13 results about "Composite blade" patented technology

The present application relates to a kind of composite material blade tenon sampling piece tensile test fixture and test method.The tensile test fixture is used to clamp the two ends of tenon sampling piece and carry out tensile test, specifically includes ear piece adapter, mortise simulation piece, pin, a pair of clamping plate and several clamping plate bolts.The upper end of ear piece adapter is connected with the upper clamp of testing machine, and the lower end of mortise simulation piece is connected with the lower clamp of testing machine.The lower end of ear piece adapter is connected with the upper end of two clamping plates by pin penetration, and pin shaft connection pair is formed.Two clamping plates are oppositely arranged and clamp tenon sampling piece by clamping plate bolt in array compression mode.The inner side of clamping plate and tenon sampling piece contact is provided with tooth groove structure, and the inner cavity profile of mortise simulation piece is adapted to the shape of the outer surface of tenus sampling piece.Compared with prior art, the present application is suitable for static strength test under 0~250 kN large load range, and significantly improves the stability and success rate of composite material special-shaped sampling piece test.

The application discloses a method for integrally injection-molding a metal small shaft and a composite small blade, extending an easy-to-break tail section of the same material from a non-injection-molding end of the metal small shaft, processing a notch and a plane on the surface of the injection-molding end of the metal small shaft, placing a tooling on the outside of a mold cavity of an injection-molding mold and corresponding to the position of the metal small shaft, adjusting the clamping position of the metal small shaft on the tooling, starting injection molding, keeping the tooling clamping the tail section of the metal small shaft during the injection molding, and removing the tail section after the injection molding. The method accurately integrally injection-molds one end of the metal small shaft and an end of the composite small blade, ensures that the length direction of the metal small shaft exposed from the end of the composite small blade meets the specified length, and ensures that the metal small shaft does not rotate in the composite small blade or is not separated from the composite small blade due to loosening of the joint position during use, so that the metal small shaft and the composite small blade form an integrated louver blade.

A composite vane with a locking feature including a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the composite vane; a dovetail section formed within the composite vane proximate the radially outer attachment region; a shoe member in operative communication with the dovetail section; a boot in operative communication with an inner portion opposite spanwise from the dovetail portion; and a failsafe fastener in operative communication with the boot and the inner portion of the composite vane.

The application belongs to the technical field of engine structure design, and particularly discloses a hybrid asymmetric layered structure of a composite blade tail edge for resisting bird strikes, which is used for forming a fan blade of a large-bypass-ratio turbofan engine, and comprises a bullet-facing surface, a central region and a bullet-facing back surface; a hybrid region is arranged in the central region, and high-toughness fibers different from those in other regions are arranged in the hybrid region to form a hybrid fiber layered structure; the hybrid region is not symmetric about the geometric median plane of the layered structure in the thickness direction, thereby forming an asymmetric layered structure. The application solves the contradiction between the stiffness and toughness of the single material system of the existing composite fan blade layered structure and the problem that the symmetric layered design limits the design freedom.

This utility model relates to the field of sedimentation tank anti-clogging technology, and in particular to a magnetically driven self-cleaning sedimentation tank sludge discharge anti-clogging device. Its technical solution includes a pretreatment chamber, on the front of which is equipped with a PLC for control and a sludge discharge valve. The pretreatment chamber contains an anti-clogging structure to prevent equipment blockage. The anti-clogging structure includes a planetary gearbox for adjusting speed and torque, and a motor for driving the device is located on one side of the planetary gearbox. This utility model, through the arrangement of the planetary gearbox, the grid body, and the composite blade, achieves three-level coordinated anti-clogging: fiber stripping, sludge breaking, and sludge pushing, improving the compactness of the structure. The magnetic drive unit enables zero-leakage transmission, fundamentally eliminating media leakage, reducing maintenance costs, and extending equipment life. Furthermore, through the coordinated use of the flushing structure, PLC, and sludge discharge valve, time-limited automatic cleaning can be achieved, reducing energy consumption and lowering operating costs.

The invention relates to a rotor element (48) for a turbine engine, comprising a metal disk (62) and a plurality of blades (49) mounted on the disk (62). At least one of said blades (49) consists of a hybrid blade (79) made of composite material and comprising a metal root (80) linked to the disk (62).

This utility model relates to the field of parts processing technology, specifically a multi-purpose composite tool body. The tool body includes: a tool shank, which includes a tool body with a groove and a threaded hole penetrating the tool body; a blade, which is installed in the groove and includes a cutting edge with a through hole; a limiting block at one end of the cutting edge and a cutting head and a cutting head 2 at the other end; the cutting head 1 including a beveled surface and a guide surface 2, with a cutting head formed between the beveled surface and the beveled surface; and a screw, which passes through the through hole and the threaded hole sequentially from the outside in, fixing the blade to the tool shank. This utility model has the advantages of simple structure, reasonable design, high processing efficiency, one-time processing capability, and a relatively wide tool body, making it worthy of widespread promotion and application.

BLOWER BLADE COATED WITH A PROTECTIVE COATING AND APPLICATION METHOD One aspect of the invention relates to a blower blade (1) made of composite material comprising a composite blade (2) including a leading edge (20) and a trailing edge (21), a metallic leading edge (4) placed on the leading edge (20) of the composite blade (2), and a coating layer applied to at least a portion of the blade surface, characterized in that the coating layer is a protective elastomer (6) deposited directly onto the composite blade (2). Figure to be published with the abstract: Figure 3.

The invention relates to a method for manufacturing a turbomachine blade, comprising the following steps: - manufacturing a blade (10) from composite material, - assembling a metallic leading edge (24) onto the composite blade thus manufactured, characterized in that the method comprises a surface treatment step by applying a mechanical surface prestress to at least a portion of the metallic leading edge (24). Figure for the abstract: Fig. 1.

The utility model relates to a kind of composite blade main load-carrying member carbon beam, length direction includes blade root portion, leaf handle portion, blade portion in sequence;Inside and outside direction is composed of beam core and beam outer layer, the beam core and beam outer layer are made of carbon fiber composite material;The beam core is solid structure;The blade root portion is equipped with first boss, second boss, third boss, the third boss is located at the root of beam core, first boss is located at the root of beam outer layer and is formed on the basis of third boss imitation, second boss is formed in the beam outer layer on the side of third boss;The cross section of first boss and second boss is wedge shape shape.The utility model solves the problem of insufficient rigidity of existing composite blade main load-carrying member carbon beam under the requirement of limited weight.