Abstract: A fastening tool. In the fastening tool, a top part guiding matching portion engages a top part guiding portion in a sliding fit; a pressing part guiding matching portion engages a pressing part guiding portion in a sliding fit; a lever hinged to a base part; a transmission part engages a transmission part guiding slot in a sliding fit; the transmission part is driven to slide by the pressing part, and the lever is driven to rotate by the transmission part, then the top part is driven to slide out, due to a reaction force acting on the pressing part by the transmission part and the friction between the pressing part and the base part, the pressing part remains to be self-locked by friction, which can constrain the pressing part and the top part is locked.

Abstract: The present disclosure provides a method of manufacturing a bonding structural test block with defects. The method of manufacturing the bonding structural test block with defects includes: providing a first plate and a second plate; applying an adhesive on an upper surface of the first plate to form an adhesive layer; heating and curing at least partial region of the adhesive layer for the first time; placing the second plate on the adhesive layer; and heating and curing the adhesive layer for the second time to form a boding structural test block. According to the present disclosure, the at least partial region of the adhesive layer is heated and cured for the first time and chemical reaction occurs, so that the at least partial region forms a defect, and controllable manufacturing of the defect is realized. The test block with the defect is subjected to mechanical detection to simulate the actual defective product.

Abstract: A method for repairing an ultra-thin structure by additive manufacturing by removing a damaged region of an ultra-thin structure by machining; acquiring a three-dimensional model of a region to be repaired; processing the three-dimensional model; constructing a powder carrying device on the periphery of the bottom of the region to be repaired, and allowing powder in the powder carrying device to be filled until flush with or tangent to the surface of the bottom of the region; melting, sintering or curing the powder around the outer contour of the ultra-thin structure by a high-energy beam or an auxiliary heating device, and combining the powder with the outer contour of the ultra-thin structure to form an outer contour thickened structure so as to form a flexible fixture; and repairing the region to be repaired by additive manufacturing technology according to a planned path obtained from the model processing.

Abstract: A method includes simplifying flowing of airflow at root of a rotor blade into flowing of free jet, and determining an airflow expansion angle according to Mach number of incoming flow at root of a stator vane; calculating a radial height difference between a first end point on a leading edge of a stator platform and a trailing edge of an adjacent rotor platform by using an axial distance thereof, the angle and a deviation coefficient; determining position of the first end point with radial height difference; determining intersection point of the leading edge and the stator platform as position of a second end point on the leading edge; and determining a profile line between the points by bridging spline curves, so that the tail end thereof is tangent to the intersection line, and the starting end thereof is kept on same plane as side wall of the leading edge.

Abstract: A rotor blade tip clearance control method and a rotor blade manufactured using same. The control method includes: coinciding, along an axial direction of an aircraft engine, center of gravity of a rotor blade with center of gravity of a rotor wheel disk supporting the rotor blade; rotating the rotor wheel disk to measure a leading edge deformation amount of the rotor blade; measuring a trailing edge deformation amount of the rotor blade; comparing the deformation amounts; and adjusting the center of gravity of the rotor wheel disk until the leading edge deformation amount tends to be approximately equal to the trailing edge deformation amount. The method can effectively improve or even solve the problem of inconsistent radial displacements of a leading edge and a trailing edge during the operation.

Abstract: An adjustable stator blade position maintaining structure for an aero-engine compressor, which keeps an adjustable stator blade at a preset position when a compressor works.

Abstract: An installation tool and installation method for fixing pins. In the mounting tool a cavity is provided in a tube body for accommodating a plurality of fixing pins. A first sliding groove and a second sliding groove are provided opposite each other and connected to the cavity. A first opening and a second opening are provided in two ends of the tube body. A pressing pin passes through the sliding grooves and is movably arranged on the tube body. The driving nut is adapted to driving the pressing pin to move towards the second opening.

Abstract: A fastening tool. In the fastening tool, a top part guiding matching portion engages a top part guiding portion in a sliding fit; a pressing part guiding matching portion engages a pressing part guiding portion in a sliding fit; a lever hinged to a base part; a transmission part engages a transmission part guiding slot in a sliding fit; the transmission part is driven to slide by the pressing part, and the lever is driven to rotate by the transmission part, then the top part is driven to slide out, due to a reaction force acting on the pressing part by the transmission part and the friction between the pressing part and the base part, the pressing part remains to be self-locked by friction, which can constrain the pressing part and the top part is locked.

Abstract: A forming method and a forming part with a cantilever structure. The forming method includes: obtaining a model of the part to be formed, adding an inclined supporting portion to the cantilever structure, performing layer separating and slicing process on the model, performing scanning path planning on each forming layer. A suspended area and a non-suspended area are provided in a plurality of forming layers forming the inclined surface, frame scanning path includes a first path and a second path, the first path corresponds to the non-suspended area and the second path corresponds to the suspended area. Based on the size of the angle of inclination, setting process parameters for preparation for the first path and the second path, and printing layer by layer based on the set process parameters for preparation.

Abstract: The present disclosure relates to a control method for winding deformation of fiber fabric and a forming mould thereof. The control method comprises step S1: lifting a plurality of positioning pins arranged on a surface of a forming mould according to a design position of a fiber fabric that is wound on the forming mould; step S2: winding the fiber fabric on the forming mould, and making a plurality of intersections of warp tracer yarn and weft tracer yarn, arranged on the fiber fabric, correspondingly cover on the positioning pins; step S3: retracting the lifted positioning pins; step S4: wrapping the fiber fabric with a fixing mould, and injecting resin after vacuumizing. The present disclosure provides a control method for winding deformation of fiber fabric and a forming mould thereof, ensuring that fiber deformations on the fiber fabric in the winding process meet the design requirements.

Abstract: A forming powder for a forming part with a low tensile anisotropy by additive manufacturing, which can be used for forming the forming part with low tensile anisotropy, a method for forming a forming part with a low tensile anisotropy, and a forming part with a low tensile anisotropy. The forming powder for the forming part with low tensile anisotropy by additive manufacturing includes the following chemical components in terms of mass percentage (wt-%): 0.03%?C?0.09%, 20.50%?Cr?23.00%, 0.50%?Co?2.50%, 8.00%?Mo?10.00%, 0.20%?W?1.00%, 17.00%?Fe?20.00%, 0%<B<0.001%, 0%?Mn?1.00%, 0%?Si?0.15%, 0%?O?0.02%, 0%?N?0.015%, the rest are Ni and inevitable impurities.

Abstract: A forming powder for a forming part with a low high-temperature durability anisotropy by additive manufacturing, which can be used for forming the forming part with low high-temperature durability anisotropy, a method for forming a forming part with a low high-temperature durability anisotropy, and a forming part with a low high-temperature durability anisotropy. The forming powder is composed of the following chemical components in terms of mass percentage (wt-%): 0.03%?C?0.09%, 20.50%?Cr?23.00%, 0.50%?Co?2.50%, 8.00%?Mo?10.00%, 0.20%?W?1.00%, 17.00%?Fe?20.00%, 0%?B?0.002%, 0%?Mn?1.00%, 0.0375%?Si?0.15%, 0%?O?0.02%, 0%?N?0.015%, the rest are Ni and inevitable impurities; wherein 0.2?C/Si?1.0.

Abstract: In order to alleviate a mismatch problem of thermal deformation, in all directions, of a connecting and installing structure between a CMC turbine outer annular component and a metal intermediate casing, a connector and an anti thermal mismatch connecting device are provided. The rod part of the connector comprises a subtractive hollow section and a cylindrical section. The subtractive hollow section is composed of a central shaft, a plurality of supporting rib plates extending outwards from a peripheral surface of the central shaft and inclined radially relative to the central shaft, and a plurality of outer annular plates arranged around the central shaft, with a circumferential gap between adjacent outer annular plates. The supporting rib plate is connected with the central shaft and the outer annular plate, and the central shaft is connected with the cylindrical section. The anti thermal mismatch connecting device the connector.

Abstract: A non-destructive testing method for lack-of-fusion (LOF) defects, and a testing standard part and a manufacturing method thereof, used for the non-destructive testing of LOF defects of an additive manufacturing workpiece. The manufacturing method of the LOF defect standard part comprises: step A, setting a LOF defect area of the standard part, in the LOF defect area, a proportion of the LOF defects in the LOF defect area is set as a first proportion value; step B, selecting an additive manufacturing forming process for manufacturing the LOF defect area to obtain a first process parameter of the additive manufacturing forming process corresponding to the first proportion value; step C, performing the additive manufacturing forming process based on the first process parameter to form the LOF defect area.

Abstract: A non-destructive testing method for crack defects, and a testing standard part and a manufacturing method thereof, used for the non-destructive testing of crack defects of an additive manufacturing workpiece. The manufacturing method of the crack defect standard part comprises: step A, setting a crack defect area of the standard part, in the crack defect area, the proportion of the crack defects in the crack defect area is set as a first proportion value; step B, selecting an additive manufacturing forming process for manufacturing the crack defect area to obtain a first process parameter of the additive manufacturing forming process corresponding to the first proportion value; and step C, performing the additive manufacturing forming process based on the first process parameter to form the crack defect area. The non-destructive testing method for crack defects of the present invention has the advantages of accurate and reliable testing results.

Abstract: A method for prefabricating a poor fusion defect by controlling a LMD process, including: obtaining a model, with a shaping zone and a defect prefabricated zone that has a preset defect; and performing a layerwise slicing process on the model. For each deposition layer of the defect prefabricated zone, the preset defect has a maximum dimension a0 in a perpendicular direction; for the shaping zone, performing a shaping process under predetermined shaping process parameters of the LMD process; and for the defect prefabricated zone, controlling shaping process parameters as follows: when a0<D, with respect to the shaping zone, changing a scan pitch between shaping paths and a powder feed rate in the deposition layer, thereby prefabricating the poor fusion defect; and when a0?D, with respect to the shaping zone.

Abstract: A method for preparing the prefabricated crack defects includes defining a defect area, defining a volume percentage of the crack defects in the defect area, adjusting the proportion of spherical powder, the proportion of hollow powder and process parameters of defect preparation according to the volume percentage of the crack defects, based on the technique of laser melting deposition, printing the defect area layer by layer by using the defect preparation powder and the process parameters of defect preparation, wherein the particle size of the defect preparation powder is between 45 ?m and 150 ?m, the proportion of spherical powder?93% and the proportion of hollow powder<0.5%, the process parameters of defect preparation including: laser power of 450W-550W, scanning rate of 600 mm/min-1200 mm/min, powder feeding rate of 4 g/min-12 g/min, spot diameter of 1 mm-1.2 mm, scanning spacing of 0.5 mm-0.8 mm and layer thickness of 0.08 mm-0.2 mm.

Abstract: A method for preparing prefabricated gas pore defects includes: defining a defect area, defining a volume percentage of the gas pore defects in the defect area, adjusting the proportion of satellite powder, the proportion of hollow powder and the process parameters of defect preparation according to the volume percentage of the gas pore defects, based on the technique of laser melting deposition, printing the defect area layer by layer by using the defect preparation powder and the process parameters of defect preparation, wherein the particle size of the defect preparation powder is between 45 ?m and 106 ?m, the proportion of satellite powder is 55-65% and the proportion of hollow powder is 2.9-3.1%, the process parameters of defect preparation comprises: laser power of 600W-1000W, scanning rate of 400 mm/min-800 mm/min, powder feeding rate of 12 g/min-20 g/min, spot diameter of 1 mm-2 mm, scanning spacing of 0.5 mm-1 mm and layer thickness of 0.15 mm-0.2 mm.

Abstract: A method for prefabricating pore defects by controlling a SLM process, including performing laser scanning on a specified metal melt layer (LY) according to a first scan path (P1) and a second scan path. The first scan path (P1) and the second scan path (P2) have a path overlap zone (A0), the path overlap zone (A0) has a predetermined width, and laser energy input superimposed in the path overlap zone (A0) is controlled to reach a predetermined energy value, whereby keyholes are formed at a plurality of positions in a lengthwise direction of the path overlap zone (A0), the specified metal melt layer (LY) is taken as a defect layer, and the keyholes in the path overlap zone (A0) is taken as pore defects.

Abstract: The present application relates to the field of superalloy, disclosing a method for internal stress regulation in superalloy disk forgings by pre-spinning. The method includes: Step S1, determining a target revolution for regulating internal stress in the disk forgings, and determining a target deformation magnitude of plastic deformation required for regulating the internal stress by the pre-spinning of the disk forgings; and Step S2, performing the pre-spinning of the disk forgings by the target revolution, monitoring a deformation magnitude of the disk forgings, and stopping the pre-spinning when a monitored deformation magnitude of the disk forgings reaches the target deformation magnitude.