| Patent application number | Description | Published |
|---|
| 20090000101 | Methods for Repairing Gas Turbine Engines - Methods for repairing gas turbines are provided. A representative method includes: identifying an affected area of a surface of a component of the gas turbine, the surface of the component defining a portion of a gas flow path through the gas turbine; applying an epoxy-based filler to the affected area; curing the epoxy-based filler; and blending the epoxy-based filler with the surface of the component. | 01-01-2009 |
| 20090064500 | METHOD OF REPAIRING A TURBINE ENGINE COMPONENT - The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component. | 03-12-2009 |
| 20090136740 | ARTICLE HAVING COMPOSITE LAYER - A composite article includes a substrate and a layer attached to the substrate. The layer includes a metal phase, a first ceramic phase, and a second ceramic phase. | 05-28-2009 |
| 20090286003 | METHOD OF COATING A TURBINE ENGINE COMPONENT USING A LIGHT CURABLE MASK - A method of coating a turbine engine component involves providing the turbine engine component with a first area and a second area. The first area neighbors the second area. A cover is disposed over the first area of the turbine engine component. The second area of the turbine engine component is coated with a first coating curable from exposure to a light. The second area of the turbine engine component is exposed to light resulting in the curing of the first coating. The cover is removed from the first area. The first area of the turbine engine component is then sprayed with a second coating different from the first coating. | 11-19-2009 |
| 20100021716 | THERMAL BARRIER SYSTEM AND BONDING METHOD - A composite article includes a substrate, a ceramic member on the substrate and a ceramic bond coat for securing the substrate and the ceramic member together. A method of securing the ceramic member and the substrate together includes pyrolyzing a ceramic precursor, such as a ceramic powder, between the substrate and the ceramic member to form the ceramic bond coat. | 01-28-2010 |
| 20110027573 | Lubricated Abradable Coating - A coated article has a metallic substrate. A coating layer comprises at least 33% by volume ceramic, at least 5% by volume of a lubricant selected from the group consisting of hexagonal boron nitride (hBN), clay, graphite, and mixtures thereof. The coating layer lacks a metal phase of more than 5% by volume. | 02-03-2011 |
| 20110110783 | Trunnion hole repair utilizing interference fit inserts - A vane shroud for a gas turbine engine has a cylindrical shaped body and a hole arranged at a circumference of the body. The hole is for receiving a trunnion from a variable vane. A counterbore is arranged concentrically around the hole on a radially inward facing surface of the body, and receives a trunnion hub from the variable vane. A shrink-fit insert is seated into the counterbore such that the trunnion hub is provided with a contact surface, and the shrink-fit insert is secured to the shroud through an interference fit. | 05-12-2011 |
| 20110256321 | ARTICLE HAVING COMPOSITE LAYER - A composite article includes a substrate and a layer attached to the substrate. The layer includes a metal phase, a first ceramic phase, and a second ceramic phase. | 10-20-2011 |
