Patent Application
20230192568
This disclosure relates to reinforcing fibers for use in ceramic matrix composites, methods of manufacture thereof and articles comprising the same. In particular, the reinforcing fiber is used to reinforce the region around cooling holes in ceramic matrix composites.
Preforms are used for the fabrication of ceramic matrix composite (CMC) structures using chemical vapor infiltration (CVI), polymer infiltration pyrolysis (PIP) and melt infiltration (MI). A preform generally comprises a plurality of plies which are made from a fabric. The fabric comprises fibers, which can be unidirectional or woven (e.g., plain weave, 5 Harness Satin Weave, 8 Harness Satin Weave, twill). These fibers are often manufactured from ceramics
Chemical vapor infiltration (CVI) is a ceramic engineering process whereby matrix material is infiltrated into fibrous preforms by the use of reactive gases at elevated temperature to form fiber-reinforced composites. CVI can be applied to the production of carbon-carbon composites and ceramic-matrix composites. Chemical vapor infiltration (CVI) can potentially be used at temperatures of up to and greater than 2700° F. Polymer infiltration pyrolysis (PIP) comprises the infiltration of a low viscosity polymer into the fiber structure, followed by pyrolysis. Under pyrolysis, the polymer precursor is heated in an inert atmosphere and transformed into a ceramic due to its decomposition. Melt infiltration is based on the infiltration of porous matrices with the melt of an active phase or precursor. These ceramic matrix composites are used in a variety of high temperature applications such as turbine blades, vanes, and so on.
When used in such a gas turbine, the ceramic matrix composite can be subjected to high temperatures and extreme thermal gradients. The high temperatures and stress caused by the extreme thermal gradient can lead to a breakdown in the ceramic matrix composite component. In order to reduce the stress and prevent overheating, cooling holes are often used in the ceramic matrix composite components. The cooling hole permits the transport of cooling gases through the component. Cooling gases reduce the temperature of the components and prevent the formation of large steep thermal gradients which can eventually lead to a reduction in the life cycle of the component.
Such cooling holes are often machined (via techniques such as drilling, milling, laser, and the like) into the surface of the ceramic matrix composite to allow cooling air to circulate through. This air circulation reduces the stress and provides better temperature control. The machining involves the application of a high amount of stress on the fibers of the ceramic matrix composite, often resulting in cracks in the ceramic matrix composite around the resulting cooling hole. These cracks can propagate in some form, often linking up with cracks in other nearby cooling holes to create larger cracks in the ceramic matrix composite. Cracks can result in additional damage to the composite which is undesirable. These cracks can cause poor performance, ultimately reducing the service life of the component.
Disclosed herein is a method of reinforcing a composite comprising determining a location of a first cooling hole in a plurality of plies; where a cooling gas is transported through the cooling hole; disposing a z-fiber in the plurality of plies at a location proximate to where the first cooling hole will be located; where the z-fiber enters the plurality of plies at either an upper surface or a lower surface; and where the z-fiber traverses a portion of the plurality of plies in the z-direction proximate to the first cooling hole; and traverses the plurality of plies in an x or y direction further away from the first cooling hole; where the z-direction is in the thickness direction of the plurality of plies and where the x and y-direction are perpendicular to the z-direction.
In an embodiment, the z-fiber traverses the entire plurality of plies in the z-direction proximate to the first cooling hole.
In an embodiment, the z-fiber traverses the entire plurality of plies in the z-direction proximate to the first cooling hole prior to traversing the plurality of plies in the x and/or y-direction.
In an embodiment, the z-fiber traverses the plurality of plies in the x-direction or the y-direction in between two plies.
In an embodiment, the z-fiber traverses the plurality of plies in the x-direction or the y-direction on an outer surface of the plurality of plies.
In an embodiment, the z-fiber penetrates the plurality of plies from the outer surface in a periodic manner.
In an embodiment, the z-fiber penetrates the plurality of plies from the outer surface in an aperiodic manner.
In an embodiment, the method further comprises drilling the cooling holes after the z-fiber is woven into the plurality of plies.
In an embodiment, the method further comprises disposing a ceramic precursor into the composite to form a ceramic matrix composite.
In an embodiment, the disposing of the ceramic precursor into the composite occurs after the cooling holes are drilled.
In an embodiment, the method further comprises removing a machine tool from the composite from the ceramic matrix composite to leave behind a reinforced cooling hole.
In an embodiment, the disposing of the ceramic precursor into the composite comprises chemical vapor infiltration, polymer infiltration pyrolysis or melt infiltration.
In an embodiment, the method further comprises disposing a plurality of z-fibers in the plurality of plies, wherein each z-fiber traverses the plurality of plies in the z-direction proximate to a cooling hole location.
Disclosed herein is an article comprising a preform comprising a plurality of plies; a ceramic matrix encompassing the preform; wherein the preform comprise one or more cooling holes; and a z-fiber disposed in the preform proximate to the cooling holes; where the z-fiber traverses a portion of the plurality of plies in the z-direction proximate to the one or more cooling holes; and traverses the plurality of plies in an x or y direction further away from the one or more cooling holes; where the z-direction is in the thickness direction of the plurality of plies and where the x and y-direction are perpendicular to the z-direction.
In an embodiment, the z-fiber traverses the plurality of plies in the x-direction or the y-direction in between two plies.
In an embodiment, the z-fiber traverses the plurality of plies in the x-direction or the y-direction on an outer surface of the plurality of plies.
In an embodiment, the z-fiber penetrates the plurality of plies from the outer surface in a periodic manner.
In an embodiment, the z-fiber penetrates the plurality of plies from the outer surface in an aperiodic manner.
In an embodiment, the z-fiber traverses the entire plurality of plies in the z-direction proximate to the one or more cooling holes.
In an embodiment, the article is a turbine blade.
The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike:
A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures.
Disclosed herein is a ceramic composite matrix that comprises a fiber reinforcement in regions of the composite proximate to a cooling hole. Disclosed herein too is a method that comprises adding 3-D z-fiber tows that are woven at precise distances of an intended cooling hole row arrangement during the formation of a CMC preform. After densification, holes would be drilled between the z-fibers. This methodology is advantageous in that it adds a strengthening mechanism to the surrounding hole region to prevent crack linkage between holes. In this method, precise spacing and hole size guidelines are determined prior to layup of the preform.
As noted above, current airfoil design incorporated cooling holes machined (e.g., drilled, slotted, and the like) into the CMC material in order to alleviate thermal stresses generated during operation. However, these drilled cooling holes may themselves act as stress concentrators due to fiber breakage and rupture that may occur during the machining operation. The stress concentration created may significantly impact the life of the part where cooling hole fatigue stress cracks initiate at locations leading to further “linking” of cracks and possibly component failure. It is therefore desirable to strengthen the region around cooling holes to prevent crack linkage between holes and consequently increase life cycle of the component. Cooling gases are transported through the cooling holes to reduce the temperature of the components and prevent the formation of large steep thermal gradients, which can eventually lead to a reduction in the life cycle of the component.
The method comprises weaving 3-D z-fibers tows into a zone where intended cooling holes are to be machined (e.g., via drilling, slotting, milling, and the like) at. Z-fibers are typically fibers added in the through-thickness direction of an article or component prior to densification of the precursors (that eventually form the ceramic matrix). Fibers placed in the thickness direction are called z-fibers, z-yarn, warp weaver, or binder yarn for 3D woven fabrics. More than one layer of fabric is woven at the same time, and the z-fibers interlaces warp and fill yarns of different layers during the process. At the end of the weaving process, an integrated 3D woven structure, which has a considerable thickness, is produced.
After densification holes would be drilled in the zone containing z-fibers. The weaving frequency would be as such that holes will be disposed in the vicinity of a z-fiber reinforced region hence decreasing the probably of a crack propagation and connectivity between holes. This methodology would add a strengthening mechanism to the region surrounding a hole and prevent crack linkage between holes. Precise parameters such zone definition, weaving frequency and z-fiber tow size guidelines are determined prior layup.
The z-fibers enter the plurality of plies and traverse the plurality of plies 200 along the z-axis (which represents the thickness of the plies) that is typically concentric to the cooling hole drilled in the plurality of plies. In an embodiment, only a single z-fiber may traverse the thickness of the plurality of plies 200 (in the z-direction) at a region close to where the hole is to be drilled. In another embodiment, two or more z-fibers may traverse the thickness of the plurality of plies 200 at a region proximate to where the hole is to be drilled. In yet another embodiment, three or more z-fibers may traverse the thickness of the plurality of plies 200 at a region proximate to where the hole is to be drilled. In an embodiment, the z-fibers may be symmetrically located or asymmetrically located about the cooling hole. A symmetrical arrangement implies that if the plurality of plies are cut along the z axis (the longitudinal axis) at a location where a drill bit is placed, then the image on one side of the drill bit is a mirror image of the other side of the drill bit.
The z-fibers may be woven through the entire thickness of the plurality of plies (as depicted in the
While the
As noted above, the z-fibers may be symmetrically distributed through the ply around the to-be drilled cooling hole.
As may be seen from the
The z-fiber typically traverses the plurality of plies in the z-direction proximate to the cooling holes and traverses the plurality of plies in the x-direction, the y-direction or both the x and y-direction when located further away from the cooling holes. The z-fiber may also traverse the plurality of plies in the z-direction at locations that are not proximate to the cooling hole. In an embodiment, the z-fiber traverses the plurality of plies in the x-direction or the y-direction in between two plies (i.e., in the interior of the plurality of plies). In an embodiment, the z-fiber traverses the plurality of plies in the x-direction or the y-direction on an outer surface of the plurality of plies. In another embodiment, the z-fiber penetrates the plurality of plies from an outer surface in a periodic manner. In another embodiment, the z-fiber penetrates the plurality of plies from an outer surface in an aperiodic manner.
In one embodiment, in one method of manufacturing a component with cooling holes, the location of the cooling holes is first determined. The cooling holes are generally located between warp and fill fibers so as to preferably not disturb the fibers. The location of the z-fibers is also determined prior the layup process. The plies are layed up and the z-fibers are woven into the layup prior to precursor infiltration. After the z-fibers are woven into the layup, the layup is subjected to precursor infiltration. After precursor infiltration, the machine tool (used to form the cooling hole, such as, for example, a drill bit) is removed leaving behind a cooling hole.
Precursor infiltration may be conducted via chemical vapor infiltration, polymer infiltration pyrolysis or melt infiltration. Chemical vapor infiltration (CVI) is a ceramic engineering process whereby matrix material is infiltrated into fibrous preforms by the use of reactive gases at elevated temperature to form fiber-reinforced composites. CVI can be applied to the production of carbon-carbon composites and ceramic-matrix composites. Chemical vapor infiltration (CVI) can potentially be used at temperatures of up to and greater than 2700° F. Polymer infiltration pyrolysis (PIP) comprises the infiltration of a low viscosity polymer into the fiber structure, followed by pyrolysis. Under pyrolysis, the polymer precursor is heated in an inert atmosphere and transformed into a ceramic due to its decomposition. Melt infiltration is based on the infiltration of porous matrices with the melt of an active phase or precursor.
After the densification of the precursors has occurred, the cooling holes are drilled into the ply. Z-fiber reinforcement is advantageous for its ability to increase the through-the-thickness strength of advanced composite laminates, joints and structural interfaces.
The term “about” is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
