The compressor has a stator vane assembly including an inner ring (1) and a seal carrier (2), where the seal carrier comprises two opposite seal carrier end faces (2-10, 2-11) and the inner ring comprises two inner ring end faces, which faces the seal carr...

The device (1) has air conduit tubes (14) for guiding air from an outer annular space radially toward a rotor shaft, and a support ring (12) for arranging the air conduit tubes in a radially closed intermediate space between two adjacent rotor disks. The s...

The arrangement has shells (1-3) connected with one another in a circumferential direction (U) and arranged adjacent to each other in an axial direction (A). The shells comprise V or U-shaped cross sections opened opposite to a through flow direction and/o...

The component has component segments (12a, 12b) arranged relative to one another such that a gap is defined between the segments. The segments are sealed opposite to each other by a sealing device (16) that includes a brush seal (18). The brush seal includ...

The system (6) has multiple nozzles (8), which are arranged in a side wall (2) that limits stream (4) and area oriented diagonally in flow direction (x). The nozzles have a rectangular flat cross-section. An injecting channel (10) is arranged with constric...

The blades (2, 4) have a blade root (8), a blade neck (10) and a platform (14) arranged between the neck and a blade pan (12). The platform has a front projection (16) and a rear projection (18), where cool cooling air stream is delimitable from hot gas st...

The fan (11) for especially an aviation gas turbine engine has a supplementary rotor (18) positioned upstream of the fan rotor (13) with blades (19) which extend radially outwards from a hub and finish at a distance from the outer wall (16) of the fan flow...

The flow structure for the compressor of especially a gas turbine has at least one toroidal chamber (18) installed concentrically to an axis (17) of the compressor in the region of the free blade ends of a blade ring (15,16). An opening (30) is located in ...

The gas turbine, especially an aviation jet engine (10), has at least one ancillary unit (14) fastened to it and receiving signals from at least one sub-unit of the gas turbine. The ancillary unit has a base element (21) and a housing element (22), with th...

The method involves feeding the fuel with a pump (2), dispensing it into the engine by a fuel dosing valve (5) and regulating the pressure to which the fuel dosing valve is subjected using a recirculation flow with a recirculation valve (4). The setting of...