LOW THERMAL STRESS ENGINEERED METAL STRUCTURES

Abstract

A structured multi-phase composite which include a metal phase, and a low stiffness, high thermal conductivity phase or encapsulated phase change material, that are arranged to create a composite having high thermal conductivity, having reduced/controlled stiffness, and a low CTE to reduce thermal stresses in the composite when exposed to cyclic thermal loads. The structured multi-phase composite is useful for use in structures such as, but not limited to, high speed engine ducts, exhaust-impinged structures, heat exchangers, electrical boxes, heat sinks, and heat spreaders.

Claims

1-53. (canceled)

54. An engineered multi-phase composite which includes a high thermal conductivity phase and a metal phase; said high thermal conductivity phase constitutes over 20 wt.% of said engineered multi-phase composite; said high thermal conductivity phase is segregated into isolated pockets forming a discontinuous phase in said engineered multi-phase composite; said metal phase is a continuous phase in said engineered multi-phase composite; said engineered multi-phase composite has a thermal conductivity that is at least 20% greater than a thermal conductivity of said metal that forms said metal phase; said engineered multi-phase composite has a density that is at least 20% less than a density of said metal that forms said metal phase; said high thermal conductivity phase includes filler; said filler including one or more materials selected from the group consisting of a) hexagonal boron nitride, b) cubic boron nitride, c) boron nitride nanotubes, d) graphene, e) diamond, f) graphite, g) carbon or carbon nanotubes, h) SiC, g) alumina ceramic, h) zirconia ceramic, i) boron oxide ceramic, j) silicon nitride ceramic, k) sialon, 1) SSiC, m) LPS-SiC, n) RBSiC, o) NSiC, p) SiSiC, q) RSiC, r) TiC, s) ZrC, t) Ti.sub.2SiC, u) A1N, v) B.sub.4C, w) TiB.sub.2C, and x) MAX-phase material, wherein said MAX-phase material is layered, hexagonal carbides and nitrides which have the general formula of M.sub.n+1AX.sub.n where n = 1 to 4, and wherein M is an early transition metal selected from the group consisting of chromium, hafnium, molybdenum, niobium, scandium, titanium, vanadium and zirconium, and wherein A is a metal selected from the group consisting of aluminum, arsenic, cadmium, copper, gallium, gadolinium, germanium, indium, lead, sulfur, silicon, tin, thallium, vanadium, and zinc, and wherein X is carbon or nitrogen; said metal phase having a melting point of at least 1000° C.; said metal phase includes one or more metals selected from the group consisting of titanium, niobium, nickel, iron, cobalt, molybdenum, tantalum, hafnium, zirconium, rhenium, and tungsten.

55. The engineered multi-phase composite as defined in claim 54, wherein said filler includes MAX-phase material includes one or more compounds selected from the group consisting of V.sub.2AlC, Ti.sub.2AlC, Ti.sub.3SiC.sub.2, V.sub.3AlC.sub.2, Ti.sub.3AlC.sub.2, Ti.sub.4SiC.sub.3, and Ti.sub.3(Si.sub.0.5Ge.sub.0.5)C.sub.2.

56. The engineered multi-phase composite as defined in claim 54, further including active phase change material; said active phase change material including one or more materials selected from the group consisting of carbon, alumina ceramics, zirconia ceramics, boron oxide ceramics, silicon nitride ceramics, sialon, SSiC, LPS-SiC, RBSiC, NSiC, SiSiC, RSiC, SiC, TiC, ZrC, B.sub.4C, TiB.sub.2C, ceramic-coated copper, ceramic-coated zinc, ceramic-coated barium, ceramic-coated calcium, ceramic-coated cerium, ceramic-coated magnesium, ceramic-coated aluminum, ceramic-coated glasses, ceramic-coated metal salts, metal-encapsulated metals, metal-coated glasses, and metal-coated metal salts.

57. The engineered multi-phase composite as defined in claim 54, wherein said high thermal conductivity phase is at least partially coated with one or more materials selected from the group consisting of a) a metal material wherein said metal material is selected from one or more materials setungsten, HfN, ZrN, copper, zinc, boron, barium, calcium, cerium, manganese, magnesium, nickel, and aluminum, and b) a metal slat wherein said metal salt is selected from the group consisting of nitrate, chloride, flouride, and bromide.

58. The engineered multi-phase composite as defined in claim 54, wherein said metal phase includes a) at least 50% wt.% niobium; b) at least 50 wt.% titanium; c) at least 40 wt.% nickel; d) at least 35 wt.% iron; e) at least 50 wt.% molybdenum; f) at least 89 wt.% tantalum, g) at least 40 wt.% rhenium, or h) at least 30 wt.% cobalt.

59. The engineered multi-phase composite as defined in claim 54, further including an outer coating; said outer coating including one or more materials selected from the group consisting of iridium, platinum, rhenium, rhodium, magnesium silicide, geranium silicide, tin silicide, lead silicide, calcium silicide, ruthenium silicide, cesium silicide, rhodium silicide, iridium silicide, nickel silicide, MCrAl wherein M includes iron, nickel and/or cobalt, and MCrAlY wherein M includes iron, nickel and/or cobalt, aluminum, aluminum alloys, and chrome alloys.

60. The engineered multi-phase composite as defined in claim 54, wherein said high thermal conductivity phase includes ceramic particles and/or agglomerate particles of 15-400 micron in size.

61. The engineered composite as defined in claim 54, further including a binder phase; said binder phase includes one or more of carbon, polymer derived carbon, Bi.sub.2O.sub.3, SiO.sub.2, LiAlSiO.sub.4, and TiO.sub.2.

62. The engineered composite as defined in claim 54, wherein said high thermal conductivity phase is encapsulated with a single or multilayer shell.

63. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is configured for use above 700° C. surface temperatures without damage to said engineered multi-phase composite.

64. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite includes a ceramic leading edge.

65. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite forms a heat exchanger structure.

66. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is used between a heat source and an insulating support or backing structure.

67. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is included a piston, piston liner, engine duct, combustor, or engine exhaust.

68. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is included in a hypersonic launch or reentry vehicle airframe, leading edge, acreage TPS, duct, flap, or seal.

69. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is used in exhaust-impinged structures, nozzles or nozzle components, flaps, rings, channels, panels, or cowls.

70. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is included in molten salt storage, a heat exchanger, a molten salt system or a molten salt tank lining.

71. The engineered multi-phase composite as defined in claim 54, wherein an outer surface of said engineered multi-phase composite includes insulation, and wherein such insulation is rigid or flexible.

72. The engineered multi-phase composite as defined in claim 71, wherein said insulation includes one or more materials selected from the group consisting of zirconia, stabilized zirconia, mullite, aluminosilicate, BAS, or EBC (environmental barrier coating).

73. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is supported by and attached to a steel, superalloy, nickel-based alloy, titanium, or aluminum to transfer loads to the ground, vehicle, airframe, or between components or panels.

74. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is included in a panel or component intersections that are impermeable.

75. The engineered multi-phase composite as defined in claim 54, wherein said engineered multi-phase composite is used with a standoff that has been placed between a higher temperature component and a load-bearing structural system, to remove, spread, and/or dissipate thermal energy to reduce overall system temperatures and/or control thermal stresses.

76. A method for forming an engineered multi-phase composite comprising a. providing a metal material to form a metal phase b. providing a high thermal conductivity material wherein i. said high thermal conductivity material has at least 40% higher thermal conductivity than said metal phase; and, ii. said high thermal conductivity material contains a CTE material; and, c. consolidating said high thermal conductivity material with said metal material to form said engineered multi-phase composite, wherein the high conductivity and CTE materials may be combined into a composite particle, wherein said phase form by said high thermal conductivity material is discontinuous in said engineered multi-phase composite, said metal phase is continuous phase in said engineered multi-phase composite, said engineered multi-phase composite has a CTE that is at least 10% less than the CTE of said metal forming said metal phase, said engineered multi-phase composite has a thermal conductivity that is at least 20% greater than a thermal conductivity of said metal that forms said metal phase, and wherein said engineered multi-phase composite is formed into a thermal managing part, said thermal managing part is attached to an insulating structure or layer.

77. The method as defined in claim 76, wherein said engineered multi-phase composite is included in one or more structures selected from the group consisting of a load-bearing airframe structure, a hypersonic launch or reentry vehicle airframe, thermal transition piece, leading edge, acreage TPS, duct, flap, or seal to resist aerodynamic heating, exhaust-impinged structures, nozzles or nozzle components, flaps, rings, channels, panels, or cowls, exhaust and engine flowpath, a heat exchanger, a molten salt contacted component or structure, a valve structure, a pump component, or jet blast deflector panel.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0199] Reference may now be made to the drawings, which illustrate various embodiments that the present disclosure may take in physical form and in certain parts and arrangements of parts wherein:

[0200] FIG. 1 illustrates a conceptual design of sharp leading edge integration enabled through thermally tailored syntactic metal matrix composites in accordance with the present disclosure.

[0201] FIG. 2 illustrates a UHTC ceramic leading edge and syntactic metal aeroshell structure utilizing low cost, reliable (ductile) thermally-engineered metallic composites in accordance with the present disclosure.

[0202] FIG. 3 illustrates a leading edge conceptual design for a heat spreader/adapter in accordance with the present disclosure.

[0203] FIG. 4 illustrates a filler that includes a cavity which is filled with a phase change material such as salt mixture, alkali metal, metal alloy, and the outer surface of the filler is coated with a metal material.

[0204] FIG. 5 illustrates a method for forming the engineered metallic composites in accordance with the present disclosure by a powder metallurgy manufacturing process.

[0205] FIG. 6 illustrates a plot depicting the thermal conductivity of several of the highest thermally conductive materials. Above 800° C. the primary choices for high thermal conductive material are cubic boron nitride and diamond.

[0206] FIG. 7 illustrates a SEM micrograph of an engineered multi-phase composite comprising of a 35 vol.% high thermal conductive phase cubic boron nitride (black particles), and 10 vol.% tungsten additive for increased toughness and hardness (white particles) in a Nb752 alloy composite.

[0207] FIG. 8 illustrates thermal and mechanical property trends over temperature (based on theoretical and empirical trending) for several HybriTherm MA956 engineered multi-phase composites of varying density.

[0208] FIG. 9 illustrates thermal and mechanical property trends over temperature (based on theoretical and empirical trending) for several HybriTherm IN783 engineered multi-phase composites of varying density.

[0209] FIG. 10 illustrates thermal and mechanical property trends over temperature (based on theoretical and empirical trending) for several HybriTherm Nb752 engineered multi-phase composites of varying density.

[0210] FIG. 11 illustrates thermal and mechanical property trends over temperature (based on theoretical and empirical trending) for several HybriTherm Ti6242 engineered multi-phase composites of varying density.

DETAILED DESCRIPTION OF THE PRESENT DISCLOSURE

[0211] A more complete understanding of the articles/devices, processes and components disclosed herein can be obtained by reference to the accompanying drawings. These figures are merely schematic representations based on convenience and the ease of demonstrating the present disclosure, and are, therefore, not intended to indicate relative size and dimensions of the devices or components thereof and/or to define or limit the scope of the exemplary embodiments.

[0212] Although specific terms are used in the following description for the sake of clarity, these terms are intended to refer only to the particular structure of the embodiments selected for illustration in the drawings and are not intended to define or limit the scope of the present disclosure. In the drawings and the following description below, it is to be understood that like numeric designations refer to components of like function.

[0213] The singular forms “a,” “an,” and “the” include plural referents unless the context clearly dictates otherwise.

[0214] As used in the specification and in the claims, the term “comprising” may include the embodiments “consisting of” and “consisting essentially of.” The terms “comprise(s),” “include(s),” “having,” “has,” “can,” “contain(s),” and variants thereof, as used herein, are intended to be open-ended transitional phrases, terms, or words that require the presence of the named ingredients/steps and permit the presence of other ingredients/steps. However, such description should be construed as also describing compositions or processes as “consisting of” and “consisting essentially of” the enumerated ingredients/steps, which allows the presence of only the named ingredients/steps, along with any unavoidable impurities that might result therefrom, and excludes other ingredients/steps.

[0215] Numerical values in the specification and claims of this application should be understood to include numerical values which are the same when reduced to the same number of significant figures and numerical values which differ from the stated value by less than the experimental error of conventional measurement technique of the type described in the present application to determine the value.

[0216] All ranges disclosed herein are inclusive of the recited endpoint and independently combinable (for example, the range of “from 2 grams to 10 grams” is inclusive of the endpoints, 2 grams and 10 grams, and all the intermediate values).

[0217] The terms “about” and “approximately” can be used to include any numerical value that can vary without changing the basic function of that value. When used with a range, “about” and “approximately” also disclose the range defined by the absolute values of the two endpoints, e.g. “about 2 to about 4” also discloses the range “from 2 to 4.” Generally, the terms “about” and “approximately” may refer to plus or minus 10% of the indicated number.

[0218] Percentages of elements should be assumed to be percent by weight of the stated element, unless expressly stated otherwise.

[0219] The present disclosure pertains to the design and materials of construction of structures in which thermal or other strain-induced loads (such as constrained thermal growth and thermal gradient loads) contribute a large portion of the stresses. In particular, the present disclosure pertains to a structured multi-phase composite which includes a metal, a ceramic, and/or a phase change material that is arranged to create a higher thermal conductivity, have controlled stiffness, and a controlled CTE to reduce thermal stresses in the structure when exposed to cyclic thermal loads. The structured multi-phase composite is useful for use in structures such as, but not limited to, heat exchangers, high speed engine ducts, exhaust-impinged structures, and high speed and reentry aeroshells.

[0220] The structured multi-phase composite typically has reduced stiffness, increased thermal conductivity or improved heat sink capabilities, and/or a CTE that is appropriate for use in thermally-loaded structures. The present disclosure advances current hot structure designs and incorporates a multifunctional (thermally-engineered/thermally-conductive) structured multi-phase composite, replacing pure ceramic or heavy heat sink or expensive actively-cooled structures with a passive thermal management structure. The structured multi-phase composite serves as a load-bearing structural element and can optionally be stiffened with ribs and/or supports, or optionally engineered with surfaces to enhance heat dissipation via convection or radiation. The structured multi-phase composite can optionally be constructed as panels that are attached to a frame, or as an isogrid or skin-stringer or other J-stiffened panel construction or I-stiffened panel construction. These types of constructions can be used to reduce or eliminate the large costs, reliability concerns, and fabrication difficulties (e.g., complex curved panels, etc.) of ceramics and ceramic composites. The structured multi-phase composite has very high thermal conductivity (e.g., 4.6 g/cc IN625 structured multi-phase composite has thermal conductivity approaching/equivalent to aluminum or SiC ceramic) and can be engineered with low modulus to reduce thermal stress and thermal distortion/deformation. The use of the structured multi-phase composite of the present disclosure can result in a tremendous advantage for use in multifunctional materials. Because a portion of the materials used in the structured multi-phase composite are metallic and have low flaw sensitivity (particularly at elevated temperatures), they can be threaded, bolted, riveted, and assembled using techniques used for the last 100 years of aviation structures.

Non-Limiting Application for High Temperature TPS

[0221] One non-limiting application of the structured multi-phase composite is used as a multifunctional material suitable for integration of ultra-high temperature (UHT) ceramic leading edges into integral structural thermal protection systems (aeroshells) systems. UHT ceramics (e.g., boride-SiC-silicide composites) enable sharp leading edges that enable good aerodynamic stability, but have significant integration, reliability, and cost issues. The structured multi-phase composite of the present disclosure provides a solution to extract and spread heat, but that can also simultaneously manage thermal growth and thermal gradient strains. The thermally-engineered, structured multi-phase composite is based on syntactic metal matrix composites (SMMCs) that can be engineered specifically for managing extreme thermal stress environments such as, but not limited to, hypersonic vehicle structures. The thermally-engineered structured multi-phase composite can be designed as a transition material between UHT leading edges and integral TPS structures. The structured multi-phase composite can be designed for 850-1500° C. applications that can extract and spread heat while managing thermal growth stresses to maintain the ceramic leading edge in compression throughout the flight profile.

[0222] FIG. 1 illustrates a non-limiting leading edge integration design 100 and the location of the hybrid thermal structured multi-phase composite (“HybriTherm”) materials. FIG. 1 illustrates a conceptual design of sharp leading edge integration enabled through thermally-tailored syntactic metal matrix composites. The integration requires high thermal conductivity, while the aeroshell is low conductivity.

[0223] Designing a compact and affordable hypersonic vehicle imposes serious demands on the combined structural weight of the vehicle itself and the associated thermal protection system (TPS). Emphasis is placed on the structure’s strength and achieving the lowest mass and thermal conductivity (of the acreage structure) to maximize payload and affordability, while solving attachment, reliability (due to thermal stresses/strains and use of ceramic materials), and integration issues that have plagued TPS systems. The thermally-engineered multi-phase composite of the present disclosure enables integration of sharp leading edge structures utilizing UHTC ceramic inserts into a high thermal conductivity, controlled thermal strain integration material.

[0224] A non-limiting segmented UHTC insert of FIG. 1 and integration scheme is illustrated in FIG. 2. FIG. 2 illustrates a UHTC ceramic leading edge and syntactic metal aeroshell structure utilizing low cost, reliable (ductile) thermally-engineered metallic composites.

[0225] A less complex assembly is illustrated in FIG. 3. FIG. 3 illustrates a leading edge conceptual design for a HybriTherm adapter (e.g., heat spreader/adapter). The shape and size of the overlap and the length of the heat spreader can be evaluated to select a design for fabrication and testing.

[0226] For a heat-impinged structure, the multifunctional high thermal conductivity structured multi-phase composite can be used as a cover over a thermally-insulating structure to spread thermal point loads while protecting an underlying structure. One such application is a jet blast deflector wherein an exhaust plume of up to 1500° C. or more impinges an area. When such a deflector is fabricated from steel, the jet blast deflector must be actively cooled. With a thermally-conductive structure faceplate that uses the multifunctional high thermal conductivity structured multi-phase composite of the present disclosure as a covering insulator, the heat can be moved away from the point of application by passive radiation or air-cooling, while preventing significant temperature rise in the deflector (and therefore buckling and warpage) of the underlying steel or other metal structure.

[0227] Another non-limiting application is to manage heat in engine structures. Adding high thermal conductivity fillers, such as BN or carbon, into aluminum or magnesium engine structures allows for increased heat transfer to either the air (air-cooled engines, such as motorcycles) or to oil or water fluids (conventional engines) so as to remove heat and allow thinner, lighter engines to be manufactured with improved fuel economy.

Production of Structured Multi-Phase Composite

[0228] The structure of the structured multi-phase composite is a syntactic composite in which the filler is roughly spherical (axisymmetrix, or equiaxed) and normally added to the metal during processing as microspheres or microcapsules. In general, the structured multi-phase composite can be fabricated by powder metallurgy techniques or via melt casting techniques. As illustrated in FIG. 4, a high thermal conductivity phase or filler 70 is provided that can optionally include a cavity 72 which can be optionally filled with a phase change material such as salt mixture, alkali metal, metal alloy, generally with a phase change temperature of 300-1350° C., and typically 650-1150° C. The outer surface of the high thermal conductivity phase or filler is coated with a metal material 80. The type of coating process used, the composition of the metal coating, and the thickness of the metal coating depends on the final application for the formed structured multi-phase composite. The coated high thermal conductivity phase or filler is then consolidated together to form the structured multi-phase composite 90.

[0229] An additional metal 92 can be added during the consolidation process.

[0230] FIG. 5 illustrates a non-limiting powder metallurgy manufacturing sequence.

[0231] Due to the high density difference between the high thermal conductivity phase and the metal phase and the reactivity of materials at high temperatures, higher temperature materials (including titanium, niobium alloys (C103, CB752), molybdenum (TZM), tungsten, tantalum, nickel alloys, and superalloys such as IN909, IN718, MA956, IN625, FeCrAlY’s, HAYNES 230, etc.) are normally fabricated using powder metallurgy techniques. Lower melting and lower density materials, such as magnesium and aluminum, can be manufactured using casting techniques such as thixomolding (semi-solid forming), squeeze casting, pressure or pressureless infiltration casting into a preform, or even stir casting. Powder metallurgy techniques include spark plasma sintering, other field-assisted sintering, pressureless sintering, hot pressing, hot isostaic pressing, injection molding, and other powder metallurgy techniques.

[0232] To reduce interface thermal resistance and enable wetting for melt infiltration, or to reduce contiguity by forming a transient liquid phase, a coating can be optionally applied to the high thermal conductivity phase prior to infiltration or coating. The coating can serve to enhance wetting (e.g., nickel, boron, copper, aluminum, and/or titanium), reduce contact resistance (e.g., tungsten and/or copper), control separation/volume fraction of the high thermal conductivity phase in a preform or during processing (any material, powders preferred), and prevent contiguity to increase toughness and strength (any method). Several techniques have been demonstrated, including adding a metal coating by such techniques as powder coating (wurster or other encapsulation technique), with or without presintering, CVD or other vapor solid coating, electroplating, molten salt plating, and other techniques. One non-limiting coating technique is powder encapsulation through a mixing process, such as wurster or other fluid bed coating, or ribbon or high shear blending of a ceramic or preceramic polymer balloon, metal powders, a clean burning (thermal removal) or easily removed binder such as PEG, wax, polysacharrides, other low ash content or easily vaporized binders, and a solvent.

[0233] In one non-limiting embodiment, heated high thermal conductivity phase particles are added to a bed of solid binder plus metal powder, which is adhered to the surface. Wax, PVB (polyvinyl butyral), and/or other low melting binders can be used in that process. A binder can be applied to the high thermal conductivity phase surface and heated to its melting point; the binder-coated high thermal conductivity phase can then be added to a bed of metal powder. In general, the metal powder size is less than ⅙.sup.th of the high thermal conductivity phase size, typically less than ⅒.sup.th of the high thermal conductivity phase size, and more typically less than 1/50.sup.th of the high thermal conductivity phase size.

[0234] Using a powder or metal-coated ceramic high thermal conductivity phase, additional metal is normally added by blending. Normally, the mixing is used to fill between the ceramic balloons to maximum green packing density. Multiple size particles of high thermal conductivity phase can be used for similar purposes to fill interstices, generally with particle cuts ¼.sup.th -⅙.sup.th of the prior size cut.

[0235] For melt-infiltrated materials, a wetting coating can be used for infiltration techniques and for other casting (thixocasting). This wetting coating can be a ceramic such as TiN, copper, silicide, and/or tungsten, but is most commonly a eutectic-forming or active metal. The wetting coating can be added as a powder or coated onto the surface. The metals can include the matrix metal, zinc, nickel, copper, titanium, silicon, palladium, among others. Most often, active metals (e.g., titanium, silicon, zirconium, palladium, etc.) are used to enhance wetting.

[0236] To control mechanical properties of the structured multi-phase composite, particularly tensile and fracture toughness, it is desirable to ensure that the ceramic phases are not contiguous (not touching). A contiguity below 0.2, and generally below 0.1 or 0.05 is desired. The desired contiguity can be controlled by wetting, powder mixing, and/or by adding a powder coating to separate the high thermal conductivity phase during the infiltration processes. The desired contiguity can also be achieved or enhanced by post-fabrication deformation processing, such as by constrained rolling or forging.

[0237] In one non-limiting embodiment, the high thermal conductivity phase is coated with a metal or metal alloy powder and then melt infiltrated with the matrix material. The powder-coated fillers can be presintered or added to a container and constrained while infiltration takes place; however, this is not required.

[0238] For improved corrosion resistance (mainly oxidation) and to increase temperature limits, the structured multi-phase composite thermal structure can be coated. For hypersonic and other high temperature structures, a thermal barrier coating such as, but not limited to, mullite, BSA, other aluminosilicates, and/or zirconia (generally yttria-stabilized zirconia) can be applied. These are generally applied between 10-100 mils (0.01″-0.1”) using plasma spray processes; however, other coating processes such as solution spray or slurry coating can also be used.

[0239] Oxidization coatings can be used and typically depend on the materials system. For titanium systems, MCrAlY or nickel-copper-chromium-aluminum alloy coatings applied by thermal spray, PVD, or slurry coating are very effective. For niobium alloys, silicide slurry coatings containing chrome and silicon, such as R512E from HiTempco™ are very effective. Titanium-chromium-silicon, and vanadium-chromium-silicon can be used, but molybdenum-, tungsten-, and iron-containing silicide systems can also be effective. For superalloy and nickel-based alloy systems, MCrAlY coatings and diffusion coatings, including those applied by pack aluminizing, can be used. For molten salt storage systems, multi-phase composites made from nickel-based alloys, such as HAYNES®230® alloy (e.g., 55-60 wt.% nickel, 20-24 wt.% chromium, 12-16 wt.% tungsten, 0-4 wt.% molybdenum, <4 wt.% iron, < 6 wt.% cobalt, 0-1 wt.% manganese, 0-1 wt.% silicon,, 0-1 wt.% niobium, 0-1 wt.% aluminum, 0-0.5 wt.% titanium, <0.3 wt.% carbon) or Hastelloy-N (e.g., 68-73 wt.% nickel, 5-8 wt.% chromium, 14-18 wt.% molybdenum, <6 wt.% iron, 0-2 wt.% silicon, 0-1 wt.% manganese, 0-1 wt.% vanadium, <0.2 wt.% carbon, <0.5 wt.% cobalt, <0.5 wt.% copper, 0-1 wt. % tungsten, <0.6 wt.% aluminum, <0.6 wt.% titanium exhibit excellent resistance to molten salts. Additional aluminizing, or using a lower cost iron alloy with a graded, coated, or layered high nickel alloy surface can be used for operation above 650° C.

EXAMPLES

[0240] Example 1: A high speed vehicle airframe panel was designed using a ceramic leading edge insert and an insulating structure. A thermal transition piece is fabricated from a BN-filled FeCrAlY, in the structure illustrated in FIGS. 1 or 2 or 3. The HybriTherm thermally-engineered attachment structure includes a MA956 alloy (37-57 wt.% iron, 16-23 wt.% chromium, 2-7 wt.% aluminum, 0-1 wt.% titanium, 0-1 wt.% copper, 0-1 wt.% manganese, 0-1 wt.% cobalt, 0-1 wt.% nickel, 0-1 wt.% Y.sub.2O.sub.3, <0.2 wt.% carbon) multi-phase composite that is fabricated by premixing 40 vol.% of 60 micron D50 spheroidized BN fillers (boron nitride), which possess a 80-92 wt.% increase (and all values and ranges therebetween) addition of nickel coating by a solution based adsorption method, with 15-35 vol.% (and all values and ranges therebetween) (e.g., 25 vol.%) of 1-10 micron powder (and all values and ranges therebetween) mixture of 70-80 wt.% iron (and all values and ranges therebetween) (e.g., 75.5 wt.% iron), 15-25 wt.% chromium (and all values and ranges therebetween) (e.g., 20 wt.% chromium), and 1-6 wt.% aluminum (and all values and ranges therebetween) (e.g., 4 wt.% aluminum), with less than 1 wt.% titanium and less than 1 wt.% yttrium using a spray-coating technique using 1-4 % (and all values and ranges therebetween) (e.g., 2%) of 2500-4000 MW (and all values and ranges therebetween) (e.g., 3000 MW) PEG in acetone to adhere them to the microballoons and then subsequently blending in an additional 20-30 vol.% (and all values and ranges therebetween) (e.g., 25 vol.%) of 250-400 mesh (and all values and ranges therebetween) (e.g., 325 mesh) prealloyed MA956 (or roughly compositional equivalent gas-atomized alloy used in plasma spray) powder. The material is spark plasma sintered at 950-1200° C. (and all values and ranges therebetween) (e.g., 1000° C.) and 5-40 MPa (and all values and ranges therebetween) (e.g., 20 MPa) pressure in graphite dies. After spark plasma sintering for 20 minutes, the material was EDM machined into an attachment structure, which assembled with a UHTC lead edge insert. The material demonstrates a 350-450% increase (and all values and ranges therebetween) in thermal conductivity at 300° C. compared to its parent metal, MA956. Additional property modifications include a 30-45% reduction (and all values and ranges therebetween) in modulus and a 30-45% reduction (and all values and ranges therebetween) in density.

[0241] Example 2: A multi-phase composite panel was fabricated using powder metallurgy processing from Hastelloy-N (e.g., 68-73 wt.% nickel, 5-8 wt.% chromium, 14-18 wt.% molybdenum, <6 wt.% iron, 0-2 wt.% silicon, 0-1 wt.% manganese, 0-1 wt.% vanadium, <0.2 wt.% carbon, <0.5 wt.% cobalt, <0.5 wt.% copper, 0-1 wt. % tungsten, <0.6 wt.% aluminum, <0.6 wt.% titanium) and alloy powders using the sequence described in Example 1, but sintered at 950-1200° C. (and all values and ranges therebetween) (e.g., 1080° C.). The material was fabricated into thin sheets, which were alternately etched with complex channels. The solid panels and machined panels were stacked and spark plasma bonded into a solid core of a heat exchanger. The material demonstrates a 400-500% increase (and all values and ranges therebetween) in thermal conductivity compared to its parent metal, Hastelloy-N. Additional property modifications include a 65-90% reduction (and all values and ranges therebetween) reduction in modulus, a 5-15% reduction (and all values and ranges therebetween) in CTE, and a 30-45% reduction (and all values and ranges therebetween) reduction in density.

[0242] Example 3: A magnesium multi-phase composite electronic box was fabricated by melt infiltrating a calcium-modified AZ61 alloy containing calcium and cerium (85-92 wt.% magnesium, 5.80-7.2 wt.% aluminum, 0.4-1.5 wt.% zinc, up to 0.15 wt.% manganese, up to 0.1 wt.% silicon, up to 0.05 wt.% copper, up to 0.005 wt.% nickel, up to 0.005 wt.% iron, up to 2 wt.% calcium, up to 1 wt.% cerium, up to 1.5 wt.% graphene platelets) into a 35-50 vol.% (and all values and ranges therebetween) (e.g., 40 vol.%) spheroidized BN filler preform space using prealloyed AZ61 (88-92 wt.% magnesium, 5.80-7.2 wt.% aluminum, 0.4-1.5 wt.% zinc, up to 0.15 wt.% manganese, up to 0.1 wt.% silicon, up to 0.05 wt.% copper, up to 0.005 wt.% nickel, up to 0.005 wt.% iron) + titanium powders applied (blended) to the fillers using squeeze casting. The 2″ thick billets were extruded into a complex finned profile for use as heat sinks in electronic boxes.

[0243] Example 4: A molten salt interior insulator liner was designed and fabricated from a diamond-filled IN783 syntactic metal composite (e.g., 33-42 wt.% cobalt, 24-32 wt.% nickel, 22-30 wt.% iron, 2-5 wt.% chromium, 2-5 wt.% niobium, 4-7 wt.% aluminum, 0-1 wt.% manganese, 0-1 wt.% silicon, 0-1 wt.% copper, 0-0.8 wt.% titanium, 0-0.2 wt.% boron, <0.1 wt.% copper) with added negative thermal expanding filler. The HybriTherm thermally-engineered liner comprising of IN783 alloy multi-phase composite that is fabricated by v-blend premixing 20-40 vol.% (and all values and ranges therebetween) (e.g., 30 vol.%) of 70-150 micron (and all values and ranges therebetween) (e.g., 100 micron) D50 irregular shaped diamond grit coated with 10-30 wt.% (and all values and ranges therebetween) (e.g., 20 wt.%) diamond, TiN by a fluid bed-CVD method, with 50-70 vol.% (and all values and ranges therebetween) (e.g., 60 vol.%) of 1-10 (and all values and ranges therebetween) micron elemental powder mixture of 22-28 wt.% iron (and all values and ranges therebetween) (e.g., 26 wt.% iron), 1-5 wt.% chromium (and all values and ranges therebetween) (e.g., 3 wt.% chromium), 4-7 wt.% aluminum (and all values and ranges therebetween) (e.g., 5.5 wt.% aluminum), 24-30 wt.% nickel (and all values and ranges therebetween) (e.g., 28 wt.% nickel), 1-4 wt.% niobium (and all values and ranges therebetween) (e.g., 3 wt.% niobium), 32-36 wt.% cobalt (and all values and ranges therebetween) (e.g., 34.25 wt.% cobalt), and 0-1 wt.% titanium powders (and all values and ranges therebetween) (e.g., 0.25 wt.% titanium powders). A secondary additive filler was added of negative CTE HfV.sub.2O.sub.7 in the amount of 4-15 vol.% (and all values and ranges therebetween) (e.g., 10 vol.%). The material mixture was fabricated into an insert liner by hot isostatic pressing sintered at 900-1200° C. (and all values and ranges therebetween) (e.g., 1050° C.) and 20-60 MPa pressure (and all values and ranges therebetween) (e.g., 40 MPa pressure) in a boron nitride coated stainless steel die. The material demonstrated a 400-700% increase (and all values and ranges therebetween) (e.g., 600% increase) in thermal conductivity at 750° C. compared to its parent metal, IN783. Additional property modifications include a 20-40% reduction (and all values and ranges therebetween) (e.g., 31% reduction) in modulus, a 18-32% increase (and all values and ranges therebetween) (e.g., 24% decrease) in CTE, and a 20-44% reduction (and all values and ranges therebetween) (e.g., 34% reduction) in density.

[0244] It will thus be seen that the objects set forth above, among those made apparent from the preceding description, are efficiently attained, and since certain changes may be made in the constructions set forth without departing from the spirit and scope of the present disclosure, it is intended that all matter contained in the above description and shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense. The present disclosure has been described with reference to preferred and alternate embodiments. Modifications and alterations will become apparent to those skilled in the art upon reading and understanding the detailed discussion of the present disclosure provided herein. This disclosure is intended to include all such modifications and alterations insofar as they come within the scope of the present disclosure. It is also to be understood that the following claims are intended to cover all of the generic and specific features of the present disclosure herein described and all statements of the scope of the present disclosure, which, as a matter of language, might be said to fall there between. The present disclosure has been described with reference to the preferred embodiments. These and other modifications of the preferred embodiments as well as other embodiments of the present disclosure will be obvious from the present disclosure herein, whereby the foregoing descriptive matter is to be interpreted merely as illustrative of the present disclosure and not as a limitation. It is intended to include all such modifications and alterations insofar as they come within the scope of the appended claims.