Abstract: A metallic alloy part having a bonded coating that includes dispersed hard-material particles embedded in a metal matrix, composed of a eutectic solder whose alloy elements include at least the base metal of the metallic alloy part. The solder is formed by fusion bonding on the metallic alloy part, a precoating composed of sequential layers of the elemental components of the solder applied on the metal part or on the hard-material particles. The composition and disposition of the various layers are graduated such that the melting points of the elemental solder components increase towards the outermost layer.

Abstract: A process for the removal of organic materials from the surfaces of drive components, particularly for the removal of meltable organic coatings, fillings or damping materials. The organic material is first melted in a bath of the same or similar organic material and an adhering residual film is diluted and stripped off from the preheated drive component by applying tempered oil thereto. After this, a diluting and striping off of a material film, which essentially consists of oil molecules still adhering to the surface, is conducted by applying an organic cleaning agent, which is free of fluorochlorohydrocarbons and chlorohydrocarbons. Then a post-treatment of the surfaces of the drive component is effected by one or more steps of applying diluted cleaning solutions with intermediate rinsing and/or drying steps, in which the cleaning solutions are increasingly diluted stepwise.

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: A turbojet fan engine is disclosed having a fan or prop fan which blows air into a secondary channel and an external shroud for the turbine and the secondary channel, in which the front end of the shroud is formed with an inlet lip and the rear end of the shroud is formed in a nozzle-like, pointed manner and at least one end of the shroud is changed, with respect to its effective profile geometry, by means of air under pressure which is taken from the engine and blown out at the appropriate end of the shroud.

Abstract: A ceramic heat insulation layer applied to a metal structural part or to an intermediate adherent layer thereon, has the surfaces of its inner, open pore structure coated with a passivating ceramic material or a metal deposition material for improving the properties of the heat insulation layer.

Abstract: A repair process for blades of turboengines damaged in the head or edge regions in which the damaged regions are first separated to leave an undamaged blade stump with an exposed, repair surface. The repair surface of the blade stump is prepared for butt welding and a repair plate of constant thickness which exceeds the maximum profile height of the blade by more than 50% is provided with a front surface adapted to the repair surface. This front surface of the repair plate is abutted against the repair surface and the blade stump and the repair blade are then butt welded. The weld joint and the repair plate are machined to the profile contour of the blade stump and to the desired blade profile. This process is used for the repair of blades of integral rotor disks of turboengines, particularly for blades of integral compressor impellers.

Abstract: A combustion chamber apparatus 1 for a gas turbine has a pilot stage and a main stage for low-emission lean-burn operation. The pilot stage is separate from the main stage and is formed by a flame tube 2 with an upstream first fuel injector 3a and with a secondary combustion zone 7a. The main stage includes a vaporization chamber 4 and a combustion chamber 5, and a second fuel injector 3b is provided at an upstream end of the vaporization chamber 4. The vaporization chamber 4 produces a homogenous fuel-air mixture which will not burn until it is in the combustion chamber 5. In lean-burn operation of the apparatus, the separate arrangement of the two chambers 4, 5 significantly reduces the formation of nitrogen oxides. For use in aircraft gas turbine engines, the apparatus has an annular shape with several main and pilot stages.

Abstract: A process for vapor depositing a metallic interlayer on the surface of a metal component, for example, by sputtering and thereafter depositing an aluminum diffusion coating on the interlayer. The metallic interlayer is vapor deposited on the surface of the component in a noble gas atmosphere, more than one-half of which, in per cent by weight, is composed of noble gases which are heavier than argon. Advantageously, the noble gases can be krypton or xenon. The process can be used with particular advantage for applying protective aluminum diffusion coatings on turbine blades.

Abstract: In a method of manufacturing fiber-reinforced engine components having a metal matrix, a long or even continuous silicon carbide fiber is first coated with a matrix metal of a titanium-based alloy by atomizing or sputtering. Then, the fibers coated with matrix material are wound onto a mold in the direction of the anticipated stresses. A covering of foils, bands, wires, pressed-on granulates, sintered-on powders or a top coating of matrix metal is then applied onto the surface of the fibers wound onto the mold. Finally the mold with the wound-on, matrix-material coated fibers and the covering of matrix metal is subjected to hot isostatic pressing. This method is used to manufacture engine shafts, shroud bands for turbine wheels or disk-less turbine wheels having retaining rings holding the blades.

Abstract: A process for the production of structural parts or substrates with composite coatings by electrolytic or electroless deposition of a metal matrix in which the structural part or substrate surface is first coated with a mixture of a water-soluble powder of salt or acid and dispersed particles, fibers, felt, mat or woven fabric. Then the salt or the acid is melted and transformed to a water-soluble substance which fixes the particles, fibers, felt, mat or woven fabric to the surface of the structural part or substrate. The water-soluble substance is dissolved by immersing the structural part or substrate in an electrolytic or electroless deposition bath, and a metal matrix is deposited onto the structural part or substrate to incorporate the dispersed particles, fibers, felt, mat or woven fabrics in the matrix as a composite coating.

Abstract: A burner for gas turbine engines is provided in which a ring-shaped swirling device is coaxially assigned to a fuel nozzle. The swirling device forms tangential ducts for an adjustable feeding of combustion air between profiles arranged along the circumference. In this case, the profiles are to be formed by corresponding sections of components which are arranged to be axially movable relative to one another. One respective section of a profile is to be a hollow body in which the corresponding other section engages in a movable manner. With the burner, a combustion is made possible that is low in pollutants while the swirling efficiency and the rotational swirl development are optimal.

Abstract: A matrix of heat exchange tubes in a heat exchanger in which a first fluid flows in the heat exchange tubes and undergoes heat exchange with a second fluid flowing externally on the heat exchange tubes. The tubes have a teardrop shape and are arranged in the matrix in parallel relation in rows in which each tube has a rounded surface at one end and a tapered narrow surface at the other end. The tubes in each row all face in the same direction and the tubes in alternate rows face in opposite directions. The tubes have alternate unequal spacing of distances a.sub.1 and a.sub.2 in successive rows. The tubes can be bent to form a U-shape matrix or a semi-circular matrix. The tubes are each manufactured by filling the space between an inner channel and an outer shell of the tube with a ceramic or metal.

Abstract: Spacer supports are connected to a matrix of heat exchange tubes of a heat exchanger to maintain the heat exchange tubes in spaced relation and resist overheating by hot fluid flowing around the tubes and the spacer supports. The spacer supports are in the form of hollow tubular bodies in which the heat exchange tubes are supported in spaced relation. The heat exchange tubes communicate with the interior of the hollow bodies so that flow of a heatable fluid in the heat exchange tubes is conveyed through the hollow body to wet the interior thereof and cool the same.

Abstract: Apparatus for sealing the side edges of flaps of a propulsion nozzle of an engine and the walls of a casing of the nozzle by sealing elements carried by the flaps and extending across a clearance between the side edges of the flaps and the walls. The sealing elements are carried in slots in the side edges of the flaps with clearance for capability of movement towards the walls. The sealing elements contact the walls to form a primary seal therewith. The flaps are formed with chambers carrying a pressure medium and plungers are supported in the flaps for being subjected to the pressure of the pressure medium and bearing against the sealing elements to urge the sealing elements against the surfaces of the walls. A differential pressure exists on both sides of the flaps and acts on the sealing elements in the clearance to press the sealing elements against respective side surfaces of the slots to form a secondary seal thereat.

Abstract: A turbofan engine includes two oppositely rotating fan rotors which are arranged upstream of the core engine, and has a booster with two contra-rotating coaxial rotors. The radially exterior booster rotor is arranged between the rearward fan rotor and the low-pressure turbine in a torque-transmitting manner. The gearless construction permits an almost uniform loading of the low-pressure shafts.

Abstract: A cooling arrangement for the cooling air of hypersonic jet engines comprises a heat exchanger in which the temperature of the cooling air is reduced by means of the fuel to be burnt in the engine. In order to keep the operating temperatures of the heat exchanger within controllable limits, a partial flow of the cooling air is branched off downstream of the heat exchanger and is admixed to the cooling air upstream of the heat exchanger for reducing the temperature.

Abstract: A guide vane ring having guide vanes is provided on two rings which are arranged coaxially and radially at a distance from one another. These two rings are held on assigned housing sections which are subjected to thermally different expansions. One ring is rigidly connected with the guide vanes, and the other ring is connected with the free ends of the guide vanes by the compressive force of a tensioning element. In addition, the other ring is divided into several piston-ring-type elements which axially follow one another and which are each slotted approximately axially and form a cylindrical sliding surface for the whole free ends of the vanes. The tensioning element is arranged on the one group of assigned housing sections while forming a radial compressive force distributed uniformly on the elements.

Abstract: An etch solution for the removal of metallic layers, which provide protection against corrosion by hot gases, and of deposits resulting from hot gas reactions on turbine blades in power units comprising a salt solution and an inhibitor. The salt solution consists of a hydrogen sulfate in the amount of 5 to 45% by weight and the inhibitor is present in the amount of 0.5 to 10% by weight. The total amount of the hydrogen sulfate and inhibitor is present with at least 50% by weight of water based on the total etch solution. Using this etch solution, layers preferably comprising MCrAlY are removed from turbine blades comprised of alloys of Ti, Co or Ni.

Abstract: Apparatus for the compact assembly of a gas turbine engine with a recuperative exhaust gas heat exchanger wherein inlet and outlet ducts of the core of the heat exchanger are supported by support plates attached to the casing of the heat exchanger. The support plates are connected to the engine casing with capability of relative movement between the ducts and the support plates so that thermally produced expansions and contractions are taken up without stress at the support points of the ducts with the support plates and within the heat exchanger. As a consequence, no expansion joints are necessary in the connection lines.

Abstract: A nozzle wall for two-dimensional (2D) hot gas nozzles of rocket or jet engines has a multilayer structure, in which a thermally conductive layer is flexibly connected to a support structure and a sliding layer is arranged between them to permit parallel movement of the thermally conductive layer. Also, a manufacturing method for the nozzle wall allows successive operations to be automatic to allow quality control inspections between these operations.