Mixed material fan blade and preparation method thereof
A technology of fan blades and mixed materials, applied in the direction of blade support components, mechanical equipment, machines/engines, etc., can solve the problems of high technical threshold and high cost, complex blade shape, and difficult processing of braided composite materials, etc., to overcome The strength performance and weight reduction effect cannot be balanced, overcome the interface separation, and overcome the effect of local stiffness discontinuity
Active Publication Date: 2022-02-18
AECC COMML AIRCRAFT ENGINE CO LTD
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Problems solved by technology
Due to the design of the metal reinforcement edge of the composite fan currently used is limited by the traditional processing technology, only a very small number of suppliers have the ability to process the metal reinforcement edge, and the technical threshold and cost are always high
In addition, the complex shape of the blade makes it extremely difficult to process the braided composite material, which becomes a bottleneck in the development and it is difficult to break through in a short time
Method used
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[0028] A variety of different implementations or examples for implementing the described subject technical solutions are disclosed below. In order to simplify the disclosure, the following describes the specific examples of each component and arrangement, of course, these are only examples, not limiting the protection scope of the present invention. For example, the description that the first feature described later in the description is formed on or above the second feature may include an embodiment in which the first and second features are formed through direct contact, and may also include an embodiment in which the first and second features are formed between the first and second features. Embodiments of additional features such that there may be no direct relationship between the first and second features. Additionally, reference numerals and / or letters may be repeated in different instances in these disclosures. This repetition is for brevity and clarity and does not i...
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Abstract
The invention provides a mixed material fan blade and a preparation method thereof, wherein the mixed material fan blade includes a basic frame made of metal wires, the distance between the metal wires and the diameter, shape and material of the metal wires are determined according to the actual external load of the fan blade The distribution is determined, and the metal wire is wrapped by a composite material composed of non-metallic fiber materials and a resin matrix to form an embedded structure, or the braided prefabricated body is formed by integral weaving with non-metallic fibers, and then thermoset and molded. It solves the problems of interface separation between metal and composite materials, insufficient connection strength, discontinuous local stiffness of fan blades, stress concentration problems, and inability to balance strength performance and weight reduction effect.
Description
technical field [0001] The invention relates to an aeroengine fan blade and a preparation method thereof. Background technique [0002] Large size and lightweight fan blades are one of the keys to large bypass ratio civil aeroengines. At present, the lightweight and large bypass ratio fan blade schemes successfully applied to products in the world include pure titanium alloy hollow fan blades and composite material-titanium alloy wrapped fan blades. If the weight reduction effect of lightweight fan blades is measured by the equivalent hollow ratio (actual blade weight / solid titanium alloy blade weight of the same size), the full titanium alloy hollow blade has achieved a weight reduction of 40% (that is, the actual hollow ratio), The composite material-titanium alloy edged blade has achieved a weight reduction of more than 60% of the equivalent hollow ratio. Due to the better weight reduction effect, the mixed structure of composite materials and metals has become the main...
Claims
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IPC IPC(8): F01D5/14F01D5/28
CPCF01D5/147F01D5/282
Inventor 曹源王少辉刘传欣倪晓琴王祯鑫王星星龙丹赵宪涛
Owner AECC COMML AIRCRAFT ENGINE CO LTD