68 results about "Composite propeller" patented technology

A method for making a propeller product is disclosed. The propeller is formed using polyurethane cores adhered to a laminate hub to form a core assembly. An encapsulating structural laminate skin is then formed on the core assembly using a resin-transfer-molding process to create a single-piece composite propeller.

The invention relates to a performed composite propeller blade of a ship and a manufacturing method of the performed composite propeller blade. Compared with a metal propeller, the preformed composite propeller blade has the advantages that the weight is low, corrosion resistance is good, the hydrodynamic performance is superior, cavitation can be delayed, cavitation corrosion is reduced, the acoustic characteristic is excellent, noise of the propeller is lowered, and the stealth performance of the ship can be easily improved. Fiber covers serve as a primary bearing mechanism, and the fiber covers are designed to be of identical thickness and cover the whole blade. By means of the performed composite propeller blade of the ship and the manufacturing method of the performed composite propeller blade, quasi two-dimensionalization of complex three-dimensional weaving is effectively achieved. The problems of delamination and stripping of guide edges and following edges of an original blade are effectively solved, the weaving difficulty is reduced, and cost is reduced; and the dead load of the propeller blade can be greatly reduced, and the appearance precision of the propeller blade is improved.

A method and apparatus comprising a composite spar. The composite spar has a root section and a main section. The root section is closed and has a shape configured to be connected to a blade retention system. The main section has an open channel. The composite spar is configured for placement inside of a blade.

One aspect of the present invention provides a propeller for an aircraft. The propeller comprises a propeller hub, a spinner for streamlining the propeller and a plurality of composite propeller blades mounted to the propeller hub. The propeller blades are arranged to rotate together in the same rotational direction in at least two parallel planes substantially perpendicular to an axis of rotation of the propeller. The propeller has a reduced sized spinner with an improved aerodynamic profile that can be better matched to an engine nacelle and also has reduced drag.

The invention belongs to the technical field of preparation of propeller blades and relates to a preparation method of an integrated composite propeller blade for a stratospheric airship. The preparation method comprises: 1, making a mold apparatus; 2, preparing carbon fiber prepreg cloth 16; 3, preparing the mold apparatus; 4, making a preform 13; 5, assembling the mold apparatus; 6, evacuating the mold apparatus; 7, heating and pressurizing for solidifying; 8, cooling to room temperature; 9, demolding; 10, finishing preparation of the finished blade. The preparation method has the advantages that the method is simple, the blade has good quality, the blade is high in strength and light in weight, and making efficiency is high; bearing capacity of a propeller is effectively improved; overall quality of the propeller is improved; yield is effectively increased; it is ensured that the propeller bears uniform stress during solidifying such that deformation or bubbles are avoided; maneuvering property of the stratospheric airship is improved, the self-weight is reduced at the premise of ensuring overall rigidity and stability, and working efficiency of the propeller is improved.

The invention provides a continuous fiber reinforced composite propeller layer lay-up design and a preparation method. According to the method, continuous fiber prepreg sheets are adopted for coatinga metal insert; through the mold pressing process, the one-step forming of a composite propeller is achieved; a preformed mold is prepared for the preforming process of composite blades, thereby guaranteeing the continuity of the connection between the blades and a propeller hub, shortening the manufacturing cycle of the composite propeller, reducing the manufacturing cost of the composite propeller, improving the product quality, and meeting the actual usage requirements on the light weight of a propeller blade material and the noise reduction; according to the propeller prepared through themethod, the continuous fiber integral blades are adopted and integrally connected with the propeller hub part, thereby avoiding the occurrence of a secondary interface; and accordingly, the machinerystability and reliability can be effectively improved.

The invention belongs to mechanical structure design, and relates to a composite propeller blade and blade root connecting structure. According to the composite propeller blade and blade root connecting structure, in order to realize reliable connection between carbon girders of composite main force-bearing parts and a metal blade root, first the carbon girders are laid on the metal blade root, and the carbon girders are composed of a plurality of layers of carbon fiber one-way cloth and satin cloth; and then carbon fiber is wound around the arc-shaped surface of the metal blade root, so thatthe carbon girders and the metal blade root are fixed together. When a propeller rotates, the centrifugal load and the pneumatic load brought by rotating are transmitted to the blade root, and the radian appearance of the metal blade root and the fiber are wound so that disengaging of the carbon girders can be prevented, and then damage to the composite propeller blade is avoided. The number of parts of the blade root connecting structure is reduced from original 12 to 5, and the composite propeller blade and blade root connecting structure is simple in structure, low in weight and good in manufacturability, the manufacturing cost is further greatly reduced, and the economic benefits are obviously increased.

The invention relates to a marine composite material propeller pre-deformation optimization method, and belongs to the technical field of impeller mechanical simulation. The method comprises the following steps: establishing a composite material propeller finite element model; and carrying out bidirectional fluid-solid coupling calculation on the deformation values and a composite material propeller calculation fluid mechanics model, extracting deformation values of the characteristic points on each blade tangent plane in the coordinate direction based on a result, and reversely superposing the deformation values into a propeller coordinate conversion formula for pre-deformation processing to finally obtain the pre-deformation composite material propeller. According to the method, changesof geometric parameters such as propeller pitch angles, lateral inclination and longitudinal inclination caused by deformation of the composite propeller blades under the fluid-solid coupling effect are comprehensively considered, and the precision of pre-deformation design is improved. In addition, the method is high in universality and universality. Compared with an existing pre-deformation design method, the method has the advantages of being small in calculation amount, easy and convenient to calculate and capable of achieving parameterized and programmed design, and a large number of calculation resources and time are saved.

The invention provides a numerical forecasting method for cavitation noise of a composite propeller, and the method comprises the following steps: building a geometric model of the propeller through three-dimensional configuration software according to the design size of the propeller; completing the construction of a hydrodynamic model; establishing a finite element model of the composite propeller by utilizing finite element software; carrying out cavitation performance simulation calculation on the composite material propeller to obtain a cavitation numerical simulation result, and obtaining the difference between the hydrodynamic performance and the cavitation performance of the composite material propeller and the metal material propeller; storing a cavitation numerical simulation result obtained in the fluid analysis software; constructing an acoustic calculation model of the composite propeller, and setting a plurality of monitoring points in the acoustic calculation model; and comparing and analyzing attenuation change rules of the cavitation radiation noise at different positions. According to the method, the vibration noise radiation condition of the propeller can be well predicted, and reference is provided for low-noise propeller design.

The invention relates to a prestress wet mode prediction method for a composite propeller based on acoustic-solid coupling, and belongs to the technical field of turbomachinery simulation. The methodcompriss the steps: based on a finite element principle, implementing fluid-solid coupling wet mode prediction of the composite propeller through an acoustic-structure coupling method; establishing acomposite material propeller model, and establishing a corresponding flow field area; carrying out mesh generation and prestress introduction on the composite material propeller model and the flow field area, and then carrying out analysis parameter setting; and finally outputting a modal analysis result to obtain a prestress wet modal frequency and a prestress vibration mode. According to the method, the actual vibration response generated by the composite propeller under the action of various vibration sources can be predicted, the influence of the additional mass of the fluid is fully considered, the high-precision prediction of the composite propeller prestress wet mode can be realized, and the prediction trueness and credibility are improved.

The invention provides a composite material propeller, comprising: a base made of metal as a whole and a plurality of slots connected together; wherein the slots are equally distributed on the circumference of the base, the opening of the slots is upward, and the spiral The root of the shaped paddle fits closely with the card slot. Based on the problems that metal material propellers are heavy and easy to corrode, and the common problem that the connection between composite materials and metal materials is easy to debond, the present invention designs the connection structure between the composite material propeller blade and the metal frame, effectively avoiding the problem caused by composite materials and metal materials Product defects occur due to poor adhesion of the frame, which improves the success rate of the product.

The invention provides a rotary heating type composite propeller curing oven comprising an oven body, a heating mechanism and a mold holding mechanism. The first end of a rotary shaft is rotationally connected with the first side wall of the oven body. The second end of the rotary shaft penetrates through the geometric centers of a first installing ring and a second installing ring sequentially to be rotationally connected with the second side wall of the oven body. The inner side of the first installing ring is fixedly connected with the rotary shaft through a plurality of first connecting rods. The inner side of the second installing ring is fixedly connected with the rotary shaft through a plurality of second connecting rods. The first ends of a plurality of support shafts are all connected with the first installing ring, and the second ends of the multiple support shafts are all connected with the second installing ring. A plurality of mold holding frames are hinged to the multiple support shafts correspondingly. A first heating disc is located on the side, away from the second installing ring, of the first installing ring and is rotationally installed on the rotary shaft. The two ends of an air conduit are connected with the first heating disc and a second heating disc correspondingly. The rotary heating type composite propeller curing oven can meet the requirement for temperature in the forming process of a composite propeller, cost is low, and in-oven temperature is uniform.