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Ambrosy
Anton Ambrosy, Tiefenbronn DE
| Patent application number | Description | Published |
|---|---|---|
| 20080318573 | METHOD FOR HANDOVER PROCEDURE OF USER TERMINAL ON RADIO INTERFACES, A BASE STATION AND A NETWORK THEREFOR - The invention concerns a method for a handover procedure of a user terminal (UE) on radio interfaces from a source base station (SBS) to a target base station (TBS) whereby the target base station (TBS) sends out user data to the user terminal (UE) before reception of a message indicating the termination of the handover procedure (HO Complete), the user terminal (UE) uses an uplink feedback for sending at least one message (Feedback) associated to the downlink transmission of said user data to the target base station (TBS), and the target base station (TBS) uses said at least one message (Feedback) associated to the downlink transmission of said user data as an indication of the presence of the user terminal (UE) within the range of the target base station (TBS), a base station (BS | 12-25-2008 |
Günter Ambrosy, Baden CH
| Patent application number | Description | Published |
|---|---|---|
| 20110099809 | METHODS FOR REPAIRING A GAS TURBINE COMPONENT - A method for repairing a gas turbine component includes: | 05-05-2011 |
| 20110099810 | METHOD FOR REPAIRING A GAS TURBINE COMPONENT - A method for repairing an ex-service gas turbine component ( | 05-05-2011 |
Günter Ambrosy, Baden-Dattwil CH
| Patent application number | Description | Published |
|---|---|---|
| 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 |
| 20100247309 | LAMELLAR SEAL FOR A TURBOMACHINE - A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella ( | 09-30-2010 |
| 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 |
Günter Ambrosy, Baden CH
| Patent application number | Description | Published |
|---|---|---|
| 20110099809 | METHODS FOR REPAIRING A GAS TURBINE COMPONENT - A method for repairing a gas turbine component includes: | 05-05-2011 |
| 20110099810 | METHOD FOR REPAIRING A GAS TURBINE COMPONENT - A method for repairing an ex-service gas turbine component ( | 05-05-2011 |
Günter Ambrosy, Baden-Dattwil CH
| Patent application number | Description | Published |
|---|---|---|
| 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 |
Günter Ambrosy, Baden-Dättwil CH
| Patent application number | Description | Published |
|---|---|---|
| 20100247309 | LAMELLAR SEAL FOR A TURBOMACHINE - A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella ( | 09-30-2010 |