual error to construct a total loss function, and performing end-to-end training on the model; during reasoning, to-be-predicted parameters are input into the trained model according to the same preprocessing mode, and then a flow field prediction result can be rapidly output. According to the method, the problems of long consumed time, low precision and poor consistency of traditional CFD simulation can be solved, millisecond-level flow field prediction is achieved, high precision and high physical consistency are achieved, and the method is suitable for efficient optimization design of the blade profile of the gas compressor.

The invention relates to the technical field of turbomachinery monitoring, and discloses a cross-dimension turbomachinery dynamic risk prediction and visualization system. A dynamic data acquisition module of the system acquires multi-source heterogeneous sensing data such as a vibration spectrum sequence, an aerodynamic load distribution matrix, a rotor axial displacement time sequence and a surface temperature field thermodynamic diagram in real time; the service degradation evaluation module extracts a vibration characteristic spectrum based on a historical degradation mode library, calculates an instability risk level in combination with an aerodynamic load deviation value, and fuses a displacement sudden change gradient and a temperature difference abnormal area to generate a service degradation track matrix; the multi-dimensional risk prediction module inputs the degradation track matrix into a space-time coupling prediction network, and outputs a dynamic risk assessment vector including time-varying fault probability distribution, a residual life prediction value and a risk propagation path set; and the risk visualization engine module constructs a three-dimensional risk thermal field model and generates a dynamic thermal grid layer superposed on the digital twinborn body.

The invention discloses a method for calculating blade tip clearance and vibration of a turbomachine blade based on continuous Gaussian fitting, and belongs to the technical field of fault diagnosis. A continuous Gaussian fitting (CGF) method is proposed to be used for obtaining a data signal which can be used for more accurately calculating a blade tip gap and a blade tip vibration characteristic. Compared with a conventional threshold value recognition method (TVM), the CGF method has the advantages that Gaussian fitting calibration is performed on blade tip state signals collected by the capacitive sensor, interference of environmental noise is greatly reduced, and the accuracy of blade tip clearance and vibration calculation is remarkably improved. Experimental results show that the CGF method shows better calculation stability under different rotating speed working conditions, especially at a low rotating speed, the calculation stability of blade tip vibration is 4.15 times that of a TVM method, and blade resonance can be recognized more accurately. According to the method, real-time monitoring can be realized, and more accurate blade tip clearance and vibration data can be provided.

Improved blade designs for turbomachinery, such as blade designs for propellers, that have non-constant airfoil distributions and / or coefficient of lift distributions across the blade span are described herein. An improved blade may include the following three blade sections between a blade root and a blade tip: a first blade section, or span, extending from the blade root to a transition start point; a transition section, or span, extending from the transition start point to a transition end point; and a second blade section, or span, extending from the transition end point to the blade tip. The transition section may define or be a linear or non-linear transition span. Further, an improved blade may be define or be configured as at least two different airfoils along the blade span and / or may be configured to have at least two different coefficients of lift along the blade span.

The invention relates to the technical field of fluid machine design and artificial intelligence crossing, in particular to an optimization design method and system oriented to turbomachinery, a storage medium and a computer program. According to the method, a standardized data bus of a parameter layer, a configuration layer, a geometric layer and a result layer penetrates through an average line, parameterized geometry and multi-objective optimization are carried out, thermophysical property calibers are unified, and sample-level archiving and playback are achieved. Through LHS / Sobol sampling, Kriging proxy, NSGA-II and other algorithms, isentropic efficiency, pressure ratio and structure / noise indexes are collaboratively optimized under the condition that constraints of mass flow, minimum thickness, tip clearance and the like are met; the system is coupled with CFD / FEM through an adapter, and supports GUI and batch processing. Compared with the prior art, the design efficiency, the cross-module consistency and the result traceability are improved, and a manufacturable Pareto optimal blade scheme is obtained.

The invention discloses a ducted fan design method with flow as a key variable, and belongs to the field of ducted fan design. The method comprises the specific steps that the flow needed by a duct is determined; the rotor inlet area and the throat area are calculated according to the flow; determining radial positions of rotor / stator inlet and outlet equidistant control points; constructing a speed triangle based on the set rotating speed and the calculated torque speed and axial speed; geometric feature determination of the rotor and the stator is completed; and exporting geometric data to turbine simulation software to complete three-dimensional modeling of the rotor and the stator. According to the method, the problems that traditional design depends on experience and is low in efficiency are solved, the design period is remarkably shortened while the precision is guaranteed, and the reliability and aerodynamic performance of the ducted fan are improved.

The present disclosure provides a kind of blade for inhibiting the blade of leakage vortex break, blade assembly, impeller machinery and blade shaping method.The blade profile is defined according to the cross section profile of the height direction accumulation, the cross section profile has the ratio of the height of the cross section profile and the total height of the blade, the dimensionless blade height H=1 is the blade tip, the dimensionless blade height H=0 is the blade root;The cross section profile also has the back bending angle δ;At the dimensionless blade height H=1, the back bending angle δ=13 °, and has the tolerance range of the numerical ratio ±20%.

The invention relates to the technical field of bearings, and provides a thrust bearing and turbomachinery. The thrust bearing comprises a fixing ring which is used for being arranged at an interval with the thrust disc in the axial direction; the multiple thrust pads are arranged in the circumferential direction of the thrust disc at intervals and located between the fixing ring and the thrust disc, gaps are formed between the thrust pads and the thrust disc, and the gaps are filled with continuous oil films; the multiple first level blocks are arranged at intervals in the circumferential direction of the fixing ring, and the contact surfaces of the first level blocks and the fixing ring are first spherical surfaces; the multiple second level blocks are arranged between every two adjacent first level blocks and one thrust pad, each second level block is provided with a plane structure facing the thrust pad and a double-spherical-surface structure facing the fixing ring, and each double-spherical-surface structure comprises two second spherical surfaces distributed at intervals; and the two second spherical surfaces are respectively in contact fit with the two adjacent first level blocks. Point contact matching between a spherical surface and a plane is adopted, so that swinging of the level block and the thrust pad is more flexible, and the self-balancing effect is better.

The application discloses a kind of intelligent water power fertilization equipment, it is related to agricultural machinery technical field, the end of the connecting pipe away from pipe component is fixedly connected with fertilizer liquid barrel, the side of the connecting pipe is fixedly connected with flowmeter, the side of the pipe component is fixedly connected with water inlet component, the side of the water inlet component is fixedly connected with first electric valve, the present application is provided with turbine mechanism, when water flow impacts turbine blade, so that turbine blade rotates on bracket, so that the water of mixed fertilizer in main pipe is fully mixed, when turbine blade rotates, by the action of centrifugal force, so that cleaning plate rotates on sliding rod by sliding block, so that when turbine blade rotates, the side of turbine blade can be cleaned by scraper, and after the side of turbine blade is cleaned by scraper, the side of cleaned turbine blade can be cleaned and wiped by cleaning roller.

The invention relates to the technical field of bearings, and provides a radial tilting pad bearing and turbomachinery. The radial tilting-pad bearing comprises a bearing body and a tilting-pad bearing body, the multiple pads are arranged on the inner wall of the bearing body at intervals in the circumferential direction of the bearing body, the multiple pads comprise the first bearing pads and the second bearing pads, the number of the second bearing pads is at least two, and the first bearing pads are the main bearing pads and are used for bearing main loads; the first oil supply plate is arranged on the side face of the first bearing pad and used for supplying oil to the first bearing pad; each second oil supply plate is arranged between every two adjacent second bearing pads, and the second oil supply plates are used for supplying oil to the second bearing pads; wherein under the condition that the oil pressure reaches a preset triggering pressure value, the oil supply amount of the first oil supply plate to the first bearing tile is correspondingly increased. The first bearing pad is emphatically supplied with oil, and the second bearing pad is supplied with oil as required, so that the bearing capacity is guaranteed, and the invalid lubrication loss is reduced.

The present disclosure relates to a hydrogen leakage recovery system (1), the system (1) comprising: at least one turbomachinery unit (11); and a recovery unit (12) fluidically coupled with said at least one turbomachinery unit (11), the recovery unit (12) comprising: a separator (121) configured to receive a mixture of hydrogen and other compounds leaked from the turbomachinery unit (11), and to separate the hydrogen from the other compounds so as to obtain a hydrogen stream, and a compressor (123) fluidically coupled with the separator (121), the compressor (123) being configured to receive the hydrogen stream from the separator (121) and to compress the hydrogen stream so as to obtain a compressed hydrogen stream.

Each turbomachine (1, 100) comprises an output shaft (3, 103), an input shaft (5, 105), and a reduction gear, one (104) of which is an epicyclic gear and the other (4) a planetary gear. Each reduction gear has a sun gear (15, 115), a ring gear (13, 113), a planet carrier (16, 116), bearings (22, 122) mounted on said planet carrier, and two-stage planets (14, 114) rotatably mounted on said bearings, with their first stage (18, 118) meshing with the sun gear and their second stage (19, 119) meshing with the ring gear. The planet carriers (16, 116) are identical. (See Figure 2 for abbreviations.)

The invention discloses a turbine blade flutter evaluation method adopting a single-channel harmonic balance model. The method comprises the following steps: 1, carrying out structural grid division on a turbine blade to obtain a vibration mode, a vibration frequency and a vibration pitch diameter of a vibration blade; 2, performing fluid grid division on the turbine blade to obtain grid coordinates under a cylindrical coordinate system; 3, aligning the coordinates of the structural grid and the fluid grid to obtain a vibration mode of the fluid grid; 4, adopting a Doppler frequency shift effect to obtain blade vibration frequencies, vibration pitch diameters and inter-blade phase angles of other blade rows except the blade row where the vibration blades are located; 5, realizing mutual transmission of upstream information and downstream information of the rotor-stator interface; 6, single-channel unsteady harmonic balance analysis is achieved; and step 7, evaluating the stability of the turbine blade flutter system. According to the method, the flutter of the multiple rows of turbine blades is evaluated, and the method has the characteristics of low calculation cost and high evaluation accuracy.

The invention relates to a turbomachine component such as a blade, comprising a wall having at least one cooling orifice (26) and a metering portion (32) and a flared diffusion portion (33). According to the invention, the diffusion portion (33) comprises a central edge (40) forming a bottom of the diffusion portion (33) oblique to a flow axis (A2) of the cooling orifice (26). Figure for the abstract: Fig. 4

Graphene-based sliding varnish and its use in turbomachinery manufacturing. The present invention relates to a sliding varnish formulation comprising a water-based carrier suspension, an inorganic binder, and graphene. This varnish formulation is used to protect turbomachine parts from contact wear in assemblies, particularly in the blades of the hot section of a reactor. Figure for the abstract: Fig. 3

The present invention provides a blade, a processing system, a processing method, a turbine blade, and a turbomachinery. The blade (BL) is a blade used in fluid and includes: a substrate (BM) and a coating layer (TBC) formed on the substrate. On the surface of the coating layer, a plurality of first grooves (9) and a plurality of second grooves (7) are formed, and the spacing (P9) of the plurality of first grooves is different from the spacing (P7) of the plurality of second grooves.

A supersonic diffuser for use in turbomachinery adapted to impart thermal energy to a process fluid is provided. The diffuser includes a vaned zone configured to define a passageway having a flow area to pass a flow of a process fluid at supersonic velocity. The vaned zone is configured to define a step-change to the flow area of the passageway at a given location, such as where the flow of the process fluid exits the vaned zone. The diffuser further includes a shock zone coupled to the vaned zone to pass the flow of the process fluid that exits the vaned zone. The shock zone is configured to support a system of shock waves that increases static temperature of the process fluid downstream of the system of shock waves. A mixing and subsonic diffusion is configured to decelerate process fluid from the shock zone to a reduced subsonic speed prior to discharge of the process fluid through an exit of the diffuser.

This application provides a blade manufacturing method, apparatus, electronic device, and storage medium, relating to the field of reverse engineering technology for turbomachinery. The method includes: acquiring multi-point cloud data of multiple blades of the same specification and marking the multi-point cloud data; interpolating, filtering, and fusing the marked multi-point cloud data to obtain blade fused point cloud data; establishing a reverse design model for multiple blades based on the blade fused point cloud data; determining the deviation between the blade output data of the reverse design model and the blade fused point cloud data; and manufacturing multiple blades using the blade output data when the deviation is within a preset deviation range. This application, by constructing multi-point cloud fused data for blades, completes the reverse design of blades and the verification and comparison with the multi-point cloud data of blades, reducing the impact of initial blade manufacturing errors on reverse design and improving the efficiency and accuracy of blade reverse design.

The invention discloses a novel turbomachinery vector sealing structure. A vector sealing cavity is formed between a stator shell containing sealing teeth and a rotor. The vector sealing cavity is of a spray pipe type structure in mirror symmetry, and the spray pipe type structure comprises multiple stages of sealing cavities which are sequentially connected end to end and are provided with double throat parts; the sealing cavity is sequentially divided into an expansion section and a contraction section in the airflow flowing direction, and a tooth tip jet flow bypass is arranged between the contraction section and the throat part adjacent to the downstream of the contraction section; the sealing cavity is designed to be of a thrust vectoring nozzle structure with a bypass channel, by means of the tooth cavity pressure difference generated by the throttling effect, bypass jet flow is spontaneously driven to be mixed with main leakage flow, a leakage path is guided to directionally deflect in the circumferential direction and the radial direction, multi-dimensional reconstruction of a sealing flow field is achieved, and the dual purposes of reducing leakage and restraining fluid excitation are achieved. And a new method is provided for reducing sealing leakage and improving the excitation suppression performance of sealing fluid.

The invention provides a bidirectional self-locking speed governor for an elevator. The bidirectional self-locking speed governor comprises a box body, a centrifugal clutch mechanism and a worm and turbine transmission mechanism, wherein the centrifugal clutch mechanism and the worm and turbine transmission mechanism are arranged in the box body; the toothed guide rail is meshed with a driving gear in the centrifugal clutch mechanism, so that the synchronous movement of the bidirectional self-locking speed limiter for the elevator and the elevator car is realized; the standby and starting work of the two-way self-locking speed limiter for the elevator is achieved through separation and combination of the centrifugal clutch mechanism. When the elevator stalls, the centrifugal part is thrown out of the limiting ejector block clamping the driven shell under the action of centrifugal force, the worm and turbine transmission mechanism connected with the driven shell is driven, and meanwhile the worm and turbine transmission mechanism is driven to achieve work of the elevator two-way self-locking speed limiter. The worm and turbine mechanism can be automatically locked in the working process; after working, the bidirectional self-locking speed limiter for the elevator can be reset by prying a driven shell of a centrifugal clutch mechanism through a turning gear or a tool; the accessory guide rail, the brake rod assembly, the bidirectional safety tongs and the rolling guide shoe are connected, and the accessory guide rail, the brake rod assembly, the bidirectional safety tongs and the rolling guide shoe and external components form a complete elevator system; when the elevator is lifted or falls and stalls, the bidirectional self-locking speed limiter for the elevator automatically drives the brake rod assembly, and the brake rod assembly jacks up the brake shoes in the bidirectional safety tongs to clamp the guide rails to achieve the braking effect.

The application provides a method for determining the structural temperature field and thermal deformation of a compressor rotating disc cavity, which can be applied to the technical field of heat analysis of turbomachinery. The method comprises the following steps: obtaining the geometric parameters, operating parameters and working substance property parameters of the gas in the disc cavity; based on the balance between the buoyancy effect and the viscous effect driven by the centrifugal force, the average heat flux density of the outer ring cover of the disc cavity is obtained according to the outer ring cover radius, the axial gap of the disc cavity, the rotating disc speed, the outer ring cover temperature, the rotating core zone temperature, the Prandtl number, the density, the dynamic viscosity and the thermal conductivity; based on the heat conduction analogy relationship of the laminar Ekman boundary layer, the local heat flux density of the rotating disc is obtained according to the rotating disc speed, the kinematic viscosity, the thermal conductivity and the difference between the rotating disc temperature and the rotating core zone temperature; and the structural temperature field distribution and the thermal deformation of the rotating disc cavity are obtained according to the average heat flux density of the outer ring cover of the disc cavity and the local heat flux density of the rotating disc.

A method for processing a turbomachinery component, includes a processing installation including a mounting device, an impact device with an impact unit and a manipulating unit. The impact unit includes an impact tool, and the impact unit is attached to the manipulating unit. The turbomachinery component is mounted on the mounting device, and the manipulating unit and the mounting device are arranged in a predetermined position relative to each other. The processing installation is automatically controlled by a control device to exert an impact with the impact tool on the turbomachinery component.

The invention relates to a turbine distributor sector (40) for an aircraft turbomachine, comprising a first platform (44a), a plurality of blades (42) projecting from the first platform in a first direction (S1) of a radial direction (R) of this sector, as well as a first end member (50a) projecting from the first platform (44a) in a second direction (S2) of the radial direction, opposite the first direction (S1), the first end member (50a) extending along a circumferential direction (C) of the sector. According to the invention, the sector comprises at least one first mechanical unloading notch (66a) made through the first end member (50a), each first notch (66a) having a radial notch bottom (68a), as well as a radial notch opening (70a) spaced from the radial notch bottom (68a) in the second direction (S2). Figure for abstract: Fig. 3

The utility model relates to the technical field of hydroelectric generation, and particularly discloses a pipeline type low-water-head hydroelectric generation turbine system which comprises a guide pipe installed in a pipeline, and a pipeline turbine chamber is formed in the guide pipe. The power generation mechanism is mounted in the pipeline turbine chamber, and the turbine mechanism comprises a spherical turbine and a rotating main shaft; the speed increasing device is used for being connected with a generator or generating electricity to increase the rotating speed of the turbine so as to be matched with the generator; the generator or the speed increasing device is in transmission connection with the transmission part of the rotating main shaft; the guide pipe is installed in an existing water supply pipeline, and then a transmission part in the turbine mechanism is connected with a generator or a speed increasing device. When water in the pipeline turbine chamber flows, the spherical turbine can be driven to rotate around the rotating main shaft vertical to the incoming flow direction under the effect of incoming flow, and therefore pressure potential energy of an incoming flow medium is converted into rotating kinetic energy of a generator rotor through the turbine mechanism to generate electricity.

The invention discloses an expansion machine impeller life prediction method based on a variable fidelity agent model, and belongs to the field of turbomachinery life analysis. The method comprises the following steps: establishing a three-dimensional model of a fluid domain and a solid domain according to structural characteristic parameters of a target turbo expander, and after grid division and boundary condition configuration, acquiring flow field data through steady-state simulation of the fluid domain and verifying the accuracy. The maximum stress amplitude is extracted by combining bidirectional heat-fluid-solid coupling transient simulation, and an improved load spectrum is constructed; sampling design is carried out on impeller shape parameters and operation condition parameters, sample point sets are divided according to the high-precision and low-precision simulation time consumption ratio, high-precision and low-precision life data are generated through two-way coupling simulation and steady-state flow one-way coupling simulation, and a data set with a fidelity label is formed. And training the proxy model by using a variable fidelity machine learning algorithm to realize life prediction. According to the method, the calculation cost is remarkably reduced through a high-low precision simulation hybrid strategy, and an efficient solution is provided for impeller service life evaluation and optimization design.

The invention relates to the technical field of turbomachinery rotor blades, and discloses a composite serial rotor blade and a design method.The rotor blade is sequentially provided with a blade tip blade, a serial blade and a blade root blade in the blade height direction, and the blade tip blade is provided with a blade tip front blade surface and a blade tip rear blade surface; a blade root front blade surface and a blade root rear blade surface are arranged on the blade root blade; the serial blades comprise a first serial blade and a second serial blade, the first serial blade is provided with a first serial front blade surface and a first serial rear blade surface, and the second serial blade is provided with a second serial front blade surface and a second serial rear blade surface; the first tandem rear blade surface and the blade tip rear blade surface are arranged in an overlapped mode, the second tandem front blade surface and the blade tip front blade surface are arranged in an overlapped mode, a slit is formed between the first tandem front blade surface and the second tandem rear blade surface and used for allowing airflow to pass through, and the problems of airflow separation, large pressure loss, low aerodynamic efficiency and the like of an existing rotor blade under high-speed airflow are solved.

The present invention discloses a hybrid modal analysis method for unsteady flow feature extraction of turbomachinery, which mainly includes the following steps: constructing a spatio-temporal matrix according to the unsteady three-dimensional velocity field; performing proper orthogonal decomposition on the spatio-temporal matrix, sorting the modes according to the modal energy magnitude and obtaining the modal dominant frequency; using the sparse enhanced dynamic modal decomposition method to obtain the sparse enhanced dynamic modal combination and calculating the modal frequency; obtaining the optimal dynamic modal combination sorting according to the proper orthogonal modal dominant frequency sorting. The present invention corrects the sorting of the sparse enhanced dynamic modes through the energy and dominant frequency information of the proper orthogonal modes of the unsteady flow of the turbomachinery, realizes the extraction of the main single-frequency dynamic modal information with good dynamic stability based on the energy scale, effectively overcomes the deficiencies of the traditional proper orthogonal decomposition method and dynamic modal decomposition method when applied to the unsteady flow of the turbomachinery, and provides a technical method for the accurate extraction of the complex unsteady flow features of the turbomachinery.

Impact insert (80) for a turbomachinery component, the impact insert (80) comprising: - a double-walled section (1, 2) having an inner wall (81) and an outer wall (82) defining an inner channel (501) formed on an inner surface (81a) of the inner wall (81), an outer channel (503) formed on an outer surface (82b) of the outer wall (82), and a central channel (502) formed between the inner surface (82a) of the outer wall (82) and the outer surface (81b) of the inner wall (81); and - a plurality of impact cooling holes (85) formed in the outer wall (82) and configured to eject impact jets (86) into the outer channel (503), wherein the impact jets (86) are formed from the cooling air (5) of the central channel (502); characterized in that the impact insert (80) further - at least one suction line (9) extending between the outer wall (82) and the inner wall (81) over the central channel (502) and comprising an inlet (9a) on the outer channel (503) and an outlet (9b) on the inner channel (501) for sucking cooling air (5) from the outer channel (503) into the inner channel (501), and wherein the suction line (9) is aerodynamically shaped with respect to a flow of the cooling air (5) flowing through the central channel (502).