Abstract: A gas turbine vane, especially a vane pertaining to an aircraft engine, comprising a blade and a vane footing. The blade is defined by a flow inlet edge or a front edge, a flow outlet edge or a rear edge, and a blade surface extending between the front edge and the rear edge and forming a suction side and a pressure side. The suction side of the blade includes at least one microprofiled or microstructured region for optimizing the flow around the blade.

Abstract: A semifinished product of composite material consists of a metallic matrix material and high tensile strength fibers embedded in the matrix material, whereby the metallic matrix material is formed of titanium or a titanium based alloy. Ceramic particles are encased or embedded in the matrix material for increasing the strength of the semifinished product with respect to torsional loading or transverse loading. The product is produced by a method in which the fibers are coated with the matrix material, ceramic particles are embedded in the matrix material coating the fibers, and then the thusly coated fibers are arranged in a desired geometry and are consolidated to form the product.

Abstract: The invention relates to a method for producing a semifinished product from a composite material. The semifinished product is made of a composite material consisting of a metallic matrix material and of high-tensile fibers embedded in the matrix material, whereby the metallic matrix material is formed from titanium or from a titanium-based alloy. According to the invention, ceramic particles are incorporated in the matrix material in order to increase the strength of the semifinished product with regard to torsional stress or transversal stress.

Abstract: A rotor for a turbo machine, in particular for a gas turbine, is disclosed. The rotor includes a rotor base body and several rotor blades arranged over the circumference of the rotor base body, in which case the rotor base body is manufactured of an MMC composite material, and in which case the rotor blades are an integral part of the rotor. The rotor base body is configured in the shape of a ring, in which case the ring-shaped rotor base body includes, in a radially internal section, at least one groove-like recess which is filled radially on the inside with fibers exhibiting tensile strength.

Abstract: A gas turbine vane, especially a vane pertaining to an aircraft engine, comprising a blade and a vane footing. The blade is defined by a flow inlet edge or a front edge, a flow outlet edge or a rear edge, and a blade surface extending between the front edge and the rear edge and forming a suction side and a pressure side. The suction side of the blade includes at least one microprofiled or microstructured region for optimizing the flow around the blade.

Abstract: A method of producing fiber-reinforced metallic building components having a complicated three-dimensional geometric shape includes the following steps. First, metal-coated SiC fibers are applied to a metallic sectional piece having a simple geometric shape, and are then held thereon without restraint by a metallic counterpart piece. Then, the unit consisting of the sectional piece, fibers and counterpart piece undergoes plastic deformation in vacuo between mold halves by applying pressure at an elevated temperature, without bonding of the fibers to one another or to the building component metal. By further increasing the pressure and/or temperature, the molded unit is compressed further between the mold halves and is consolidated to a monolithic part by metallic bonding (diffusion welding), whereby the part, either alone or bonded to other parts, forms the building component, after cooling and removing it from the mold halves.

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 structural component is formed with an outer shell of sintered, solid, powder particles, and a porous core of sintered, hollow, bodies arranged in layers. The hollow bodies are of increased diameter in the layers in a direction from the outer periphery of the core towards the center of the core. The material of the outer shell and of the core is a metal or ceramic.

Abstract: In the rotor of a turbomachine, especially the turbine of a gas turbine engine, each rotor blade is mounted in the rotor disk rim by a blade root having a serrated profile that engages a correspondingly formed axial groove in the rotor disk rim. A shroud band is constructed so that at a predetermined operating point of the turbine, adjacent blades are supported against one another so as to damp vibrations. Light weight and heavy weight rotor blades are mounted alternatingly around the circumference of the rotor disk. The blade root and corresponding axial groove associated with each light weight or heavy weight blade are differently dimensioned or shaped to correspond to the differing loads associated with the heavy weight blades and the light weight blades respectively. Different materials, having different densities, are used for the heavy weight blades and the light weight blades.

Abstract: Diesel engine exhaust gas is cleaned by burning soot to convert the soot into gas. For this purpose the exhaust gas from the diesel engine is caused to travel through a helical or spiral channel, whereby centrifugal force causes soot particles to collect on radially outer, inner circumferential channel surfaces, where the collected soot is combusted by heating elements reaching into these channels, preferably into channel pockets.

Abstract: A drive system with a combustion engine also has a turbo-charger with a shaft supported by sleeve bearings in a housing. The housing is connected to the cooling water circulating circuit of the drive system for cooling the sleeve bearings and the housing of the turbo-charger shaft simultaneously with cooling the engine. A water pump wheel is mounted on the shaft in the housing for circulating the cooling water through the bearings, through the housing, and through the cooling circuit of the combustion engine, whereby the supply of cooling water to the sleeve bearings is load dependent.

Abstract: A burst guard ring for stopping and retaining blade fragments thrown from a failing rotor of a turbine engine includes an outer fiber belt of a highly elastic material, preferably aramid fibers in a silicone rubber matrix surrounding the engine housing. Ceramic tiles are provided radially inwardly of the fiber belt or in the fiber belt exclusively at certain critical locations where any bulging of the fiber ring due to blade fragment impact would damage auxiliary devices or pipelines arranged adjacent or close to the engine at such critical locations. In non-critical areas the fiber belt provides sufficient protection without the ceramic tiles. The high energy absorbing protective effect of elastic fibers is advantageously combined with the low straining or expansion of ceramic, so that a low total weight is achieved.

Abstract: A method including embedding a porous silicon ceramic compact, or workpiece, in a powder which is not sinterable at the process temperature, and subjecting the powder and embedded compact to heat and pressure in a hot isostatic press. The powder transmits the pressure to the compact. The powder may be the same material as the compact, except without a sintering agent, or the powder may be graphite powder. The grain size of the powder is between 2 .mu.m and 50 .mu.m. The powder and embedded compact are placed in a container prior to hot pressing; the container may be made of thin sheet metal or of quartz glass.

Abstract: The rotor of an axial-flow compressor with means for sealing the rotor blade tips relative to a casing wall provided with a coating is to be capable of abrasion but at the same time also low in wear. The present invention resolves these contradicting requirements for the coating on the casing in that individual blades, arranged between normally contoured, unshrouded rotor blades, are widened at their tips and reinforced with a radially outer layer, the material of which is matched to that of the coating. This will enable the coating to be subjected to less wear and to offer more resistance to erosion than heretobefore.

Abstract: A hot gas impinged turbine blade suitable for use under super-heated gas operating conditions has a hollow ceramic blade member and an inner metal support core extending substantially radially through the hollow blade member and having a radially outer widened support head. The support head has radially inner surfaces against which the ceramic blade member supports itself in a radial direction on both sides of the head. The radially inner surfaces of the head are inclined at an angle to the turbine axis so as to form a wedge or key forming a dovetail type connection with respectively inclined surfaces of the ceramic blade member. This dovetail type connection causes a compressive stress on the ceramic blade member during operation, whereby an optimal stress distribution is achieved in the ceramic blade member.

Abstract: An improvement for a turbocompressor having a rotor, a stator and a casing, and an abradable coating provided between the rotor blades and the casing, or between the stator vanes and the rotor, such that the blades make initial contact with the coating to abrade the coating and produce a minimal clearance. The abradable coating is formed on a member having a first layer of carbon-fiber reinforced graphite adapted for attaching the coating member to the casing or rotor, and a second layer of graphite in the region in which the blade tips are intended to rub. The second layer may optionally contain, preferably radially oriented brush-type graphite-fiber reinforcements, or be entirely composed thereof.

Abstract: A turbine blade adapted for use with hot gases comprising a radially inward portion of metal including a core projecting radially outwards on which is supported a ceramic portion of airfoil section enclosing the core. The inner end of the ceramic portion forms a continuous surface contour with the metal inward portion. The ceramic portion extends no more than one-half of the total span of the blade and, preferably, about one-third of the blade span. In a particular embodiment, the wall thickness of the ceramic portion can increase in an radially outwards direction.

Abstract: A multiple-layer wall is provided for a hollow body to sustain high thermal and mechanical loads and to afford adequate thermal insulation. The wall has, on the inside, a heat and/or wear resistant ceramic inner layer and, surrounding it, a preferably prestressed retaining layer of fiber reinforced plastic. An intermediate layer of a thermally insulating ceramic material can also be provided. The wall can also have a retaining layer of metal. At least the retaining layer is shrink-fitted. The retaining layer of metal and/or the intermediate layer moreover can be deposited by a sintering process. Prestressing is achieved also by the shrinkage resulting from the sintering process. As a result of prestressing, the inner layer, when under internal pressure, comes under substantially no circumferential tension or under circumferential compression only. The wall is used especially with precombustion chambers of Diesel engines or with cylinder barrels or internal combustion engines.

Abstract: A blade for a fluid flow engine, especially a gas turbine, has a protective coating against injurious attack by the propellant or working medium. A metal blade having a diffusion layer or a sprayed coating for inhibiting corrosion is known. Such coating renders the blade highly resistant against heavily erosive and corrosive attack, especially by pulverized coal combustion gas or similar agents. The present blade is made of ceramic material, especially a dense ceramic material with a surface layer of at least one of the following materials: TiN, TiC, B.sub.4 C, BN and titanium carbon nitride. These materials are easy to apply and provide a good bond with the ceramic material. If the ceramic materials are silicon carbide (SiC) or silicon nitride (Si.sub.3 N.sub.4) an especially good bond is achieved. This coating strongly resists removal, as it does oxidation and heat. Local removal down to the ceramic material, as it may result from rather long service, is recognizable immediately.

Abstract: A method of manufacturing molded articles of metal alloys, especially of nickel-base alloys, chromium-base alloys, titanium-base alloys, and dispersion-hardened alloys. A powder of the alloy, or a blend of powders of alloy constituents, is mixed with one or more plastics, selected from thermoplastics, duroplastics, and internal lubricants to form an injectionable granulate compound, the plastic content amounting to about 30% to 50% by volume. The compound is prepared by dissolving the plastic in a solvent which will not attack the base material of the alloy, and by blending it with the metal powder, after which the solvent is evaporated. The injectionable granulate compound is then injection molded to form a molded article. By heat treatment at 600.degree. C. or below in inert gas the plastic is eliminated from the molded article. The article is then sintered. To improve its strength, the article may subsequently be subjected to hot isostatic pressing.