18 results about "Variable geometry turbine" patented technology

The invention discloses a coupling end area loss control and flow regulation variable geometry turbine structure and application thereof.Each turbine guide vane is composed of a vane body part and an adjustable flap, each vane body part comprises a root fixing section, a front edge stand column section and a tip fixing section, and the two fixing sections are fixedly arranged on the inner end wall and the outer end wall respectively; the front edge stand column section is arranged between the two fixing sections. The adjustable flap is arranged between the two fixed sections, the upper end and the lower end of the adjustable flap are supported between the two fixed sections in a controlled and rotatable mode, the front edge of the flap and the concave arc-shaped transition curve of the stand column section are conformal, and a continuous and smooth pneumatic molded surface is formed in a butt joint area. A split interface fixed winged knife structure is used to perform pneumatic partition of potential leakage paths. According to the invention, while the adjustable control of the mass flow of the turbine inlet is realized through the adjustable flap, the secondary flow and leakage loss of the end region can be effectively inhibited by setting the end region fixed geometry and winged knife leakage isolation functions, and the device is suitable for a multi-working-condition aero-engine.

The invention provides a design optimization method suitable for a variable geometry turbine with more than 100 variables, which comprises the following steps: acquiring control parameters of a three-dimensional blade model of a variable geometry turbine part, and establishing a design space; the method comprises the following steps: selecting a set number of uniformly distributed design samples in a design space as an initial population, and sequentially performing differential operation, interlace operation guided by an RBF proxy model and selection operation based on a parent target evaluation value on the samples in the population to generate a plurality of child samples; a local search strategy based on an RBF proxy model is used for an optimal sample in the population, and a child sample is generated; combining all generated filial generation samples, performing performance evaluation, and updating the current population; the number of iterations is set for each optimization, and knowledge migration from a low-fidelity population to a high-fidelity population is realized by adopting a knowledge migration strategy based on a probability distribution model; and performing updating iteration on the high-fidelity population until the number of high-fidelity sample evaluation times reaches a set upper limit.

The application discloses a variable geometry turbine guide vane assembly coupled with a non-axisymmetric end wall structure and a molding method. The variable geometry turbine guide vane assembly comprises a hub, a casing, a plurality of rotating shafts and a plurality of guide vanes. The hub and the casing jointly enclose an annular flow channel. The rotating shafts are equidistantly arranged in the annular flow channel in the circumferential direction and extend along the radial direction of the annular flow channel. The guide vanes are rotatably arranged on the rotating shafts. There are gaps between the upper ends of the guide vanes and the casing and between the lower ends of the guide vanes and the hub. The area on the outer side of the hub opposite to the guide vanes and / or the area on the inner side of the casing opposite to the guide vanes is provided with a continuous concave-convex structure. The maximum convex height of the concave-convex structure is lower than the height of the gap, and the maximum concave height is lower than the wall thickness of the component. The reduction of the surface pressure difference on both sides of the guide vanes can reduce the leakage flow loss at the upper and lower end walls of the guide vanes, reduce the passage vortex intensity, reduce the secondary flow loss of the flow channel and improve the efficiency of the variable geometry turbine.

A high-stability variable geometric section turbine assembly for an engine exhaust gas turbocharger comprises a rotating blade set, an adjusting ring, a VGT body, a deflector rod and an electric push rod, one end of the deflector rod is hinged to the output end of the electric push rod, the other end of the deflector rod is hinged to an adjusting hole in the inner side of the adjusting ring, and the adjusting ring is installed in cooperation with a limiting groove in the VGT body through a limiting boss. A ring hole in the outer side of the adjusting ring and the rotating blade set are installed in a clearance mode, in the engine starting or low-power operation stage, the electric push rod drives the rotating blade set to rotate through the driving lever and a transmission mechanism of the adjusting ring, the through-flow area between blades is reduced, and the air inlet density is increased. In the normal operation stage of the engine, the through-flow area between the blades is increased, the engine power is improved, and therefore the output characteristic of the engine in the full-power stage is improved. The reliability of the VGT assembly under the high-temperature and high-pressure conditions is improved, and the VGT assembly has the advantages of being simple in structure, relatively isolated from the external environment, capable of achieving reverse locking, accurate in adjustment and the like.

The present disclosure provides a flexible variable geometry turbine blade and a variable geometry turbine for reducing end region aerodynamic loss, and relates to the technical field of variable geometry turbine blades for aeroengines and gas turbines. The flexible variable geometry turbine blade is installed between a casing and a hub of a turbine, and comprises an upper blade part, a lower blade part and a flexible component. An upper end of the upper blade part is rotatably installed on the casing; the lower blade part is oppositely arranged with the upper blade part along a blade height direction, and a lower end of the lower blade part is rotatably installed on the hub; and the flexible component is connected between the upper blade part and the lower blade part in a deformable manner along the blade height direction, and is suitable for absorbing a thermal deformation difference between the casing and the hub.

A variable geometry turbine device includes: a turbine casing provided with an inlet duct, and defining an exhaust port and a bypass chamber therein; a gear rotating sleeve disposed inside the bypass chamber; a rack actuator; combined nozzle guide vanes including: a fixed nozzle and an elastic nozzle mechanism; and a turbine. A first annular chamber and a second annular chamber are defined between the exhaust port and the bypass chamber. A first radial channel and a second radial channel are defined under the bypass chamber, and are connected to the first annular chamber and the second annular chamber respectively. A side of the gear rotating sleeve defines a first notch and a second notch configured to be selectively connected to the first radial channel and the second radial channel respectively; and opening and closing of the first radial channel and the second radial channel have a time difference.

This invention discloses a method, apparatus, computer equipment, and computer-readable storage medium for correcting an adjustable guide vane clearance leakage loss model, relating to the field of variable geometry turbine adjustable guide vane technology. The method includes: constructing a database of multiple clearance flow fields for the blade tip / root clearance and structures containing a rotating shaft based on CFD experimental flow field data of a variable geometry turbine, obtaining independent leakage losses. A machine learning method, primarily using neural networks, is used to fit the corrected AMDCKO model, obtaining blade tip and root clearance loss models, which are then superimposed into a total clearance loss model without a rotating shaft. A rotation shaft correction coefficient KZ is introduced, and its diameter and position are used as variables to model the leakage loss at the tip of the adjustable guide vane containing the rotating shaft. Embedding this model into a one-dimensional performance prediction program can improve the accuracy and reliability of loss calculation, providing a scientific theoretical basis and technical support for the aerodynamic optimization design and parameter matching of variable geometry turbines.

Diagnostic procedures for a turbocharged internal combustion engine in a vehicle, including: Activating a monitoring device and adjusting an actuator during the operation of an internal combustion engine with a closed-loop turbocharger boost control system by a controller, and providing an indication of deterioration by the controller based on the duration of an actual deviation exceeding a threshold deviation level between an expected change in boost pressure and an actual change in boost pressure over a driving cycle without referencing a command or measurement of a variable geometry turbine (VGT) or wastegate, where the internal combustion engine is operated by the control system with a closed-loop turbocharging control under conditions other than idle conditions, which includes any of the passage of a threshold vehicle running time, reaching a threshold combustion engine temperature and maintaining a threshold intake manifold pressure.

The application belongs to the technical field of engines, and specifically discloses a variable-geometry turbine guide vane and an intelligent control method thereof. The variable-geometry turbine guide vane comprises an inner edge plate, an outer edge plate, a blade assembly and a driving assembly. The inner edge plate and the outer edge plate are annular. The outer edge plate is arranged at the circumferential outer portion of the inner edge plate. A flow-through space is formed between the outer edge plate and the inner edge plate. A plurality of blade assemblies are arranged in the flow-through space at intervals in the circumferential direction. The blade assembly comprises a fixed blade and a movable blade. The fixed blade and the movable blade are arranged in the circumferential direction and the axial direction of the flow-through space in sequence. The outer circumferential wall of the inner edge plate is provided with a first sliding groove. The inner circumferential wall of the outer edge plate is provided with a second sliding groove. The two ends of the movable blade are arranged in the first sliding groove and the second sliding groove, respectively. The driving assembly is arranged on the outer edge plate and connected with the plurality of blade assemblies, respectively. The first sliding groove and the second sliding groove are matched with a preset track. The application reduces the leakage loss on the basis of realizing accurate change of the turbine flow-through capacity, and improves the working efficiency of the turbine.

The invention belongs to the technical field of aero-engines, and particularly relates to a variable geometry turbine guide vane configuration with a segmented flow guide front edge, which comprises a fixed section for forming an outer profile of an adjusting guide vane part and a rotating section for forming an outer profile of the other part of the adjusting guide vane part, the multiple adjusting guide vanes are distributed in the circumferential direction, and the rotating section molded surface of each adjusting guide vane and the fixed section molded surface of the adjacent adjusting guide vane form a throat part where main flow gas flows. The two ends of the fixed section are fixedly connected with the upper edge plate and the lower edge plate respectively; the rotating section is sequentially provided with a driving hole and a rotating shaft hole in the airflow direction, and a rotating shaft hinged between the upper edge plate and the lower edge plate is arranged in the rotating shaft hole in a penetrating mode. A driving shaft penetrates through the driving hole and is connected with the linkage ring, the actuating cylinder drives the linkage ring to rotate, and the linkage ring drives the rotating section to rotate around the rotating shaft through the driving shaft, so that the flow area of mainstream gas at the throat part is adjusted. Airflow is prevented from penetrating through radial gaps at the two ends, and the flow loss is relatively small.

The application provides a hybrid vehicle exhaust energy recovery device and method based on a variable geometry turbine, which comprises an exhaust gas power generation and storage unit, an exhaust gas supercharging unit and a control unit. The exhaust gas power generation and storage unit comprises a first exhaust pipe, a power turbine and an electric energy system. The exhaust gas supercharging unit comprises a second exhaust pipe, a supercharging turbine and a compressor. The control unit comprises an electric quantity sensor, a PLC controller and a reversing valve. The air inlets of the first and second exhaust pipes are connected with a main exhaust pipe. The reversing valve is arranged on the main exhaust pipe and corresponds to the first and second exhaust pipes. The power turbine is connected with the electric energy system. The supercharging turbine is connected with the compressor. The input end of the PLC controller is electrically connected with the electric quantity sensor. The output end of the PLC controller is electrically connected with the reversing valve. The electric quantity sensor is connected with the electric energy system. The application improves the utilization efficiency of exhaust gas, improves the utilization efficiency of the generator as a whole, and improves the economy and environmental protection of the hybrid vehicle as a whole.

The purpose of this invention is to provide a variable geometry turbine sector blade test piece including a gear transmission mechanism for controlling the adjustable guide vane angle. The test piece includes a test section rim, a test section hub front section, a test section hub rear section, an upper half of an adjustable guide vane shaft, and a lower half of an adjustable guide vane shaft. An upper bushing is mounted on the upper half of the adjustable guide vane shaft and fitted into a mounting hole in the test section rim. A lower bushing is mounted on the lower half of the adjustable guide vane shaft. The test section hub front section and test section hub rear section are respectively fitted with slots to fix the shaft. Test blades are installed and arranged in the test section flow channel between the test section rim and the test section hub front and rear sections. This invention can achieve effective and high-precision adjustment of the test blade angle. Simulation results show that the angle error between each test blade is controlled within 0.1°, and the guide vane angle can be controlled in real time, improving the accuracy of the experiment.

The invention provides a thermal deformation self-adaptive adjustment variable geometry turbine, and relates to the technical field of variable geometry turbines for aero-engines and gas turbines.The thermal deformation self-adaptive adjustment variable geometry turbine comprises an inner flow channel casing, an outer flow channel casing and an outer casing which are coaxially arranged from inside to outside in a sleeving mode, and an inner flow channel is limited on the inner side of the inner flow channel casing; an outer flow channel is defined by an annular area between the outer flow channel casing and the outer casing; the turbine blade is arranged between the inner flow channel casing and the outer flow channel casing, the turbine blade is provided with a rotating shaft, the rotating shaft extends in the blade height direction of the turbine blade and is provided with a first end and a second end which are far away from each other, the first end is connected with the outer casing through a spherical hinge structure, and the second end is connected with the interior of the inner flow channel casing through a spherical hinge structure; therefore, the rotating shaft is allowed to generate angle deflection.

The application discloses a variable-geometry turbine parameter optimization method and system suitable for one-dimensional design, and the method comprises the following steps: determining the boundary conditions of the variable-geometry turbine, and selecting optimization variables and preset value ranges of the optimization variables based on the boundary conditions; constructing a multi-working-condition performance objective function and a constraint system based on the optimization variables and the preset value ranges; and searching and optimizing the variable-geometry turbine parameters under multiple working conditions by using a SHADE algorithm. The application optimizes the meridian flow passage radial profile, reserves space for variable-geometry adjustment, guarantees smooth airflow, improves the aerodynamic characteristics under all working conditions, slightly reduces the turbine efficiency under the reference working condition, and significantly improves the efficiency under non-design working conditions; the variable-geometry turbine can automatically match the guide vane adjustment angle according to the working conditions, and improve the efficiency and stability under all working conditions; the application greatly shortens the optimization design calculation time, improves the aerodynamic performance prediction accuracy, completes the work of the traditional method in several days in several hours, and meets the engineering rapid design requirements.

The invention discloses a variable geometry turbine adjustable guide vane pneumatic torque measuring device and method, and belongs to the technical field of blade pneumatic torque measurement, the variable geometry turbine adjustable guide vane pneumatic torque measuring device comprises an arc-shaped mounting frame, a static torque sensor, a driving positioning mechanism and a plurality of adjustable guide vanes, and the adjustable guide vanes are rotatably connected to the arc-shaped mounting frame at equal intervals in the circumferential direction; the static torque sensor is installed on the adjustable guide vane, and the drive positioning mechanism is installed on the arc-shaped installation frame. According to the invention, the pneumatic torques of different rotation angles of the adjustable guide vane can be measured, the position of the adjustable guide vane is restrained through the arc-shaped mounting rack, and the adjustable guide vane is taken as a measurement object and rotates by taking the rotation shaft of the adjustable guide vane as the center, so that the throat area and the outlet airflow angle can be adjusted, and the flow of mainstream gas can be adjusted; the static torque sensor can be used for measuring the pneumatic torque borne by the adjustable guide vane in real time; the adjustable guide vane is rotationally adjusted and fixed through the driving and positioning mechanism, and the stability of the adjustable guide vane of the turbine is guaranteed.

The invention provides a variable geometry turbine adjusting system with a thermal state self-centering supporting function and a variable geometry turbine, and relates to the technical field of aero-engines and gas turbines.The variable geometry turbine adjusting system comprises a supporting ring, a linkage ring and a plurality of maintaining structures; the supporting ring is coaxially arranged on the outer side of a static casing of the turbine. The linkage ring is rotatably arranged on the outer side of the supporting ring in a sleeving mode and suitable for being connected with and driving the multiple adjustable blades distributed in the circumferential direction of the turbine to synchronously rotate around the blade rotating shaft. The multiple maintaining structures are evenly distributed in the circumferential direction of the turbine at intervals and connected and supported between the supporting ring and the static casing correspondingly, and the maintaining structures are suitable for maintaining the supporting ring and the static casing to be coaxial under the condition that the static casing is subjected to thermal expansion deformation.

A nozzle ring 112 for a variable geometry turbine comprises: a generally annular wall; an inner flange 19; an outer flange 20; and two protrusions 30, 32. The inner flange is generally perpendicular t

The invention provides a turbine blade variable geometry flow field reconstruction and performance optimization method and system, and belongs to the field of variable working condition flow field reconstruction of variable geometry turbines. The problems that an existing neural network agent model is limited to two-dimensional blade profile analysis and is insufficient in performance when dealing with experimental data are solved. The method comprises the steps that geometric control parameters and working condition variables of the turbine bent blade are obtained and normalized, normalized data are input into a bent blade surface physical reconstruction neural network module, and a turbine bent blade surface physical field is reconstructed; reconstructing a turbine bent blade outlet key physical field according to an outlet key physical field neural network module and the reconstructed blade surface physical field; a gradient optimization module is used for calculating overall performance parameters of the reconstructed outlet key physical field, gradient information is obtained through back propagation, geometric control parameters are updated through a moving asymptotic algorithm, and performance optimization of the blade is achieved. The method is mainly used in the field of turbine blade optimization.