Abstract: The present invention provides dual-fuel burners for the oxidation of liquid and of gaseous fuel with air. A dual-fuel burner is provided with an atomizer nozzle which generates a divergent spray cone of liquid fuel, and with an annular atomizer lip as an impact member for the liquid fuel spray cone. The dual-fuel burner has a primary channel for a first air stream through the spray cone and the inside of the atomizer lip, and a secondary channel for a second air stream over the outside of the atomizer lip with a common, coaxial mouth at an atomizer edge thereof. A channel for the gaseous fuel leads into the inside of the atomizer lip between the primary and secondary channels and discharges into one or both of the primary and secondary channels upstream of the atomizer edge.

Abstract: The curvature of an edge such as the trailing edge of a turbine blade having a specular reflection surface is inspected by illuminating the surface area to be measured with a laser beam and sensing the reflected laser light. The laser beam intensity across the cross-section of the laser beam is varied by a radiation intensity matrix located between the laser beam generator and the edge to be sensed or measured, whereby local radiation intensity variations are provided in the form of illuminating laser beam segments (A, B, C, . . . ) having different intensities. The beam reflected segments (A', B', C', . . . ) have a reflection angle that is equal to the incidence angle of the respective illuminating laser beam segments (A, B, C, . . . ). This fact is used for the correlation (A, A'; B, B'; C, C', . . . ). The reflected beam segments (A', B', C', . . . ) are scanned in a line-by-line fashion whereby the radiation intensity values varying along the curvature are measured.

Abstract: A vibration damper for rotor housings includes a rubber-elastic damping band (6) that encircles the outer circumference of the rotor housing (4) in a contour fitting manner. A clamping band (7) encircles the damping band (6) and secures the damping band to the housing (4). The clamping band is made of a material having a different modulus of elasticity than the material of the rotor housing, which achieves a detuning of the vibrational system including the rotor housing and the vibration damper as components. Such a detuning reduces the vibrational tendency of the rotor housing. Frictional rubbing between the damping band and the housing surface, and between the damping band and the clamping band effectively damps or dissipates the energy of any vibration that does occur.

Abstract: A change-over arrangement for an integrated turboramjet engine has a guide ring which can be displaced in the axial direction and an annular cone which can be displaced against the guide ring. In the turbo-operation, the annular cone is in its front position and the guide ring is in its rear position closing off a ram air inlet duct, and in the ramjet operation, the annular cone, in its rear position, closes off the turbo-inlet duct, and the guide ring opens up the ram air inlet duct. As a result, a low-loss introduction of the air current can take place into the turbo-inlet duct or into the ram air inlet duct, without, at the same time, requiring disadvantageous enlargements of the diameter of the outer casing of the engine.

Abstract: A propeller blade of fiber-reinforced plastic with a combined erosion, icing and lightning protection system has a metal shroud fitted to its leading edge, the shroud enclosing a cavity and accommodating a heating conductor at its interior. A ground line of the heating conductor is connected to ground and serves as a lightning conductor.

Abstract: Rotor blades have feet engaged in axial grooves in a rotor disc and foot plates on the blades form with the surface of the rotor disc, axially and circumferentially extending intermediate spaces. Between sections of the blades and the rotor disc, overlaps of structural parts are developed at the intermediate spaces, by which the blades are fixed axially in the grooves in one direction. The overlaps of the structural parts can be formed between profiled or ground contours surfaces of the blade feet and profiled or broached contours surfaces of the rotor disc.

Abstract: An axial blade wheel of a gas or steam-driven turbine comprising blades having substantially laminar boundary layer flow up to a point of maximum velocity on the upper surface of the blade, the upper surface of the blade being provided in a region downstream of the point of maximum velocity where the fluid flow velocity decreases with a spoiler edge of saw tooth profile which extends substantially over the entire blade length.

Abstract: A non-contacting sealing arrangement for sealing two counter-rotating shafts with the aid of a housing having a tire-casing-like shape which surrounds at least one centrifugal disk connected for rotation in unison with one rotatable shaft and laterally surrounded by the casing-like part with a narrow gap; the casing-like part is arranged eccentrically to the axis of the shaft on which the centrifugal disk is mounted in order to thus assure a return feed for the liquid sealing medium, such as oil, to bearing places. The invention enables alternate pressure loads and is particularly suited in applications between at least two bearing chambers of aircraft propulsion units.