Abstract: This invention relates to a component of an iron, cobalt or nickel-base alloy with a protective arrangement to prevent aluminizing or chromizing during gas diffusion coating, with a first layer as an interlayer and a second layer as a getter layer for reaction gases, where the first layer is a slip casting layer composed of oxide ceramic particles carried in a low-carbon vehicle free from halide, and the second layer is a metal layer or a metallic slip casting layer. The metal layer contains at least 50% by weight of the base-metal fraction of the component and exhibits all major alloy constituents of the component. The metal layer may be a sintered metal shape.

Abstract: An adjustable radial flow diffuser for a radial flow compressor includes adjusting elements having diffuser blades. The adjusting elements are arranged in a diffuser annulus uniformly distributed along the diffuser circumference with an angular pitch .delta.. The adjusting elements further are swivellable about an adjusting axis V parallel to the longitudinal axis of the compressor for changing the narrow cross-section between the diffuser blades. The adjusting elements have either a substantially U-shaped or H-shaped cross-section with sector-shaped plates that are mounted on both sides of a blade root to form the legs. The diffuser blade forms the web of the substantially U or H shaped cross-section.

Abstract: Surfaces of structural components of metal or the like are protected by depositing a wear-resistant dispersion coating of a matrix metal and hard-material particles embedded in the metal matrix. The depositing is accomplished by a sequential plasma spraying and particle blasting, whereby the hard-material particles are applied separately from the plasma stream to inject the particles into the plastically still deformable matrix metal. The coating steps are performed in an evacuated chamber or in an inert gas environment. These coatings are especially suitable on the blade tips of gas turbine engines, on the sealing fins of labyrinth seals or as "rub" coatings on circumferential rotor surfaces or the like.

Abstract: A seal for a gap between two components which are displaceable relative to each other through limited distances in three spatial directions, the seal being formed by at least two partially overlapping corrugated, bellows-like seal elements which are arranged one after the other in the longitudinal direction of the gap. Each seal element is connected to one of the components at a fixed point of attachment and is slidably and guidably connected to both components. Adjacent seal elements can also be slidably and guidably connected to one another. The seal provides sealing action for comparatively large relative movements of the two components and, thus for greatly varying widths and shapes of the gap.

Abstract: A heat exchanger having an inlet duct for admission of a first fluid to be heated, an outlet duct for discharge of the first fluid after heating thereof, the ducts being arranged in substantially parallel relation, and an assembly of a plurality of heat exchanger tubes connected to the inlet and outlet ducts for receiving the first fluid from the inlet duct to convey the first fluid through the tubes for discharge into the outlet duct. The heat exchanger tubes are of U-shape each including a curved bend region in which reversal of direction of flow of the first fluid is effected. The assembly of heat exchanger tubes extends laterally of the ducts into the path of travel of a second fluid which flows around the tubes in a passage area to effect heat exchange with the first fluid in the tubes.

Abstract: A fuel injection device having three concentric streams of air for the atomization of fuel sprayed onto a sleeve by an injector facing into the sleeve. The inner and outer streams of air are imparted with swirl in opposite direction, while the central stream of air is free of swirl. The two inner streams of air atomize the fuel as a result of shear forces, while the outer stream of air forms a stable recirculation region in a combustion chamber into which the fuel injector device extends.

Abstract: A cooled gas turbine power plant has a compressor and a high pressure turbine connected to the compressor. The cooling air quantity for the turbine is controlled in response to instantaneous load conditions and in direct response to the cooling air quantity control of the compressor. This control of the cooling air quantity for the turbine is achieved by a direct mechanical coupling of a slide valve for the turbine cooling air control with the control of the compressor, whereby good power output values and low fuel consumption values are achieved for the high pressure turbine, especially under partial load operating conditions. The compressor may be controlled by an adjustment of the angular position of its guide vanes or blades or by an adjustment of the quantity of its discharge air.

Abstract: A device for the reduction of secondary losses in the bladed flow duct of a turbomachine, wherein the device is arranged in the region of at least one of the two duct walls and, presently, intermediate two circumferentially adjacent blades, and is of the type in that the duct wall has a boundary layer step so that the face of the boundary layer step faces towards the pressure side of the blade.

Abstract: A combustion engine for gas turbine engines, constituted of an outer housing and having at least one flame tube inserted therein which is suppliable with secondary or mixing air through the intermediary of an annular passageway formed between the outer housing and the flame tube while, on the other side, the primary zone within the flame tube has fuel-enriched combustion air conveyable thereto, and wherein there are provided at least two fuel atomizer nozzles which are controllable independently of each other.