Patent application number | Description | Published |
20090111639 | Planetary Gear - A planetary gear train is described which includes a sun gear, three or more planet gears, an annulus as well as a planet gear carrier, whereby the input is provided via the sun gear and the output is provided via the annulus or via the planet gear carrier, whereby each planet gear is mounted on both sides in a roller bearing, and whereby the planet gear carrier includes two axially spaced bearing washers as well as at least three webs that connect the bearing washers. Each roller bearing is configured as a single-row or multi-row cylindrical roller bearing, each planet gear has a flexurally elastic axis projecting axially on both sides beyond the gear body of the planet gear, and the connection between each roller bearing and the appertaining axis is configured to be spherically moveable. | 04-30-2009 |
20100202889 | METHOD FOR PRODUCING A LIGHTWEIGHT TURBINE BLADE - A method for producing a lightweight turbine blade for a gas turbine is disclosed. In an embodiment, the method includes casting of a blade element with a blade wall and at least one cavity enclosed by the blade wall. The blade wall is at least partially reduced in thickness by machining after the casting. This provides a method for producing a blade element, in which the wall thickness of the blade wall can be adapted to the mechanical load of the blade element, and the weight of the blade element can be reduced at the same time. | 08-12-2010 |
20120039706 | COMPRESSOR HAVING A GUIDE VANE ASSEMBLY WITH A RADIALLY VARIABLE OUTFLOW - A compressor is disclosed. The compressor has at least one guide vane assembly which can be adjusted to change the outflow angle, and a rotor which is connected downstream of the guide vane assembly. The guide vane assembly and rotor are arranged between a housing and a hub of the compressor. The guide vane assembly is divided in the direction of extension from the housing to the hub into two or more sections which can be radially adjusted relative to one another, or has a clearance radially in the direction of extension, the clearance allowing a substantial amount of flow to pass. | 02-16-2012 |
20120057958 | CLEARANCE CONTROL SYSTEM, TURBOMACHINE AND METHOD FOR ADJUSTING A RUNNING CLEARANCE BETWEEN A ROTOR AND A CASING OF A TURBOMACHINE - The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor ( | 03-08-2012 |
20120063884 | CLEARANCE CONTROL SYSTEM, TURBOMACHINE AND METHOD FOR ADJUSTING A RUNNING CLEARANCE BETWEEN A ROTOR AND A CASING OF A TURBOMACHINE - The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor ( | 03-15-2012 |
20130084166 | SEGMENTED COMPONENT - A component, in particular for a gas turbine, is disclosed. The component has at least two component segments which are arranged relative to one another leaving a gap and are sealed against each other by a sealing device. The sealing device includes at least one brush seal. Also disclosed is a gas turbine, in particular an aircraft engine, having such a component. | 04-04-2013 |
20140298772 | MISCHVORRICHTUNG UND TURBOFANTRIEBWERK MIT EINER DERARTIGEN MISCHVORRICHTUNG - The invention relates to a mixing device and a turbofan engine having such a mixing device | 10-09-2014 |