A nickel-based superalloy composition is provided that includes 6.1 wt. % to 6.6 wt. % aluminum; 5.6 wt. % to 6.6 wt. % tantalum; 9.0 wt. % to 11.0 wt. % chromium; 5.5 wt % to 6.2 wt. % tungsten; 1.1 wt. % to 1.4 wt % molybdenum; 2.0 wt. % to 2.6 wt % rhenium; 5.5 wt. % to 10.0 wt % cobalt; 0.2 wt % to 0.5 wt % hafnium; up to 0.05 wt % carbon; 0.002 wt % to 0.01 wt % boron; and a balance of nickel and incidental impurities, wherein the composition exhibits a rupture life that is greater than 40 hours at 982.2° C. and 40 ksi, and wherein the composition exhibits a corrosion resistance of less than 50.8 μm attack at 926.7° C. after a 940 hour burner rig test. Components are also provided formed from the composition.

A nickel-based superalloy is provided, which includes: 5.6 wt % to 6.6 wt % aluminum; 6.0 wt % to 9.0 wt % tantalum; 4.0 wt % to 7.0 wt % chromium; 4.0 wt % to 7.0 wt % tungsten; 0.5 wt % to 2.5 wt % molybdenum; 1.5 wt % to 5.5 wt % rhenium; 7.0 wt % to 13.0 wt % cobalt; 0.1 wt % to 0.7 wt % hafnium; 0.001 wt % to 0.005 wt % carbon; 0.002 wt % to 0.05 wt % boron; up to 0.1 wt % yttrium; and a balance of nickel and incidental impurities, wherein the composition exhibits a rupture life that is greater than 80 hours at 1093.3° C. and 20 ksi and an oxidation resistance of less than 25.4 μm surface loss at 1176.7° C. after a 400 hour Mach I test. Components are also provided formed from such a nickel-based superalloy.

A casting method includes forming a seed. The seed has a first end and a second end. The forming includes bending a seed precursor. The seed second end is placed in contact or spaced facing relation a chill plate. The first end is contacted with molten material. The molten material is cooled and solidifies so that a crystalline structure of the seed propagates into the solidifying material. The forming further includes inserting the bent seed precursor into a sleeve leaving the bent seed precursor protruding from a first end of the sleeve.

A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

A casting method includes forming a seed. The seed has a first end and a second end. The forming includes bending a seed precursor. The seed second end is placed in contact or spaced facing relation a chill plate. The first end is contacted with molten material. The molten material is cooled and solidifies so that a crystalline structure of the seed propagates into the solidifying material. The forming further includes inserting the bent seed precursor into a sleeve leaving the bent seed precursor protruding from a first end of the sleeve.

A turbine component includes a substrate made from monocrystalline nickel-based superalloy including rhenium, which has a γ-γ′ Ni phase, and an average weight faction of chromium of less than 0.08, a sublayer made from nickel-based metal superalloy covering the substrate, in which the sublayer made from metal superalloy includes at least aluminium, nickel, chromium, silicon, hafnium and has, predominantly by volume, a γ′-Ni 3 Al phase.

A nickel-based superalloy includes, in weight percent, 6 to 8% aluminum, 12 to 15% cobalt, 4 to 8% chromium, 0 to 0.2% hafnium, 0.5 to 4% molybdenum, 3.5 to 6% rhenium, 4 to 6% tantalum, 1 to 3% titanium, 0 to 2% tungsten, 0 to 0.1% silicon, the balance being nickel and unavoidable impurities.

A nickel-based superalloy includes, in weight percent, 4 to 6% aluminum, 5 to 8% cobalt, 6 to 9% chromium, 0.1 to 0.9% hafnium, 2 to 4% molybdenum, 5 to 7% rhenium, 5 to 7% tantalum, 2 to 5% tungsten, 0 to 0.1% silicon, the balance being of nickel and unavoidable impurities.

A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.

The present invention concerns a turbine part comprising a substrate made of nickel-based monocrystalline superalloy, comprising chromium and at least one element chosen among rhenium and ruthenium, the substrate having a γ-γ′ phase, an average mass fraction of rhenium and of ruthenium greater than or equal to 4% and an average mass fraction of chromium less than or equal to 5% and preferably less than or equal to 3%, a sub-layer covering at least a part of a surface of the substrate, characterised in that the sublayer has a γ-γ′ phase and an average atomic fraction of chromium greater than 5%, of aluminium between 10% and 20% and of platinum between 15% and 25%.