Abstract: A fiber composite material has individual reinforcing fibers embedded in a bonding matrix material. The bonding of the fibers to the embedding matrix material is controlled along the length of the fibers by axially spaced fiber surface bonding zones having a high bonding ability and alternating with further fiber surface low bonding or non-bonding zones having a low or no bonding ability relative to the matrix material. The bonding zones having a high or maximal bonding ability are distributed optimally as to size, location and spacing along the length of a fiber so that loads or forces including the breaking load are transmitted from one bonding zone to the next bonding zone which are preferably formed as ring zones. The low-bonding or non-bonding zones are so dimensioned that bonding zones of fibers located adjacent to one another do not overlap in a direction across the length of the fibers.

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 method for the production of a protective layer on a structural part against thermal, chemical and/or mechanical stresses, particularly structural parts of complex shape such as turbine blades in which powder of a starting material for the layer is suspended in a suspension liquid and the suspension is held at a temperature just above the freezing point of the suspension. The structural part to be coated is maintained at a temperature below the freezing point of the dispersing liquid and is dipped into the suspension so that a layer of the powder present in the suspension freezes firmly on the part. The thickness of the layer is dependent on the temperature of the structural part and the length of time during which the structural part remains immersed on the suspension. The structural part now coated with the powder layer is subjected to freeze drying and is thereafter heated to a temperature above the freezing point of the suspension.

Abstract: A method of producing dispersion hardened metal alloys which incorporate highly reactive metals or their alloys whose oxides are not adapted to be easily reduced. According to the method, the highly reactive metals of their alloys are added as powder particles to a solution of a salt of a reducible metal which is to form a metallic matrix in which the reactive metals or their alloys are to be integrated, after which the solution is atomized to form particles from which the solvent is removed to yield the final product of the metal matrix with the highly reactive metals or their alloys integrated therein as a second phase.

Abstract: An anti-rupture ring is slit axially at least at one location and is provided thereat with clamping devices which permit a rapid tightening and loosening of the anti-rupture ring. In one embodiment, the clamping of the anti-rupture ring can be varied hydraulically so as to minimize clearance losses in operation. The invention can be used in all types of turbo engines endangered by breakage of rotor blades, particularly in aircraft gas turbine construction, and it permits simple, damage-free mounting and a well-defined clamping of the anti-rupture ring.

Abstract: A composite material of metals and nonmetallic substances exhibits the following structure:(a) a first material of high mechanical strength and(b) a second material of high oxidation-resistance, both at elevatedtemperatures are arranged so that the latter completely envelopes the former.

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 process and apparatus for treating finely divided powders of brittle materials capable of sintering or injection molding, such as ceramics or intermetallic phases in a predetermined maximum size of the powder particles which is maintained with reliability.

Abstract: A process for manufacturing structural parts of complicated shape from intermetallic phases capable of sintering by means of special additives which serve at the same time as sintering assist and increase the ductility of the finished structural part. The process includes the steps of making by melting a pre-alloy of the intermetallic phase, comminuting the pre-alloy into fine powder and mixing the fine powder with one or more additives into a mass which can then be shaped and subsequently sintered at a temperature of 70 to 95% of the absolute melting point of the intermetallic phases into a structural part of increased ductility and a density greater than 95% of the theoretical density which might possibly be subjected to subsequent pressing operations.

Abstract: A hybrid blade for a fluid flow engine has a U-shaped core of metal or a metal alloy and a ceramic outer jacket which forms together with a mounting plate a unitary, single piece structure. The legs of the core straddle the mounting plate and a heat insulating member is inserted between a crosspiece of the core and the mounting plate. This structure permits relative movement between the core and the jacket to compensate for different heat expansion coefficients.

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.