Patent application number | Description | Published |
20110099810 | METHOD FOR REPAIRING A GAS TURBINE COMPONENT - A method for repairing an ex-service gas turbine component ( | 05-05-2011 |
20110103940 | ABRADABLE COATING SYSTEM - An abradable coating system ( | 05-05-2011 |
20110106290 | METHOD OF APPLYING MULTIPLE MATERIALS WITH SELECTIVE LASER MELTING ON A 3D ARTICLE - In a method for manufacturing an article ( | 05-05-2011 |
20110264413 | METHOD FOR REPAIRING AND/OR UPGRADING A COMPONENT OF A GAS TURBINE - In a method for repairing and/or upgrading a component ( | 10-27-2011 |
20120018115 | PROCESS FOR PRODUCING A 3-DIMENSIONAL COMPONENT BY SELECTIVE LASER MELTING (SLM) - A process produces a 3-dimensional component ( | 01-26-2012 |
20120251777 | COMPONENT FOR A TURBOMACHINE AND METHOD FOR MANUFACTURING SUCH A COMPONENT - A component for use in an engine in which the component is subjected to at least one of a high temperature, a corrosive atmosphere, an oxidizing atmosphere, a high mechanical load, a cyclic thermal load and transient conditions such that the component is prone to crack formation and propagation. At least one base material includes a self healing system in a form of an added active phase, the self healing system including at least one of a melting point depressant and a substance having a softening or a melting point below or within a range of an operating temperature of the component. | 10-04-2012 |
20130020377 | BRAZE ALLOY FOR HIGH-TEMPERATURE BRAZING AND METHODS FOR REPAIRING OR PRODUCING COMPONENTS USING A BRAZE ALLOY - In a Ni-based, Co-based, or Ni—Co-based braze alloy ( | 01-24-2013 |
20140178699 | COATINGS FOR TURBINE PARTS - A method and a turbine part having a coating with a matrix layer that includes a high temperature resistant hydrophobic polysiloxane filler, wherein the coating has superior mechanical strength and temperature resistance. | 06-26-2014 |
20140295087 | METHOD FOR ADDITIVELY MANUFACTURING AN ARTICLE MADE OF A DIFFICULT-TO-WELD MATERIAL - The invention relates to a method for additively manufacturing an article made of a difficult-to-weld highly-precipitation-strengthened Ni-base super alloy that comprises Al and Ti in the sum of more than 5 wt.-% or a difficult-to weld carbide/solution-strengthened cobalt (Co)-base super alloy, whereby a metal particle mixture of at least a first phase and a second phase is provided as a starting material, said first phase of the mixture being a base material and said second phase of the mixture being a material which is a derivative of the first material and has relative to said material of said first phase an improved weldability, and whereby the metal particle mixture is processed by means of an additive manufacturing process which is one of selective laser melting (SLM), selective laser sintering (SLS), electron beam melting (EBM), laser metal forming (LMF), laser engineered net shape (LENS), or direct metal deposition (DMD). | 10-02-2014 |
Patent application number | Description | Published |
20110291311 | PROCESS FOR EXTENDING THE CYCLIC SERVICE LIFE OF THERMAL BARRIER COATINGS, IN PARTICULAR ON GAS TURBINE COMPONENTS - A process for extending the cyclic service life of thermal barrier coatings made of yttrium-stabilized zirconium oxide (YSZ) or the like which have been applied to a substrate with an oxidizing bond coat in between includes increasing or long-term stabilizing the strain tolerance of the thermal barrier coating. | 12-01-2011 |
20140287149 | METHOD FOR COATING A COMPONENT OF A TURBOMACHINE AND COATED COMPONENT FOR A TURBOMACHINE - The invention relates to a coating system for a component of a turbomachine, which includes at least two different base powders. Each of the at least two different base powders has an individual predetermined distribution within the coating system. Further, each of the at least two different base powders is responsible for a specific property of the coating system. | 09-25-2014 |
20150028021 | METHOD FOR PROCESSING A MODULAR HYBRID COMPONENT - The invention relates to a method for processing a modular hybrid component having a first part made of a first material and a second part made of a second material, which is different from the first material with regard to its electromagnetic and/or thermal properties. The method including exposing the modular hybrid component to an alternating electromagnetic field, whereby both parts are heated up differently, and that a brazing or soldering joint or field sensitive mineral cement between the first part and the second part is affected by the heating action. | 01-29-2015 |
20150041434 | METHOD FOR SEPARATING A METAL PART FROM A CERAMIC PART - The invention relates to a method for separating a metal part from a ceramic part, which are joined at a connecting face within a modular hybrid component, especially of a gas turbine. The method includes said component being subjected to a reducing atmosphere in a gaseous process at elevated temperatures to dissolve the connection between said metal part and said ceramic part, especially by dissolving the ceramic part itself. | 02-12-2015 |