Abstract: A sealing ring is provided for non-hermetic fluid seals with a restricted passage between sealing elements rotating relative to one another the sealing has a carrier and at least one sealing rib extending radially on the outside or inside around the carrier. The edge of each rib forms a flow restriction with an opposing running in surface, with the sealing rib presenting an abrasive geometry. Each sealing rib has for the most part a smooth, rotationally symmetrical contour, and one or a few cutting elements are arranged at one or a few points on each sealing rib so that each element projects radially and axially on one or both sides from the sealing rib contour.

Abstract: A regulator or engine regulator having two regulator channels (20, 20′) which each have at least two processor units (22, 24 or 22′, 24′, respectively) is developed in that in each case one processor unit (for example 22, 22′) operates as a calculation unit for each safety-critical function in both regulator channels (20, 20′), in order to determine calculation results from at least some of the input data (E, E′), and in each case one other processor unit (for example 24, 24′) operates as a monitoring unit in order to compare the calculation results from the calculation unit firstly with its own estimate of the correct results and secondly with corresponding results from the respective other regulator channel (20′, 20). An engine and method for regulating an actuating or propulsion system, or an engine, have corresponding features.

Abstract: A blade ring for a gas turbine engine, especially an aircraft engine, may be a rotor ring or disk or a stator ring. At least one blade (9) forming an airfoil (2) is secured to at least one carrier ring (1, 10). The blade (9) is fixed to the carrier ring or disk or shroud (1, 10), either through a platform (4) forming a foot portion of the blade or through a neighboring transitional section (12) forming part of the carrier ring or disk or shroud. The mechanical stress and the overall axial length of the blade ring are reduced by a transition fillet (6) between the surfaces (3) of the airfoil (2) and the platform (4) or the peripheral section (12). The transition fillet (6) has a curve (7) that narrows toward the platform (4) or peripheral section (12) with radii (R1, R2, R3) that have different centers and are largest close to the blade surface (3, 8) and smallest close to the ring surface. This fillet construction extends all around the blade and relative to an inner ring or disk and/or an outer ring.

Abstract: A rotor for a propulsion plant has hybrid rotor blades arranged circumferentially around and extending essentially radially from a rotor. To reduce vibrations, the rotor blade has a metallic blade root and each blade has a metallic blade section that forms at least a portion of the blade leading edge and the area of the blade surface adjacent to the blade leading edge, and a blade section made of fiber-reinforced synthetic material or composite material. The blade sections (3, 4) of each blade (1) are so correlated to each other that damage or loss of the composite material blade section (4) still enables the propulsion plant to deliver a required emergency power.

Abstract: A method for producing a corrosion-resistant and an oxidation-resistant coating on a component in which a slurry is formed by mixing a binder solution with (1) a base powder selected from the group consisting of (a) MCrAlY wherein M is Ni or Co or both, (b) NiCrAl and (c) mixtures of (a) and (b) with (2) an added powder of Al, Pt, Pd, Si or mixtures thereof, each of the said powders having a grain size between 5 and 120 &mgr;m. The slurry is applied onto a component made of a superalloy based on nickel or cobalt. The slurry is hardened on the component to form a hardened slurry coating by heating the slurry to a temperature between room temperature and 450° C., and the hardened slurry coating is heated, to produce diffusion thereof into the component, at a temperature between 750° C. and 1250° C.

Abstract: A method for repairing/manufacturing an integrally bladed rotor for a turbine or turbo engine, in which, in the case of a repair, at least one vane section to be replaced is removed leaving a stub section to which a replacement vane section is to be welded, and, in the case of manufacturing, a carrier to be provided with vanes has stubs projecting over its peripheral surface, to each of which a vane is to be welded, includes the steps of: arranging an inductor around the front face of the stub section or stub; positioning a replacement vane section or vane at a small radial distance from and aligned with the stub section or stub; and welding the replacement vane section or vane to the stub section or stub, respectively, in a protective gas atmosphere by exciting the inductor with high-frequency current and moving the opposing heated part surfaces together.

Abstract: A protective layer for load-transferring contact surfaces of gas turbine components, especially titanium turbine components is capable to take up alternating loads at higher temperatures. The protective layer is formed of an alloy having the following composition in percent by weight: aluminum (Al) 4-8%; chromium (Cr) 2-5%; iron (Fe) 0-3.5%; and copper (Cu) remainder.

Abstract: An engine with counter-rotating rotors, which are coaxially arranged and are driven via a shaft by a turbine whose working medium is supplied by a gas generator with an air inlet, the air inlet (3) being arranged between (in the axial direction) the rotors (1, 2) in order to reduce the noise annoyance (FIG. 1), the rotors driven by an epicyclic gear, the internal gearwheel driving the rear rotor the plant carrier driving the front rotor.