| Patent application number | Description | Published |
|---|
| 20090038739 | Replacement of a lubricant layer bonded to a part of a gas turbine engine - A method and system is described herein for repairing a part used in a gas turbine engine, which has a damaged or worn lubricant layer bonded to a surface of the part. After removing the damaged or worn lubricant layer, a polymeric adhesive may be used to attach a replacement lubricant layer to the metal surface. The polymeric adhesive may be a film or a paste. In some embodiments, the adhesive includes a non-metallic filler. The polymeric adhesive is stable at an operating temperature of the part to which it is attached. In one embodiment, the adhesive is polyimide, which is well-suited for use in a high pressure compressor of the gas turbine engine that operates at high temperatures. In other embodiments, the adhesive is bismaleimide (BMI) or cyanate ester. | 02-12-2009 |
| 20090067993 | COATED VARIABLE AREA FAN NOZZLE - A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is movable between a plurality of positions to change an effective area associated with a bypass airflow through a fan bypass passage of a gas turbine engine. A protective coating is disposed on the nozzle section and resists change in the effective area of the nozzle section caused by environmental conditions. | 03-12-2009 |
| 20090092842 | ARTICLE AND METHOD FOR EROSION RESISTANT COMPOSITE - A composite layer for resisting erosion includes a sacrificial layer for exposure to an erosion environment, a body layer, and an erosion resistant layer located between the sacrificial erosion layer and the body layer for protecting the body layer upon erosion of the sacrificial layer. | 04-09-2009 |
| 20090148275 | Laminate air seal for a gas turbine engine - A laminate air seal for a gas turbine engine includes at least one fabric layer made of fiberglass, ceramic fiber, basalt and/or carbon, and a polymeric resin that is stable at an operating temperature of the gas turbine engine. The resin may be preimpregnated into the fabric layers, or introduced into the fabric during assembly and formation of the laminate. The resin may be polyimide, bismaelimide (BMI) or cyanate ester. A particular resin selected may depend, in part, on the operating temperatures in that region of the gas turbine engine. In some embodiments, the laminate seal may include a coating to increase lubricity of the seal. In one embodiment, the laminate air seal is used to seal a gap between a pylon fairing and an exhaust nozzle of the turbine engine. | 06-11-2009 |
| 20090165926 | Method and assembly for bonding metal layers in a gas turbine engine using a polyimide adhesive - A method and system is described herein for using a polyimide adhesive to bond a first metal layer to a second metal layer used in a gas turbine engine. The polyimide adhesive may be a film or a paste and is able to withstand operating temperatures in excess of 600 degrees Fahrenheit (315 degrees Celsius). In an exemplary embodiment, the second metal layer is an outer face skin of an exhaust nozzle and the first metal layer is a metal doubler configured to cover a damaged portion of the outer face skin. In some embodiments, the first and second metal layers may be formed of titanium. | 07-02-2009 |
| 20100279104 | TURBINE FRIENDLY ABRADABLE MATERIAL - The invention comprises an abradable material containing up to 30 weight percent of fumed silica having a maximum particle from about 5 nanometers to about 20 nanometers and about 1.5 to about 5 weight percent of an abradable organic microballoon filler within an abradable silicone polymer matrix having an elasticity of less than X percent. | 11-04-2010 |
