Abstract: A combustion chamber of a gas turbine includes an external combustion chamber wall and at least one shingle that is mounted at the same, as well as a base plate and a combustion chamber head, characterized in that the shingle extends over the entire length of the combustion chamber and is held at its frontal end area, as it appears with respect to the flow direction of the combustion chamber, inside a groove of the base plate, and at its back end area inside a groove of the external combustion chamber wall.

Abstract: The present invention relates to an annular combustion chamber of a gas turbine with—relative to the engine axis—a radially outer combustion chamber wall and a radially inner combustion chamber wall, with the combustion chamber walls forming an annular combustion space, with a combustion chamber head having a plurality of fuel nozzles and air inlet openings, with the respective central axes of the fuel nozzles forming an envelope rotationally symmetrical to the engine axis, the envelope dividing the combustion chamber into an annular and radially outer area and an annular and radially inner area, with the radially outer area and the radially inner area having the same volumes.

Abstract: A method for producing a component provided with a supporting structure includes using at least one first laser for layer by layer manufacturing of the component out of a powdery material, using at least one second laser for producing a supporting structure, supporting the component, layer by layer out of the powdery material and operating the at least one first laser with a lower power than a power of the at least one second laser.

Abstract: A combustion chamber of a gas turbine with an outer combustion chamber wall and with tiles attached to the inner side of said wall or to a combustion chamber of the single-wall design, wherein the combustion chamber has in a center area, relative to the flow direction, a slot extending around the circumference of the combustion chamber and dividing the outer combustion chamber wall and the tiles for the supply of mixing air.

Abstract: An assembly of an axial turbomachine includes at least one outlet guide vane of a compressor and a diffuser arranged downstream of the outlet guide vane in the flow direction. The outlet guide vane is connected to the compressor and the diffuser is connected to the combustion chamber, without there being a direct mechanical connection between the diffuser and the outlet guide vane.

Abstract: The present invention relates to an annular gas-turbine combustion chamber having a radially outer and a radially inner combustion chamber wall relative to a machine axis, a combustion chamber head and a combustion chamber outlet nozzle, where the combustion chamber head includes several fuel nozzles spread over its circumference for supplying air and fuel, the latter exiting in an outlet surface of the fuel nozzles, where the respective fuel nozzle has a burner axis which is vertical to the outlet surface and where the intersections of the burner axes with the outlet surfaces define a circular burner centerline around the engine axis, characterized in that a cross-sectional area of the fuel nozzle radially outside the burner centerline is identical to a cross-sectional area radially inside the burner centerline.

Abstract: A device for mixing fuel and air of a jet engine includes at least one air-carrying duct and at least one further fuel-carrying duct. Guide elements extending over the duct height and distributed over the circumference of the duct are provided at least in the air-carrying duct, in the area of which guide elements a twist can be imparted to the air flowing in the air-carrying duct in order to improve mixing between the air and the fuel downstream of the ducts. The guide elements are provided at a trailing edge with at least one downstream extending projection and/or upstream extending recess designed at least approximately or at least in some areas with a sharp edge.

Abstract: A combustion chamber of a gas turbine having a head plate and a combustion chamber head, where the head plate is connected to the combustion chamber, and where several heat shields arranged in the interior of the combustion chamber are bolted to the head plate 6, characterized in that each heat shield and the combustion chamber head are fastened to the head plate by means of joint bolted connections.

Abstract: A jet engine has a bypass duct limited by an inner wall and an outer wall and inside which a fluid flows. Between the inner and outer walls of the bypass duct a support unit is provided that includes strut-like support elements connected at opposite ends to the inner and outer walls, respectively. Central longitudinal planes of the support elements describe in the areas of the support elements facing the inner wall a positive acute angle with an engine axis, and in the areas of the support elements facing the outer wall a negative acute angle with the engine axis. Flow cross-sections are each enlarged in the area between the side surfaces of the support elements each describing an acute angle with the walls, starting from the areas facing the fluid flow in the direction of the areas of the support elements facing away from the fluid flow.

Abstract: A combustion chamber of a gas turbine, including an external combustion chamber wall as well as an internal combustion chamber wall, wherein the internal combustion chamber wall, at its frontal end area as it appears with respect to the flow direction of the combustion chamber, is supported in a longitudinally slidable manner inside a groove of a base plate that is arranged in the area of a combustion chamber head, and is fixedly attached at the external combustion chamber wall at its back end area.

Abstract: A combustion chamber of a gas turbine with an outer combustion chamber wall and with tiles attached to the inner side of said wall or to a combustion chamber of the single-wall design, wherein the combustion chamber has in a center area, relative to the flow direction, a slot extending around the circumference of the combustion chamber and dividing the outer combustion chamber wall and the tiles for the supply of mixing air.

Abstract: The present invention relates to a gas-turbine combustion chamber having a head plate as well as an outer and an inner combustion chamber wall, wherein the combustion chamber is formed by segments or partial segments manufactured in one piece by means of a DLD method and welded to one another.

Abstract: Combustion chamber shingle of a gas turbine, including a bolt for bearing the combustion chamber shingle at the combustion chamber wall, wherein the combustion chamber shingle is formed substantially in a plate-shaped manner, and has at least one bearing element at one side, at which the bolt that is formed as a separate structural element is anchored in a form-locking manner, wherein the bolt, at its end area, is provided with a baring area that is arranged at a rectangular position to the bolt axis and that is arranged inside a recess of the bearing element, wherein the bolt has a centric passageway recess, and wherein the recess of the bearing element is dimensioned so as to be bigger than the baring area of the bolt, so that a hollow space is created between the surface of the combustion chamber shingle and the baring area of the bolt.

Abstract: A combustion chamber of a gas turbine includes an external combustion chamber wall and at least one shingle that is mounted at the same, as well as a base plate and a combustion chamber head, characterized in that the shingle extends over the entire length of the combustion chamber and is held at its frontal end area, as it appears with respect to the flow direction of the combustion chamber, inside a groove of the base plate, and at its back end area inside a groove of the external combustion chamber wall.

Abstract: A bleed air outlet provided in the bypass duct of a turbofan engine includes a bleed air tube protruding into the bypass duct and a cover having a plurality of air outlet openings provided in the top of the cover, with the cover being conceived as an elongate, essentially oval, shell-like aerodynamic fairing element (3) which, while extending in the longitudinal direction of the bypass duct, is provided with a longitudinally convexly curved and transversely essentially straight top (10) and sidewalls (11) arcuately extending from the latter to an inner bypass duct wall. Such a design of the bleed air outlet reduces pressure losses, acoustic emissions and vibrations in the bypass duct.

Abstract: The present invention relates to a gas-turbine combustion chamber having a head plate and an outer and an inner combustion chamber wall, characterized in that the combustion chamber is designed in one piece by means of a DLD method, or is assembled from segments which are welded to one another and manufactured in one piece by means of a DLD method, as well as to a method for manufacturing the gas-turbine combustion chamber.

Abstract: The present invention relates to a combustion chamber heat-shielding element of a gas-turbine, having a bolt for mounting the combustion chamber heat-shielding element on a combustion chamber wall or a combustion chamber head, where the combustion chamber heat-shielding element is designed substantially plate-like and where on one side at least one bolt, which is designed as a separate component, is anchored on it by means of a bonded connection.

Abstract: The present invention relates to a combustion chamber tile of a gas turbine with a plate-like basic element which is provided with at least one effusion cooling hole extending through the basic element from a surface of one side to the other side, with the effusion cooling hole being designed, from the one side of the basic element and beginning from an inlet opening, substantially at right angles to the surface over part of its length, wherein the effusion cooling hole inside the basic element has a straight section and is then provided with an offset section.

Abstract: The present invention relates to a laser depositioning device with a machine bed, onto the surface of which can be deposited a powder material, using at least one first laser for layer by layer melting of the powder material, characterized in that at least one second laser is provided to melt on the powder material layer by layer, with the second laser having a higher power than the first laser, as well as to a method for producing a component provided with a supporting structure.

Abstract: The present invention relates to a combustion chamber for a gas turbine with a combustion chamber head and a heat shield which are designed in one piece, with the heat shield being provided with at least one recess, in which is arranged a burner or an annular sleeve enclosing the burner, with a burner seal being provided between the heat shield and the burner, characterized in that the heat shield is provided in the area of the recess with an annular groove, in which is arranged at least one elastic sealing element forming the burner seal.