Abstract: An oil supply system for a propeller turbine engine includes a first oil circuit for supplying the turbomachine and a second oil circuit for supplying the propeller gearbox and the high-pressure pump associated with a propeller adjusting device. The two oil circuits are integrated into a common oil tank and connected to one another by means of an oil supply line in the flow direction downstream of the first and the second oil conveying pumps in such a way that a limited oil volumetric flow can flow from the first oil circuit into the second oil circuit, and only in this direction, if the pressure difference between the first and the second oil circuits falls below a certain level in the event of a pressure reduction in the second oil circuit.

Abstract: The present invention relates to a turbine blade of a gas turbine with an airfoil arranged on a blade root and having at least one cooling air duct running in the longitudinal direction of the turbine blade, arranged inside the turbine blade and extending through the blade root, characterized in that at least one swirl-generating element is arranged in the transitional area between blade root and airfoil in the cooling air duct, with the swirl-generating element including an outer ring and several swirl-generating stator vanes arranged thereon, which are connected to a centric area, as well as to a method for its manufacture.

Abstract: The present invention proposes a rolling tool device for compression rolling of, in particular, blade elements of a rotor area of a jet engine with a tool carrier to which two pliers-type bodies are rotatably connected, with the pliers-type bodies each being provided with a rolling area. A distance between the rolling areas is variable in dependence of a rotary movement of the pliers-type bodies. A separate spacer device is provided by means of which a minimum distance between the rolling areas can be defined.

Abstract: A sound-absorbing arrangement for an engine nacelle includes a first damping structure that includes a sound-damping honeycomb structure between a perforated inner layer and an outer layer, wherein the first damping structure has a first section and a second section that are arranged behind one another in the axial direction. The arrangement further includes a second damping structure that is formed in a ring-shaped manner and adjoins the first damping structure in the second section of the same in the radially external direction. The second damping structure is formed by multiple hollow chambers that adjoin each other in the circumferential direction, wherein the hollow chambers are formed without a honeycomb structure.

Abstract: A transfer coupling has a static component and a rotatable component arranged in axial alignment. The static component includes a first number (n?1) of radially extending ports and the rotatable component has a second number (n) of radially extending ports, the radially extending ports arranged in a common circumferential plane, wherein the ports on each component are equally spaced around the component and the number of ports on a first of the components is one less than on the second of the components.

Abstract: A transfer coupling includes a static component and a rotatable component arranged concentrically, the static component including a first number of radially extending ports and the rotatable component having a second number of radially extending ports the radially extending ports arranged in a common circumferential plane wherein the ports are configured and arranged, in use, to homogenise a flow area for a fluid being transferred through the ports and thereby create a homogenous volume flow.

Abstract: A slide bearing device, includes an inner ring-shaped internal element, an intermediate element that encloses the internal element in the radial direction of the slide bearing device and is at least approximately ring-shaped, and a ring-shaped external element that encloses the intermediate element in the radial direction. The internal element is rotatable relative to the external element, and the intermediate element is rotatable relative to the internal element and relative to the external element. In a default state of the slide bearing device, the internal element is arranged at a distance to the intermediate element in the radial direction of the slide bearing device, and the intermediate element is arranged at a distance to the external element. The internal element and the external element are made of a metallic material and the intermediate element with a non-metallic material.

Abstract: A component, especially contrived and designed for being used in a turbomachine, includes a high-temperature coating being arranged above a base of the component. The base has at least one structural element for connecting it to the high-temperature coating, with the cross-section of the at least one structural element having at least three different widths, i.e. a base width at the lower end of the at least one structural element, a center width above it, and a tip width above that, where on average the center width is greater than or equal to the base width, but less than four times the base width, in particular less than or equal to three times the base width.

Abstract: A stator vane adjusting device of a gas turbine has a plurality of stator vanes each rotatable about a radial axis 44 and arranged in at least two radial planes, as well as at least one stator vane adjusting ring connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device. The actuating device includes a crankshaft element rotatable about a stationary pivot axis by an actuator. A first lever is articulated by a joint to the stator vane adjusting ring, with its free end being connected by a joint to a center area of a second lever, the second lever being mounted at its one end on a stationary pivot point and at its other end being linked by a joint to a third lever, which is mounted by a joint at its free end on the crankshaft element.

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 method for manufacturing thermally stressed engine components having a geometrically complex structure includes metal injection molding metal powder mixed with a binder to form green compacts of individual parts, which are debindered to form brown compact sections which are joined together to form a multi-part brown compact which are sintered in the assembled state. The brown compact sections have differing shrinkage properties in the sintering process, depending on the metal powder used, with a greater shrinking first brown compact section being automatically pressed against a second brown compact section during sintering. Connecting elements having positively engaging projections and recesses are provided at joining surfaces of the brown compact sections and have differing shrinkage such that during sintering of the assembled brown compact, the brown compact section with projections undergoes a greater shrinkage than the brown compact section with recesses.

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: The present invention proposes a rolling tool device for compression rolling of, in particular, blade elements of a rotor area of a jet engine provided with a tool carrier to which two pliers-type bodies are rotatably connected about a joint pivot bearing relative to the tool carrier. The pliers-type bodies are each provided with a rolling area, and a distance between the rolling areas is variable in dependence of a rotary movement of the pliers-type bodies. The pliers-type bodies in the zone of the rolling areas are each provided with a part, where main axes of the parts have an extension component in the direction of a rotary axis of the pivot bearing.

Abstract: The present invention relates to a compressor blade of a gas turbine having an airfoil made of a fiber-reinforced plastic, which is fastened by means of a blade root to a disk, as well as a metallic leading-edge element, which is arranged on the leading-edge side of the airfoil and partially encompasses the latter, with the leading-edge element itself being fastened to the disk.

Abstract: A washer of a combustion chamber tile of a gas turbine having a round disk-shaped basic body provided with a central recess and a flat contact surface arranged on a first side of the washer, wherein several groove-like air ducts are provided on a second side that extend from a circumferential rim of the washer radially relative to the center axis of the washer, and in the center area of the washer in the axial direction.

Abstract: Accessories are mounted to a gas turbine engine from a frame attached to a pylon which is used to mount the engine to an airframe. The frame independently mounts the accessories so that engine vibrations are not transmitted to the accessories.

Abstract: An oil supply system for a propeller turbine engine including a propeller, a propeller gearbox connected to the propeller and a propeller adjusting device for altering the pitch angle of the propeller blades. The system includes an oil circuit and a propeller main pump for supplying the propeller gearbox and a propeller high-pressure pump supplying the propeller adjusting device with oil. The system includes an oil accumulator for providing, in the event of an undersupply of oil by the propeller main pump, oil contained in the oil accumulator to the inlet of the propeller high-pressure pump such that the pump inlet pressure at the inlet of the propeller high-pressure pump does not fall short of a certain minimum value. The oil accumulator is incorporated into the inflow to the propeller high-pressure pump to be continuously supplied and charged with oil of the propeller main pump.

Abstract: The present invention relates to a method for repairing an abradable coating of a compressor of a gas turbine, where a worn abradable coating is repaired, where an analysis and/or selection of areas of the abradable coating to be repaired is conducted by means of a boroscope in the non-removed state of the gas turbine, where a tool is passed through at least one boroscope aperture of the gas turbine to the area to be repaired and the worn abradable coating is at least partially removed, where the removed material is extracted, where the area of the abradable coating to be repaired is cleaned and/or prepared for application of a repair medium, where a hardenable aluminum oxide-based repair medium is applied to the area to be repaired by means of a type of airbrush and then hardened, and where the area provided with the repair medium is subsequently mechanically treated.

Abstract: A blade for use in a fluid-flow machine, where at least one of the meridional flow line profile sections MSLi and MSLo is provided at a distance of max. 35% of the main flow path width from the respective inner and outer main flow path boundaries. The blade has in at least parts of a central area a multi-profile configuration such that at least two partial profiles (7, 9, 10) arranged one behind the other in the flow direction are provided, of which each has substantially the shape of a blade profile, where a passage (8) is provided between each two partial profiles and is passed through by fluid from the blade pressure side to the blade suction side.

Abstract: A method for determining a machining result during surface machining of components, has the following method steps of: providing a component, applying at least one device, which changes under pressure, to the component, machining the surface of the component provided with the at least one device, evaluating the machining operation on the basis of the change in the at least one device as a result of the surface machining of the component. At least one device is in the form of a film which changes at least one property during the surface machining of the component.