| Patent application number | Description | Published |
|---|
| 20090110954 | Bimetallic Bond Layer for Thermal Barrier Coating on Superalloy - A bimetallic bond layer ( | 04-30-2009 |
| 20090123722 | Coating system - The invention relates to a coating system ( | 05-14-2009 |
| 20090148278 | ABRADABLE COATING SYSTEM - This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal between turbine blade disks and the surrounding ring seal without causing excessive wear to the blade tips. The abradable coating system includes columns of an abradable material. Thus, interference between the blades and the abradable coating system causes the individual columns to break off at the base. This abrasion mechanism may reduce blade wear and spalling of the coating system when compared to conventional coatings. | 06-11-2009 |
| 20090258247 | Anisotropic Soft Ceramics for Abradable Coatings in Gas Turbines - A layered abradable thermal barrier coating (TBC) | 10-15-2009 |
| 20100015350 | PROCESS OF PRODUCING AN ABRADABLE THERMAL BARRIER COATING WITH SOLID LUBRICANT - A process ( | 01-21-2010 |
| 20100050649 | COMBUSTOR DEVICE AND TRANSITION DUCT ASSEMBLY - A combustor device and transition duct assembly is provided for use in a gas turbine engine. The combustor device comprises combustor structure having an exit portion; spring clips mounted to the exit portion of the combustor structure; and a burner assembly. The transition duct comprises a conduit having inlet and outlet sections and an abradable material layer provided along a circumferential portion of the inlet section of the transition duct conduit. The transition duct conduit inlet section may be coupled to the combustor structure exit portion such that the spring clips engage the abradable material layer. | 03-04-2010 |
| 20110043820 | Method of Measuring Coating Thickness Using Infrared Light - A method of measuring a thickness of a coating on a substrate material. A first pulse of monochromatic light having a predetermined first wavelength is emitted toward the coating and substrate material. A second pulse of monochromatic light having a predetermined second wavelength is emitted toward the coating and substrate material, the second wavelength being different than the first wavelength. A first elapsed time is measured from emission of the first pulse of light to reception of a reflection of the first pulse of light from a surface of the substrate material at an interface with the coating. A second elapsed time is measured from emission of the second pulse of light to reception of a reflection of the second pulse of light from an outer surface of the coating. A thickness of the coating is determined as a function of a difference between the first and second elapsed times. | 02-24-2011 |
| 20110171394 | METHOD OF MAKING A COMBUSTION TURBINE COMPONENT USING THERMALLY SPRAYED TRANSIENT LIQUID PHASE FORMING LAYER - A method of making a combustion turbine component includes thermal spraying a transient liquid phase (TLP) forming layer onto a combustion turbine component substrate and thermal spraying a main material layer onto the TLP forming layer. The combustion turbine component substrate, TLP forming layer, and main material layer are heat treated to thereby bond the main material layer to the combustion turbine component substrate. | 07-14-2011 |
