Provided are a Ni-based alloy for hot die having a high high-temperature compressive strength and a good oxidation resistance and being capable of suppressing the deterioration in the working environment and the shape deterioration, and a hot forging die made of the Ni-based alloy for hot die. The Ni-based alloy for hot die comprises, in mass %, W: 7.0 to 15.0%, Mo: 2.5 to 11.0%, Al: 5.0 to 7.5%, Cr: 0.5 to 3.0%, Ta: 0.5 to 7.0%, S: 0.0010% or less, one or two or more selected from rare-earth elements, Y, and Mg in a total amount of 0 to 0.020%, and the balance of Ni with inevitable impurities. In addition to the composition described above, one or two elements selected from Zr and Hf can further be contained in a total amount of 0.5% or less.

An alloy composition includes, by weight: 20% to 23% of Cr; 8% to 10% of Mo; 3.15% to 4.15% of Nb+Ta; 0.25% to 1.5% of B; 0.35% to 1.75% of N; and a balance of Ni.

A method for forming a component for a gas turbine engine may include forming a first portion of the component that includes a cast metal or metal alloy, forming a second portion of the component that includes presintered preform defining at least one support structure, positioning the second portion on the first portion to define an assembly such that the first portion and the second portion define at least one cooling channel therebetween, and heating the assembly to join the first portion and the second portion and form the component.

A porous body including a framework having a three-dimensional network structure, the framework having a body including nickel, cobalt, a first element and a second element as constituent elements, the cobalt having a proportion in mass of 0.2 or more and 0.8 or less relative to a total mass of the nickel and the cobalt, the first element including of at least one element selected from the group including of boron, iron and calcium, the second element including of at least one element selected from the group consisting of sodium, magnesium, aluminum, silicon, potassium, titanium, chromium, copper, zinc and tin, the first and second elements together having a proportion in mass of 5 ppm or more and 50,000 ppm or less in total relative to the body of the framework.

Electric-powered, closed-loop, continuous-feed, endothermic energy-conversion systems and methods are disclosed. In one embodiment, the presently disclosed energy-conversion system includes a shaftless auger. In another embodiment, the presently disclosed energy-conversion system includes a drag conveyor. In yet another embodiment, the presently disclosed energy-conversion system includes a distillation and/or fractionating stage. The endothermic energy-conversion systems and methods feature mechanisms for natural resource recovery, refining, and recycling, such as secondary recovery of metals, minerals, nutrients, and/or carbon char.

The present invention relates to a substrate-triggered single crystal superalloy directional solidification process, including: (1) preparing a single crystal substrate material having crystallographic characteristics that match crystallographic characteristics of the single crystal superalloy; (2) fabricating a single crystal substrate chilling plate using the obtained single crystal substrate material; and (3) applying the obtained single crystal substrate chilling plate in a directional solidification apparatus, and then preparing a single crystal alloy product by performing superalloy melting and directional solidification. Compared with grain selector method and seeding with grain selector method, in addition to control the crystallographic orientation of the single crystal superalloy precisely, the present invention could reduce the height of block and the whole mold through canceling the spiral grain selector, significantly improve the axial heat dissipation and temperature gradient at the solid-liquid interface, and then reduce the occurrence of freckles and stray grains near platform.

A nickel-niobium intermetallic alloy contains, in weight percent, silicon from about 1.5 to about 3.5 percent; chromium from 5 to about 15 percent; nickel from about 45 to about 75 percent; niobium from about 14 to about 30 percent; cobalt up to about 7 percent; and iron up to about 10 percent; wherein the nickel plus niobium content is about 70 to about 90 percent and the total silicon, chromium, cobalt and iron content is about 10 to about 30 percent. The alloy can have a cast microstructure of at least 95 volume percent intermetallic phases and no more than about 5 volume percent solid solution phases. The intermetallic phases can include rod-like intermetallic phases of Ni.sub.3Nb and Ni.sub.8Nb.sub.7. The microstructure can be a lamellar microstructure and/or the microstructure can have less than 5 volume percent Ni—Fe and Ni—Co rich intermetallic phases.

Provided are a Ni-based heat resistant superalloy for aircraft engine cases excellent in high-temperature characteristic such as tensile characteristics and low-cycle fatigue characteristics in a high-temperature range and also excellent in workability, and an aircraft engine case formed of the same. The Ni-based heat resistant superalloy has composition containing, by mass, Co: 4.0 to 11.0%, Cr: 12.0 to 17.0%, Al: 2.0 to 4.0%, Ti: 2.0 to 4.0%, Al+Ti: 4.6 to 6.7%, Mo: more than 5.5 to 10.0%, W: more than 0 to 4.0%, B: 0.001 to 0.040%, C: 0.02 to 0.06%, Zr: 0 to 0.05%, Mg: 0 to 0.005%, P: 0 to 0.01%, Nb: 0 to 1.0%, Ta: 0 to 1.0%, and Fe: 0 to 2.0%, and the balance of Ni with inevitable impurities, and is suitable for aircraft engine cases.

Provided are a Ni-based heat resistant superalloy for aircraft engine cases excellent in high-temperature characteristic such as tensile characteristics and low-cycle fatigue characteristics in a high-temperature range and also excellent in workability, and an aircraft engine case formed of the same. The Ni-based heat resistant superalloy has composition containing, by mass, Co: 4.0 to 11.0%, Cr: 12.0 to 17.0%, Al: 2.0 to 4.0%, Ti: 2.0 to 4.0%, Al+Ti: 4.6 to 6.7%, Mo: more than 5.5 to 10.0%, W: more than 0 to 4.0%, B: 0.001 to 0.040%, C: 0.02 to 0.06%, Zr: 0 to 0.05%, Mg: 0 to 0.005%, P: 0 to 0.01%, Nb: 0 to 1.0%, Ta: 0 to 1.0%, and Fe: 0 to 2.0%, and the balance of Ni with inevitable impurities, and is suitable for aircraft engine cases.

A precipitation hardenable, cobalt-nickel base superalloy is disclosed. The is characterized by the following weight percent composition. C about 0.01 to about 0.15 Cr about 6.00 to about 15.00 Ni about 30.00 to about 45.00 W about 3.00 to about 15.00 Ti about 0.50 to about 4.00 Al about 3.00 to about 7.00 Nb up to about 2.50 Ta up to about 6.00 Hf up to about 1.50 Zr up to about 1.50 B up to about 0.20 Mo up to about 2.50 Si up to about 1.50
The balance of the alloy is cobalt and usual impurities. The alloy provides a novel combination of strength and ductility after long-term exposure to elevated operating temperatures as found in gas turbines and jet engines. A fine-grain steel article made from the alloy is also disclosed. The steel article is also characterized by a continuous surface layer of Al.sub.2O.sub.3 and Cr.sub.2O.sub.3 that protects the alloy from oxidation at the elevated operating temperatures.