Patent application number | Description | Published |
20130209223 | TURBOMACHINE - A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades, whereby the trailing edges of the blades of the upstream row of blades and the leading edges of the blades of the downstream row of blades are arranged at an axial edge distance that decreases from the center of the main flow path in the direction of at least one main flow limiter. | 08-15-2013 |
20130209224 | TURBOMACHINE - A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades ( | 08-15-2013 |
20130209241 | TURBOMACHINE - A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides. | 08-15-2013 |
20130209259 | BLADE GROUP ARRANGEMENT AS WELL AS TURBOMACHINE - A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade. | 08-15-2013 |
20130318988 | AIRCRAFT ENGINE WITH TURBINE HEAT EXCHANGER BYPASS - An aircraft engine, in particular a helicopter engine, having a one or multi-stage compressor system (V), a combustion chamber (BK) connected downstream therefrom, and a one- or multi-stage turbine system (HT, NT) connected downstream therefrom, a compressor heat exchanger system (WV), a turbine heat exchanger system (WT), and a bypass means for optionally guiding the working medium through or past at least one turbine heat exchanger (WT) of the turbine heat exchanger system. | 12-05-2013 |
20130343900 | PROCESS FOR PRODUCING A RUN-IN COATING - Disclosed is a process for producing a run-in coating ( | 12-26-2013 |
20140154085 | GAS TURBINE AND GUIDE BLADE FOR A HOUSING OF A GAS TURBINE - A gas turbine, in particular an aircraft engine, having a housing in which at least one guide blade ( | 06-05-2014 |
20140241893 | SYSTEM FOR SPECIFYING AN INSTALLATION POSITION OF ROTOR BLADES, SECURING ELEMENT, ROTOR BLADE, TURBOMACHINE, AND METHOD - A system for specifying an installation position of adjacent rotor blades of a blade row of a turbomachine is disclosed. The system has a plurality of axial securing elements, which have at least two sections with different profile areas for the arrangement in each case between a groove base of a rotor shaft and a blade root, which are joined together by a connecting web at a groove distance from one another, and which have counter-contours on the blade root side for forming in each case a positive-fit pair with the profile areas. Also disclosed are a securing element and a rotor blade for this type of system, a turbomachine having a rotor which has this type of system, and a method for manufacturing this type of rotor. | 08-28-2014 |