Abstract: The invention is directed to a friction welding process for mounting blades of a rotor for a flow machine. A plurality of oblong welding surfaces are provided at a circumferential surface of a carrier and are respectively welded to a welding surface of a blade. The welding temperature is generated by pressing the welding surfaces together and by an oscillating relative motion between the blade and the carrier in the welding plane. At least the blade or the carrier is additionally heated to a temperature lying below the welding temperature in the region of the welding surface.

Abstract: In a method for coating workpieces with a coating material by a gas phase diffusion coating process, the coating material is conveyed in the form of a metal halide compound from a coating material source (9A, 9B, 9C) to the workpiece (7) by means of a metal halide gas circulation flow (F). The gas circulation flow (F) is physically induced due to convection by establishing a temperature gradient between the workpiece (7) and the coating material source (9A, 9B, 9C), and is reinforced by the chemical reactions taking place. An apparatus for carrying out a gas phase diffusion process includes a reaction vessel (3) enclosing a reaction chamber (1) in which the workpiece (7) is arranged. The apparatus further includes a metal halide generator (9A, 9B, 9C) arranged in the reaction chamber (1), and a heater (5) as well as a cooling device (6) and a thermal conduction arrangement (8) for establishing a temperature gradient between the workpiece (7) and the metal halide generator (9A, 9B, 9C).

Abstract: A process and arrangement for manufacturing brush-type seals having inclined bristles provides at least one ring-shaped brush-type seal having radially extending bristles of a length which, by way of the inclining of the bristles with respect to the radii of the ring-shaped brush-type seal leads at least essentially to the desired brush diameter; positions the at least one brush-type seal and at least one heatable annealing wall of an annealing device relative to one another so that the free bristle ends, while the bristles are bent, rest against the annealing wall, and simultaneously or subsequently rotating the at least one brush-type seal and at least the heatable annealing wall relative to one another until the bristles are inclined with respect to the radii of the ring-shaped brush-type seal in its ring plane by a definable angle; heats the annealing wall to a definable temperature; maintains the temperature of the heated annealing wall for a definable time period; and removes the at least one brush-type

Abstract: In a method for coating workpieces with a coating material by a gas phase diffusion coating process, the coating material is conveyed in the form of a metal halide compound from a coating material source (9A, 9B, 9C) to the workpiece (7) by means of a metal halide gas circulation flow (F). The gas circulation flow (F) is physically induced due to convection by establishing a temperature gradient between the workpiece (7) and the coating material source (9A, 9B, 9C), and is reinforced by the chemical reactions taking place. An apparatus for carrying out a gas phase diffusion process includes a reaction vessel (3) enclosing a reaction chamber (1) in which the workpiece (7) is arranged. The apparatus further includes a metal halide generator (9A, 9B, 9C) arranged in the reaction chamber (1), and a heater (5) as well as a cooling device (6) and a thermal conduction arrangement (8) for establishing a temperature gradient between the workpiece (7) and the metal halide generator (9A, 9B, 9C).

Abstract: A brush for sealing a gap between a rotor/stator system comprises a rotor-concentric clamping ring whose interior chamber receives bristle bundles that project into gap. The bundles are wrapped around core ring that extends into the interior of clamping ring. The core ring has separating disks that are spaced apart from one another in the circumferential direction by an angular pitch .alpha., and by winding ribs that are wrapped by the bundles. The winding ribs connect adjacent separating disks in such fashion that as a result of the diagonal positioning of separating disks in the circumferential direction, bundles are aligned at an angle .beta. to radius R. This makes it possible to hold bristle bundles securely with a predetermined angular orientation.

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 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 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 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 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 system is provided for cooling especially the backplate of a flame tube of a combustion chamber for gas turbine engines, of the type having at least one burner arranged on the backplate and having a fuel nozzle and at least one swirler arranged coaxially with the fuel nozzle for the supply of combustion air. The backplate is cooled with compressed air diverted from a compressor and ducted to a head end of the combustion chamber. The backplate forms at least one cooling air duct to carry the compressed air supplied for backplate cooling, and the cooling air duct communicates at its outlet end at the burner with the flame tube such that the compressed air issuing from the cooling air duct enters into combustion in the primary zone. At its outlet end the cooling air duct can communicate with the air inlets of at least one swirler.

Abstract: Rotor blades (1) are held by means of toothed roots (3) in correspondingly profiled axial grooves (4) of a rotor wheel rim (5). Between each root end and the base of an axial groove (4), there is formed a radial gap (S) accommodating a rivet (6). Each rivet (6) is centrally guided on two inserts (9, 9') resting against the base of the axial groove (4) in the radial gap (S) and having bent or angled end parts (10, 10') resting against the front and rear faces of the wheel rim (5). Seating wedges (11, 11') surround the upset head (8) and the set head (7) of the rivet (6) and are axially and radially clamped to wedge-shaped complementary surfaces (G, G') of the root end and of the respective insert (9, 9') by riveting. As a result, an improved radial and axial clamping of the rotor blades is achieved.

Abstract: A bearing arrangement is provided for rotors of jet engines with a bearing, which is mounted on a rotor carrier via a bearing carrier. In the event of failure, for example if the blade of a compressor rotor breaks, damage to or destruction of the rotor carrier or of the housing should be prevented by the fact that a breaking piece, which breaks under a defined load, is arranged concentrically between the rotor carrier and the bearing carrier. In this way, the transfer of extreme radial loads to the rotor carrier or to the rotor housing enclosing it is largely avoided, provided that the rotating member has not yet come to a standstill. The bearing arrangement is particularly of interest for turbo jet engines for aeroplanes, where for example, in the case of damage to a fan-rotor blade, the effect of a destructive force of a rotor running at high speed on neighboring housing areas can be reduced.

Abstract: The blades of a turbine rotor are secured to a rotor disk by inserting the blade foot with its serrations into a respective serrated groove in the rim of the rotor disk, whereby serrations of blade foot side surfaces mesh with corresponding serrations in the side walls of the grooves in the rotor rim to interlock the blade foot with the rotor disk in the radial direction. The axial locking of the blade foot in the groove is accomplished by a rivet connection having a rivet shaft positioned in a gap between the radially inwardly facing sole of the blade foot and the radially outwardly facing bottom of the groove. The rivet heads rest against washers or washer rings. If flat head rivets are used, these heads are received in countersunk recesses in the washers or washer rings that bear partially against the side surface of the rotor disk rim and partially against an axial end surface of the respective blade foot.