348 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 relates to an aircraft turbomachine subassembly comprising an annular duct (36) extending concentrically about a longitudinal axis and in which an air stream flows from upstream to downstream, the annular duct comprising a duct portion (28) defining a swan neck having an upstream inlet section and a downstream outlet section. A plurality of radial arms (B1, B2) extend circumferentially in the duct portion (28). One or several intermediate walls (P1, P2) extend between two circumferentially adjacent arms (B1, B2) which form a pair of circumferentially adjacent arms among the plurality of circumferentially adjacent arms so as to locally separate, between the two arms of the pair of arms, the annular duct portion (28) into a radially inner portion (Ci) and a radially outer portion (Ce) further away from the longitudinal axis than the radially inner portion.

A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a water separator configured to receive the compressed air from the compressor and remove moisture from the compressed air to dry the compressed air. Furthermore, the system includes a turbine configured to receive the dried air from the heat exchanger, with the dried air expanding as the dried air flows through the turbine. Moreover, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, the moisture removed from the compressed air by the water separator is routed to the defroster to melt the captured frozen particulate matter.

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 provides a flow field velocity measurement device and velocity measurement method for a rotor channel of turbomachinery, and relates to the technical field of fluid mechanics, the flow field velocity measurement device comprises a laser suitable for generating first line laser; a tracer particle flow field is formed in the cartridge receiver, and a rotatable rotor is arranged in the tracer particle flow field; the transparent window is arranged on the window of the casing; the sheet light source forming assembly is suitable for reflecting the first line laser to the interior of the cartridge receiver and forming a plurality of sheet light sources capable of moving in the radial direction of the rotor; the camera assembly is suitable for shooting tracer particles in the tracer particle flow field through the transparent window based on a plurality of sheet light sources at different radial positions to obtain multiple frames of particle images corresponding to different radial positions; and the processor is suitable for obtaining the flow field speed of the rotor channel based on the multi-frame particle image.

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.

A method for active bi-directional control of an outer structure of a gas turbine engine comprises sending, by a controller, a first control signal to a power electronics for varying an electric current supplied to a heating element to cause the outer structure to move in a first radial direction, and sending, by the controller, a second control signal to a valve assembly for varying a cooling air flow supplied to the outer structure to cause the outer structure to move in a second radial direction. The first radial direction is opposite the second radial direction.

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 birotor surface pressure measurement system and method based on double endoscopic pressure sensitive paint, and belongs to the technical field of turbomachinery pressure measurement. The method mainly comprises a double-endoscopic type optical pressure sensitive measuring system, a double-rotor phase locking system of a photoelectric sensor and an encoder and a double-endoscopic type rotor surface pressure synchronous measuring method, excitation and imaging of PSP are integrated in the same hard rod type endoscope, an optical straight rod endoscope with a 70-degree viewing angle is adopted, the visual field angle is 90 degrees, and the optical straight rod endoscope and the optical straight rod endoscope are integrated. And the endoscope rod extends into the flow field for a certain length, so that the acquisition of a global rotor blade image is realized. An endoscopic detection hole is formed, an optical endoscope is installed on the wall face of a cartridge receiver, a camera and the endoscope are fixed through a three-dimensional displacement mechanism, and the stability of an endoscopic measurement system is guaranteed. The reflective patch is attached to a rotor rotating shaft, the photoelectric sensor directly faces the reflective patch, external trigger signals of the photoelectric sensor are transmitted to the signal generator and the multi-channel data acquisition system respectively, and the signals are used for controlling light emitting of the light source and shooting of the camera on one hand and used for phase locking of the rotor on the other hand. And the encoder is arranged at one end of the motor shaft, is connected with the multi-channel data acquisition system, and is combined with the photoelectric sensor to jointly realize phase locking of the double rotors. Dark background images Id1 and Id2 and reference images Ir1 and Ir2 of the birotor are shot, and the corresponding reference pressures are Pr1 and Pr2 respectively. A phase-locked enhanced image synchronous acquisition method is adopted to obtain light-emitting images I1 and I2 of the surface of the rotor. And finally obtaining pressure distribution P1 and P2 of the surfaces of the double-rotor blades through image processing and a pressure sensitive coating calibration relational expression.

The invention discloses a multi-target and multi-component integrated optimization method and equipment for a counter-rotating axial flow fan, and belongs to the technical field of turbomachinery optimization design. According to the method, parametric modeling is carried out on multiple components such as two rows of blades, an inlet current collector and an outlet diffuser of the contra-rotating axial flow fan, geometric parameter combinations of all the components are selected as multi-dimensional decision variables, and a multi-dimensional decision space is determined; obtaining decision sample sets according to the multi-dimensional decision space, solving a plurality of aerodynamic performances of the counter-rotating fan corresponding to different decision sample sets through numerical simulation, and forming a multi-target aerodynamic sample set; combining a genetic algorithm to optimize a weight and a threshold to train a neural network agent model; performing global search and nonlinear optimization through a genetic algorithm based on a neural network agent model by taking the optimal multi-target aerodynamic performance as an optimization target, and outputting a Pareto optimal solution set; and determining a global optimal solution and carrying out numerical simulation verification to obtain an optimized geometric model of the counter-rotating fan. The pneumatic performance of the contra-rotating axial flow fan can be effectively improved.

The invention discloses a temperature-controllable open-type low-Reynolds-number intelligent wind tunnel, and relates to the field of cascade wind tunnel tests applied to the turbomachinery field. The problems that an existing low-Reynolds-number wind tunnel test bed can only conduct simulation at the normal temperature, and a heated low-Reynolds-number test cannot be conducted are solved. An air inlet device (A-11) is connected with an air inlet heater (A-14) through a main air inlet adjusting valve (A-12) and an auxiliary air inlet adjusting valve (A-13) which are arranged in parallel, air flow sucked by the air inlet device (A-11) from the atmosphere is heated by the air inlet heater (A-14), then enters a first expansion joint (A-15) and is connected with a wind tunnel body (B), and a secondary flow system (C) is connected with an experiment module (B-23) in the wind tunnel body (B). And the exhaust system (D) is connected with the exhaust side of the experiment module (B-23). The device and the method are used for aerothermal performance experiments of key components of turbomachinery and high-altitude aircraft simulation tests in a low Reynolds number environment.

A motor cooling shroud optimized for a fully reversible turbomachine where the motor cooling shroud improves the turbomachine's performance by efficiently controlling the cooling flow over a motor in both operating directions. The motor cooling shroud may be substantially cylindrical and may have a first end, an opposite second end, and a sidewall spanning between the first and second ends. The second end may define a central opening that is coaxial with a central axis of the fully reversible turbomachine. The sidewall may be configured to encircle a motor of the fully reversible turbomachine such that a motor cooling pathway is defined between the outer surface of the motor and the sidewall. At least one sidewall opening may be disposed in the sidewall proximate to the first end. A plate may be coupled to the second end such that the plate is spaced from the central opening.

The invention provides a turbomachinery geometric data fitting method and system, a storage medium and electronic equipment, and relates to the field of computer-aided engineering. The method comprises the steps that external geometric data of the turbomachinery are analyzed, geometric feature data of multiple turbomachinery sections are obtained, and the geometric feature data comprise hub casing line data, blade uniform section line data and blade top gap data; on the basis of the hub casing line data, the blade uniform section line data and the blade top clearance data, fitting is conducted on each impeller mechanical section, and an initial fitting result is generated; and in response to an adjustment operation on the initial fitting result on the fitting interaction interface, updating the initial fitting result, and displaying the updated target fitting result on the fitting interaction interface. According to the invention, accurate analysis and interactive fitting of external geometric data of the turbomachinery can be realized, and the multi-section data processing efficiency and accuracy are improved.

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.