Method of making a turbine engine component
US5181550A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 16, 1991 |
| Grant date | Jan 26, 1993 |
| Priority date | — |
| Expiry date | Sep 16, 2011 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB22D19/04
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.