Abstract: The present invention relates to a testing apparatus for testing vibration damping elements of moving blades, with a mounting means to be attached to an oscillating apparatus, whereby a damping element to be tested is to be arranged between the mounting means and the blades, and at least one extendable body that can be charged with pressure is arranged between the mounting means and the damping element.

Abstract: A brush seal assembly for turbo-engines is provided for sealing off spaces on a circumferential gap which are differently acted upon by pressure, particularly between an engine stator and an engine rotor. A holding device for a bristle bundle is provided on the engine stator, from which holding device the bristle bundle is guided between circumferential webs in a sealing manner against the engine rotor and forms an axial gap in the circumferential direction with respect to one web facing the high-pressure side. The upstream one of the circumferential webs, together with the engine rotor surface, forms an axial ring gap for flow of fluid therethrough. Turbulence reducing structure is disposed upstream of the upstream web in the high pressure space and serves to reduce the turbulence in flow of air from the upstream space through the axial ring gap. This turbulence reducing structure can be in the form of a metal sponge and/or a honey comb structure.

Abstract: The present invention provides dual-fuel burners for the oxidation of liquid and of gaseous fuel with air. A dual-fuel burner is provided with an atomizer nozzle which generates a divergent spray cone of liquid fuel, and with an annular atomizer lip as an impact member for the liquid fuel spray cone. The dual-fuel burner has a primary channel for a first air stream through the spray cone and the inside of the atomizer lip, and a secondary channel for a second air stream over the outside of the atomizer lip with a common, coaxial mouth at an atomizer edge thereof. A channel for the gaseous fuel leads into the inside of the atomizer lip between the primary and secondary channels and discharges into one or both of the primary and secondary channels upstream of the atomizer edge.

Abstract: A method for manufacturing a cathode for a molten carbonate fuel cell includes oxidation of a porous precursor electrode and contact with molten carbonate. Following assembly of a layered arrangement containing the precursor electrode, a matrix layer made of molten carbonate, and a porous anode, the precursor electrode is anodically oxidized with a preset curve for the current density, and doped by contact with molten carbonate.

Abstract: The invention relates to a manufacturing process for brush-type seals having the following steps:Stacking of bristles in a bristle receiving shaft such that the bristles are partially situated next to the space for at least one brush cheek;adjusting the bristle receiving shaft in synchronization with the stacking of the bristles relative to a point of introduction of the bristles into the bristle receiving shaft so that the position of a bristle stack surface in the bristle receiving shaft remains at least essentially constant relative to the point of introduction;fastening the bristles on at least one brush cheek in the bristle receiving shaft; andremoving the at least one brush cheek with the bristles fastened thereto from the bristle receiving shaft.In addition, the invention provides an arrangement for manufacturing brush-type seals by means of which the above-mentioned process can be carried out correspondingly.

Abstract: Brush seal for sealing two spaces of differing pressure (P1, P2) between a stator (20) and a rotor (10) of a turbomachine. The bristles (30) of the brush seal comprise angled bristle sections (31), of which the ends run against the seal surface of the rotor (10). In this manner, a low bristle stiffness and a low required radial structural space can simultaneously be achieved.

Abstract: A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extending radially therefrom, and a stator having a plurality of compressor blades extending radially between a stator hub and a housing. The hub (2) of the rotor (1), and/or the hub of the stator, and/or the housing of the stator, have a circumferential surface contour that is not continuously rotationally symmetrical. Namely, a concave contour (K) is provided in the circumferential surface of the hub near the base of each blade (3) on the pressure side (PS) thereof, while the circumferential surface on the suction side (SS) of the base of each blade has a contour that is linear, slightly convex, convex/concave, or slightly concave to a lesser degree than the concave contour (K) on the pressure side of each blade.

Abstract: A brush seal is provided for sealing, with minimized leakage, a circumferential gap (S), for example between a rotor (1) and a stator (2) in a gas turbine engine. The brush seal includes a bristle housing (4) rigidly mounted on the stator or the rotor, and bristles (6) having fixed ends securely and durably held in the housing (4) and free ends protruding toward and into the annular gap (S). The housing (4) includes two holder disks (5A, 5B) with an interspace (Z) therebetween, wherein the interspace includes at least one of an axially directed first clamping portion (8) and a radially directed second clamping portion (10), and a widened non-clamping portion (7A, 7B). The fixed ends of the bristles are clampingly held in the first and second clamping portions, while the free ends of the bristles extend generally toward the opposite rotor or stator while being movably supported and guided by the widened non-clamping portion of the interspace (Z).

Abstract: A protective coating is applied on a local region of a surface of a component on which direct deposit of a uniform coating of protective material is impeded due to a complex shape of the region to be covered or inaccessibility or inability to apply a uniform deposition or electrical field therefor. The coating is formed by a foil having a solder backing layer with a thin layer of uniform thickness of the protective material electrolytically deposited on the backing layer, the foil being cut to size corresponding to an area of the local region of the component to be protected. The cut to size foil is positioned and held on the local region of the component to be protected; and fixed in place by melting the solder to fuse the foil to the component and cover the local region.

Abstract: A blade for a fluid flow machine such as a jet turbine engine includes a blade body (2) that is to be exposed to the fluid flow and therefore is subject to damage by erosion due to abrasive particle entrained in the fluid flow and due to thermal loading. The blade body (2) is a layered body including base layers (6) of a fiber reinforced synthetic material and a metallic cover layer (7) applied as an erosion protective layer onto at least a portion or the entirety of the surface of the base layers (6). The cover layer (7) includes metallic fibers or threads (9A, 9B) which are bonded with the fiber reinforced synthetic material of the adjacent base layers (6) by the same synthetic resin binder material permeating through and forming a matrix for all the layers (6 and 7). The metallic fibers or threads (9A, 9B) embedded in a synthetic resin matrix are characterized by a high degree of erosion resistance and a good tolerance for defects in the case of local impact or erosion damage.

Abstract: A brush seal (1, 101) seals a circumferential gap (S.sub.1) between two relatively rotatable machine components (2, 102; 3, 103), such as the rotor or a shaft and a stator of a fluid flow machine, such as a gas turbine engine. A plurality of seal bristles (4, 104) are fixed in a bristle holder (5) in an annular shape, and are mounted on the stator (3, 103) so that the free bristle ends (7, 107) extend toward and provide a seal against a seal surface (9, 109) of the rotor (2, 102). Each bristle includes a middle body portion (4A) that is tilted at a first tilt angle (.alpha..sub.1) in the circumferential direction following the rotation direction, and the free bristle end (7, 107) is bent or angled relative to the tilted body portion (4A) so as to extend at a second tilt angle (.alpha..sub.2) which is smaller than the first tilt angle (.alpha..sub.1). Preferably, the first tilt angle (.alpha..sub.1) is in the range from 30.degree. to 60.degree., while the second tilt angle (.alpha..sub.

Abstract: A seal arrangement provides a reliable and durable seal even around a protruding edge or corner of a rim of a first component that is connected to a second component, for example the rim of an oil pan that is connected to the rim of a crankcase and the rim of the housing of an equipment mount of an internal combustion engine. An angular edge is formed at the intersection of a first sealing surface between the oil pan and the crankcase and a second sealing surface between the oil pan and the equipment mount housing. First and second grooves extend in skew directions and offset from one another along the first and second sealing surfaces, and an offset recess extends along and in the direction of the intersection edge to interconnect the first and second grooves. A rubber-elastic seal member includes major portions received in the grooves and an offset portion received in the offset recess. The seal member is press-sealed against facing complementary surfaces.

Abstract: A brush seal (3) is provided to seal two differently pressurized spaces (R.sub.1, R.sub.2) on opposite sides of a rotor (1) cooperating with a stator (2), for example in a gas turbine engine, around a circumferential gap between the rotor (1) and the stator (2). The brush seal (3) includes seal bristles (5) having free ends extending annularly concentrically and parallel to a rotation axis of the rotor (1) and fixed ends received in a seal housing (6). A perimeter rim of the rotor (1) has an axis-concentric circumferential groove (7) therein, and the free ends of the seal bristles (5) reach into this circumferential groove (7). During operation of the rotor (1), fluid boundary layers are formed respectively between the seal bristles (5) and the side walls (9A, 9B) of the circumferential groove (7). The boundary layers (G.sub.I, G.sub.

Abstract: In a method of repairing worn blade tips of compressor or turbine blades, the worn blade tip (4) is first removed from the remaining blade portion (2) at a standardized height (h). The actual geometry of the end of the remaining blade portion (2) at the height (h) is measured, for example by optical digital image processing means. A repair part (4') is cut from a plate or sheet of repair material having a thickness (d) essentially corresponding to the difference between the nominal finished height (H) of the repaired turbine blade (1) and the standardized height (h) of the remaining blade portion (2) undergoing repair. The repair part (4') is cut to have a contour corresponding to the measured actual geometry of the end of the remaining blade portion (2) at the standardized cut-off height (h), for example using a laser cutting process CNC-controlled by the acquired data representing the actual blade geometry.

Abstract: A blade for a rotor, especially a turborotor, is made of two hollow blade foot sections having matching seam surfaces to form a hollow blade with a thickened foot that is butt-welded with its blade foot sole (7) to an integral welding stub of a rotor hub or disk. The two hollow blade foot sections are soldered to each other along a radially outer seam section (5) between the seam surfaces and welded to each other along a radially inner seam section (6) between the seam surface. The radially inner seam section extends from said blade foot sole. The welded seam normally ends in the thickened blade foot section (6) and is thus shorter than the soldered seam section (5).

Abstract: A lubricating system for an internal combustion engine maintains lubrication even in extreme emergency positions of the engine such as slants within the range of about 90.degree. to about 270.degree., relative to the horizontal and even for upside down engine positions. For this purpose, a hydraulic accumulator (16) is connected to the lubricant circulating circuit through a parallel connection of a non-return valve (17) and a controllable valve. Under normal operating conditions, the hydraulic accumulator is charged with lubricant under the pressure prevailing in the lubricant circulating system. Under emergency conditions, the normal lubrication is stopped and emergency lubrication continues through the controllable valve that is opened in response to a pressure drop in the normal lubricant circulating system.

Abstract: A blade for a rotor, especially a turborotor, is made of two hollow blade foot sections having matching seam surfaces to form a hollow blade with a thickened foot that is butt-welded with its blade foot sole (7) to an integral welding stub of a rotor hub or disk. The two hollow blade foot sections are soldered to each other along a radially outer seam section (5) between the seam surfaces and welded to each other along a radially inner seam section (6) between the seam surface. The radially inner seam section extends from said blade foot sole. The welded seam normally ends in the thickened blade foot section (6) and is thus shorter than the soldered seam section (5).

Abstract: Apparatus for vibration damping a rotor rotatably supported in a stationary housing by a bearing whose retainer housing is concentrically engaged in the stationary housing in an axial position by elastic elements. In order to avoid or reduce vibrations produced by rotation of the rotor particularly resonance vibrations, an oil space is formed between the stationary housing and the bearing retainer which is sealed at its ends by axially spaced sealing rings. An inlet channel is provided in the stationary housing for supplying oil under pressure into the space and outlet channels for the oil are formed in the bearing retainer in the vicinity of the sealing rings. The oil discharge channels are provided with constricted regions whose flow cross-sections and lengths are related to the flow cross-section of the oil inlet channel such that the oil discharge channels act as chokes or throttles.

Abstract: A brush seal for sealing a gap between two spaces at different pressures on opposite sides of a rotor and a stator. The brush seal is formed as a plurality of bristles and the bristles are mounted in the stator to project radially therefrom, across said gap, to contact the rotor. A clamping ring clamps a stack of the bristles around an annular core in U-shaped fashion with legs of the bristles extending through an annular slot towards the rotor. The clamping ring includes a C-shaped section which clamps the bristles against the core and reverse bend portions at opposite ends of the C-shaped section. The reverse bend portions are axially spaced from one another and form the annular slot through which the legs of the bristles extend.

Abstract: A method is provided for improving the loading behavior of an internal combustion engine that is supercharged by an exhaust turbocharger and is operated in an essentially steady-state mode, in which system-related sags in rpm when a load is applied the entire performance potential of the motor can be exploited by a temporary cutting in of a dynamic load- and motor-operation-adjusted variable regulation of the beginning of delivery. By regulating the beginning of delivery, the indicated average pressure is increased while exhausting the stated mechanical load limits, while the boost pressure buildup, which otherwise is delayed disadvantageously and is necessarily produced in Diesel engines supercharged with exhaust turbochargers by the limited acceleration capability of the turbocharger, can be used to increase performance by influencing the combustion process, said influence being regulated by the beginning of delivery.