Patent application number | Description | Published |
20080229797 | Method and apparatus for hot forming of sheet metal in titanium-base alloys - A titanium sheet to be formed is heated in a sealingly closed tool by the radiation heat from the heating elements integrated into the tool to a forming temperature not exceeding 600° C., and is deformed towards a cold tool contour by the action of a non-oxidizing gaseous pressure medium introduced into the tool and heated to the hot-forming temperature, as well as by underpressure generated on the side of the workpiece facing away from the pressure medium. | 09-25-2008 |
20090087309 | Protective ring for the fan casing of a gas-turbine engine - A protective ring ( | 04-02-2009 |
20090249622 | Method for the manufacture of integrally bladed rotors - The manufacture or repair of blisks, in particular high-pressure turbine blisks for gas-turbine engines is accomplished by producing a joint between the rotor disk and the pre-manufactured blades by circular friction welding. Due to the small forces and the low acceleration required for heat generation by friction and the balanced circular movement during frictional welding at a constant setting angle between disk and rotor, exact and uniform arrangement and alignment of the blades on the periphery of the rotor disk are possible even with small and complex joining surfaces of the turbine blades and with dissimilar materials. | 10-08-2009 |
20090265933 | Method for the manufacture of turbine or compressor rotors for gas-turbine engines - With the manufacture of turbine engine rotor drums, the opposite joining surfaces of rotor disks are brought into contact and at least one of the two rotor disks clamped into a fixture is set in a circular movement until the joining areas reach a pasty state due to the frictional heat. The circular movement of the rotor disks, in which the axis of the rotor disk moves along a circular path, is optically recorded and deviations due to imbalance are corrected by weight compensation at the fixture. Upon reaching the pasty material state the joining areas weld together, with the rotor disks being at rest and in axial alignment. Manufacture is cost-effective and guarantees precise axial alignment of the rotor disks and a long service life of the engine rotor drums. | 10-29-2009 |
20090283503 | Method for the manufacture of a blisk - A method for manufacturing integrally bladed rotors by laser brazing a rotor disk ( | 11-19-2009 |
20100080710 | Stator vanes of a stator vane cascade of an aircraft gas turbine - A method for manufacturing a stator vane | 04-01-2010 |
20100109184 | METHOD FOR THE MANUFACTURE OF AN ENGINE SHAFT - For the manufacture of a tubular low-pressure turbine shaft made of a fiber-composite material with metallic driven/driving protrusions ( | 05-06-2010 |
20100113170 | ENGINE SHAFT FOR A GAS-TURBINE ENGINE - A low-pressure turbine shaft ( | 05-06-2010 |
20100113171 | ENGINE SHAFT IN THE FORM OF A FIBER-COMPOSITE PLASTIC TUBE WITH METALLIC DRIVING AND DRIVEN PROTRUSIONS - On a low-pressure turbine shaft made of fiber-composite material, the connection to the metallic driven protrusion or the driving protrusion ( | 05-06-2010 |
20100126662 | METHOD FOR THE MANUFACTURE OF HYBRID COMPONENTS FOR AIRCRAFT GAS TURBINES - When manufacturing hybrid components, especially the fan blades or stator vanes of an aircraft gas turbine including a metallic enveloping structure and a supporting structure in fiber-composite material, the mating faces of the metallic structure are cleaned and roughened with plasma prior to fitting the fiber-composite material and the metallic molecules activated so that high attractive forces take effect and an intimate, extremely strong adhesive connection is produced between the metal and the fiber-composite material. Fan blades or stator vanes of the fan structure of a gas-turbine engine which are manufactured according to this method are capable of transmitting high loads and feature a long service life. | 05-27-2010 |
20100129651 | HYBRID COMPONENT FOR A GAS-TURBINE ENGINE - A hybrid component for a gas-turbine engine includes a supporting structure ( | 05-27-2010 |
20100140230 | METHOD FOR THE MANUFACTURE OF A WELDED ROTOR FOR A GAS-TURBINE ENGINE - With a method for manufacturing welded rotors for a turbine, especially a gas-turbine engine, in which two or more rotor disks are joined to each other by conventional welding processes using welds extending radially to the rotor axis and the weld zone is subsequently thermally treated at a certain temperature to relieve residual tensile stresses by relaxation, the weld is set to a significantly lower non-relaxatory temperature level than the heat-affected zone adjoining the weld so that, as a result of the high temperature gradient, a residual compressive stress or at least a substantially reduced residual tensile stress is impressed on the weld. Compared to conventionally heat treated and welded rotors, improved strength properties in the weld zone and an increased service life are obtained as a result of the reduced tensile stresses. | 06-10-2010 |
20100258199 | INTAKE CONE IN A FIBER COMPOUND MATERIAL FOR A GAS-TURBINE ENGINE - The intake cone for a gas-turbine engine is wound in one piece from fiber compound material with fiber layers crossing one another. It is provided with a fiber compound belt, wound in the circumferential direction of the intake cone, in the connecting area with a mounting flange, which is of segmented design and thus features reduced circumferential stiffness, of a metallic retaining ring attached to a fan rotor disk. The intake cone is easily manufacturable with almost constant wall thickness and in high quality, can reliably be subjected to non-destructive testing and, in combination with the mounting flange, which is flexible in the radial direction, ensures safe connection of the two components despite the different thermal and elastic behavior of the respective materials. | 10-14-2010 |
20100259013 | ABRADABLE LABYRINTH SEAL FOR A FLUID-FLOW MACHINE - An abradable labyrinth seal for a fluid-flow machine seals a sealing gap between a stationary carrier ( | 10-14-2010 |
20110038666 | ENGINE SHAFT OF HYBRID DESIGN - On an engine shaft of hybrid design with an externally toothed power transmission element ( | 02-17-2011 |
20120017663 | METHOD FOR THE MANUFACTURE OF A WORKPIECE WITH DEFINED SURFACE - A method for manufacturing a workpiece | 01-26-2012 |
20120020802 | COMPRESSOR BLADE OF A GAS-TURBINE ENGINE WITH A SELF-SHARPENING LEADING-EDGE STRUCTURE - A compressor blade | 01-26-2012 |
20120033787 | METHOD FOR RADIOGRAPHIC INSPECTION OF COMPONENTS - During the radiographic inspection of components by X-rays for better detection of defects, preferably automated, an uneven surface topography ( | 02-09-2012 |
20120045032 | METHOD FOR FILMLESS RADIOGRAPHOC INSPECTION OF COMPONENTS - With filmless radiographic inspection of components by means of digital X-ray technology, an uneven surface geometry of the component is smoothened by defining a digital virtual smoothening layer for better, preferably automated, recognition of defects, where the digital radiation signals generated by an X-ray detector are overlaid with digitized surface measurement signals, so that a change in absorption and intensity of radiation due to the surface topography of the component, i.e. due to an uneven surface, is compensated for and only a density caused by internal material defects is represented in the X-ray image. | 02-23-2012 |
20120304658 | Segment component in high-temperature casting material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for the manufacture of an annular combustion chamber - The present invention relates to a segment component in high-temperature casting material for an annular combustion chamber of an aircraft engine, characterized by a combustion-chamber wall which in operation shields a fuel flame extending along a burner axis from the environment, with the combustion-chamber wall having a bulge which points in a direction facing away from the burner axis. The invention furthermore relates to an annular combustion chamber, an aircraft engine with an annular combustion chamber as well as a method for the manufacture of an annular combustion chamber. | 12-06-2012 |
20130202088 | Method for Radiographically Inspection a Component by Means of X-ray Beams Using a Smoothing Agent and Smoothing Agent for Carrying Out the Method - The present invention relates to a method for radiographically inspecting a component by means of X-rays, where at least one component surface to be radiographed is provided with a surface structure, with at least the surface provided with the surface structure being smoothed by means of a smoothing material to level out the surface structure, with at least one organic compound and at least one metal powder being used as smoothing material, with the X-ray absorption behaviour of the smoothing material essentially equaling the X-ray absorption behaviour of the material of the component, as well as to a smoothing material for carrying out the method in accordance with claim. | 08-08-2013 |
20140030106 | Compressor blade of a gas turbine as well as method for manufacturing said blade - The present invention relates to a compressor blade of a gas turbine having an airfoil made of a fiber-reinforced plastic and a leading-edge element connected to said airfoil, characterized in that the leading-edge element includes two partial elements, which are fabricated as separate elements and connected to one another, with the leading-edge element being connected to the airfoil essentially using the clamping effect of the two partial elements, as well as to a manufacturing method. | 01-30-2014 |
20140030107 | DECOUPLED COMPRESSOR BLADE OF A GAS TURBINE - The present invention relates to a compressor blade of a gas turbine having an airfoil made of a fiber-reinforced plastic, which is fastened by means of a blade root to a disk, as well as a metallic leading-edge element, which is arranged on the leading-edge side of the airfoil and partially encompasses the latter, with the leading-edge element itself being fastened to the disk. | 01-30-2014 |
20140030109 | low-Modulus Gas-Turbine Compressor Blade - The present invention relates to an aircraft gas-turbine compressor blade having an airfoil with a leading edge, with at least the area of the leading edge being made from a low-modulus titanium alloy. | 01-30-2014 |
20140127005 | METHOD FOR PRODUCING A COMPONENT, COMPONENT AND TURBOMACHINE HAVING A COMPONENT - A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fibre composite layer and/or a plastic component. | 05-08-2014 |