Rapid processing of laminar composite components
A method of manufacturing a CMC structure includes infiltrating a porous substrate with a composite material and performing a first densification on the infiltrated porous substrate, forming a first densified porous substrate, wherein the first densification includes techniques selected from the group of techniques comprising photonic curing, photonic sintering, pulsed thermal heating, or combinations thereof.
1. A turbine engine component, comprising:
a laminar Ceramic Matrix Composite (CMC) structure manufactured by the method comprising:
infiltrating a porous substrate with a composite material;
performing a first densification on the infiltrated porous substrate and the composite material, forming a first densified porous substrate, wherein the first densification includes techniques selected from the group of techniques consisting of photonic curing, photonic sintering, pulsed thermal heating, and combinations thereof;
repeating the above steps a predetermined number of times to form a plurality of first densified porous substrates;
assembling the plurality of the first densified porous substrates, forming a layered structure of the plurality of the first densified porous substrates, wherein forming a layered structure of the plurality of the first densified porous substrates includes forming an interface layer between at least some of the first densified porous substrates, wherein the interface layer comprises a particulate composition, chopped fibers, or a suspension or dispersion of ceramic, metal, or carbonaceous particulates, platelets, nanotubes, or nanofibers; and
performing a second densification on the layered structure of the plurality of first densified porous substrates, forming a second densified porous substrate;
wherein the laminar CMC structure comprises a second densified porous substrate having a plurality of first densified porous substrates that have an interface layer positioned between at least some of the first densified porous substrates.
2. The turbine engine component of claim 1 wherein performing a second densification is via at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS) process, or a localized heating at a bonding interface.
3. The turbine engine component of claim 1 , wherein the porous substrate is selected from the group consisting of cellular foams, unitapes, woven fabrics, non-woven fabrics, knits, braids, chopped fiber mats, and combinations thereof and the porous substrate is formed of a material selected from the group consisting of metals, glasses, ceramics, carbon, polymers, and combinations thereof.
4. The turbine engine component of claim 1 , wherein infiltrating a porous substrate is selected from the group of techniques consisting of slurry infiltration, vapor infiltration, resin infiltration, doctor blading, filtration, polymer infiltration, melt infiltration (MI), preceramic polymer infiltration, Chemical Vapor Deposition (CVD), Chemical Vapor Infiltration (CVI), Atomic Layer Deposition (ALD), and combinations thereof.
5. The turbine engine component of claim 1 , wherein the composite material is selected from the group consisting of a carbides, oxides, nitrides, borides, and combinations thereof.
6. The turbine engine component of claim 1 , wherein each of the plurality of first densified substrates comprises a silicon carbide matrix with silicon carbide fibers.
7. The turbine engine component of claim 1 , wherein the first densification is performed on individual cut plies of the porous substrate.
8. The turbine engine component of claim 1 , wherein the first densification is performed on a continuous tow of a single ply of the porous substrate.
9. The turbine engine component of claim 1 , wherein the CMC structure is one of an airfoil, blade, vane, disk, nozzle, diffuser, combustor, seal, rotor, case, heatshield, beam, or plate.
10. A gas turbine engine component, manufactured by the method comprising:
infiltrating a porous substrate with a composite material;
performing a first densification on the infiltrated porous substrate and the composite material, forming a first densified porous substrate, wherein the first densification includes techniques selected from the group of techniques consisting of photonic curing, photonic sintering, pulsed thermal heating, and combinations thereof;
repeating the above steps a predetermined number of times to form a plurality of first densified porous substrates;
assembling the plurality of the first densified porous substrates, forming a layered structure of the plurality of the first densified porous substrates, wherein forming a layered structure of the plurality of the first densified porous substrates includes forming an interface layer between at least some of the first densified porous substrates, wherein the interface layer comprises a particulate composition, chopped fibers, or a suspension or dispersion of ceramic, metal, or carbonaceous particulates, platelets, nanotubes, or nanofibers; and
performing a second densification on the layered structure of the plurality of the first densified porous substrates, forming a second densified porous substrate, wherein performing the second densification is via at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS) process, or a localized heating at a bonding interface;
wherein the gas turbine engine component comprises a second densified porous substrate having a plurality of first densified porous substrates that have an interface layer positioned between at least some of the first densified porous substrates.
11. The gas turbine engine component of claim 10 , wherein the porous substrate is selected from the group consisting of cellular foams, unitapes, woven fabrics, non-woven fabrics, knits, braids, chopped fiber mats, and combinations thereof and wherein the porous substrate is formed of a material selected from the group consisting of metals, glasses, ceramics, carbon, polymers, and combinations thereof.
12. The gas turbine engine component of claim 10 , wherein infiltrating a porous substrate is selected from the group of techniques consisting of slurry infiltration, vapor infiltration, resin infiltration, doctor blading, filtration, polymer infiltration, melt infiltration (MI), preceramic polymer infiltration, Chemical Vapor Deposition (CVD), Chemical Vapor Infiltration (CVI), Atomic Layer Deposition (ALD), and combinations thereof.
13. The gas turbine engine component of claim 10 , wherein the composite material is selected from the group consisting of a carbides, oxides, nitrides, borides, and combinations thereof.
14. The gas turbine engine component of claim 10 , wherein each of the plurality of first densified substrates comprises a silicon carbide matrix with silicon carbide fibers.
15. The gas turbine engine component of claim 10 , wherein the gas turbine engine component is one of an airfoil, blade, vane, disk, nozzle, diffuser, combustor, seal, rotor, case, heatshield, beam, or plate.
16. A gas turbine engine component, comprising:
a densified porous substrate that comprises a densified layered structure of a plurality of first densified porous substrates, wherein each of the plurality of first densified substrates comprises a porous substrate infiltrated with composite material, wherein:
the porous substrate is selected from the group consisting of cellular foams, unitapes, woven fabrics, non-woven fabrics, knits, braids, chopped fiber mats, and combinations thereof and is formed of a material selected from the group consisting of metals, glasses, ceramics, carbon, polymers, and combinations thereof; and
the composite material is selected from the group consisting of a carbides, oxides, nitrides, borides, and combinations thereof;
wherein the densified layered structure of the plurality of the first densified porous substrates includes an interface layer between at least some of the first densified porous substrates, wherein the interface layer comprises a particulate composition, chopped fibers, or a suspension or dispersion of ceramic, metal, or carbonaceous particulates, platelets, nanotubes, or nanofibers
wherein the densified layered structure of the plurality of the first densified porous substrates has been subjected to a second densification step to form a second densified porous substrate having a plurality of first densified porous substrates that have an interface layer positioned between at least some of the first densified porous substrates.
17. The gas turbine engine component of claim 16 , wherein each of the plurality of first densified substrates comprises a silicon carbide matrix with silicon carbide fibers.
18. The gas turbine engine component of claim 16 , wherein the layered structure of the plurality of the first densified porous substrates has been densified to form the densified porous substrate via at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS) process, or a localized heating at a bonding interface; and each of the plurality of first densified substrates comprises a porous substrate infiltrated with composite material, wherein the porous substrate infiltrated with composite material has been densified using techniques selected from the group of techniques consisting of photonic curing, photonic sintering, pulsed thermal heating, and combinations thereof.
19. The gas turbine engine component of claim 16 , wherein the gas turbine engine component is one of an airfoil, blade, vane, disk, nozzle, diffuser, combustor, seal, rotor, case, heatshield, beam, or plate.
20. The gas turbine engine component of claim 16 , wherein the a densified porous substrate is coated to increase structural integrity, heat resistance, or environmental protection.