| Patent application number | Description | Published |
|---|
| 20080297761 | Measuring Apparatus - A measuring apparatus (1) for contactless detection of a distance between a surface ( | 12-04-2008 |
| 20090255117 | GAS TURBINE HOT GAS COMPONENT REPAIR METHOD - A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair. | 10-15-2009 |
| 20100080688 | HOT GAS COMPONENT OF A TURBOMACHINE INCLUDING AN EMBEDDED CHANNEL - A component, especially a hot gas component of a turbomachine, has at least one passage ( | 04-01-2010 |
| 20110103967 | ABRASIVE SINGLE-CRYSTAL TURBINE BLADE - A turbine blade for a turbine rotor, is provided having a single-crystal basic body which has a blade tip and extends in the radial direction. The turbine blade includes at least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on the radially outer blade tip, and in that an at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and consists of oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least certain regions of said epitaxial intermediate coating. | 05-05-2011 |
| 20110103968 | WEAR-RESISTANT AND OXIDATION-RESISTANT TURBINE BLADE - A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there. | 05-05-2011 |
