Abstract: An adjustable radial flow diffuser for a radial flow compressor includes adjusting elements having diffuser blades. The adjusting elements are arranged in a diffuser annulus uniformly distributed along the diffuser circumference with an angular pitch .delta.. The adjusting elements further are swivellable about an adjusting axis V parallel to the longitudinal axis of the compressor for changing the narrow cross-section between the diffuser blades. The adjusting elements have either a substantially U-shaped or H-shaped cross-section with sector-shaped plates that are mounted on both sides of a blade root to form the legs. The diffuser blade forms the web of the substantially U or H shaped cross-section.

Abstract: A throttle flap construction (12) is installed in an exhaust gas duct (11). For the installation the duct wall is provided with a radially facing, axially extending narrow slot (20) centrally provided with a circular opening so that a flap disk (14) may pass radially inwardly through the slot while a bearing portion (17) of the flap disk (14) may pass through the central circular opening. During installation, the flap disk (14) extends vertically when the throttle unit is inserted, a cover (16) is bolted to a flange (11A) surrounding the slot (20) and the central opening (21). Thus, the duct (11) can be properly sealed without cutting entirely through the duct in a radial plane.

Abstract: An arrangement for sealing structural members particularly in the case of turbo-engines is provided. A structural member is to be divided along a first plane into segments, which can be moved relative to one another, and is to be movable in a second plane which is angularly offset with respect to the first plane. Projections of the segments sealingly engage in a groove of an additional structural member. Expansion gaps, which are arranged between abutting edges of the segments, are to be sealed off longitudinally and transversely with respect to the course of the gap by sealing plates. In this case, each expansion gap is to be sealed off between a sealing plate arranged transversely to the course of the gap and an opposing surface of the groove acting as a sealing surface by means of a V-shaped insert.

Abstract: A device operates a swirling device which controls the flow rate of combustion air of a burner for gas turbine engines. At the head end of a combustion chamber, a ring body which is arranged coaxially with respect to the fuel nozzle is to have swirling ducts whose cross-sections are controllable by duct walls of a ring which is axially displaceable on the ring body. The axial displacement of the ring is to take place by means of a control piston which is axially displaceable in a housing, is spring-loaded on one side, is also actuated by a valve-controlled pressure difference existing on the spring side between an ambient pressure and a primary air pressure, controls openings communicating with the valve and the head end of the combustion chamber, and is acted upon on piston surfaces, which are free with respect to the housing, on the one side, by a pressure of supplied primary air existing at the head end and, on the other side, by the chamber pressure existing at the burner.

Abstract: An abradable layer for labyrinth seals of a turbo-engine, particularly a gas turbine is provided. The labyrinth is made of a layered composite material with a core and a shell and embedments. A process for the manufacturing of this abradable layer is provided. In this case, the core is made of a felted or three-dimensionally crosslinked fiber body made of iron base, nickel base or cobalt base alloys and the shell consists of one or several precious metals or precious-metal alloys. Each core is completely surrounded by the shell material, in which case the embedments consist of oxidation-stable sliding materials of the oxide, carbide or nitride group with a hexagonal crystal lattice layer structure.

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: An exhaust gas duct for a row of a plurality of combustion engine cylinders has an exhaust pipe section extending alongside the cylinders and a cooling housing in which the exhaust pipe section is mounted. The cooling housing has a middle longitudinal section and two end sections, one of which is a cover and the other is a mounting connector duct end ring. The middle section has substantially circular end portions with cooling liquid flow ducts therein and a flange portion for mounting to a cylinder head. The middle section is made of extruded standardized stock of light metal which facilitates the manufacture and assembly of the duct. A compact structural volume is also achieved thereby. The extruded stock material assures a good dimensional accuracy, a high surface quality, and good sealing characteristics.

Abstract: Inner and outer surfaces of structural components are aluminized by an aluminum gas diffusion process. For this purpose a gas mixture of a halogenous gas, aluminum monohalide gas, hydrogen, and negligible proportions of aluminum trihalide gas is caused to flow over the outer and inner surfaces of the component to be coated. The process is performed in a vessel in which at least two different temperature zones are maintained for keeping one or more aluminum sources at a higher temperature than the component to be coated. Especially gas turbine engine blades are protected against oxidation and corrosion by the so formed aluminum diffusion coatings on outer and inner surfaces of the blades.

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: A structural component made of an iron-base alloy is protected against corrosion by a coating which is produced to have three layers. First, a primary coating or first layer is applied, and then a top coating or second layer is applied. An intermediate layer is formed by a reaction between the first and second layers. Specifically, the intermediate layer is formed after application of the primary coating and of the top coating, by a heat treatment within a reaction temperature range in which intermetallic nickel aluminum or cobalt aluminum compounds are formed. A fourth sealing coat is optional. The primary coating is a nickel or cobalt coating. The intermediate layer comprises intermetallic compounds of nickel aluminide or cobalt aluminide formed by the reaction. The top coating is an aluminum base or aluminum alloy base high-temperature lacquer including a binder. Such a combination coating is especially resistant to fretting, oxidation and etching corrosion.

Abstract: An exhaust gas turbocharger having rotor runners disposed in roller bearings protects the roller bearings from shocks and vibrations by a pressure-oil-filled oil film damper. By a shut-off device arranged in the main lubricating oil duct, the lubricating oil supply of the roller bearings is shut off when the rotor runners are stopped. However, the pressure oil supply of the oil film damper remains operative so that the oil film damper retains its operability.

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 structural component made of an iron-base alloy is provided with a corrosion inhibiting coating which has three layers, namely a primary coating or layer, an intermediate layer, and a top coating or layer. A fourth sealing coat is optional. The primary coating is a nickel or cobalt coating. The intermediate layer comprises intermetallic compounds of nickel aluminide or cobalt aluminide. The top coating is an aluminum base or aluminum alloy base high-temperature lacquer including a binder. Such a combination coating is especially resistant to fretting, oxidation and etch corrosion. The component is suitable especially for parts of gas turbine engine housings. The intermediate layer is formed after application of the primary coating and of the top coating, by a heat treatment within a reaction temperature range in which intermetallic nickel aluminum or cobalt aluminum compounds are formed.

Abstract: A structural component made of a base metal composition on a nickel or cobalt basis is provided with a protective coating against oxidation, corrosion, and thermal fatigue. The protective coating and the base metal are made of chemically the same or identical material, whereby the bonding of the protective coating is increased, the tendency to crack is reduced, and the resistance to thermal fatigue is improved. The grain size of the coating is substantially smaller than the grain size of the base metal composition.

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.

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.