Abstract: A protective sheet for a resin pre-impregnated fiber board (prepreg) incorporates ferromagnetic material. This permits effective and safe manipulation of the fiber board during processing (trimming) and in the manufacture of fiber components.

Abstract: A sintered metallic light-weight structural material consists of spherical voids and lattice-type webs of intermetallic compounds. Owing to its weight-specific strength, which is superior to that of conventional super-alloys, this material is suited especially for application in aircraft and turbine engine construction.

Abstract: A brush-type seal has a wire bundle which is bent in a U-shape and is surrounded by a radially inward slotted ring shaped tube and by a housing consisting of two connected support rings. Application and maintenance of clamping forces is possible and is provided for to the ring shaped tube through the support rings. Attachments are provided on one supporting for fastening at a housing. The support rings are connected by welding at a welding joint which is spaced from the slotted tube which directly contacts the wire bundle.

Abstract: A turbine ramjet engine is provided which has a ram pressure air duct shrouding the basic turbo-engine in an annular manner. When the ramjet operation is disconnected, this ram pressure air duct, while at the same time intake air is released into the basic engine, is blocked off with respect to the supply of ram pressure air. It is provided to unblock or block an intake-side air inflow cross-section of the basic engine by the axial adjustment of a drop-shaped body with respect to a flow divider. A ring slide is provided which is axially adjustable to always be opposite this body which blocks the ram pressure air duct when the inflow cross-section of the basic engine is unblocked and unblocks it when the inflow cross-section is blocked. In addition, the ram pressure air duct is to be widened in a multicornered manner in the upstream direction at the level of a blocking zone caused by a local overtravelling of countersurface of the mentioned body and the ring slide.

Abstract: A tube matrix for a heat exchanger is connected between two spaced ducts for conveying a fluid from one duct to the other. The tube matrix has a plurality of spaced heat exchange tubes whose ends are secured to the ducts and which have a generally S-shape between the ducts. At the points of lateral offset and at the intermediate point therebetween, spaces are provided for keeping adjacent tubes in spaced relation from one another. Each loop of the S-shape tube is formed with two successive sections each of which includes two segments of opposite curvature such that in all there are eight segments which make up the tube. Preferably, the tube is a one piece member and the shape is formed by bending the tube. At each of the points where the tubes are secured and are connected by the spacers, tangents to the tubes extend parallel to one another.

Abstract: A gas turbine jet engine is disclosed with a fan delivering into a bypass duct to generate mainly propulsion thrust, and with a thrust reversing device having flaps which for reverse thrust operation pivot into the fan air stream and cooperate with an axially extended extreme section of the outer wall of the bypass duct to uncover delection ports arranged at breakthroughs in the outer wall. The extreme section of the outer wall and the thrust reverser flaps are linked one with the other for relative movement between them such that in a first phase of actuation relative to a fixed extreme nozzle section, the extreme section provides an additional fan nozzle area which communicates with the inlet flow areas formed by the flaps relative to the bypass duct.

Abstract: A compressor impeller has a ring-shaped shroud band which is mounted at blade tips, each blade tip being enclosed in an identical radially slidable manner by a guide block, and the guide blocks being fastened to the shroud band. As a result, a narrow sealing gap and thus lower aerodynamic losses can be implemented than in conventional compressors, and the different centrifugally and thermally induced expansions of the blade and of the shroud band can be compensated.

Abstract: An arrangement for adjusting guide blades by thermal expansion has an expansion rod which has a significantly different coefficient of linear expansion with respect to the supporting housing and is aligned in the circumferential direction of the turbo-engine and is connected with an adjusting ring by way of a step-up lever. As a result, a guide blade adjustment can be achieved easily as a function of the working gas temperature.

Abstract: A delicate or awkward to grip component which is to be friction bonded to another has formed on it a flange or like formation which can be gripped firmly by a wedging action. The component is loaded into a shuttle, provided with a releasable wedge clamp, which is carried by the output drive member of a friction bonding machine. Machine forces for the necessary friction heating and bonding phases of the operation are transmitted to component through faces on the shuttle which abut the component flange.

Abstract: A hot gas overheat protection device is provided for gas turbine engines and the like. An outer metal wall having cooling air supplied through cooling holes therethrough from the outside is shielded from hot gas flow by the provision of highly temperature resistant lining wall elements spaced from the metal wall. A thin metal skin is provided between the metal wall and the wall elements defining intermediate spaces communicating with cooling air ports in the metal wall. The thin metal skin has a melting point equal to or lower than that of the metal wall so as to provide for fusion or rupture of the thin metal skin in the event the insulating wall elements are locally ruptured, whereby the cooling air is provided through the cooling air ports in a direction against the flow of hot gases to thereby mitigate the effects of the rupture and protect the metal wall.

Abstract: A sealing device is provided, specifically between engine spaces which fluidically are acted upon by a different pressure, particularly for turbo-engines, such as gas turbo-engines. The sealing device includes at least one brush sealing device non-rotatably anchored at the stator side, the free bristle ends of this brush sealing device being guided in the direction toward an engine rotor. In this case, the brush sealing device is to be constructed as a radial sliding ring sealing device. The free ends of the bristles, while forming a secondary sealing, are guided in a circumferential groove of a sliding ring which is separated at least at one circumferential point, and which, on the side facing away from the bristles, forms a self-centering primary sealing at the engine rotor.

Abstract: This invention relates to a coupling involving two components butting one on the other under preload via at least one mating surface, where a coupling sleeve overlapping the two components in the area of the mating surface lodges against the first component via an abutment and the preload is transmitted to the second component via a welded joint. In this manner the components are joined together in a heat-resistant, inseparable, small-bulk and low-weight connection that can be gas-tight if the mating surface and the components are designed accordingly and that is feasible also when the components are made of materials that do not permit brazing or welding them together or cold or hot forming.

Abstract: A fuel feed method and apparatus for a turboramjet engine having a combustion chamber operable as a turbine engine afterburner and as ramjet engine combustion chamber is disclosed which features the concurrent injection of kerosene and hydrogen. At low Mach numbers, kerosene is the predominant fuel injected, while at growing speeds, hydrogen is injected in increasing proportions. This provides for a short combustion chamber length while minimizing the on-board fuel load and benefits especially small-size hypersonic aircraft.

Abstract: A turbo engine with a gas turbine to drive propellers or propfan blades is disclosed which includes a speed reduction transmission interposed behind the gas turbine output drive shaft and the propellers or propfan blades. A cooling air impeller is provided to provide the supply of cooling air to an oil cooler for the speed reduction transmission. The impeller is arranged directly on the turbine output drive shaft.

Abstract: An anti-wear coating is produced on the surface of a structural part of titanium or titanium alloy by forming a chromium layer on a nickel-titanium diffusion layer on the surface of the part.

Abstract: A heat exchanger having two mainfold ducts extending in parallel, adjacent relation connected to each other by heat exchange tubes. The manifold ducts are formed by a plurality of duct segments axially aligned one after the other in sealed relation and a support frame is arranged externally of the manifold ducts and is secured to and supports the duct segments individually at one of their ends. Each duct segment is secured to the frame at one of its ends while its other end is guidably supported and allowed to axially expand and contract relative to the end of the adjacent duct segment. This provides favorable resistance to the loads developed during operation as well as simple dismantling of the heat exchanger.

Abstract: A process of manufacturing a spacer element for spaced heat exchange tubes of a heat exchanger in which the tubes are of elliptical cross section and arranged in rows and columns. In the process a band of stranded interwoven fine wires are wound between and on the surfaces of the spaced heat exchange tubes and is fused to the tubes at the regions of contact therewith by a heating operation to form a spacer for holding the tubes in spaced relation. The heating operation can be carried out by heating the tubes and band in an oven, either in a vacuum or with a protective gas.

Abstract: A heat exchanger having manifolds in essentially parallel arrangement and having a special-section tube matrix which is arranged in a housing to project into a hot gas stream carried in the housing, the tube matrix being subdivided into sections and containing U-shaped reversal zones, where compressed air to be heated is admitted into the matrix via one manifold, is reversed in its direction and fed to the other manifold. The matrix sections are divided by transverse baffle walls. The ends of transverse supports extending around the tube matrix and the manifolds are connected to the housing in the vicinity of the U-shaped reversal zones, and the manifolds are supported in the housing for axial movement at both ends and are mounted rigidly on one support and axially movably on at least one further support.

Abstract: The air ducts of a heat exchanger are formed of a plurality of duct sections arranged axially one after the other and are clamped together in sealed relation by tension bars arranged symmetrically at the inner surface of the duct sections. The tension bars conform in shape to that of the duct sections to abut thereagainst.

Abstract: Apparatus for venting rotor parts of an axial flow compressor of a gas turbine power plant having an axial diffuser arranged behind the rotor and stator vanes at the last compressor stage. An annular chamber is formed downstream of the last rotor disk between adjacent rotor and stator parts and compressed air downstream of the diffuser is introduced into the chamber. The air in the chamber is divided into two individual streams, one of which is recycled to the compressor through an annular slot between the rotor and guide vanes at the last compressor stage and the other of which is discharged as a stream of leakage air into the secondary air system of the turbine.