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: An integrated double seal assembly includes a carbon seal ring and at least one annular labyrinth seal fin. The seal provides a compact solution for sealing a rotating shaft.

Abstract: A high-pressure turbine of a gas-turbine engine provided with a turbine disk (1) carrying rotor blades (2) and with stator blades (3), and with a lateral wheel cavity (5) being formed between the turbine disk (1) and the stator ring (4), wherein a seal (8) is provided in axial direction between stator blade platforms (6) and rotor blade platforms (7) and which is arranged radially outwardly adjacent a main gas duct (9).

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: An intelligent seal support management system includes a device for automatically compensating for increased heat or decreased heat in a vessel.

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 turbine comprises an oil deflector including at least one set of seal rings, and a shaft including an annular step. The step includes a circumferential surface in proximity to the seal rings of the oil deflector and a side surface extending radially from a center portion of the shaft and defining a groove positioned radially underneath the circumferential surface.

Abstract: The so-called comb-type labyrinth sealing device (S1) is disposed in a gap between a rotor blade (2), i.e. a rotating member, and a labyrinth packing (9), i.e. a stationary member. The sealing device (S1) has a plurality of sealing fins (F1, F2) arranged on the opposite sides of the gap opposite to each other. The sealing fins are axially spaced apart at unequal pitches, and hence a possibility that some of the clearances between the opposite sealing fins (F1, F2) decrease when a casing holding the labyrinth packing (9) and a rotor (1) are axially displaced relative to each other due to the difference in thermal expansion between the rotator and the casing increases.

Abstract: A rotor system for a gas turbine engine is provided having an outer rotor which includes an annular outer spool that comprises at least one ring portion of increased thickness with respect to the remainder of the outer spool, attached to a relatively thinner, axially extending arm portion. A plurality of outer turbine blades are attached to the ring portion of the outer spool and extend radially inwardly into a working gas flowpath of the engine. A casing surrounds the outer spool and defines an annular cavity between the casing and the outer spool, which is sealed by forward and aft brush seals at the forward and aft ends thereof. At least one inlet port is formed through the casing for admitting a flow of cooling air to the annular cavity. Means are provided for directing this cooling air flow to the ring portion of the outer spool.

Abstract: A gas turbine stator including at least a first injector providing a passage for a main cooling air stream into a pressurized chamber. An evacuation mechanism discharges air coming from an internal labyrinth gland of a first cavity towards a lower-pressure second cavity. A second injector evacuates the air contained in the second cavity towards a main duct. The stator further includes a third injector designed to generate an overpressure close to the internal labyrinth gland in the pressurized chamber.

Abstract: A gas turbine arrangement includes a rotor, a hot-gas passage, through which a hot-gas stream (12) flows while the gas turbine is operating, at least one first row of turbine blades or vanes (1), which have an airfoil(3) with a suction side (11) and a pressure side (10), and a platform (4), and at least one second row of turbine blades or vanes (2), which are arranged upstream of the first row of turbine blades or vanes (1) in the direction of the hot gases (12), and in the axial direction of the rotor and likewise have a platform (4). There is at least one seal (5, 6), through which a cooling air leakage stream (7) emerges while the gas turbine is operating, between the first row of turbine blades or vanes (1) and the second row of turbine blades or vanes (2), in the region of the respective platforms (4). An element guides the leakage stream (7) of cooling air along the surface of the platform (4) to the pressure side (10) of the first row of turbine blades or vanes (1).

Abstract: A method and apparatus for reducing self sealing flow in a combined cycle double flow steam turbine, the method and apparatus include providing a brush seal in a packing ring of a packing ring assembly at either end defining the double flow steam turbine.

Abstract: The coupling between discrete axially aligned first and second turbine shafts includes a flange on one end of one shaft and a rotor wheel on the other shaft. Holes in axial alignment with one another through the flange and rotor wheel receive fastening elements securing the rotor wheel and flange to one another, thereby securing the shaft sections to one another. The fastening elements engage segments on the side of the rotor wheel remote from the flange to facilitate clamping of the flange and rotor wheel to one another. The segments also include outer arcuate surfaces which form sealing surfaces with radially opposed labyrinth teeth of packing ring segments forming part of the turbine diaphragms.

Abstract: A system to feed cooling air to a gas turbine, wherein the cooling air is taken from a high-pressure source, inside the gas turgine, and is conveyed to radial accelerators (129, which give rise to the tangential acceleration of the air in the direction of the peripheral motion of the rotor surface. After it has been accelerated to the peripheral sepped of the rotor, the cooling air enters radial holes (13), and, whilst passing radially through the radial holes (13), undergoes a reduction in the quantity of tangential motion, Subsequently, the cooling air is released into the hollow rotor, with a correspondingly reduced outlet radius (14). A series of labyrinth seals combined with brush seals separate the chamber for combined with brush seals separate the chamber for feeding of air to the radial holes (13), from the low-pressure environment around the pad #2 (15) of the said gas turbine.

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 method facilitates assembling a seal assembly for a gas turbine engine rotor assembly. The method comprises coupling a disk retainer to a first stage disk, and coupling an interstage seal assembly including an outer shell within the rotor assembly such that a downstream arm extending from the outer shell engages a second stage disk while an upstream arm extending from the outer shell engages the disk retainer.

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

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 seal of a vertical pump with a front casing disposed on a main casing which has a motor disposed therein. A volute chamber is disposed inside the front casing to receive a centrifugal impeller. A suction inlet is disposed axially on the front casing opposite the motor. A water outlet is disposed thereon opposite the lateral side of the impeller to engage with a discharge pipe. The suction inlet and outlet are in communication with a volute chamber. The pump has a non-contact seal disposed on the impeller. The seal can jam when a liquid crystallizes. Therefore, if no heat is generated due to the friction of the seal, the pump operates better. Furthermore, it prevents a back impeller vane from stirring the air and ejecting the liquid with a lot of air bubbles when the pump operates. Therefore, it eliminates the air bubbles from causing problems during the manufacturing process of a printed circuit board.

Abstract: A hydraulic turbine is adapted to introduce oxygen into a water flowing through a water passageway of a turbine. The turbine has a circumferential chamber formed between a rotating band and a stationary discharge ring. The chamber has a gas admission aperture for receiving an oxygen containing gas into the chamber. A downstream end portion of the band has a plurality of spaced apart vanes providing chamber outlet passageways between the vanes and through the band. The vanes are configured to rotate with the band and to draw the oxygen containing gas and water from the chamber through the outlet passageways in the band and into the water passageway.

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 seal assembly and method for a turbomachine having a rotary member and a stationary member circumscribing the rotary member. The seal assembly comprises an annular-shaped platform on the rotary member so as to be disposed at an outer circumferential region thereof. The platform is supported radially outward from the rotary member so as to project beyond axially-adjacent regions of the rotary member. The platform has a contact region radially separated from the rotary member by a cavity. A sealing member is disposed at a radially inward region of the stationary member, with a portion of the sealing member in rubbing contact with the contact region.

Abstract: A turbine bucket and cover assembly includes a bucket having a shank portion and an airfoil portion separated by a platform portion; and a bucket cover arranged on a sloped radially outer tip of the airfoil portion, the bucket cover having a radially inner surface matching the sloped edge and a radially outer surface lying in a plane parallel to a longitudinal axis of a rotor on which the bucket is adapted to be mounted. A related method includes the steps of a) providing a bucket cover having substantially parallel radially inner and outer surface; b) removing material from the bucket cover so as to form a new radially outer surface defining an acute angle relative to the radially inner surface; and c) securing the bucket cover on the sloped airfoil tip of the turbine bucket such that the radially outer surface is substantially parallel to the turbine rotor axis.

Abstract: Balancing piston for centrifugal compressors, to control and damp subsynchronous vibrations, comprising a cylindrical body which is secured onto the rotor and a cylindrical structure which contains the body on the stator side with interposition of a seal with small cells wherein the play between the rotor and the stator increased in the direction of the flow of gas through the play.

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: 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 flange covering a disc of a turbine blade to allow ventilation. A diverted face of the disc is provided with a labyrinth seal with lickers to form a seal. Cutters of the lickers are inclined axially and staggered axially and radially, to off-set the center of gravity of a flexible web of the disc and to encourage deformation of the web towards the disc under the effect of centrifugal forces, to reinforce the contact of a bearing face with a pressure plate of the disc. Thus, hooks usually used to unite the periphery of the web to the disc become superfluous.

Abstract: A fan-shroud structure 10 includes a fan 12 mounted for rotation about an axis B. The fan has a plurality of blades 20 with tips of the blades being coupled to an annular band 22. A shroud 26, including an annular labyrinth seal 28, is disposed generally adjacent to the annular band thereby defining a gap 30 between the annular band and the seal. The seal has a corrugated profile and is constructed and arranged to provide resistance to air flow as air swirls and flows back into the gap and to minimize air leakage across the gap.

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 method enables a structural cover for a gas turbine engine to be manufactured. The method includes forming a torroidial body including an integrally-formed windage cover portion and a seal flange portion, and forming a plurality offastener openings extending from a forward side of the torroidial body to an aft side of the torroidial body, such that when installed in the gas turbine engine, the windage cover portion facilitates shielding the fastener openings from a gas flow path.

Abstract: A gas turbine engine rotor disk assembly includes a disk having an annular hub circumscribed about a centerline. An annular web extends radially outwardly from the hub to an annular rim. A plurality of dovetail slots extend generally axially through the rim. A plurality of cooling air slots extending generally radially through the rim and are skewed circumferentially with respect to the centerline and slanted axially aftwardly with respect to a normal radius perpendicular to the centerline. In the exemplary embodiment, each cooling air slot has parallel side walls skewed circumferentially with respect to the centerline and an aft wall extending between the side walls and slanted axially aftwardly with respect to the normal radius. The side walls are skewed circumferentially about 5 degrees with respect to the centerline and the aft wall is slanted axially aftwardly about 18 degrees with respect to the normal radius.

Abstract: The so-called comb-type labyrinth sealing device (S1) is disposed in a gap between a rotor blade (2), i.e. a rotating member, and a labyrinth packing (9), i.e. a stationary member. The sealing device (S1) has a plurality of sealing fins (F1, F2) arranged on the opposite sides of the gap opposite to each other. The sealing fins are axially spaced apart at unequal pitches, and hence a possibility that some of the clearances between the opposite sealing fins (F1, F2) decrease when a casing holding the labyrinth packing (9) and a rotor (1) are axially displaced relative to each other due to the difference in thermal expansion between the rotator and the casing increases.

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: Spline seals are disposed in circumferentially registering slots of adjacent arcuate sealing segments disposed in grooves of the casing of a steam turbine about a rotor. The spline seals extend in the gap between the endfaces of the segments and minimize or preclude steam leakage past the endfaces. The spline seals may be oriented axially or inclined radially to minimize leakage paths in the radial inclined and axial directions, respectively. 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 the spline seals provided as retrofits.

Abstract: A seal is disposed between a rotating part and a stationary part. At least one of the parts is provided with projections which protrude into the seal gap. The seal gap (5) extends approximately radially so that both parts are provided with projections which extend in an axial direction, which are located concentrically in relation to the axis of rotation of the rotating parts and which engage with each other. Said projections are configured in the form of rows of blade-like elements. This effectively seals approximately radially extending seal gaps.

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 includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.

Abstract: Spline seals are formed at the joints between packing casing shells in a steam turbine having high pressure and intermediate pressure turbine sections sealing between the high pressure and intermediate pressure regions on opposite axial sides of the packing casing. The spline seals extend in registering grooves from adjacent the seal segments of the rotor radially outwardly to adjacent axial load surfaces cooperable between the outer shell and the packing casing. The spline seals minimize or eliminate steam leakage paths through the horizontal joint of the packing casing shells.

Abstract: There is provided a nuclear power station primary pump of the type comprising a drive shaft for rotating a wheel, a heat exchanger, a thermal barrier cover comprising a peripheral skirt provided at its base with a circular end wall, and a diffuser comprising a peripheral skirt provided at its base with a rim. The circular end wall co-operates with the base of the heat exchanger to define a bottom chamber for cold water and includes a central bore provided with a succession of circumferential and superposed rings forming a lip seal of the labyrinth type, and a space is formed between the thermal barrier cover and the diffuser to maintain stagnant cooling fluid.

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: An axially loaded floating brush seal useful in a stationary gas turbine engine having a first rotary compressor component having a rotor having a radial surface, a second non-rotary component having an end ending near the radial surface with the floating brush seal being positioned between the first and the second components to substantially reduce the flow of air between the first and second components. A method for controlling the flow of cooling air into a chamber in the second component using the rotary brush seal is also disclosed.

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: The present invention provides for a method to reduce the strength of the honeycomb of a jet turbine stator, increasing its machinability, with a resultant reduction in measured peak tooth temperature, while maintaining or even improving its high temperature capability, so as not to limit its operating environment. The air seal functionality is unaffected, and even improved in some instances. The machinability of the honeycomb is increased by using a light element diffused into the honeycomb ribbon to produce the effect of reducing its strength and ductility while maintaining the environmental resistance needed. The present invention also includes the stator honeycomb produced by the foregoing method.

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 honeycomb structure is arranged on a stator of a gas turbine and is arranged opposite the moving blades of the gas turbine. The honeycomb structure is composed of metal sheets in such a way that webs having double the sheet thickness are obtained and connections of single thickness are obtained between the webs. The angle &agr; between the circumferential direction of the stator and the webs of double thickness is 5° to 175°. This serves to avoid undesirable efforts such as, for example, overheating during friction at the honeycomb structure of the moving blades of the gas turbine.

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: 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 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: 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.