Abstract: This aircraft gas turbine is provided with a rotor, a rotor blade (24), a casing, a stationary blade (26), and a guide member (53). The rotor blade (24) has fins (43) projecting from the outer peripheral surface (42a) of a rotor blade shroud (42). A stationary blade shroud (51) of the stationary blade (26) forms a cavity (Ct) with at least the rotor blade shroud (42) and the fins (43). The guide member (53) is provided inside the cavity (Ct) and extends inward from the radial outer side, and an inner-side end part (53a) on the radial inner side faces the outer peripheral surface (42a) of the rotor blade shroud (42) with a gap therebetween.

Abstract: An abradable element (7) for a turbomachine comprises a body (8) formed from an abradable material and extending between a wear face (11) and a bottom (9). The body comprises blind cavities (12) opening up into the wear face and filled in with a material with a colour different from the colour of the material forming the body of the element (7) to form wear indicators of the wear face (11) of the element (7).

Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.

Abstract: A hydraulic construction unit includes a centrifugal pump assembly which includes an electrical drive motor and at least one impeller which is driven by the electric drive motor. At least one valve element is arranged such that the valve element is movable by way of a fluid flow which is created by the impeller. At least one section of a wall delimits a flow path in the hydraulic construction unit and is configured to be movable as a moveable section. The movable section of the wall is part of the valve element or is connected to the valve element for movement. The movable section is movable so as to be at least partly effected by friction forces of a fluid flow which runs along the wall.

Abstract: A motorcompressor comprising an electric motor, a load, a shaft assembly, the electric motor and the load being mounted on the shaft assembly, a casing configured to completely house the electric motor, the load and the shaft assembly for its entire length, a divider located in the casing to define a motor chamber and a load chamber, the divider comprising at least a pumping device configured to transfer a part of the fluid present in the motor chamber to the load chamber so as to obtain in the motor chamber a pressure that is lower than a pressure at a load inlet.

Abstract: A system for a turbomachine includes a rotor blade configured to rotate along a circumferential direction within a casing of the turbomachine and a shroud positioned outward of the rotor blade along a radial direction. The rotor blade includes a root, a tip spaced radially outward from the root, a pressure side tip rail that extends around the tip of the rotor blade along a pressure side wall, and a suction side tip rail that extends around the tip of the rotor blade along a suction side wall. The shroud includes a radially inner surface facing the pressure side tip rail and the suction side tip rail of the rotor blade and spaced from the pressure side tip rail and the suction side tip rail of the rotor blade by a clearance gap. The shroud also includes a plurality of grooves extending continuously along the circumferential direction.

Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.

Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assembly includes a turbine wheel assembly and a turbine shroud. The turbine wheel assembly includes a disk and a plurality of blades that extend outwardly from the disk in a radial direction away from an axis. The turbine shroud extends around the blades of the turbine wheel assembly to block gasses from passing over the blades during operation of the turbine assembly. The turbine shroud includes a plurality of blade track segments arranged circumferentially adjacent to one another about the axis to form a ring. Each blade track segment has a runner that forms a primary track surface facing the axis and spaced from the axis in the radial direction.

Abstract: A turbine is provided with a seal device. The seal device includes: at least one step surface disposed in a region of an outer peripheral surface of a rotor facing a shroud of a stationary vane in the radial direction of the rotor, the at least one step surface facing upstream in a flow direction of the fluid and dividing the region of the outer peripheral surface into at least two sections in an axial direction of the rotor: at least two seal fins protruding toward the at least two sections from the stationary vane and facing the at least two sections via a seal gap; and a swirling-component application portion disposed on an end side of the shroud of the stationary vane with respect to the axial direction of the rotor and configured to be capable of applying a swirling component to the fluid flowing toward the seal gap.

Abstract: Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

Abstract: An impeller for a turbine engine is disclosed, such as a turbojet engine or a turboprop engine of an aircraft, for rotating about an axis of rotation in a predetermined direction of rotation and for having a flow of gas passing therethrough, comprising a series of blades distributed circumferentially about the axis of rotation of the wheel, the radially external end of each blade comprising a heel supporting at least one radially external lip, extending circumferentially in an oblique direction relative to the radial plane perpendicular to the axis of rotation, the lip being angled circumferentially in the downstream direction in the aforementioned direction of rotation such as to enable a compression of the gases located upstream from the lip during the rotation of the impeller.

Abstract: A centrifugal fan having improved efficiency and noise reduction includes a hub configured to have a central part combined with a rotary shaft, a shroud spaced apart from the hub, and a plurality of blades provided between the hub and the shroud. The shroud includes outer circumferential parts each connecting the trailing edges of a plurality of respective adjacent blades. Each outer circumferential part is asymmetrically formed based on the center of the outer circumferential part.

Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.

Abstract: A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.

Abstract: A grease leakage preventing structure is provided for a gear reducer of a dynamoelectric machine with a gear reducer, which is capable of preventing, if soft grease with high consistency is employed in a gear reducer driven at a high speed for high output power, leakage of grease from the reducer toward the dynamoelectric machine, by covering an output shaft of the dynamoelectric machine with a grease blocking member.

Abstract: An axial flow compressor for a gas turbine engine is disclosed having a casing treatment that includes a shrouded rotor and an airflow member disposed in a passage between a casing and the shrouded rotor. In one form the airflow member is stationary with the casing and in another the airflow member is coupled to rotate with the shrouded rotor. The airflow member can have an airfoil shape in some embodiments. A passage inlet that extracts working fluid and provides it to the passage can be formed between a leading edge of the rotor and a trailing edge. A passage outlet can be formed upstream of the leading edge of the rotor.

Abstract: A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface. The grooves are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Abstract: A hydrodynamic face seal ring for use in a rotary machine includes a support ring having at least two support ring segments and a radially-extending, first face. The support ring is configured to releasably couple to an inner surface of an outer casing of the rotary machine. The face seal ring also includes a sealing ring substantially concentric with the support ring. The sealing ring includes at least two sealing ring segments and a radially-extending, second face. The sealing ring is releasably coupled to the support ring such that the first face is mated against the second face.

Abstract: An internal combustion engine includes in one aspect a source of a pressurized working medium and an expander. The expander has a housing and a piston, movably mounted within and with respect to the housing, to perform one of rotation and reciprocation, each complete rotation or reciprocation defining at least a part of a cycle of the engine. The expander also includes a septum, mounted within the housing and movable with respect to the housing and the piston so as to define in conjunction therewith, over first and second angular ranges of the cycle, a working chamber that is isolated from an intake port and an exhaust port. Combustion occurs at least over the first angular range of the cycle to provide heat to the working medium and so as to increase its pressure.

Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a stator assembly and a rotor assembly having a rotor disk coupled to a plurality of rotor blades, the plurality of rotor blades extending radially outward from the rotor disk. The assembly also includes a casing that at least partially circumscribes the plurality of rotor blades. The assembly also includes a dynamic sealing device coupled to the stator assembly. The at least one dynamic sealing device is configured to insert a seal between the casing and the plurality of rotor blades to facilitate reducing a clearance gap defined between the plurality of rotor blades and the casing while the rotor assembly is operating.

Abstract: The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.

Abstract: A fan for an engine ventilation system includes a housing defining an inlet and an outlet. A hydraulic motor is coupled to the fan housing and includes a motor housing, motor shaft, and shaft seal disposed between the motor housing and the motor shaft. An impeller assembly is disposed in the housing, as well as a stationary baffle that includes a baffle inner edge disposed axially between the impeller assembly and a second wall of the fan housing. A deflector disc is coupled to the impeller assembly and includes a deflector disc outer edge positioned axially rearward of the baffle inner edge. The deflector disc and baffle direct any hydraulic fluid leaking past the shaft seal away from the impeller assembly to a collection chamber.

Abstract: A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component.

Abstract: A seal assembly disposed between a rotor and a stator especially of a turbo-machinery is provided with a close clearance gap there between. The clearance gap is bordered by a rotor surface at the side of the rotor and by a stator surface at the side of the stator. The rotor surface or the stator surface or both are provided with openings which open into at least one chamber arranged at the side of the openings turned away from the clearance gap.

Abstract: A bearing support assembly for supporting a bearing assembly within a bearing compartment of a gas turbine engine includes a centering spring and a bearing support member integrally joined together to form a one piece structure. The centering spring connects to the bearing assembly and has a portion that extends conically relative to a centerline axis of the gas turbine engine. The bearing support member extends from the centering spring to connect to an engine case of the gas turbine engine.

Abstract: A seal assembly arranged adjacent to a primary flow region, the seal assembly including: first and second components; a seal arranged between the first and second components to seal a secondary flow region from the primary flow region; and a first recess portion provided in the first component and arranged adjacent to the seal and the primary flow region, the first recess portion further being arranged to receive flow from at least one of the primary flow region and the secondary flow region and shed flow to the primary flow region, wherein the first recess portion is configured to promote a first flow feature within the first recess portion, the first flow feature flowing with a portion of the first flow feature adjacent to the primary flow region and the portion of the first flow feature being shed to the primary flow region in substantially the same direction as the flow in the primary flow region.

Abstract: An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

Abstract: A rotor blade for a gas turbine engine, comprising an aerofoil having pressure and suction surfaces, leading and trailing edges, and an array of passages at a tip region of the aerofoil. The passages extend from the pressure surface to the suction surface of the aerofoil and are disposed so that the array creates, in operation, a planar jet of gas issuing from the suction surface. The jet is inclined outwardly from the suction surface and towards the tip, and in the direction from the leading edge to the trailing edge. The jet inhibits migration away from the suction surface of a clearance vortex formed by leakage of air over the tip of the rotor blade.

Abstract: A method of assembling a sealing assembly for use in a turbomachine includes providing a rotatable element that includes an end portion with a plurality of grooves partially extending circumferentially about a portion of an outer surface of the end portion of the rotatable element. The method also includes providing a stationary portion that includes an upper section and a lower section. The method further includes inserting at least a portion of the end portion of the rotatable element into the lower section. The method also includes coupling the upper section to the lower section, thereby defining a rotor shaft cavity. The end portion of the rotatable element at least partially extends through the rotor shaft cavity, thereby defining a clearance between the end portion of the rotatable element and the stationary portion.

Abstract: A fluidic actuator comprising: a fluid nozzle for delivering fluid and a tube having an open end and a closed end, the open end spaced from the fluid nozzle. Also a pair of electrodes mounted in the tube and spaced apart to create a spark gap therebetween. A voltage source is arranged to supply a voltage across the pair of electrodes wherein the voltage causes plasma formation in the spark gap thereby shortening the effective length of the tube.

Abstract: In accordance with one embodiment of the present disclosure, a method may include installing a first seal around a motor shaft. The method may also include installing a second seal around the motor shaft, wherein the second seal and the first seal may form a hydrodynamic seal when the motor shaft rotates. The method may further include installing a spacer in-between the second seal and the first seal.

Abstract: A circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a seal runner operable to be fixed to a structure for concurrent rotation with the structure about an axis. The circumferential sealing arrangement also includes a housing that encircles the seal runner or is encircled by the seal runner. The circumferential sealing arrangement also includes a primary seal element at least partially disposed in the housing. The primary seal element includes a first surface cooperating with a second surface of the seal runner to form a circumferential seal between the primary seal element and the seal runner. The circumferential sealing arrangement also includes a secondary seal element positioned between the housing and the primary seal element on a first side of the primary seal element along the axis of rotation. A second side of the primary seal element along the axis of rotation opposite the first side seals against the housing.

Abstract: The invention relates to a hydrodynamic sliding bearing of a shaft (2), in particular of a magnetic coupling pump (1), wherein the hydrodynamic sliding bearing (4) comprises a clamping sleeve (7) disposed between bearing sleeves (6), wherein the bearing sleeves (6) are each mounted with their bearing front side (8) on an axial bearing element (9). The hydrodynamic sliding bearing (4) is characterized in that the bearing sleeve (6) and the clamping sleeve (7) have on their respective front sides (11, 12) a respectively correspondingly designed spherical region (18, 19) which intermesh, wherein the clamping sleeve (7) has at least one concentric groove (28, 29, 31) and wherein the axial bearing element (9) has a recess (42) adapted to the bearing front side (8) of the bearing sleeve (6).

Abstract: A nose dome for a turbomachine rotor is provided. The turbomachine rotor has an impeller which is arranged in an overhung fashion with respect to a bearing point of the turbomachine rotor. The nose dome can be connected axially to the impeller in order to guide an axial inflow and/or outflow of the impeller, and includes a coupling device. The impeller and the nose dome can be mechanically coupled radially with the coupling device, such that the vibration behavior of the turbomachine rotor may be influenced. The turbomachine with the turbomachine rotor including the nose dome is also provided. The impeller and nose dome are coupled radially using the coupling device, such that the vibration of the turbomachine rotor is damped.

Abstract: A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings.

Abstract: The present invention provides a rotary blood pump with both an attractive magnetic axial bearing and a hydrodynamic bearing. In one embodiment according to the present invention, a rotary pump includes an impeller assembly supported within a pump housing assembly by a magnetic axial bearing and a hydrodynamic bearing. The magnetic axial bearing includes at least two magnets oriented to attract each other. One magnet is positioned in the spindle of the pump housing while the other is disposed within the rotor assembly, proximate to the spindle. In this respect, the two magnets create an attractive axial force that at least partially maintains the relative axial position of the rotor assembly. The hydrodynamic bearing is formed between sloping surfaces that form tight clearances below the rotor assembly.

Abstract: According to one aspect of the invention, a turbine assembly includes a first bucket with a first slashface and a second bucket including a recess formed in a second slashface of the second bucket, wherein the second slashface is adjacent to the first slashface when the first bucket is positioned adjacent to the second bucket. The turbine assembly also includes a pin configured to be placed in the recess, wherein the pin is magnetically urged toward the first slashface to reduce fluid flow between the first and second buckets.

Abstract: A seal assembly for a compressor includes a static member fixedly disposed within a compressor casing and having an end surface and a rotatable separator coupled with a compressor shaft and spaced from the static member. The separator has an axial end with a radial end surface located adjacent to the static member end surface such that a clearance space is defined therebetween. The separator has a plurality of openings extending inwardly from the end surface and spaced about the shaft axis such that land surface sections are defined on the end surface. The land surface sections or/and the openings are configured to prevent fluid flow radially inwardly through the clearance space. The static member has two annular walls receiving an end portion of the separator, with annular ridges providing labyrinth seals disposed against inner and outer surfaces of the separator, and an annular deflector with an angled deflector surface.

Abstract: A rotary coupling having a first element and a coaxial second element, the first and second elements being rotatable relative to each other and defining an annular passage between radially facing walls thereof. The coupling has a sealing ring at an end of the annular passage, the sealing ring being mounted to the wall of the first element and rotating relative to the second element, and having an active configuration in which the sealing ring is urged against the wall of the second element to seal the end of the annular passage, and a return configuration in which the sealing ring does not seal the end of the annular passage. A control system is used to apply a variable load to the sealing ring, wherein the sealing ring moves between the active and return configurations in response to variation in the applied load.

Abstract: A pressure balance seal includes a sealing surface facing an inward radial direction, and a stator interface comprising at least one surface interfacing with a stator. The pressure balance seal further includes a friction reducing feature. The friction reducing feature includes a cavity on the sealing surface. The cavity is configured to receive a fluid such that a normal force acting on the pressure balance seal is counterbalanced by a force generated by a pressure of the fluid.

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: Disclosed is a turbine, a turbine seal structure, and a process of servicing a turbine. The turbine includes the seal structure. The seal structure is mechanically secured within the hot gas path of the turbine. The process of servicing includes positioning the seal structure within the hot gas path of the turbine and mechanically securing the seal structure within the turbine.

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: 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: A steam seal system is disclosed. In one embodiment, the steam seal system includes: a low pressure steam turbine positioned on a shaft; a pair of end packings surrounding the shaft, each of the pair of end packings located proximate an axial end of the low pressure steam turbine along the shaft; and an pair of extraction conduits fluidly connected to the low pressure steam turbine and the shaft, the pair of extraction conduits connected to the shaft at a location axially outward of the pair of end packings and the low pressure steam turbine.

Abstract: An aspirating face seal includes a primary seal, a secondary seal, and a biasing device. The primary seal includes a first seal component and a second seal component. The first seal component is configured to be coupled to a rotor and rotatable with the rotor. The secondary seal includes a plurality of flexible elements and configured to be disposed between the second seal component and a stator housing. A biasing device is coupled to the second seal component such that the second seal component is biased along an axial direction away from the first seal component during a non-operating condition.

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for providing a turbine interstage rim seal. According to an example embodiment of the invention, a method is provided for sealing a turbine rotor-bucket interface. The method can include linking a first portion of one or more rim seal segments with one or more flow path seal segments. The method includes rotating the one or more rim seal segments, upon application of centrifugal force, to displace a second portion of the one or more rim seal segments; and sealing at least a portion of a gap between a rotor and a bucket associated with a turbine with at least one or more rotated rim seal segments.

Abstract: Self-balancing face seals and gas turbine engine systems involving such seals are provided. In this regard, a representative self-balancing face seal assembly includes: a rotatable seal runner having a first seal runner face and an opposing second seal runner face; a first face seal operative to form a first seal with the first seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal; and a second face seal operative to form a second seal with the second seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal.

Abstract: A mid-turbine frame assembly includes a mid-turbine frame, a ring structure and a plurality of actuated struts. The ring structure surrounds the mid-turbine frame, and has an interior surface and an exterior surface. The actuated struts connect the ring structure to the mid-turbine frame. The actuated struts are strain actuated so that the actuated struts reposition the ring structure in response to a strain.

Abstract: Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner.