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: A turbine cooling circuit includes a flow sleeve having an aft end for adjoining the rim of a turbine disk. A seal rotor is spaced from the aft end adjacent a row of inlet holes. An inducer has an outlet disposed radially outwardly from the sleeve inlet holes. And, a seal stator surrounds the seal rotor to define a rotary seal disposed radially inwardly from the inducer outlet.

Abstract: In a steam turbine, a combined brush and labyrinth seal is provided between a diaphragm web and a sealing surface on a rotatable component radially outwardly of the rotor surface. The contact between the brush seal and sealing surface lies along an axially upstream projecting flange of an annular platform such that heat generated by frictional contact between the bristles and the sealing surface has minimal effect on the rotor surface and hence rotor dynamics. A backup labyrinth seal is provided between the web and platform. Additionally, axially upstream projecting flanges are provided on the downstream buckets and which flanges are spaced radially outwardly of the rotor surface and lie in registration with the diaphragm web. Labyrinth teeth seal between the diaphragm web and the bucket flanges serving as a backup seal.

Abstract: A method and apparatus carrying the method for sealing a radial gap between coaxial inner and outer rotating shafts of a gas turbine engine includes using a radial seal as a main seal to seal the gap for a normal engine operation condition, and using an axial seal as a back-up seal for a double seal of the gap. The radial seal provides a seal which meets relatively restrictive leakage requirements for the normal engine operation condition and the axial seal provides a back-up seal which meets less restrictive leakage requirements but is much more tolerant of radial displacement and vibration between the coaxial inner and outer rotating shafts. Thus, an engine operable condition is ensured under abnormal conditions, such as bird strikes, in which the coaxial relationship between the inner and outer rotating shafts are affected by unbalancing forces caused by the bird strike, thereby causing a failure of the radial seal.

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: A turbine cooling circuit includes a flow sleeve having an aft end for adjoining the rim of a turbine disk. A seal rotor is spaced from the aft end adjacent a row of inlet holes. An inducer has an outlet disposed radially outwardly from the sleeve inlet holes. And, a seal stator surrounds the seal rotor to define a rotary seal disposed radially inwardly from the inducer outlet.

Abstract: The adjoining edges of bucket covers are sealed one to the other. A brush seal projecting from a stationary shroud overlies the bucket covers. A joint at which the adjacent covers sealingly engage each other precludes radial outflow of high pressure fluid into bristles of the brush seal, preventing radial and axial deflection of the bristles and consequent failure of the bristles. The joints between the covers may comprise lap or tongue-and-groove joints.

Abstract: In a fluid machine such as multistage centrifugal compressor, the pressure of a working fluid is raised with the rotation of a impeller. A shaft sealing device is mounted at the end of the rotary shaft in order to prevent the working gas of the raised pressure from leaking out of the fluid machine and then polluting the surroundings. In a case where the fluid machine operates to rotate at high speed, a labyrinth sealing device is employed for the purpose of reducing a frictional loss in the shaft sealing device. The labyrinth sealing device includes a plurality of stages of labyrinth fins which are formed on a casing or the rotary shaft, and a layer of abradable coating to-be-bitten which is formed in the surface part of the rotary shaft or the casing opposing to the labyrinth fins. The clearances between the labyrinth fins and the rotary shaft or the casing are made narrower on the low-pressure side of the labyrinth sealing device than on the high-pressure side thereof.

Abstract: A diaphragm has an annular groove formed of deep and shallow grooves with the deep groove opening into the shallow groove. A combination spill strip/brush seal is disposed in the groove. The brush seal comprises a pair of flexible bars secured to the proximal ends of the brush bristles by welding and is received in the shallow groove and a recess in an axial face of the spill strip. The spill strip has base portions extending into the deep groove. The combination spill strip/brush seal is secured in the annular groove by peening material of the diaphragm into the spill strip/brush seal combination. The brush seal may be used with different diameters of spill strips and diaphragm grooves.

Abstract: The knife edge air seal ring of a gas turbine is modified to receive a replacement or second seal ring portion having a wire brush seal. The replacement or wire brush air seal ring is mounted with the existing knife edge air seal mounting ring at a location so that the existing mounting ring may be used, while providing adequate strength and structural support for installation of the second, wire brush seal ring. The replacement seal ring may be provided with knife edge seals as well, if desired.

Abstract: A packing ring seal assembly for use in a steam turbine for minimizing leakage flow between stationary and rotating steam path parts includes a stationary annular seal ring having a plurality of axially spaced, annular sealing teeth extending in a radial inward direction and adapted to cooperate with sealing surfaces on a rotating component of the steam turbine, wherein radial clearance between the sealing teeth and the sealing surfaces varies by predetermined amounts.

Abstract: Between the rotor and stator of an axial turbo machine, sealing strips of a labyrinth seal that are mortised into sealing strip grooves are provided. Between the sealing strips relief grooves are provided in such a way that the axial stiffness of the rotor or stator is essentially steady. This may be achieved by one or more flat relief grooves, a corrugated surface, or by filling the relief grooves entirely or partially with a suitable, elastic material so that a more even axial tension distribution is achieved between the sealing strip grooves and relief grooves along the rotor or stator section.

Abstract: Disclosed are improved spillstrip and packing rings, and packing ring segments employing novel brush elements for use in forming seals in axial flow elastic fluid machines, and compressor and turbine machines containing the same.

Abstract: A turbocharger for an internal combustion engine is of the type having an impeller mounted on a shaft carried by a bearing supplied with lubricating oil, the shaft being located in a bore and having an oil and air seal between the bearing and the impeller hub. The seal is a floating ring seal mounted in the bore and extending radially into a circumferential recess in the impeller hub. In use, the ring seal experiences a pressure differential across it which urges it to slide axially along the bore so that it forms a sealing interface with a side face of the recess. The shaft rotates relative to the ring seal, which is therefore subject to wear against the side face of the recess. Hence, a shoulder is provided in the bore to limit excessive axial sliding of the ring seal due to wearing away of the ring seal against the side face of the recess.

Abstract: In a fluid machine such as multistage centrifugal compressor, the pressure of a working fluid is raised with the rotation of a impeller. A shaft sealing device is mounted at the end of the rotary shaft in order to prevent the working gas of the raised pressure from leaking out of the fluid machine and then polluting the surroundings. In a case where the fluid machine operates to rotate at high speed, a labyrinth sealing device is employed for the purpose of reducing a frictional loss in the shaft sealing device. The labyrinth sealing device includes a plurality of stages of labyrinth fins which are formed on a casing or the rotary shaft, and a layer of abradable coating to-be-bitten which is formed in the surface part of the rotary shaft or the casing opposing to the labyrinth fins. The clearances between the labyrinth fins and the rotary shaft or the casing are made narrower on the low-pressure side of the labyrinth sealing device than on the high-pressure side thereof.

Abstract: A gas turbine generally comprises a compressor, a combustor and a turbine body operatively connected to the compressor through a rotation shaft, and the turbine body is composed of a plurality of rotors formed with turbine. discs and movable blades which are arranged in plural stages along an axial direction of the turbine body, in which a rear shaft is connected to a downstream side of a final stage disc of the turbine discs so as to extend rearward from the final stage turbine disc and supported by means of a bearing. The rear shaft is formed with a cooling medium supply passage for supplying a cooling medium to the turbine disc and a cooling medium recovery passage for recovering the cooling medium from the turbine disc, and a further cooling medium passage is formed between the rear shaft and either one of the cooling medium supply passage and the cooling medium recovery passage.

Abstract: An improved spool for a compressor of a gas turbine engine comprising spacer disks disposed between adjacent rotor disks, and a plurality of hollow tie rods that extend through the rotor disks and the spacer disks. The tie rods are tensionable to provide axial preload between the disks, and also conduct active air for thermally conditioning spool components. The spacer disks have an outer portion with a catenary shape that extends between the peripheral rims of the adjacent rotor disks. Sealing teeth located on the outer portion are preferably radially aligned with a web portion that extends radially inward from a center region on the outer portion. Each tie rod has at least one aperture through its wall for transmitting active air. In one embodiment, active air is injected through apertures in the forward stub shaft of the spool and is urged into at least one space between a rotor disk and a spacer disk, then into, along, and out of the hollow tie rods.

Abstract: An annular seal comprising a mass of bristles (10) packed together in a layer axially adjacent to an annular backing plate (12). The bristles (12) and backing plate (14) are mounted on and extend from a radially outer member (4) towards and around a cylindrical inner member (2). The outer (4) and inner (2) cylindrical members rotate relative to each other about an axis (1). The bristles (10) co-operate with the inner cylindrical member (2) to form a seal thereagainst. An expansion ring (18) is disposed radially inwardly of the backing plate (14) and is mounted in substantially the same plane from the backing plate (14) via a suitable mounting arrangement (16) which is arranged to permit radial movement of the expansion ring (18) relative to the backing plate (14) and the operational position of the inner cylindrical member (2).

Abstract: The cast part (1) comprises a basic body (2) of a first material and a coating of at least one second material. The second material is applied to a co-cast skeleton structure (3) on the surface (20) of the basic body, with it forming a covering (4) or a covering layer (42).

Abstract: In a machine having a shaft with a shaft axis, an outer region, and a shaft seal, a component is provided for the shaft seal. The component has a cast part formed of a first metallic material directed along the shaft axis and has an inner wall shaped, at least in regions, in a circumferential direction relative to the shaft axis, and an outer wall directed towards the outer region. A fluid guide is disposed and formed in the cast part and runs in the circumferential direction, at least in regions, and opens into the inner wall. At least one fluid conduit formed of a second metallic material fluidically connects the inner wall to the outer region. The fluid conduit is also fluidically connected to the fluid guide.

Abstract: A retainer which, in an exemplary embodiment of the invention, is used in a gas turbine engine inter-stage seal assembly to retain an annular seal ring flange of a seal ring against an annular platform flange extending radially inwardly from an inner platform of an annular nozzle stage having nozzle vanes. The retainer includes a body having a central portion through which a bore is formed around a bore axis and a central tab extends radially outwardly from the central portion with respect to the bore axis. First and second arms, respectively, extend in opposite respective first and second tangential directions, with respect to the bore axis, away from the central portion and each other. Axial spacers extend aftwardly from first and second free ends of the first and second arms, respectively and anti-rotation feet with rounded ends depend from the first and second free ends in an opposite direction from which the central tab extends.

Abstract: This invention relates to barrier seal systems for sealing the annular space between a housing and a rotating shaft which extends through a bore in the housing. The seal system has inboard and outboard mechanical end face seals. The inboard seal faces have spiral grooves for pumping a buffer fluid from a buffer chamber between the two seals toward the high pressure side of the inboard seal. The primary ring of the inboard seal may be double balanced. For high pressure applications, the buffer fluid may be pressurized and a pumping ring may be included in the outboard seal to circulate buffer fluid. High pressure applications also require two hard seal rings and optimum dam and face widths. Buffer fluid can be supplied to the seal system by a reservoir connected by a gravity feed line. A buffer fluid containment device may be attached to the high pressure side of the seal to prevent process fluid from contaminating the seal faces or secondary seals.

Abstract: The present invention includes a method of repairing an annular metallic article and the repaired article itself which has an axially extending annular support and a projection generally radially extending therefrom. The projection has an associated operating radial height as measured from a radially facing annular first surface of the support and an associated shape. An upper portion of the projection is removed forming a stub extending away from the first surface and having a bonding surface at a stub end spaced apart from the first surface. A metallic material is metallurgically bonded to the bonding surface forming an annular heat affected zone in the stub bounded by the bonding surface. A first portion of the metallic material is removed to restore the projection to the operating height and shape. At least one annular outer surface of the tooth extending over at least a portion of the heat affected zone is laser shock peened, preferably after the first portion of the metallic material is removed.

Abstract: Brush seals are employed on steam turbine rotors without the risk of causing thermal rotor bowing and without compromising the sealing performance. In one form, a groove in the rotor has an insert in frictional contact with the brush seal. The non-uniform distribution of heat due to frictional contact between the brush seal and proud portions of the rotor is dissipated within the insert such that adjoining rotor portions are substantially uniformly heated without causing thermal bow. In a further form, a groove or grooves are provided in the rotor surface adjacent to the brush seal and maintain non-uniform heat distribution locally in the rotor without causing thermal bow of the rotor. In another form, a land projects radially outwardly of the rotor surface in contact with the brush seal. The non-uniform distribution of heat due to frictional contact between proud portions of the land and the brush seal dissipates into a uniform distribution of heat in the rotor proper to avoid thermal bowing.