Abstract: A sealing apparatus in a gas turbine. The sealing apparatus includes a seal housing apparatus coupled to a disc/rotor assembly so as to be rotatable therewith during operation of the gas turbine. The seal housing apparatus comprises a base member, a first leg portion, a second leg portion, and spanning structure. The base member extends generally axially between forward and aft rows of rotatable blades and is positioned adjacent to a row of stationary vanes. The first leg portion extends radially inwardly from the base member and is coupled to the disc/rotor assembly. The second leg portion is axially spaced from the first leg portion, extends radially inwardly from the base member, and is coupled to the disc/rotor assembly. The spanning structure extends between and is rigidly coupled to each of the base member, the first leg portion, and the second leg portion.

Abstract: A turbomachinery includes a labyrinth seal (2) to prevent unstable vibration of a rotor formed by dividing the seal into segments (7) in a circumferential direction and combining the segments (7) whose comb teeth (5) differ in height. The labyrinth seal (2) preferably includes two kinds of segments (7) whose comb teeth (5) differ in height for each kind of segment, and the segments (7a) of the greater comb tooth height are arranged in a certain reference direction on a cross section right-angled to a rotational axis, and in a direction opposite to the reference direction, and the segments (7b) of the smaller comb tooth height are arranged in a direction right-angled to the reference direction, and in a direction opposite to that right-angled to the reference direction.

Abstract: A disc seal assembly for use in a turbine engine. The disc seal assembly includes a plurality of outwardly extending sealing flange members that define a plurality of fluid pockets. The sealing flange members define a labyrinth flow path therebetween to limit leakage between a hot gas path and a disc cavity in the turbine engine.

Abstract: The invention relates to a pump turbine system comprising a turbine with a turbine impeller as well as a turbine spiral housing; and a pump with a pump impeller as well as a pump spiral housing; an electrical machine which is in drive communication with the shaft or can be brought into such communication; a hydraulic short circuit can be produced between turbine and pump.

Abstract: A turbo compressor in an axial type of construction is disclosed. The turbo compressor has a bladed stator and a bladed rotor, and has a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially within their aerofoil on an inner ring belonging to the stator. The inner ring is split, i.e., segmented, at at least two points of its circumference. Furthermore, the inner ring has for each guide blade at least one bearing bush which can be inserted radially into an opening from inside.

Abstract: A seal assembly for a turbomachine may include at least one arcuate plate coupled to an interior surface of a stationary housing; a circumferentially-segmented packing ring disposed intermediate to a rotor and the plate; a plurality of arcuate teeth disposed intermediate to the ring and the rotor, wherein a clearance of each tooth decreases progressively going from an upstream side of the turbomachinery to a downstream side; wherein the progressive decrease in the clearances of the teeth creates a passive feedback, such that as a tip clearance decreases, outward radial forces cause the packing ring to move away from the rotor and as the tip clearance increases, inward radial forces cause the packing ring to move toward the rotor; and a biasing member disposed intermediate to the arcuate plate and the ring and coupled to both.

Abstract: A steam turbine 20 is provided with a casing 109, a turbine rotor 25 disposed through the casing 109, and labyrinth portions 50, 55 which are disposed at the boundary between the casing 109 and the turbine rotor 25. The steam turbine 20 is further provided with a sealing steam pipe 65 for supplying sealing steam to the labyrinth portions 50, 55 and a gas supply pipe 60 for supplying the labyrinth portions 50, 55 with a cooling gas for cooling the turbine rotor 25 or a heating gas for heating the turbine rotor 25.

Abstract: A fan with pressurizing structure includes a rotor having a main body, blades spaced on the main body, a magnetic body annularly mounted in the main body, and a shaft axially connected to an inner side of the main body; a frame having a sleeve and at least one bearing rotatably received in the sleeve, and an opposing end of the shaft being inserted into the bearing; a stator assembly fitted around the sleeve and including silicon steel plates and a base plate; and a plurality of first pressurizing sections selectively provided on one of the base plate and an end face of the magnetic body. With the first pressurizing sections, deposition of moisture and salt fog in the sleeve and the rotor can be prevented to avoid corroded and damaged bearing and rotor shaft, and the service life of the whole fan is increased.

Abstract: A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body.

Abstract: A card seal with an annular arrangement of plates that form the card seal, where the plates are rotated at an angle around a longitudinal axis of the plates so that the gaps between adjacent plates are not parallel to the rotational axis of the rotor shaft, and where an annular disk is rotatably secured to the rotor shaft and located adjacent to card seal on the low pressure side, or on the high pressure side or even on both sides such that rotation of the annular disk pumps fluid into or draws fluid out from the plate gaps to decrease or eliminate any differential pressure across the card seal. Thus, card seal leakage is reduced or eliminated.

Abstract: An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area.

Abstract: Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.

Abstract: A seal formed between at least two blades in the turbine of a turbine engine, a first turbine blade and a second turbine blade, wherein one of the turbine blades comprises a turbine rotor blade and the other turbine blade comprises a turbine stator blade, and wherein a trench cavity and the seal is formed between the first turbine blade and the second turbine blade when first turbine blade is circumferentially aligned with the second turbine blade, the seal comprising: a cutter tooth and a honeycomb; wherein: the cutter tooth comprises an axially extending rigid tooth that is positioned on one of the first turbine blade and the second turbine blade and the honeycomb comprises an abradable material that is positioned on the other of the first turbine blade and the second turbine blade; and the cutter tooth and the honeycomb are positioned such that each opposes the other across the trench cavity when the first turbine blade is circumferentially aligned with the second turbine blade.

Abstract: Methods and systems for reducing a flow of ambient air into a bearing lubricating oil system are provided. The system includes a lubricating oil bearing cover that is stationary with respect to the bearing wherein the bearing is configured to support a portion of a rotatable machine shaft. The cover includes a first end cap extending radially inwardly towards the shaft such that a cavity surrounding the bearing is formed by the cover and the first end cap and a set of seal rings positioned substantially concentric with the shaft and forming a seal against lubricating oil flow. The seal rings include a plurality of wire bristles extending radially inwardly from the end cap wherein the wire bristles are configured to extend to a surface of the shaft when assembled and the bristles are configured to present a tortuous flow path to gas infiltrating the cavity.

Abstract: In one embodiment, a catenary seal structure may be mechanically supported only by two adjacent rotor wheels to isolate a volume between the two adjacent rotor wheels. The catenary seal structure may be annularly disposed about the rotational axis of the adjacent rotor wheels.

Abstract: A gas-turbine axial compressor has a casing 3 and a rotatable shaft 6, which form an annular duct, in which at least one stator 2 and one rotor 4 are arranged. A shroud 21 is arranged at a free end of the stator 2 vanes, which extends over part of the axial length of the stator 2. A rotor platform 23 of at least one rotor 4 extends axially beneath a further part of the axial length of the stator 2, at which no shroud 21 is arranged.

Abstract: A system including: a first turbine segment comprising a first blade coupled to a first shank. The system also includes a second turbine segment including a second blade coupled to a second shank, as well as an elongated flexible seal disposed in a gap between the first and second shanks. The elongated flexible seal includes an opening configured to channel a fluid flow into a hollow region of the elongated flexible seal to induce expansion of the elongated flexible seal in the gap.

Abstract: A labyrinth seal for a bypass discharge-type motor-fan unit includes a motor unit from which extends a rotating shaft that passes through an aperture in an end plate to drive a fan unit. Disposed within the aperture is a labyrinth seal configured to prevent liquid entrained in a working airflow from entering the motor unit. The rotating shaft also includes a vacuum bore, such that the negative pressure generated by the operation of the fan unit draws any liquid out of an evacuation zone maintained between the motor unit and the end plate. As such, the components of the motor unit are protected from being exposed to the liquid, thereby extending the operating life motor-fan unit.

Abstract: A stator stage of a compressor of a turbomachine including an annular row of variable-pitch vanes is disclosed. Each vane includes an external cylindrical pivot defining the axis of rotation of the vane, and an internal cylindrical pivot mounted in a housing of an internal ring. The internal pivot of each vane extends along an axis substantially parallel to the axis of rotation of the vane and at a distance from this axis, and is mounted in the housing of the ring by a swiveling or a tilting system.

Abstract: A turbomachine (1), in particular a gas turbine, has a stator (2) and a rotor (3) and with at least one axial sealing device (6) arranged between them. On the stator side, the sealing device (6) has a radially stepped sealing contour (8) with regions (9, 10) projecting and retracting in the direction of the rotor (3), on the rotor side a plurality of sealing fins (11) projecting in the direction of the stator (2) being arranged, which engage in each case into adjacent retracting regions (10) of the stator-side sealing contour (8). On the rotor side, at least one additional fin (12) projecting in the direction of the stator (2) is provided, which is positioned between two adjacent sealing fins (11) arranged on the rotor side and which lies opposite a projecting region of the stator-side sealing contour (8).

Abstract: A seal assembly for deflecting contaminated fluid flowing through the seal assembly from an upstream space to a downstream space includes an annular housing, at least one vent hole peripherally disposed on the annular housing, a first set of seals disposed within the annular housing adjacent to the downstream space, the first set of seals having an inclined surface to deflect the flow of contaminated fluid through the at least one vent hole, and a second set of seals mounted on the shaft, disposed within the annular housing, adjacent to the first set of seals and adjacent to the upstream space. The second set of seals may have larger inside diameter than the first set of seals. The seal assembly may prevent contaminated fluid from entering an air bearing cooling circuit, thereby preventing bearing wear, erosion and failure.

Abstract: A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a control pocket defined between a radially inner surface and a spaced radially outer surface. The control pockets and their associated knife edge seals create a difficult flow path to prevent leakage into radially inner portions of the turbine section.

Abstract: In one aspect, the present disclosure is directed to a turbine engine. The engine may include a main housing defining a compressor compartment and an air intake housing mounted to the main housing. The engine may also include a rotor including a compressor portion disposed within the compressor compartment, and a hub portion extending from the compressor compartment through an opening in the air intake housing into a bearing compartment defined by the air intake housing. The engine may further include a seal mounted in the opening in the air intake housing in an annular gap between the hub portion of the rotor and the air intake housing and configured to form a seal between the bearing compartment and the compressor compartment. The seal may be configured to be removed from the opening in the air intake housing while the air intake housing is mounted to the main housing.

Abstract: A gas turbine comprises forward and aft rows of rotatable blades coupled to a disc/rotor assembly, a row of stationary vanes positioned between the forward and aft rows of rotatable blades, and rotatable sealing apparatus. Each of the stationary vanes comprises an inner diameter platform having first sealing structure. The rotatable sealing apparatus comprises seal housing apparatus coupled to the disc/rotor assembly and has second sealing structure adapted to engage with the first sealing structure.

Abstract: Disclosed is a seal for a turbomachine including at least one fixed component located proximate to a rotating component of the turbomachine defining a clearance therebetween. At least one magnet is located at the at least one fixed component. The at least one magnet is, when activated, capable of moving the at least one fixed component thereby adjusting the clearance between the fixed component and the rotating component. Further disclosed is a turbomachine utilizing the seal and a method for adjusting a position of at least one fixed component of a turbomachine.

Abstract: A triple acting radial seal used as an interstage seal assembly in a gas turbine engine, where the seal assembly includes an interstage seal support extending from a stationary inner shroud of a vane ring, the interstage seal support includes a larger annular radial inward facing groove in which an outer annular floating seal assembly is secured for radial displacement, and the outer annular floating seal assembly includes a smaller annular radial inward facing groove in which an inner annular floating seal assembly is secured also for radial displacement. A compliant seal is secured to the inner annular floating seal assembly. The outer annular floating seal assembly encapsulates the inner annular floating seal assembly which is made from a very low alpha material in order to reduce thermal stress.

Abstract: A turbine stator for an aircraft turbine engine is disclosed. The turbine stator includes a stator wall supporting a high pressure air injector fixed on the downstream side, and an annular abradable element support. The lower radial end of the element support is fixed to the high pressure air injector and the upper radial end of the element support is fixed to the stator wall, such that they jointly delimit a cavity under pressure. The turbine stator also includes at least one vibration damping device located in the cavity under pressure. The vibration damping device is in contact with each of the two elements taken among the stator wall and the annular support.

Abstract: A turbomachine comprising high- and low-pressure compressor shafts guided in bearings isolated from an internal enclosure by a sealing end plate, and radial pressurization tubes connecting the enclosure to an air passage passing through the intermediate casing, the ends of these tubes being engaged in sealed manner in radial ducts of the intermediate casing and in radial chimneys of the sealing end plate, the chimneys being of a length is sufficient to enable the ends of the tubes to be moved in translation therein between a service position and a mounting position for the tubes.

Abstract: A turbomachine includes a casing defining a hot gas path, and a shroud member attached to the casing. The shroud member is spaced from the casing to define a gap. The shroud member includes a first end having a first hook member provided with a first sealing surface and a second end including a second hook member provided with a second sealing surface. At least one of the first and second sealing surfaces includes a plurality of labyrinth seal elements that reduce air leakage through the gap into the hot gas path.

Abstract: A labyrinth seal is provided for forming a seal between a first and a second component which rotate relative to each other. The seal has an abradable lining mounted to the first component, and a plurality of fins projecting from the second component. The fins are arranged in abutment with the abradable lining to form a labyrinthal path for a flow of air through the seal. The seal further has a bypass passage which extends through the abradable lining. The bypass passage allows air to flow through the seal and bypass the labyrinthal path.

Abstract: Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a stator assembly and a rotor assembly configured to operatively engage each other to form a first seal and a second seal; the first seal being provided by a hydrostatic seal having a seal face and a seal runner; and the second seal being provided by a back-up seal such that responsive to a failure of the first seal, the back-up seal maintains at least a portion of a pressure differential established by the first seal prior to the failure.

Abstract: Subject: To provide a sealing structure, and control method therefor, which improve sealing performance between a rotating region and a fixed region, prevent fins from being damaged, and prevent increases in the amount of steam leakage from any clearances newly formed by further abrasion of an abradable material. Solution: The sealing structure in which free-cutting spacers 28 on a sealing base plate 25 and sealing fins 24 on a rotor 18 are opposed to each other is provided, in the sealing structure of which the sealing base plate 25 is disposed so as to be movable in an axial direction of the rotor 18. When a steam turbine 3 increases in load, a pressure head 30 moves in an axial steam-pressure loading direction of the rotor 18 and the sealing base plate 25 connected to the pressure head 30 moves in the axial steam-pressure loading direction.

Abstract: The present disclosure relates to a seal assembly for a turbomachine that includes at least one arcuate plate, a biasing member, and a packing ring. In addition, the seal assembly includes a plurality of arcuate teeth disposed intermediate to the packing ring and the rotor. The plurality of arcuate teeth includes at least one subset of arcuate teeth. The clearance of at least one of the arcuate teeth is different from the clearances of the rest of the arcuate teeth. The clearances of the arcuate teeth of the at least one subset do not progressively increase going from an upstream to a downstream side of the turbomachinery.

Abstract: The present application provides a variable steam seal system for use with a steam turbine. The variable steam seal system may include a seal steam header, a first pressure section, a first pressure seal positioned about the first pressure section, and a flow path through the first pressure seal and extending to the seal steam header. The first pressure seal may include a moveable seal packing ring for varying the flow path through the first pressure seal to the seal steam header.

Abstract: The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.

Abstract: According to one embodiment of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends.

Abstract: A uniquely configured rotating seal tooth is used in conjunction with commonly used labyrinth-type seals that provide a seal between a rotating component and a stationary component. The uniquely configured rotating seal tooth produces a compression mechanism to counter leakage flow through the labyrinth of seal teeth, thereby lessening the pressure gradient that drives leakage and reversing the direction of some of the leakage flow.

Abstract: In one embodiment, a system includes a rotary machine and a packing seal that is disposed between rotary and stationary components of the rotary machine. The packing seal includes a pair of seal lands spaced axially along the rotary component and a seal tooth disposed at an axial position between the pair of seal lands. At least one seal land of the pair of seal lands or the seal tooth includes a curved flow-facing side and is slanted toward the curved flow-facing side.

Abstract: A high pressure first stage turbine and seal assembly are described. In one embodiment, a high pressure turbine section is provided. The turbine section includes at least one stage, at least one rotor and a bucket assembly. The bucket assembly includes a bucket and an attachment fixture. The stage has a high root reaction during operation. An intermediate space is between the bucket assembly and a stationary component of the turbine section. A seal is provided between the stationary member and the rotor to facilitate preventing leakage from the intermediate space toward an end of the stage. Steam balance holes are provided in the rotor or the bucket to facilitate feeding steam towards an end of the turbine stage.

Abstract: Whirl flow of leakage flow is reduced to reduce the occurrence potential of steam whirl. A rotor oscillation preventing structure for a steam turbine includes: a stator vane 3; a moving blade 1; a shroud cover 2 installed on an outer circumferential side distal end of the moving blade 1; and a plurality of seal fins 6 installed, at any interval in the axial direction of a rotor, on an wall surface of a stationary body located on an outer circumferential side of the shroud cover 2, a whirl preventing structure comprised of whirl preventing plates 9 or whirl preventing grooves 11 is provided at a shroud cover inlet return portion 10 of the shroud cover 2 so as to block the whirl flow of leakage flow 8 on an upstream side in an operating steam flow direction of the seal fins to reduce an absolute velocity component of the leakage flow 8 in a rotational direction of the rotor.

Abstract: A turbine rim cavity seal with a variable gap clearance control in a gas turbine engine. A stator vane includes an inner shroud with an inter-stage sealing housing extending inward and separating a front rim cavity from an aft rim cavity. Front and aft rotor disks are located on the sides of the stator vane and include labyrinth seal teeth extending upward to form a seal with an abrasive material supported on the underside of the housing cavity. The abrasive material includes a slanted sealing surface. A hydraulic actuator moves the rotor disks in an axial direction to control the seal gap and regulate the purge air flow into the front rim cavity and leakage flow through the seal into the aft rim cavity. In another embodiment, the sealing surface is stepped as well as slanted.

Abstract: A seal plate assembly for use with a rotor wheel assembly of a turbine engine. The seal plate assembly may include a seal plate positioned about a rim of a rotor wheel. The seal plate may include a number of seal plate segments and a number of locking pins extending through the seal plate segments and into the rim of the rotor wheel.

Abstract: A stepped labyrinth seal having a plurality of teeth forming gaps between a stationary honeycomb member, where the cavities formed between adjacent teeth include a plurality of vortex flow generating strips on the wall of the cavity that redirect the leakage flow from a gap back toward the gap and in a direction toward the gap in order to limit the leakage flow through the gap. The vortex generating strips extend along the cavity floor and up the sides of the teeth forming the cavity. The strips slope downward from the downstream tooth toward the upstream tooth in the direction of rotation, and with a curvature in the direction of rotation. The stepped labyrinth seal is intended for use in a gas turbine engine having a plurality of stages in the turbine, with the labyrinth seal being used to seal the gap between rotating blades and the honeycomb surface on the stationary casing.

Abstract: A turbine engine utilizes an oil director to direct any leakage oil from a rear bearing compartment of the turbine engine toward a drain opening for an oil drain. The oil drain is formed in a heat shield located between the low pressure turbine and the exhaust nozzle. The oil drain directs the leakage oil to a benign area of the turbine engine.

Abstract: A bearing sealing arrangement for rotating machines uses a radially-acting labyrinth seal (2) to minimize bearing lubricant leakage and an axially-acting screw-type gasket (3) to return what fluid escapes through the labyrinth seal to the bearing (10). In embodiments, the labyrinth seal uses rings (4) with plastic wear surfaces formed about internal metal bands, the plastic forming corresponding profiles on the ends (27,28) of the bands so that the profiles interlock when overlapped to form the rings. The screw-type gasket preferably includes rotor-mounted helical fillets (22) formed in a section (21) that is retained in a seat (20) on the rotor. The section in embodiments is retained by inserting a ring-shaped key (23) into the section, thereby forcing the section into undercuts of the seat. The arrangement is particularly useful in wind machines, such as wind-turbines.

Abstract: The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that present different stiffnesses between adjacent pairs of sectors. The invention is applicable to a compressor, a turbine, or to a rotor and stator assembly.

Abstract: A rotor blade assembly includes a slot for mounting a rotor blade that extends partially through a rotor disk and a continuous uninterrupted hoop seal that extends about the circumference of the rotor disk. The rotor disk includes an integrally formed seal that includes at least one knife edge disposed concentrically about the rotor disk. The slot receives a root portion of a rotor blade but does not extend through the seal. As the seal remains an uninterrupted full hoop about the circumference of the rotor disk, additional rigidity and strength are realized. The increased rigidity and strength provided by the full hoop structure provides for the reduction in material and physical dimensions without compromising desired performance of the seal.

Abstract: A gas turbine with a shroud and labyrinth-type sealing arrangement has a casing 1 and at least one rotor 9, whose blades 2 are provided with a shroud 3. The labyrinth seal 4 is provided between the shroud 3 and the casing 1 and the shroud 3 includes at least two radially spaced and axially protruding annular fins 5, which are part of the labyrinth seal 4 At least one sealing fin 6 is provided on the casing 1 which extends essentially radially to the shroud 3 at least over a part of the circumference and at least partly in a space between the annular fins 5.

Abstract: An integrated duct, baffle and knife edge seal arrangement employing the radially inner distal edge of the baffle for sealing the radially inner stator/rotor interface of an inter-stage cavity.

Abstract: The present application describes a turbine section. The turbine section may include a pair of rotors, a seal ring positioned between the pair of rotors, and a first weld at a first end of the seal ring and a second weld at a second end of the seal ring.