Abstract: A blade device for turbo-engines, comprising a blade shell, a blade core and a blade base, has a blade core comprising a bundle of small tubes which provides the blade device with high stability and stiffness. The arrangement has the advantage that the blade device can be used universally in the case of almost all blade devices, and the blade core permits a heat exchanger function.

Abstract: A process and an arrangement are disclosed for the removal of a low-melting embedding body from a higher-melting embedded component. A groove is provided along a molding-in base of the component and by means of the widening of the groove via heatable elements, the resulting halves of the embedding body are removed. The process and the arrangement are particularly suitable for separating embedded guide and moving blades from the manufactured embedding body.

Abstract: Apparatus for the support and adjustment of stator blades of a gas turbine, in which an adjusting ring is connected to the stator blades by adjustment levers disposed outside the turbine housing. The adjusting ring is supported for rotation in the circumferential direction on a support ring, which has elastic resilience in the radial direction, the support ring being suspended on and centered in a movable manner on radial pins fixed in an outer housing of the turbine. The connection of the adjusting ring and the support ring is achieved by a ball-bearing which is pre-stressed. When the adjusting ring is displaced circumferentially, the stator blades are pivoted around suspension shafts by levers fixed to the shafts and connected to the adjusting ring for universal pivotal movement.

Abstract: The invention relates to a radial-flow wheel for a turbo-engine comprising a hub and blades distributed on the hub-side outer circumference, the meridian section contour of the outer surface of the hub being a catenarian curve. This radial-flow wheel has the advantage of low frictional losses.

Abstract: A propelling nozzle has upper and lower primary and secondary flaps which are disposed opposite one another at a mutual distance and which are sealingly movably guided between lateral wall portions of a four-cornered nozzle housing. The primary flaps are arranged pivotally about a fixed axis of rotation on the nozzle housing. The secondary flaps, in each case upstream of levers non-rotatably connected with the primary flaps, are pivotally linked to pivots situated on the side facing away from the nozzle flow. The secondary flaps change into the primary flaps with a surface section which is bent concentrically with respect to the pivots. The primary and secondary flaps are arranged in a four-cornered nozzle housing which is itself closed in. In each case the secondary flaps are arranged on the nozzle housing in an axially movable and angularly adjustable manner at the downstream end. The levers are formed on interior sections which are bent away from the primary flaps in a toggle-lever-type manner.

Abstract: A thermally stressed rotary connection of two coaxially aligned shafts includes two metallic coupling sleeves which are connected with the shafts by way of elastic intermediate layers. The two metallic sleeves engage one another. A ceramic centering sleeve is provided radially around the outside of the coupling sleeves and is shrunk onto the two shafts. The arrangement has the advantage of an effective connectability of different shafts such as ceramic or metal, in which case the two shafts may be connected with one another during the mounting. This allows undivided housings to be used.

Abstract: The proposal is for a thrust nozzle for aircraft fitted with jet engines especially for lateral thrust vector control, in which the upstream ends of at least two flaps (8, 12) actuated via lever-like adjusters are arranged to pivot simultaneously at different angles of rotation about spindles running across the nozzle axis (20) and between walls (22, 23) running substantially parallel to the nozzle axis of a square nozzle housing in such a way that, with a permanently convergent nozzle contour, a narrowest cross-section is formed between the flaps (8, 12) at the outlet side; one end of each lever-like adjuster (28, 29) is to engage in downstream ends of the flaps, said adjusters being arranged at their movably mutually coupled other ends to travel in a guide path (30) which is curved so as to produce continuously different flap rotation angles; one or more narrowest cross-sections can either be kept continuously constant or change dependently upon the jet deflection angle.

Abstract: Turboramjet engine having a variable air intake, a ram air duct annularly enveloping the basic turbojet engine, and shutoff devices with which the ram air duct is energized with air when the basic turbojet engine is shut off and with which the basic turbojet engine is energized with air when the ram air duct is shut off. An air tract communicates with the air intake on a tubular duct carried axially on the basic turbojet engine and expands to an annular inlet section to the ram air duct. The shutoff devices are associated at least on the inlet side with quadrilateral sections of the tubular duct. As shutoff means for the inlet flow, use is made of an axially adjustable and internally swept sleeve valve and at least one flap that can be pivoted against a partial inlet area of the inlet section, which flap seals off the sleeve valve in lid-fashion when the inlet section is in a jointly exposed position.

Abstract: A process for testing the tolerances of bores made by laser pulses records a matrix image of the bore region during each laser pulse and evaluates the matrix image to determine the average bore diameter. Compliance with the required tolerances can thereby be achieved during the boring operation. The evaluation of the matrix image is made by optically forming a half tone, dot matrix, mosaic image of the bore and its surrounding region, adding gray scale values of the dots in the columns and rows and differentiating the column and row totals to produce spaced maxima for the rows and columns. The distance between the spaced maxima in the rows and columns represents the diameter of the bore in the direction of the rows and columns respectively.

Abstract: A nozzle for a hypersonic engine includes an axially displaceable mushroom-shaped central body. Two mutually opposing expansion flaps are provided which, when the flying Mach number is low, can be swivelled with respect to one another and, when the flying Mach number is high, can be swivelled apart. As a result, an extensive change of the divergence of the nozzle can be achieved while maintaining a high mechanical stiffness and a low leakage level.

Abstract: A shroud band for a rotor wheel having integral rotor blades wherein the shroud band has at least one Z-shaped separation gap at the band periphery, the Z-shaped gap having two parallel damping gaps which are axially spaced apart and which are inclined at an angle of from 70.degree. to 90.degree. relative to the axial direction. The damping gaps are narrow and are joined by an inclined wider free gap portion. During rotation, the damping gaps close up and the adjoining surfaces of the band come into frictional engagement whereas the free gap remains open.

Abstract: A propelling nozzle for an aircraft engine has an interior shroud of high thermal conductivity which is penetrated by a number of cooling ducts and is surrounded from the outside by a solid support shroud. A cast-in intermediate layer is provided between the interior shroud and the support shroud. This has the advantage that manufacturing tolerances of the interior shroud and of the support shroud may be compensated. Only very minimal demands must be made on the accuracy of shaping the interior shroud and the support shroud.

Abstract: A stationary centerbody includes vaulted areas displaced substantially by 180.degree. axially as well as along the circumference with respect to one another on its largest relative diameter. The vaulted areas, while enclosing a shut-off surface which is diagonal on the circumference side with respect to the end of an engine shroud forming a casing lip, encloses an axially spaced circumferential surface which is shut off in the manner of an annular slide valve from the end of the shroud.

Abstract: An integrated turboramjet engine has an axially slidable inlet cone, a rigid guide ring arranged concentrically outside the inlet cone, and a lock ring which can be slid axially against the inlet cone, whereby the air volume flowing into the air inlet can be introduced alternately into a turbo-inlet duct or a ram-air inlet duct in a low-loss and flow-promoting manner.

Abstract: With surface sections vaulted with respect to the valve centerline the valve mates with a stationary companion surface on an annular casing lip to optionally shut off or expose the engine by having vaulted surface sections which are arranged at an axial distance an angularly offset over the circumference by essentially 180.degree. with the valve centerline, forming its largest relative diameter; where the vaulted surface sections form a valve of axially and circumferentially three-dimensionally displaced drop or mushroom shape.

Abstract: A heat exchanger has two collecting pipes and a streamlined-section tube matrix connected with these two pipes. The collecting pipes comprise several thin sheet metal shells connected with one another which permits simplified and higher speed manufacture of the collecting pipes, particularly since manufacture of cutouts in the collecting pipes for fitting through the small streamlined-section tubes, which is otherwise very time-consuming, can be significantly simplified.

Abstract: A method and apparatus for regulating the damping of masses rotating on roller bearings. An oil pressure film in an oil pressure gap has its viscosity changed via temperature control as a function of the vibrating condition of the rotating masses in order to provide an optimally quiet operation of the rotating system.

Abstract: A method for compensating thermally induced displacement between a workpiece clamped for machining relative to a tool arranged on a tool holder of an automatically controlled machine tool, such as a lathe, where use is made of mechanical sensors to sense and correct deviations between programmed and actual tool positions relative to the workpiece. With the workpiece clamped in place, a mechanical workpiece sensor clamped in a work holder is adjusted to make mechanical contact with the workpiece in the actual position in which the workpiece is to be machined or has been previously machined. Adjustment to a thermally compensating position of a tool measuring device coupled to a mechanical tool sensor is made via the adjusted mechanical workpiece sensor.

Abstract: A heat exchanger having two parallel manifold ducts that communicate with one another through a matrix of several rows of heat exchange tubes, in which a number of sheet metal tray members placed on top of one another form the rows of tubes. Two complementary sheet metal tray members are joined to one another each having a number of parallel longitudinal slots that are interrupted by webs. The heat exchange tubes are formed by opposed trough-shaped portions formed between the slots of the joined complementary tray members.

Abstract: A composite material is produced from a metal core and fiber-reinforced plastic material, in which the reinforcing fibers penetrate into and entwine around the metal core without coming into contact with the metal core. Parts for aircraft and turbine construction can be made from the composite material to provide higher impact strength and rigidity at less weight as compared to metal components.