A kind of non-residual preparation method of multi-element carbon and ceramic matrix thermal structure composite material and turbine blade
A technology of composite materials and turbine blades, applied in the field of materials, can solve the problems of three-dimensional braided composite materials, such as the decline of mechanical properties, the damage of overall fiber reinforcement, and the long densification period, to achieve strong integrity and continuity, long densification period, high density effect
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Method used
Image
Examples
preparation example Construction
[0027] Such as figure 1 As shown, according to an embodiment of the present invention, a method for preparing a multi-element carbon and ceramic-based thermal structural composite material turbine blade without margin comprises the following steps:
[0028] S101: A four-step method is used to weave the turbine blade fiber fabric prefabricated body in three dimensions. The four-step three-dimensional integral weaving of continuous fiber turbine blade prefabricated body not only makes the fibers in the prefabricated body complete and continuous in the space multi-axis plane and between planes, but also the three-dimensional integral fabric structure can overcome long fibers, short fibers, two-dimensional weaving, The disadvantages of 2.5-dimensional weaving and three-dimensional needle-punched texture; it has good integrity, not easy to delaminate, high toughness, high impact resistance, excellent energy absorption capacity, outstanding fatigue resistance, near-net shape manufac...
Embodiment 1
[0042] Embodiment 1 provides a preparation process of a fiber-reinforced multi-component carbon and ceramic-based thermal structural composite turbine blade, the specific steps are as follows:
[0043] Step 1: Use the four-step method to weave the fiber fabric prefabricated body in three dimensions, and the weaving angle is 20°~45° o , the preform is C-Si-Al continuous fiber, the fiber volume fraction is 35%-45%.
[0044] In step 1, the turbine blades are designed in one piece, which has the advantages of easy sealing and assembly, and cancels the limitation of the cooling system required by the traditional nickel-based superalloy materials, and the corresponding size adjustment can be made considering the matching of thermal expansion coefficients. Considering comprehensively, the length of the airfoil of the designed turbine blade is increased by 0.3% to 0.5% compared with the airfoil of the turbine blade made of superalloy.
[0045] Step 2: Prepare (C+SiC) on the turbine b...
Embodiment 2
[0051] Embodiment 2 provides a preparation process of fiber-reinforced multi-element carbon and ceramic-based thermal structural composite materials, the specific steps are as follows:
[0052] Step 1: Use the four-step method to weave the prefabricated body three-dimensionally as a whole, and the weaving angle is 20°~45° o , the preform is C-Si-Al continuous fiber, the fiber volume fraction is 35%-45%.
[0053] In step 1, the prefabricated body adopts an integral design, which has the advantages of easy sealing and assembly, and cancels the limitation of the cooling system required by the traditional nickel-based superalloy material, and the corresponding size adjustment can be made considering the matching of thermal expansion coefficient.
[0054]Step 2: Prefabrication (C+SiC) by chemical vapor infiltration n The composite interface layer has a thickness of about 300nm-400nm.
[0055] Step 3: Adding (C+SiC) n The prefabricated body of the composite interface layer is com...
PUM
| Property | Measurement | Unit |
|---|---|---|
| bending strength | aaaaa | aaaaa |
| density | aaaaa | aaaaa |
| thickness | aaaaa | aaaaa |
Abstract
Description
Claims
Application Information
Login to View More