2895 results about "Ceramic matrix composite" patented technology

The invention discloses a two-dimensional fiber cloth reinforced ceramics based composite material and the preparation technique, which adopts the two-dimensional fiber cloth as the reinforcing phase and the ceramic powder or the refractory metal powder as the stuffing, and the carbon and the carborundum as the base. The process steps are following: first the sizing agent with different ceramic powder and metal powder is coated on the two-dimensional fiber cloth, and then overlapping, puncturing and repeated densification are carried out. The preparation method has the advantages of lowering preparation cost and shortening preparation cycle, and the two-dimensional fiber cloth reinforced ceramics based composite material has the advantages of high shear strength between layers, structural stability and high reliability. The types of fiber cloth and the base can be adjusted and optimized in a wider range according to the applications, so as to be applicable for different fields.

Novel composite disc brake rotor assemblies are provided, along with novel and efficient methods for manufacturing them. Preferably, the rotor assemblies comprise annular wear plates formed of particle reinforced aluminum-based metal matrix composite (MMC), ceramic matrix composite (CMC), or of ‘carbon graphite foam.’ The wear plates, made of a first material, are attached to annular surfaces of a central rotor, made of a second material, by fusing bonding layers between the wear plates and the rotor surfaces. The bonding layers are comprised of at least one of a metal alloy having a melting temperature lower than that of either the first or second materials, and a high-temperature adhesive. Preferably, the wear plates comprise projections that are positioned within adjacent receiving recesses in the center rotor. The bonding layers and projections enhance thermal and acoustical transference between the wear plates and the center rotor section. Carbon graphite foam provides for substantially enhanced heat transference. Use of the fusable binding layer, or adhesive provides for an efficient, low cost method of manufacturing for composite disc brake rotor assemblies.

The present invention discloses novel polymer-ceramic matrix composites and processes for making same. The composites can be used in biomedical applications, in particular, coatings of implants and other medical devices, where both the ceramic phase and the polymer phase are bio-compatible. The composites combine a reinforcing polymer phase with a continuous ceramic matrix to create materials with properties that are new and superior to polymer or ceramic phases alone. The composites can incorporate a bioactive agent.

A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

The invention discloses a preparation method of a graphene reinforced metal-matrix composite, which comprises the following steps of: firstly, dispersing the graphene oxide on the surface of the flaky metal powder; and then obtaining the graphene/metal composite powder through the reducing treatment; and at last, carrying out densification treatment by adopting a powder metallurgic technology to obtain the compact graphene reinforced metal-matrix composite. The flaky metal powder has the plane two-dimensional form, is inclined to the directional piling to form a laminated structure, and is helpful for inducing the graphene orientation distribution and giving play to the reinforcing effect. The preparation method disclosed by the invention is simple and feasible, is capable of regulating the graphene content and is suitable for preparing the massive composite.

A method of manufacturing a composite structure uses a layer of an insulating material (22) as a mold for forming a substrate of a ceramic matrix composite (CMC) material (24). The insulating material may be formed in the shape of a cylinder (10) with the CMC material wound on an outer surface (14) of the cylinder to form a gas turbine combustor liner (20). Alternatively, the insulating material may be formed in the shape of an airfoil section (32) with the CMC material formed on an inside surface (36) of the insulating material. The airfoil section may be formed of a plurality of halves (42, 44) to facilitate the lay-up of the CMC material onto an easily accessible surface, with the halves then joined together to form the complete composite airfoil. In another embodiment, a box structure (102) defining a hot gas flow passage (98) is manufactured by forming insulating material in the shape of opposed airfoil halves (104) joined at respective opposed ends by platform members (109). A layer of CMC material (107) is then formed on an outside surface of the insulating material. A number of such composite material box structures are then joined together to form a vane ring (100) for a gas turbine engine.

The present invention is a hybrid ceramic matrix composite turbine engine component comprising an outer shell section(s) and an inner core section(s), wherein the outer shell section(s) and the inner core section(s) were bonded together using an MI process. The outer shell section(s) comprises a SiC/SiC material that has been manufactured using a process selected from the group consisting of a slurry cast MI process and a prepreg MI process. The inner core section(s) comprises a material selected from the group consisting an Si/SiC composite material and a monolithic ceramic material. The Si/SiC composite material may be manufactured using the Silcomp process. The present invention may be a high pressure turbine blade, a high pressure turbine vane, a low pressure turbine blade, or a low pressure turbine vane. The present invention is also a method of manufacturing a hybrid ceramic matrix composite turbine engine component.

An assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine including a longitudinal centerline axis extending therethrough. The sealing assembly includes a substantially annular first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end and a substantially annular second sealing member positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion. Accordingly, the first sealing member is maintained in its seated position as the support member aft portion moves radially with respect to the liner aft end and the second sealing member is maintained in its seated position as the support member aft portion moves axially with respect to the turbine nozzle. The first and second sealing members are also maintained in their respective seating positions as the support member aft portion moves axially with respect to the liner aft end and radially with respect to the turbine nozzle.

Embodiments of the invention relate to various cooling systems for a turbine vane made of stacked ceramic matrix composite (CMC) laminates. Each airfoil-shaped laminate has an in-plane direction and a through thickness direction substantially normal to the in-plane direction. The laminates have anisotropic strength characteristics in which the in-plane tensile strength is substantially greater than the through thickness tensile strength. Such a vane construction lends itself to the inclusion of various cooling features in individual laminates using conventional manufacturing and forming techniques. When assembled in a radial stack, the cooling features in the individual laminates can cooperate to form intricate three dimensional cooling systems in the vane.

A turbine engine shroud segment is provided with a radially outer surface including a pair of spaced apart, opposed first and second edge portion surface depressions, for example spaced circumferentially, having a seal surface shaped to receive, in a surface depression formed between assembled adjacent segments in a shroud assembly, or axially assembled adjacent segments and engine members, a radially outer fluid seal member. The depression portions of a shroud segment are joined with the radially outer surface of the shroud segment through an arcuate transition surface. Stresses generated during engine operation in the shroud material are reduced, enabling practical use of a low ductility material, for example a ceramic matrix composite. The edge portion surface depressions are provided with a first shape and the fluid seal member, disposed at the depression, is provided with a surface of a second shape matched in shape with the first shape.

An attachment method and flange for connecting a ceramic matrix composite (CMC) component, such as a gas turbine shroud ring (36, 68), to a metal support structure. A CMC flange (20A) may be formed by attaching a wedge-shaped block (26) of a ceramic material to a CMC wall structure (22), and wrapping CMC layers (24) of the wall structure (22) at least partly around the block (26), forming the flange (20A) with an inner oblique face (34) and an outer face (35) normal to the wall structure. An adjacent support structure, such as a metal support ring (40A), may abut the outer face (35) of the CMC flange (20A) and be clamped or bolted to the CMC flange (20A).

A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

A crystal whisker and particle toughened ceramic-based composition used to make large thin-wall member is prepared through granulating to prepare the coagulated substance of crystal whiskers and particles, preparing the prefabricated body of crystal whisker-particle reinforcing body, and depositing the ceramic base in said prefabricated body by chemical vapour osmosis process.

A mounting arrangement (10) for a multivane segment (12) of ceramic matrix composite (CMC) composition positioned between outer and inner metallic rings (14, 16). Selected ones of the vanes (18a) of the multivane segment surround internal struts (24) joining the outer and inner rings. Spring members (26, 28) accommodate differential thermal growth between the multivane segment and the outer and inner rings, and a compliant material (30) seals against gas leakage around the segments.

The disclosure relates to structures and a method for providing an air cooled rotor with ceramic-metal composite friction surface plates, and in particular to a brake rotor including a rotor hat; a ventilation disc having a plurality of cooling vanes extending therefrom; a ceramic matrix composite (CMC) friction surface plate on each side of the ventilation disc; and a fastener for holding the CMC friction surface plates and the ventilation disc to the rotor hat.