18 results about "Turbine blade" patented technology

A method is provided for manufacturing a wind turbine rotor blade in which the blade is formed as a laminated structure by laying a composite material of fibre reinforcement material and/or core material in a mould defining the shape of the blade; evacuating the mould after laying the composite material; introducing a liquid polymer into the evacuated mould and wetting the composite material; curing the liquid polymer after the composite material has been wetted; and removing the mould after curing the liquid. At least one lightning conductor is integrated into the composite material before wetting it with the liquid polymer. Moreover, a wind turbine rotor blade made from a single laminated structure is provided with at least one lightning conductor is integrated into the laminated structure.

The invention discloses an aero-engine turbine blade reliability evaluation method based on fracture mechanics. The method comprises the following steps: S1, establishing a simplified model of a bladesection by taking a turbine blade as a research object, calculating a stress intensity factor of the turbine blade containing an initial I-type crack at a blade root by applying a finite element method, substituting the stress intensity factor into a shape factor calculation formula, and determining a shape factor parameter; S2, establishing a turbine blade reliability model based on the generalized stress intensity interference model; and S3, establishing a probability density function of load and fracture toughness, establishing a probability life model and a reliability model for the bladein combination with a Paris formula, and solving the model to obtain the change condition of the reliability of the turbine blade along with the life. According to the method, initial defects existing in the blade are considered, on the basis of the initial defects, the crack propagation life of the I-shaped cracks on the surface of the blade under the cyclic load is established, and life prediction and reliability evaluation of the blade can be more accurate.

A turbine blade (1) with a side surface (7) having an aerodynamic profile. The turbine blade (1) further comprises an end surface (6) and is mounted in a turbine, whereby the end surface (6) is delimited by a gap from a casing (8) of the turbine. The end surface (6) comprises a recess (2) which is shaped such that it acts as an improved aerodynamic seal.

A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane.

The invention relates to a full-automatic pressing production line for a large turbine blade. The full-automatic pressing production line for the large turbine blade is characterized by comprising a gas heating furnace, a plurality of operation manipulators, a blade pre-profiling hydraulic machine, a blade shaping and trimming hydraulic machine, a workpiece flash waste material collecting device and a finished product storage device, wherein the gas heating furnace is positioned on one side of the pre-profiling hydraulic machine; the first operation manipulator is arranged on the other side of the gas heating furnace; the second operation manipulator is arranged on the other side of the pre-profiling hydraulic machine; the blade shaping and trimming hydraulic machine is arranged on the other side of the second operation manipulator; the flash waste material collecting device and the third manipulator are respectively arranged on the side which is close to the blade shaping and trimming hydraulic machine; and the finished product storage device is arranged on the other side of the blade shaping and trimming hydraulic machine. The full-automatic pressing production line has the advantages that workers do not need to operate in high-temperature and severe environments, the labor intensity is reduced, die changing operation is safe and reliable, flash waste materials can be quickly separated from one another conveniently, materials are discharged automatically, the movable worktable can be positioned accurately, and the product quality and the production efficiency can be greatly improved.

The invention discloses a wind turbine blade with an embedded diversion pipe capable of controlling tip vortex. The wind turbine blade comprises a blade tip device, an air inlet, an air outlet and a diversion pipe, wherein a plurality of air inlets are arranged at the leading edge nearby the blade tip of the blade tip device; a plurality of air outlets are arranged at the blade tip of the blade tip device; the air inlets are communicated with the air outlets by diversion pipes; and the diversion pipes are internally provided with throttling devices for controlling the air flow. The wind turbine blade provided by the invention has simple structure, is used as a blade extension segment connected to the wind turbine blade without changing the main body of the wind turbine blade, and is separately designed according to the actual situation of providing the blade wind turbine, or integrally designed by considering the device and the pneumatic structure portion of the wind turbine blade as a whole, thus maximally controlling the generation of the tip vortex, improving the pneumatic efficiency of the wind turbine and reducing the noise level.

The present invention belongs to the field of engine part technology in mechanical engineering, and is especially weight reducing new structure of turbo impeller for vehicular turbocharger. The weight reducing new structure of turbo impeller includes internal hexagonal hole concentric with turbo impeller and outside the lightening hole for the location and assembling of the rotor of the supercharger, lightening hole concentric with turbo impeller and communicated to the internal hexagonal hole, and conic hole concentric with turbo impeller for the friction welding of the shaft. The weight reducing new structure is determined through numerical analysis, structure optimization, etc. The present invention has the advantages of effectively reduced turbo impeller weight, saving in material, reduced cost, raised connection strength between turbo impeller and shaft, etc.

The invention discloses machining tooling and machining method for an ultra-large gas turbine blade. The machining tooling comprises a rotary table, and a first clamp and a second clamp fixed to the rotary table; the rotary table is provided with a through hole penetrating through two opposite ends of the rotary table and used for containing the turbine blade; the first clamp is located at the first end of the through hole, and is used for positioning and clamping an extension root of the turbine blade; and the second clamp is located at the second end of the through hole, and is used for positioning and clamping a blade body of the turbine blade. According to the machining tooling, the rotary table is arranged in a hollow form, the turbine blade is placed in the hollow through hole, and the first clamp and the second clamp are arranged at the two ends of the through hole so as to fix the extension root of the end where a tenon of the turbine blade is located and the blade body of the end where a blade crown of the turbine blade is located, thus guaranteeing that the tenon and the blade crown of the turbine blade cannot deviate when the turbine blade is machined, and further, the machining precision of the tenon and the blade crown of the turbine blade is improved, the size of the whole machining tooling is also reduced, the machining range of the machine tooling is effectively reduced, and cost is reduced.

The invention discloses a novel gas air film cooling structure for an aircraft engine and a turbine guide blade of a gas turbine. The cooling structure comprises a blade basal body, an air film gap, a connecting rib and a step surface, and is characterized in that a step-shaped gap air film flow outlet structure is formed by an inner blade and an outer blade on the blade pressure surface basal body and the connecting rib, so that cooling air flows out in the tangential direction of the blade surface. The cooling flow outlet structure of a novel blade can form a uniform and consistent cooling air film on the blade surface; the air outlet air film is higher in stability; the vortex effect of cold air flowing out is weakened; the cooling air film is large in covering area and high in cooling efficiency; and meanwhile, the cooling air in the tangential direction is mixed with a high-temperature main flow, so that the pneumatic loss of the blade is reduced, and the blade has both high cooling efficiency and high-efficiency pneumatic performance. The structure also can enable the blade to be produced by a piece connecting structure, and can simplify the blade processing and maintenance process.

The invention provides a turbine blade trailing edge cooling structure. The structure comprises a trailing edge cavity and an array formed by a plurality of expansion holes, wherein the trailing edgecavity is positioned inside the trailing edge of a turbine blade, the expansion holes penetrate through the outer surface of the trailing edge through the trailing edge cavity, the expansion holes areaxially divided into a straight section and an expansion section, the expansion section is close to the outer surface of the trailing edge, the straight section is close to the trailing edge cavity,a cross-sectional area of the expansion section is greater than that of the straight section, and cold air in the trailing edge cavity flows out of the expansion holes to form an air film covering thetrailing edge of the turbine blade. The turbine blade trailing edge cooling structure can improve the cooling effect of the turbine blade, reduce the pneumatic loss of the turbine blade and improve the structural strength of the turbine blade.

The embodiment of the invention provides a mould and method for manufacturing a wind generating set blade. The mould for manufacturing the wind generating set blade comprises an upper mould body and a lower mould body which are used for moulding the wind generating set blade, and stopping protrusions are arranged on the upper mould body and/or the lower mould body and located on the lower sides of the placed positions of girder prefabricating members of the mould bodies where the stopping protrusions are located. According to the mould and method for manufacturing the wind generating set blade, by arranging the stopping protrusions on the mould for manufacturing the wind generating set blade, the slidable moving problem of the girder prefabricating members is solved.

The magnetic field communication system for measuring the flutter of the turbine blade in accordance with an embodiment of the present disclosure includes a sensor module placed on an outer surface of the turbine blade to sense a signal on the flutter of the turbine blade; an interface converting the signal on the flutter sensed by the sensor module into a magnet field signal to transmit it to the outside of a casing surrounding the turbine blade; and an adaptor receiving the magnetic field signal to generate a power source of the system, and analyzing the magnetic field signal to determine the degree of the flutter of the turbine blade.

The invention relates to an automatic retracting wind turbine blade and a control method thereof. The wind turbine blade comprises a fixed blade and a telescopic blade, a data monitoring platform receives wind speed data and wind direction data acquired by a wind speed measuring device and transmits the data to a processor, the processor calculates the telescopic length of the blade according to the wind speed data and the wind direction data, and a blade retraction control system controls the telescopic blade to stretch or retract. The control method comprises the following steps: acquiring atraining data set; constructing and training a machine learning model; acquiring wind speed data and wind direction data in real time, and calculating blade telescopic length based on the machine learning model; and controlling the telescopic blade to stretch or retract by the blade telescopic control system Compared with the prior art, the blade telescopic length is calculated according to the wind speed data and the wind direction data based on the machine learning model, control is more accurate, the optimal blade telescopic length under the current wind speed and the current wind direction can be obtained, the blades cannot be damaged, wind energy can be captured more effectively, and the power generation efficiency is improved.

The invention relates to an offshore wind turbine pre-assembly process which comprises the following steps: step 1, placing in place: loading a wind turbine cabin and a wind turbine blade on a working platform to a target sea area; 2, a cabin is installed, a draught fan installation stand column and a crane are installed on a floating deck of the operation platform, and the draught fan cabin is fixedly installed on the draught fan installation stand column through the crane on the operation platform; and 3, blade installation is conducted, specifically, the fan blade is lifted by the crane to be installed on the fan cabin. According to the pre-assembly process for the offshore wind turbine, the construction efficiency of the wind turbine can be effectively improved on the premise that the assembly precision is guaranteed.