Metal founding – Process – Shaping liquid metal against a forming surface
Patent
1991-09-16
1993-01-26
Lin, Kuang Y.
Metal founding
Process
Shaping liquid metal against a forming surface
164 98, B22D 1904
Patent
active
051815508
ABSTRACT:
A turbine engine component is made by forming a heat resistant layer on each airfoil of a plurality of airfoils. This heat resistant layer has a higher melting temperature than the melting temperature of material forming the airfoil. After heat resistant layers have been formed on the airfoils, a mold is formed around the airfoils. Molten metal is poured into the mold. The molten metal engages the heat resistant layers on the airfoils and solidifies to form a shroud ring. As the molten metal solidifies, slip joints between the solidified metal and end portions of the airfoils are free of bonds. The heat resistant layer is at least partially formed of chromium sesquioxide (Cr.sub.2 O.sub.3). A layer of chromium sesquioxide is formed by heating a nickel-chrome superalloy airfoil. As the airfoil is heated, the layer of metal immediately adjacent to the outer surface of the airfoil is depleted of chromium. This results in the formation of an outer layer of chromium sesquioxide and an inner layer from which the chromium has been depleted. Both layers have a higher melting temperature than the melting temperature of the material forming the airfoil.
REFERENCES:
patent: 4728258 (1988-03-01), Blazek et al.
Blazek William S.
Wheaton Harold L.
Lin Kuang Y.
PCC Airfoils, Inc.
LandOfFree
Method of making a turbine engine component does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Method of making a turbine engine component, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Method of making a turbine engine component will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-1408010