Metal treatment – Stock – Nickel base
Reexamination Certificate
2001-05-18
2004-05-25
King, Roy (Department: 1742)
Metal treatment
Stock
Nickel base
C420S441000
Reexamination Certificate
active
06740176
ABSTRACT:
FIELD OF THE INVENTION
This invention concerns the composition of a metal alloy suitable for use as single crystal seeds.
BACKGROUND OF THE INVENTION AND PRIOR ART
Components cast as single crystals, using the process of directional solidification, generate a crystal atomic structure related to the growth of preferred crystal planes. In nickel base superalloys the resultant crystal has a structure determined by growth of the <001> crystal planes. This structure is aligned in the direction of solidification which is normally along the principal geometric axis of the component e.g. a gas turbine engine blade aerofoil.
In certain cases there are applications for components with crystal orientations different from the <001> produced under normal solidification conditions. Such applications include nozzle guide vanes and turbine blades requiring control of material rigidity.
To produce a crystal structure aligned in a direction other than the preferred solidification growth direction it is established practice to solidify from a seed crystal which has the required crystal structure. Solidification from these seeds is by epitaxial growth in which the molten superalloy solidifies directly from a partially melted seed crystal made from the same or equivalent superalloy as the cast component.
A drawback encountered with this known method of determining crystal growth direction during solidification is that a high level of castings are rejected because the seed crystals when partially molten are liable to generate unwanted oxide films which interrupt epitaxial growth of the single crystal and cause further crystals to solidify in which the atomic orientations are randomly distributed.
Epitaxial growth may also be interrupted if the alloy has a wide solidification temperature range (for example, greater than 50° C.). This is because an alloy having a wide solidification temperature range tends to form a large mushy zone during solidification (i.e. a zone in which liquid and solid phases coexist), in which random crystal growth can occur.
A principal objective of the present invention is to reduce the rejection rate of single crystal alloy castings.
A further objective of the present invention is to provide a formulation of an alloy suitable for use as a seed alloy for single crystal casting, which alloy does not produce oxide films under the directional solidification conditions used for the casting of superalloys.
A yet further objective of the present invention is to provide a formulation of an alloy suitable for use as a seed alloy for single crystal casting, which alloy has a relatively narrow solidification temperature range.
SUMMARY OF THE INVENTION
According to the present invention there is provided an alloy composition suitable for use as a single crystal seed, the alloy composition comprising nickel and, in the proportion of 5 to 50 weight %, a further metal selected from the Transition Series of elements in Period VI of the Periodic Table of Elements.
Preferably, the alloy composition contains no component which forms an oxide layer at the solidification temperature. In particular, the alloy composition contains no aluminium or titanium.
Preferred alloys in accordance with the present invention consist essentially of nickel and the further metal selected from the Transition Series of elements in Period VI of the Periodic Table of Elements. That is to say, the alloy composition preferably consists of those two components only, apart from incidental impurities, which should be minimised.
The further metal is preferably tungsten or tantalum, and is present in the range 13 to 50% by weight. Where the further metal is tungsten, it is more preferably present in the composition in the range 30 to 50% by weight. Where the further metal is tantalum, it is more preferably present in the composition in the range 25 to 45% by weight, for example approximately 30% by weight.
Preferred alloy compositions in accordance with the present invention are suitable for use in the manufacture of components such as gas turbine engine aerofoils and have a solidification temperature which is not less than 1250° C. and not more than 1450° C., and more preferably not less than 1300° C. and not more than 1400° C. Solidification takes place over a temperature range which is not greater than 50 C.°, and is preferably not greater than 20 C.°.
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ASM Handbook, vol. 3, “Alloy Phase Diagrams”.
Ford David A
Hill Anthony D.
King Roy
Oliff & Berridg,e PLC
Rolls-Royce plc
Wilkins, III Harry D
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