Abstract: An inner shroud (6) for the stator blades (3) of the compressor of a gas turbine is a plastic component and includes certain additives, which may be concentrated in partial areas for specific functionality, and/or pre-manufactured inserts for sealing, ensuring sliding properties, wear protection and/or setting heat expansion. Such an inner shroud made of plastic material fulfills all requirements usually imposed on inner shrouds made of metal, while being simply producible and having low weight.

Abstract: A rotor and a stator assembly, wherein the rotor (30) comprises at least one stage of rotor blades (32) and the stator (34) comprises at least one stage of turbine stator vanes (36). The rotor blades (32) have aerofoils and platforms (42) and the turbine stator vanes (36) having aerofoils and platforms (48). A seal (43,45) is defined between the rotor blade (32) platforms (42) and the stator vane (36) platforms (48) wherein a portion (42B) of the rotor blade platforms (42) and/or a portion (48B) of the stator vane (36) platforms (48) comprise a shape memory alloy member or a bimetallic member. The shape memory alloy member, or bimetallic member, controls the flow of cooling air through the seals (43,45) allowing a greater cooling flow at higher temperatures than at lower temperatures.

Abstract: A combustion chamber inner casing (24) has a flange (28) on its downstream end. A retaining seal ring (40) is bolted to the flange (28) and traps a flanged seal ring (46) against the flange (28) in a manner that allows the seal ring (46) to move by expansion, relative to seal ring (40).

Abstract: A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, 4) and sealing element (5, 6) are assembled for use in the rotor. The heat shield (3, 4) includes a first slot (7, 8) for accommodating a first member (11, 12) of the sealing element (5, 6), and a root portion of the blade (2) includes a second and third slot (9, 10) for accommodating a second member (13, 14) of the sealing element (5, 6). The first slot (7, 8) extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot (9) extends, and the first member (11, 12) extends in a direction which is substantially mutually perpendicular to a direction in which the second member (13, 14) extends.

Abstract: A drum-type rotor carries an annular row of moving blades having root portions held within a slot in the periphery of the rotor. A turbine casing surrounds the rotor and carries a static blade assembly with an annular row of static blades which, together with the annular row of moving blades, constitutes an impulse turbine stage. The static blade assembly has a radially inner static ring confronting a periphery of the rotor with a seal acting therebetween. The static blade assembly has an outer static ring which has a substantially greater thermal inertia and stiffness then the inner static ring and is capable of sufficient radial sliding relative to the casing so as to accommodate relative thermal expansion and contraction of the outer static ring and the turbine casing.

Abstract: A seal arrangement for reducing the seal gaps within a rotary flow machine, preferably an axial turbomachine, has rotor blades and guide vanes, which are respectively arranged in at least one rotor blade row and guide vane row and have respective blade/vane roots (2,3) which protrude into fastening contours within the rotor blade and guide vane rows. A sealing element (4) of plastically deformable material is provided between at least two adjacent blade/vane roots (2,3) along a rotor blade row or guide vane row or between a blade/vane root (2,3) of a rotor blade or guide vane and a rotary flow machine component directly adjoining the blade/vane root.

Abstract: It is disclosed a seal assembly (5) which comprises a layered structure. It consists of a first layer (9, 12) of a base material, a second layer (10) of thermal insulating material on top of the base material and a third layer (11, 12) of base material or an oxide resistant material on top of the second layer (10) of thermal insulation. The inventive seal assembly (5) described herein can be arranged between combustor liner segments (2).

Abstract: A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).

Abstract: Spline seals are disposed in circumferentially registering slots of adjacent arcuate packing seal segments disposed in grooves on inner hooks of a steam turbine diaphragm assembly. The spline seals extend in a gap between the endfaces of the segments and minimize or preclude steam leakage flows past the endfaces. The spline seals may be oriented in axial and circumferential directions to minimize leakage flow paths in a generally radial direction and/or may be inclined radially in a downstream direction to seal against steam leakage flow in an axial direction. The spline seals are disposed in the slots which may be formed as part of original equipment manufacture or may be machined in segments with spline seals provided as retrofits.

Abstract: Aspects of the invention relate to a compressor system for a turbine engine that not only provides large compressor seal clearances as the engine passes through non-standard operating conditions, but also minimizes the clearances during normal engine operation, thereby increasing the efficiency of the compressor. In one embodiment, a substantially annular seal land is secured at one end to an annular extension arm on a compressor disk. When the engine reaches steady state operation, the non-attached end of the seal land can extend radially outward to reduce the clearance between the seal land and a shroud extending over the ends of the adjacent stationary airfoils. The seal land can be designed to resist the rotational forces imparted by the turning rotor until a certain desired operating condition is reached. In one embodiment, the seal land reaches full extension when the engine is operating at about 3600 rpm.

Abstract: A method to facilitate sealing between a rotary component and a stationary component is provided. The rotary component includes at least one bucket secured thereon, the bucket having a flow admission side and a flow exit side. The method includes coupling a spill strip in a gap defined between the rotary and stationary component, wherein the spill strip has a substantially flat contact surface, and coupling a cover to a radially outer tip of the bucket, wherein a protrusion extends from the bucket cover to contact the substantially flat contact surface of the spill strip.

Abstract: A sealing assembly for disposition in a rotary machine is disposed between a rotary component and a stationary component of the rotary machine. The sealing assembly includes at least one sealing strip affixed by caulking to one of the rotary and stationary components. An abradable portion is disposed on another of the rotary and stationary components and is positioned radially opposite to the at least one sealing strip. The abradable portion includes a thermal spray coated material, and the thermal spray coated material includes Cobalt, Nickel, Chromium, Aluminum, Yttrium (CoNiCrAlY) and further includes a material selected from the group consisting of hexagonal boron nitride, a thermoset polymer, and combinations thereof.

Abstract: A ventilation device for a high pressure turbine rotor in a turbomachine, the turbine comprising upstream and downstream turbine disks fitted with blades, the device comprising a cooling circuit being supplied by a cooling airflow D taken from the back of the combustion chamber. The circuit is such that the airflow passes through orifices formed in an upstream flange of the upstream disk, such that this airflow circulates in the axial direction towards the downstream side between an inner reaming of the upstream disk and a downstream flange of the downstream disk, the device also comprising a labyrinth inserted between the two disks, such that the airflow is divided into a first flow F1 and a second flow circulating on each side of labyrinth towards the blades.

Abstract: A blade retention assembly is provided that comprises: a disk, a plurality of blades, each having a dovetail disposed in one of an array of slots formed in the outer periphery of the disk, an annular inner retainer attached to the disk, and a plurality of arcuate blade retainers, the blade retainers being secured to the inner retainer by a hooked rabbet joint. A blade retainer is also provided, comprising an arcuate body having a planar inner face having an arcuate depression formed therein defining a sealing lip, and an aft face disposed opposite the inner face which has an arcuate rim formed therein.

Abstract: A simplified support device (110) for nozzles (112) of a gas turbine stage, of the type in which the support device (110) is interposed in a rotor of the gas turbine, between an upstream blading disc (122) and a downstream blading disc (124) of the nozzles (112), and is provided with honeycomb-type alveolar seals (120); the nozzles (112) of the gas turbine stage comprise an annular body which is divided into nozzle segments (112) and the honeycomb-type alveolar seals (120) are anchored directly to these nozzle segments (112).

Abstract: A sealing air bypass flow path is provided in a gas turbine for supplying sealing air to a sealing air supply flow path by bypassing the flow path between each tangential on board injection (TOBI) nozzles and disk holes.

Abstract: A device for sealing between the guide vanes (1) and the rotor (17) of turbomachines, especially gas turbines has inner rings (3) suspended on the vane footing (14) of the guide vanes (1) in a thermally elastic manner with soldered honeycomb seal (4) and labyrinth tips (5) arranged on the rotor (17). First flow channels, which are connected to the cavities (21) of the cooled guide vanes (1), through which said cavities cooling air flows, are led through the vane footings (14). The first flow channels are connected to at least one of second flow channels led through the inner ring (3) to the vicinity of the honeycomb seal (4). The second flow channels open into at least one of third flow channels that are open at the rear edge of the inner ring (3) or are led to an annular groove (10) open toward the honeycomb seal (4) on the underside of the inner ring (3).

Abstract: In the diaphragm packing area of a steam turbine, a raised platform affords an annular sealing surface for contact with a brush seal carried by the diaphragm. The platform includes a plurality of platform sealing segments secured to a locking device carried by the rotor. The locking device includes a raised rim having flanges with axially oppositely projecting teeth circumferentially spaced one from the other by slots. The platform segments each include a channel section having flanges with axially inwardly directed teeth. By displacing the platform sealing segments radially inwardly and passing the teeth of the locking device and platform segments through the respective slots, the platform segment teeth lie radially inwardly of the locking device teeth. The platform segments are then rotated radially to align the teeth to secure the sealing surface against radial movement. One segment may be staked, welded or screwed to the locking device to preclude circumferential movement during turbine operation.

Abstract: In the diaphragm packing area of a turbine, a raised platform affords an annular sealing surface for contact with a brush seal carried by the diaphragm. The platform includes a plurality of platform sealing segments secured to a locking device carried by the rotor. The locking device includes a pair of raised rims having flanges with teeth projecting axially toward one another and defining slots therebetween. The platform segments each include underlying flanges with axially oppositely directed teeth. By displacing the platform sealing segments radially inwardly and passing the teeth of the locking device and platform segments through the respective slots, the platform segment teeth lie radially inwardly of the locking device teeth. The platform segments are then rotated radially to align the teeth to secure the sealing surface against radial movement. One segment may be staked, welded or screwed to the locking device to preclude circumferential movement during turbine operation.

Abstract: A method of assembling a steam turbine includes positioning a sealing member in a leakage path defined between a first stage nozzle diaphragm and a packing casing, wherein the first stage nozzle diaphragm has a first coefficient of thermal expansion, and the packing casing has a second coefficient of thermal expansion, and coupling the first stage nozzle diaphragm and the packing casing such that the sealing member is fixedly secured between the first stage nozzle diaphragm and the packing casing.

Abstract: A steam turbine has a diaphragm (20) and a rotor/bucket assembly (1). Steam directed to the assembly flows through the diaphragm. A setback (38b) is formed in a root setback face (38) of the diaphragm adjacent the assembly, and a plurality of grooves (36) formed in the setback provide a steam flow path (Qf) between the diaphragm and rotor/bucket assembly. The grooves are radially extending grooves extending the height of the setback, and the number, width, and spacing of the grooves are a function of the design of the steam turbine. When the steam turbine is in a fully closed position, the grooves provide a steam flow path by which upstream pressure on the rotor/bucket assembly is relieved and damage to the assembly prevented.

Abstract: A method for sealing between a rotary component and a stationary component. The method including positioning a seal assembly having a plurality of teeth adjacent the stationary component and positioning a packing surface to interface with the rotary component. The packing surface at the rotary component includes at least one step that has an axial width that is approximately equal to a distance the rotary component axially shifts relative to the stationary component during transition from startup to steady state operating conditions.

Abstract: A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim protection material to avoid wear to the shim on the contact side. The shim protection material can include one or more metal fiber cloth layers secured to the shim, for example, by seam welding to a pair of rails or to the legs of the shim.

Abstract: The root region of a flowpath through a turbine includes a sealing configuration for minimizing leakage flow and secondary aerodynamic losses. Entrance and exit root radial seals are provided between upstream and downstream nozzles at locations radially inwardly of the root region of the flowpath to minimize radial leakage flow. To minimize intrusion flow into the flowpath from rotor pumping action and consequent aerodynamic losses, an exit flow guide on each bucket turns the exiting radial flow in a predominantly axial direction. Additionally, the upstream bucket root radius and nozzle root radius are faired or tapered to minimize the possibility of a protuberance projecting into the flowpath at steady state operation. An additional entrance root axial fin is provided on the buckets to reduce the flow coefficient and afford further reduction in leakage flow.

Abstract: In the diaphragm packing area of a steam turbine, a raised platform affords an annular sealing surface for contact with a brush seal carried by the diaphragm. The platform includes a plurality of platform sealing segments secured to a locking device carried by the rotor. The locking device includes a raised rim having flanges with axially oppositely projecting teeth circumferentially spaced one from the other by slots. The platform segments each include a channel section having flanges with axially inwardly directed teeth. By displacing the platform sealing segments radially inwardly and passing the teeth of the locking device and platform segments through the respective slots, the platform segment teeth lie radially inwardly of the locking device teeth. The platform segments are then rotated radially to align the teeth to secure the sealing surface against radial movement. One segment may be staked, welded or screwed to the locking device to preclude circumferential movement during turbine operation.

Abstract: In the diaphragm packing area of a turbine, a raised platform affords an annular sealing surface for contact with a brush seal carried by the diaphragm. The platform includes a plurality of platform sealing segments secured to a locking device carried by the rotor. The locking device includes a pair of raised rims having flanges with teeth projecting axially toward one another and defining slots therebetween. The platform segments each include underlying flanges with axially oppositely directed teeth. By displacing the platform sealing segments radially inwardly and passing the teeth of the locking device and platform segments through the respective slots, the platform segment teeth lie radially inwardly of the locking device teeth. The platform segments are then rotated radially to align the teeth to secure the sealing surface against radial movement. One segment may be staked, welded or screwed to the locking device to preclude circumferential movement during turbine operation.

Abstract: A composite face seal has an annular seal rotor and an annular seal stator, both having a metal base portion and a radially extending flange. The flange has first and second axially facing surfaces. A first ceramic ring may be mounted to the first surface of the flange of either or both of the seal rotor and the seal stator by a first braze joint. A second ceramic ring may be mounted to the second surface of the flange of either or both of the seal rotor and the seal stator by a second braze joint. Each of the braze joints may include a molybdenum ring disposed between two braze rings or, for thicker seal assemblies, molybdenum and nickel rings disposed between braze rings.

Abstract: A method enables a nozzle assembly for a gas turbine engine rotor assembly to be fabricated. The rotor assembly includes at least two adjacent rows of rotor blades coupled together by a disk spacer arm. The method includes providing a nozzle assembly that includes at least one nozzle including a vane that extends outwardly from a radially outer side of an inner band, coupling the nozzle assembly into the rotor assembly between the two adjacent rows of rotor blades, and coupling a seal assembly that includes a backing piece to the nozzle assembly such that the backing piece is substantially parallel to the rotor assembly disk spacer arm.

Abstract: A blade retention assembly is provided that comprises: a disk, a plurality of blades, each having a dovetail disposed in one of an array of slots formed in the outer periphery of the disk, an annular inner retainer attached to the disk, and a plurality of arcuate blade retainers, the blade retainers being secured to the inner retainer by a hooked rabbet joint. A blade retainer is also provided, comprising an arcuate body having a planar inner face having an arcuate depression formed therein defining a sealing lip, and an aft face disposed opposite the inner face which has an arcuate rim formed therein.

Abstract: A method enables a nozzle assembly for a gas turbine engine rotor assembly to be fabricated. The rotor assembly includes at least two adjacent rows of rotor blades coupled together by a disk spacer arm. The method includes providing a nozzle assembly that includes at least one nozzle including a vane that extends outwardly from a radially outer side of an inner band, coupling the nozzle assembly into the rotor assembly between the two adjacent rows of rotor blades, and coupling a seal assembly that includes a backing piece to the nozzle assembly such that the backing piece is substantially parallel to the rotor assembly disk spacer arm.

Abstract: A base plate and honeycomb member disposed at the inner circumference side of an inside shroud are fixed to the inside shroud, at a phase deviation in the peripheral direction, with respect to the inside shroud, so as to plug the missing range of seal member, out of gaps between adjacent inside shrouds, and therefore leakage of purge air from the missing range of seal member is prevented without adding new constituent members.

Abstract: A collision plate having plural small holes is provided at an interval from a bottom surface of an inner shroud to form a chamber and guides cooling air from the small holes into the chamber. A leading edge flow path is provided at a leading edge side along a width direction and introduces the cooling air. A side flow path is provided along both sides of the inner shroud and guides the cooling air to a trailing edge side. A header is formed along the width direction near the trailing edge and guides the cooling air from the side flow path. Plural trailing edge flow paths are formed at the trailing edge side at intervals along a width direction, in which one end of each flow path is connected to the header and the other end is open at the trailing edge, and the cooling air in the header is ejected from the trailing edge.

Abstract: A gas turbine engine aspirating face seal includes a rotatable engine member and a non-rotatable engine member and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces circumscribed about a centerline are operably associated the rotatable and non-rotatable engine members respectively. Radially inner and outer tooth rings axially extend away from a first one of the rotatable and non-rotatable gas bearing face surfaces across the leakage path and towards a second one of the gas bearing face surfaces. A pull off biasing means is used for urging the inner and outer tooth rings axially away from the second one of the gas bearing face surfaces. The rotatable engine member may be a side plate mounted on a rotor disk and the non-rotatable engine member is mounted on a translatable piston axially movably supported on a stationary face seal support structure.

Abstract: In a steam turbine, a combined brush and labyrinth seal is provided between a diaphragm web and a radially outwardly projecting platform between axially adjacent wheels on the rotor. The brush seal is located upstream of the labyrinth seal teeth. The platform has at least one and preferably a pair of flanges or fins projecting in opposite axial directions adjacent radial outer ends of the platform. Non-uniform heat distribution resulting from the frictional contact between the bristles of the brush seal and a sealing surface on the platform along the rotor surface affecting rotor dynamics is thereby eliminated or minimized.

Abstract: A gas turbine engine aspirating face seal includes a rotatable engine member and a non-rotatable engine member and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces circumscribed about a centerline are operably associated the rotatable and non-rotatable engine members respectively. Radially inner and outer tooth rings axially extend away from a first one of the rotatable and non-rotatable gas bearing face surfaces across the leakage path and towards a second one of the gas bearing face surfaces. A pull off biasing means is used for urging the inner and outer tooth rings axially away from the second one of the gas bearing face surfaces. The rotatable engine member may be a side plate mounted on a rotor disk and the non-rotatable engine member is mounted on a translatable piston axially movably supported on a stationary face seal support structure.

Abstract: In a steam turbine, a combined brush and labyrinth seal is provided between a diaphragm web and a radially outwardly projecting platform between axially adjacent wheels on the rotor. The brush seal is located upstream of the labyrinth seal teeth. The platform has at least one and preferably a pair of flanges or fins projecting in opposite axial directions adjacent radial outer ends of the platform. Non-uniform heat distribution resulting from the frictional contact between the bristles of the brush seal and a sealing surface on the platform along the rotor surface affecting rotor dynamics is thereby eliminated or minimized.

Abstract: The subcavity between a stator seal assembly and the upstream rotor disc in the interstage disc cavity of a gas turbine is divided into a radially inward region and a radially outward region by an annular baffle that extends from the seal assembly partially across the subcavity toward the rotor disc. The volume of cooling air injected into the interstage disc cavity can be reduced to increase turbine efficiency because the baffle interrupts recirculation in the subcavity to confine ingress of the hot main gas flow to the radially outward region away from the rotor seals.

Abstract: A steam turbine has a rotor mounting axially spaced rotor wheels having male dovetails for mounting a plurality of axially spaced buckets having female dovetails. A plurality of arcuate bridging members extend axially between the axially adjacent bucket dovetails at locations spaced radially outwardly of the surface of the rotor shaft. A diaphragm in radial opposition to the bridging member mounts a brush seal having bristles engaging the bridging member. The bridging member carries backup labyrinth seal teeth for sealing with the diaphragm. The friction generated by contact between the brush seal bristles and bridging members lies radially outwardly of the rotor whereby non-uniform distribution of heat about the rotor surface due to frictional contact with the brush seal is avoided, with consequent avoidance of rotor bowing.

Abstract: A steam turbine has a rotor mounting axially spaced rotor wheels having male dovetails for mounting a plurality of axially spaced buckets having female dovetails. A plurality of arcuate bridging members extend axially between the axially adjacent bucket dovetails at locations spaced radially outwardly of the surface of the rotor shaft. A diaphragm in radial opposition to the bridging member mounts a brush seal having bristles engaging the bridging member. The bridging member carries backup labyrinth seal teeth for sealing with the diaphragm. The friction generated by contact between the brush seal bristles and bridging members lies radially outwardly of the rotor whereby non-uniform distribution of heat about the rotor surface due to frictional contact with the brush seal is avoided, with consequent avoidance of rotor bowing.

Abstract: An intermediate-stage seal carrier for a high-pressure jet-engine turbine includes a supporting area for vane retainers, wherein the supporting area includes only one annular wall upstream of and abutting the vane retainers.

Abstract: In a steam turbine, a combined brush and labyrinth seal is provided between a diaphragm web and axial projecting platforms on bucket dovetails at a location spaced radially outwardly of the outer diameter of the rotor. The downstream axially adjacent bucket dovetails also have platforms serving as complementary sealing surfaces to labyrinth teeth formed on the web. By locating the combined labyrinth and brush seal radially outwardly of the outer diameter of the shaft, thermal bowing of the rotor is eliminated. By providing backup labyrinth seals at the same radial location, axial thrust loads are eliminated in the event of brush seal failure.

Abstract: A gas turbine has buckets rotatable about an axis, the buckets having angel wing seals. The seals have outer and inner surfaces, at least one of which, and preferably both, extend non-linearly between root radii and the tip of the seal body. The profiles are determined in a manner to minimize the weight of the seal bodies, while maintaining the stresses below predetermined maximum or allowable stresses.

Abstract: A locking device for use in retaining rotationally interengaged components in engagement with one another, the device comprising a body member (16) adapted to be located between adjacent interengaging formations (13, 14) on the components to prevent relative rotation of the components, and a wire retaining member (17) adapted to locate the body member in position, the retaining member comprising at least two hook-like members (18) engaged in spaced apertures (20) in the body member, each hook-like member having first and second portions (18B, 18C) extending beyond the body member into engagement with inner and outer surfaces of one of the components.

Abstract: A unitary interstage sealing ring for bridging and sealing the space between the blade shanks of adjacent turbine rotors in a multi-stage turbine. The sealing ring serves to confine relatively cool air conveyed to the turbine so the cooling air flows into the turbine blades for maintaining the blades at a desired temperature. The sealing ring includes a disk-shaped body member that includes a pair of axially-spaced, radially-extending arms that terminate in respective seal teeth for engagement with a stationary annular sealing member. Each of the radial arms includes an outwardly-extending axial arm that terminates in a disk engagement member for sealing engagement with the face of an adjacent turbine disk to confine cooling air within the space between the adjacent turbine disks. Additionally, one of the disk engagement members includes at least one, projection that contacts a respective turbine rotor to limit relative rotation between the sealing ring and the turbine.

Abstract: In a multi-stage turbine wherein at least one turbine wheel supports a row of buckets for rotation, and wherein the turbine wheel is located axially between first and second annular fixed arrays of nozzles, a cooling air circuit for purging a wheelspace between the turbine wheel and the second fixed annular array of nozzles comprising a flowpath through a shank portion of one or more buckets connecting a wheelspace between the turbine wheel and the first fixed annular array of nozzles with the wheelspace between the turbine wheel and the second fixed annular array of nozzles.

Abstract: A turbine closure bucket adapted to complete assembly of a row of tangential entry buckets on a rotor wheel includes an airfoil portion and a mounting portion for mounting the bucket to a turbine wheel. The mounting portion has front and back faces, with weight reduction cavities formed internally in the front and back faces. Externally, the front and back faces of the closure bucket are substantially identical to front and back faces of adjacent buckets in the row.

Abstract: A turbine nozzle includes a seal pad mounted to a seal support from an inner band thereof. The seal pad is provided for cooperating with seal teeth in an interstage seal. A bypass aperture extends through the seal support to bypass cooling air around the seal pad for providing relatively cool air aft of the seal teeth for improving cooling of the interstage seal in this region.

Abstract: A device for positioning of nozzles of a stator stage and for cooling of rotor discs in gas turbines, of the type including nozzle segments consisting of several airfoils. Each nozzle segment is connected at its top to an outer ring to define a chamber containing cooling air and is positioned at its base on an inner ring. The nozzle segments form a circumferential array about the axis of the gas turbine. In each airfoil of the nozzle segment, there is provided at least one tube, which is inserted in a corresponding duct inside the airfoil for delivering cooling air to the first and second stage discs.

Abstract: This invention relates to an intermediate-stage seal carrier for a high-pressure jet-engine turbine with a supporting area 1 at vane retainers, characterized in that the supporting area 1 comprises only one annular wall 3 upstream of and abutting the vane retainers 2 (FIG. 3).

Abstract: Described is a sealing arrangement for reducing leakage flows inside a rotary fluid-flow machine, preferably an axial turbomachine, having moving and guide blades, which are in each case arranged in at least one moving- or guide-blade row respectively and have blade roots, via which the individual moving and guide blades are connected to fastening contours. A sealing element having felt-like material is provided between at least two adjacent blade roots within a guide- or moving-blade row or between guide and/or moving blades and adjacent components of the fluid-flow machine.