Patent application number | Description | Published |
20080264065 | Gas-turbine combustion chamber wall - A gas-turbine combustion chamber wall for a gas-turbine has a combustion chamber wall | 10-30-2008 |
20090193810 | Combustion chamber lining - A combustion chamber for a gas turbine has a metallic supporting structure | 08-06-2009 |
20090235667 | Gas-turbine combustion chamber with ceramic flame tube - A gas turbine combustion chamber includes an essentially cylindrical flame tube | 09-24-2009 |
20100192588 | METHOD FOR THE PROVISION OF A COOLING-AIR OPENING IN A WALL OF A GAS-TURBINE COMBUSTION CHAMBER AS WELL AS A COMBUSTION-CHAMBER WALL PRODUCED IN ACCORDANCE WITH THIS METHOD - A cooling-air opening in produced in a wall ( | 08-05-2010 |
20110005233 | COMBUSTION CHAMBER HEAD OF A GAS TURBINE - A combustion chamber head of a gas turbine has a confinement enclosing a dampening volume ( | 01-13-2011 |
20110011093 | GAS-TURBINE COMBUSTION CHAMBER WITH STARTER FILM FOR COOLING THE COMBUSTION CHAMBER WALL - A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the combustion chamber by a heat shield ( | 01-20-2011 |
20120117973 | GAS-TURBINE COMBUSTION CHAMBER WITH A COOLING-AIR SUPPLY DEVICE - A gas-turbine combustion chamber has a cooling-air supply device delivering cooling air to a combustion chamber wall | 05-17-2012 |
20120240583 | SEGMENTED COMBUSTION CHAMBER HEAD - A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burners | 09-27-2012 |
20120240595 | COMBUSTION CHAMBER HEAD WITH HOLDING MEANS FOR SEALS ON BURNERS IN GAS TURBINES - A combustion chamber head of a gas turbine has a base plate | 09-27-2012 |
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 |
20130042627 | COMBUSTION CHAMBER HEAD OF A GAS TURBINE WITH COOLING AND DAMPING FUNCTIONS - A combustion chamber head of a gas turbine has a substantially annular combustion chamber outer wall | 02-21-2013 |
20130055716 | Gas-turbine combustion chamber with a holding means of a seal for an attachment - Gas-turbine combustion chamber with a combustion chamber head made from a metallic material and mounting at least one burner, and with a combustion chamber wall made from a ceramic material, where at least one igniter plug or other combustion chamber attachments such as acoustic dampers, sensors or valves are arranged in a recess of the combustion chamber wall, and where in the area of the recess a seal is arranged that is mounted by means of a metallic holding means from another component than the CMC combustion chamber wall. | 03-07-2013 |
20140238030 | IMPINGEMENT-EFFUSION COOLED TILE OF A GAS-TURBINE COMBUSTION CHAMBER WITH ELONGATED EFFUSION HOLES - The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall including a tile carrier, on which wall tiles are mounted at a distance to form an impingement cooling gap, where the tile carrier has impingement cooling holes and the tile is provided with effusion holes, where the tile has on its side facing the tile carrier a surface structure which raises from the surface of the tile and extends in the direction of the tile carrier. | 08-28-2014 |
20140290258 | METHOD FOR THE ARRANGEMENT OF IMPINGEMENT COOLING HOLES AND EFFUSION HOLES IN A COMBUSTION CHAMBER WALL OF A GAS TURBINE - A method for the arrangement of effusion holes and impingement cooling holes in a combustion chamber wall including: distribution of the effusion holes in the surface to be cooled in accordance with pattern, diameter and dimension selections made; distribution of the impingement cooling holes in accordance with pattern, diameter and dimension selections made; checking of the number of matches and their spacing from one another, taking into account the component and assembly tolerances; comparison with the permitted number and their minimum spacing; and, if quality requirements are not met, taking corrective actions, including selecting alternative diameters and patterns. | 10-02-2014 |