Abstract: A blowout rate correction system comprises a sensor and a processor in communication with the sensor. The sensor is to measure sound characteristics associated with an exit point of a borehole. The processor is to determine a blowout rate of hydrocarbons exiting the borehole based on the sound characteristics. In some embodiments, the processor activates a device when the blowout rate exceeds a selected threshold. Additional apparatus, methods, and systems are disclosed.

Abstract: Optical analysis devices may be configured for optically interacting a material of interest with a chemical filter and a detector that together are configured to detect a characteristic of the material of interest, wherein optically interacting the material of interest with the chemical filter comprises absorbing, by the chemical filter, at least a portion of an electromagnetic radiation having optically interacted with the material of interest. Relative to cementing operations, such optical analysis devices may be useful in identifying fluids, analyzing compositions of cement slurries, investigating the status of a reaction occurring in a cement slurry, detecting and/or monitoring corrosion of a set cement, and the like.

Abstract: A method of estimating properties of wellbore cement by penetrating the cement, and monitoring the amount of energy or power required for penetrating the cement. Penetrators include a drill bit that bores into the cement, and probes or pins that are forced into the cement. The energy or power monitored can be current and/or voltage supplied to a motor that drives the drill bit or probe. Comparing the monitored energy or power with that required to penetrate a reference cement sample of known properties can yield information about the cement being sampled. When the wellbore is lined with multiple coaxially disposed strings of casing with cement between adjacent strings and on the outer surface of the outer string; the method further includes obtaining core samples from portions of each string, each layer of cement, and formation adjacent the wellbore.

Abstract: A communication assembly including at least one sensor assembly made up of interrogation circuitry and one or more antennae. The interrogation circuitry comprises at least one inductor coil sensor including a single turn coil inductor for reception of signals from the MEMS data sensors.

Abstract: In order to address the above noted problems, embodiments of the present invention use distributed acoustic sensing to monitor the fluid level in an ESP activated well so as to monitor the condition and performance of the ESP. Embodiments of the invention use the ESP as an acoustic source in order to monitor the annulus fluid level within the well and to monitor the frequency of the ESP. Additionally, embodiments of the present invention may use distributed acoustic sensing to monitor the flow rates of the production fluid above and below the ESP to determine the pump's efficiency. In particular, some embodiments utilize one or more optical fibers to measure the acoustic waves generated by the ESP, wherein the fiber cabling has already been deployed along the length of the well. As such, the present invention is a non-invasive, in-situ method for monitoring the condition and performance of an ESP.

Abstract: A logging-while-drilling optical fiber communication device includes a rotary wireless transceiver module fixed on a protective connector; an active antenna of the rotary transceiver is placed in the first drill pipe by drilling hole through the protective connector; an optical fiber communication drawworks is located at the top of a second drill pipe, the optical fiber is downwardly released into other under-well drill pipes, the bottom of the optical fiber is connected with the well-bottom wireless receiving module; the lowest part of the drill pipe are provided with a drilling data acquisition device and a well-bottom wireless transmitting module. In the present invention, the optical fiber cable is used as transmission medium, by the means of modulating information data obtained by well logging into optical wave, and transmitting to the optical communication link, high-speed bi-directional transmission of well logging information can be realized.

Abstract: An apparatus for sensing acoustic waves below a surface of the earth includes an optical fiber disposed below the surface of the earth and having a series of sensing units along the optical fiber with each sensing unit having three or more reflectors and an optical interrogator in optical communication with the optical fiber. The reflectors in each sensing unit are positioned to provide a linearized response that approximates a sawtooth wave better than a sinusoidal wave to sense the acoustic waves in a desired dynamic range. The optical interrogator is configured to transmit an input light signal into the optical fiber and receive a reflected light signal from the optical fiber due to the input light signal in order to measure a strain on each sensing unit due to interaction with the acoustic waves and to determine a location of the sensing unit corresponding to the sensed strain.

Abstract: An electro-acoustic communications node system and method for downhole wireless telemetry, the system including a housing for mounting to or with a tubular body; a receiver transducer positioned within the housing, the receiver transducer structured and arranged to receive acoustic waves that propagate through the tubular member; a transmitter transducer and a processor, positioned within the housing and arranged to retransmit the acoustic waves to another acoustic receiver in a different housing, using the tubular member for the acoustic telemetry. In some embodiments, the transducers may be piezoelectric transducers and/or magnetostrictive transducers. Included in the housing is also a power source comprising one or more batteries. A downhole wireless telemetry system and a method of monitoring a hydrocarbon well are also provided.

Abstract: A fluid pressure pulse generator for a telemetry tool comprising a stator and a rotor. The stator comprising a stator body and a plurality of radially extending stator projections spaced around the stator body, whereby adjacently spaced stator projections define stator flow channels extending therebetween. The rotor comprising a rotor body and a plurality of radially extending rotor projections spaced around the rotor body. The rotor projections are axially adjacent the stator projections and the rotor is rotatable relative to the stator such that the rotor projections move in and out of fluid communication with the stator flow channels to generate fluid pressure pulses in fluid flowing through the stator flow channels.

Abstract: A method utilized in borehole logging, such as in surveying or exploration relating to a subsurface formation. The method includes deploying a logging instrument that includes a pressure sensor into a borehole drilled into the formation. The method includes the steps of obtaining a first pressure value at a first depth in the borehole, obtaining at least one further pressure value subsequent to the first pressure value during withdrawing or advancing the logging instrument in the borehole, and determining one or more characteristics of the subsurface formation, utilizing at least one of the further pressure values, or a change in pressure (??) between the first pressure value and a said further pressure value or values, or a change in pressure (??) between a said further pressure value and another said further pressure value, or a combination of two or more of such values.

Abstract: A system and method is provided for enhancing hydrocarbon production. The method and system involve geochemistry analysis and include multiply substituted isotopolog and position specific isotope geochemistry. The method and system involve using clumped isotope and position specific isotope signatures to enhance monitoring of well and stimulation performance.

Abstract: A method for obtaining a fluid sample downhole that has at least a target fluid and an undesirable fluid may include receiving the fluid sample into a sample tank positioned that has a main chamber and isolating at least a portion of the undesirable fluid from the target fluid in the main chamber. A related apparatus may include a conveyance device configured to be conveyed along a borehole and a fluid sampling tool positioned along the conveyance device. The conveyance device may include a probe receiving the fluid sample from a formation; a pump drawing the fluid sample through the probe; and at least one sample tank receiving the fluid sample from the pump. The sample tank may include a main chamber receiving the fluid sample and an isolation volume isolating at least a portion of the undesirable fluid from the target fluid in the main chamber.

Abstract: Systems, methods and devices for analyzing a sample of fluid extracted from a hydrocarbon-producing geological formation to detect a quantitative amount of hydrogen sulfide or disclosed. The systems methods and devices involve including a scavenger within a sample compartment to react with the hydrogen sulfide therein. The concentration of hydrogen sulfide in the sample may be derived as a function of the amount of scavenger remaining in the sample after reaction with hydrogen sulfide, an amount of byproduct of a reaction between the scavenger and the hydrogen sulfide, or an amount of hydrogen sulfide as measured following a secondary reaction that releases the hydrogen sulfide from the scavenger.

Abstract: A method and system is provided that analyzes flow characteristics of return fluid that flows to a surface-located facility during well operations (such as plug mill-out or cleanout/workover operations) in order to characterize local formation properties of the formation. The method and system can be used to characterize a hydraulically-fractured hydrocarbon-bearing formation that is traversed by a well having a number of intervals that are hydraulically isolated from one another by corresponding plugs.

Abstract: The present disclosure relates to a cutter assembly for an undercutting machine for cutting a rock workface and a method of disassembling a cutter assembly. The cutter assembly includes a shaft supporting structure, a shaft at least partly arranged within the shaft supporting structure, a cutter device arranged on the shaft or the shaft supporting structure, a first rolling element arranged between the shaft supporting structure and the shaft in a floating or slidable manner in an axial direction, and a second rolling element arranged between the shaft supporting structure and the shaft. A line orthogonal to an outer surface of the second rolling element crosses the longitudinal axis of the shaft at a center plane of the first rolling element or within a range of +/?25% of an axial extension of the first rolling element from the center plane.

Abstract: A mining machine includes a frame, a boom supported for pivoting movement relative to the frame, and a cutter head pivotably coupled to the boom. The cutter head includes a housing, a cutter shaft coupled to the housing, a cutting disc, and an excitation mechanism. A second portion of the cutter shaft extends parallel to a cutter axis. The cutting disc is coupled to the second portion of the cutter shaft and is supported for free rotation relative to the cutter shaft about the cutter axis. The cutting disc includes a plurality of cutting bits defining a cutting edge. The excitation mechanism includes an exciter shaft and a mass eccentrically coupled to the cutter shaft. The excitation mechanism is coupled to the first portion of the cutter shaft. Rotation of the exciter shaft induces oscillating movement of the second portion of the cutter shaft and the cutting disc.

Abstract: A round-shank pick, comprising a pick head and a pick shank, the pick head including a base part and a cutting element, which is connected to the base part and is composed of a hard material, in particular hard metal, wherein the base part has a wear-resistant layer on the outer surface thereof at the connection to the cutting element, which wear-resistant layer covers at least one segment of the outer surface of the base part facing the cutting element and wherein an end face of the wear-resistant layer facing the cutting element is covered by the cutting element. The base part has an axially oriented cut-out for receiving a fastening segment of the cutting element, the base part has a counter surface facing the cutting element and extending around the cut-out, and the counter surface and the end face of the wear-resistant layer form a continuous flat surface.

Abstract: A unitary bit/holder assembly includes a reverse taper insert having a diamond coated tip mounted thereon that is received in an annular flange forwardmost portion of a holder body. In a modification, the diamond coated tip is received in a recess on a generally cylindrical forwardmost portion of the holder body.

Abstract: A high-strength confined concrete support system for an underground tunnel. The support system includes multiple confined concrete arches, bolts and cables, and a prestressed steel strand backfilling system. The confined concrete arches all support the surrounding rock of the tunnel and are sequentially arranged along the tunnel. Every two adjacent confined concrete arches are connected by a longitudinal connection structure. The support system is provided with a plurality of layers of steel bar meshes on the surrounding rock side and the tunnel side, and shotcrete layers are sprayed on the support system and the steel bar meshes. The prestressed steel strand backfilling system comprises a prestressed steel strand system and a filling material. The filling material fills the space between each confined concrete arch and the surrounding rock to equalize a load on the confined concrete arch and generate prestress.

Abstract: A device for constructing an underground reservoir by dissolving limestone using carbon dioxide. The device includes a CO2 storage tank; an absorption tower; a decompression valve; a gas-liquid separator; a crystallizer; a vacuum pump; a buffer tank; a first booster pump; a second booster pump; and a third booster pump. The decompression valve is connected to a limestone layer, and is connected to the gas-liquid separator. The absorption tower is connected between the gas-liquid separator and the limestone layer.

Abstract: The purpose of the present invention is to provide a scroll fluid machine, the reliability of which is ensured and which can be manufactured with high productivity. The present invention provides a scroll fluid machine comprising: a stationary scroll having a spiral wrap upstanding therefrom; an orbiting scroll provided facing the stationary scroll and orbiting; a casing provided outside the orbiting scroll; a drive shaft for causing the orbiting scroll to orbit; an orbiting bearing for transmitting the rotational movement of the drive shaft to the orbiting scroll; and a plurality of rotation prevention mechanisms for preventing the orbiting scroll from rotating. The scroll fluid machine is characterized in that: the rotation prevention mechanisms have crankshafts and also have crank bearings for supporting the crankshafts; and the gap between each of the crankshafts and the corresponding one of the crank bearings is set to be greater than the gap between the drive shaft and the orbiting bearing.

Abstract: A method for epitaxial addition of repair material onto a process surface (38) of a directionally solidified component (30). The component is positioned in a fluidized bed (34) to drift particles of a repair material over the process surface as laser energy (36) is rastered across the surface to melt the particles and to fuse repair material onto the entire surface simultaneously. The component is moved downward (39) in the bed in a direction parallel to the grain orientation in the component as material is added to the surface, thereby providing continuous epitaxial addition of material to the surface without recrystallization.

Abstract: The present disclosure relates generally a gas turbine engine and a rotor therefor. The rotor may include a symmetric rim thereon to prevent the propagation of induced vibratory responses. The rim may have one or more sloping surfaces to prevent the re-attachment of boundary layer flow.

Abstract: A contoured turbine airfoil assembly including an end wall (30a) formed by platforms (30) located circumferentially adjacent to each other, and a row of airfoils (34a, 34b) integrally joined to the end wall (30a) and spaced laterally apart to define flow passages (46) therebetween for channeling gases in an axial direction. A trough (62) is defined between a pressure side ridge (48) and a suction side ridge (58) located forward of each pair of airfoils (34a, 34b). Each trough (62) has a direction of elongation aligned to direct flow into the flow passage (46) centrally between each pair of airfoils (34a, 34b).

Abstract: A method of manufacturing an aerofoil blade includes the steps of providing: an aerofoil sub-assembly having a pair of aerofoil skins, wherein at least one of the skins is formed to have on its outer face an outer primary relief feature formed proud of the adjacent region of the outer face and an outer secondary relief feature projecting from the outer primary relief feature; arranging the aerofoil sub-assembly in a cavity die mould; and performing a hot forming process to form an internal cavity between the respective aerofoil skins by inflating the sub-assembly to conform the outer faces of the respective skins to the cavity die mould, whereby in conforming the respective outer faces of the skins to the cavity die mould, the outer primary and secondary relief features are transferred to the inner face of the respective skin to form respectively inner primary and secondary relief features.

Abstract: A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.

Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.

Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.

Abstract: Ceramic matrix composite airfoils for gas turbine engines are provided. In an exemplary embodiment, an airfoil includes opposite pressure and suction sides extending radially along a span. The pressure and suction sides define an outer surface of the airfoil. The airfoil further includes opposite leading and trailing edges extending radially along the span, the pressure and suction sides extending axially between the leading and trailing edges. The airfoil also includes a filler pack defining the trailing edge; the filler pack comprises a ceramic matrix composite material. Moreover, the airfoil includes a plenum defined within the airfoil for receiving a flow of cooling fluid, and a cooling passage defined within the filler pack for directing the flow of cooling fluid from the plenum to the outer surface of the airfoil. Methods for forming airfoils for gas turbine engines also are provided.

Abstract: A turbine blade according to the invention includes a first wall surface facing a cooling passage through which cooling air flows; a second wall surface facing a working fluid passage through which a working fluid flows; a communication hole establishing communication between the cooling passage and the working fluid passage; and a projection provided on the downstream side of the flowing direction of the cooling air in the opening of the communication hole formed in the first wall surface, the projection protruding from the first wall surface toward the cooling passage. The projection includes a slope section formed on the first wall surface that ascends in the direction opposite the flowing direction of the cooling air toward the cooling passage and a curved section formed as a convex section on the side of the cooling passage, the curved section extending along the opening in the form of an arc.

Abstract: A composite fiber stator ring for a gas turbine engine compressor includes a plurality of composite fiber vane structures. Each of the composite fiber vane structures includes a plurality of fiber plies. All of the fiber plies flow in a single direction at each joint of the corresponding composite fiber vane structure. The plurality of composite fiber vane structures are arranged circumferentially in a ring.

Abstract: A method for manufacturing a blade (1) for a turbomachine, the blade having a hardfacing on its tip (4) and an erosion-protection coating (13) at least on its airfoil (3) is provided. Initially, a blade tip hardfacing is applied to the blade tip and, subsequently, a mask (10) is positioned in the region of the blade tip hardfacing, the mask covering the blade tip hardfacing, and, subsequently, the erosion-protection coating is deposited. The mask is removed after the erosion-protection coating is completed. A blade for a turbomachine, the blade having a hardfacing on its tip (4) and an erosion-protection coating (13) at least on its airfoil (3) is also provided. The erosion-protection coating at least partially covers the blade tip hardfacing, and the thickness of the erosion-protection coating decreases continuously in and/or toward the region of the blade tip hardfacing.

Abstract: An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.

Abstract: A blade assembly comprises a blade (120) and one or more wear pads (170, 172). The blade has an airfoil (122) having a leading edge (126), a trailing edge (128), a pressure side (130), a suction side (132), and extending from an inboard end to a tip (125). The blade further includes an attachment root (124). The one or more wear pads are along the attachment root. The one or more wear pads have a plurality of slits (228, 230 242).

Abstract: A gas turbine engine, a blisk and methods of manufacturing are disclosed. The blisk includes a disk and a plurality of blades. Each blade includes a platform, an airfoil, and a shank portion radially extending between the platform and the disk. The airfoil includes cooling features. Cooling cavities are defined between shank portions of adjacent blades and are in communication to the internal of blades via cooling feed channels. A coverplate is coupled to a downstream side of the blisk to cover the cooling cavities. A plurality of inner tabs extends from an inner edge of the coverplate to securely couple the coverplate to the disk. The disk and the plurality of blades may be integrally formed or casted as a single unit. The platform, the airfoil, and the shank portion may be formed integrally as a single unit and bonded to the disk to form the blisk.

Abstract: A variable-pitch vane including a plurality of propeller blades (2). Each blade has a variable pitch according to a blade rotational axis (A1) and a root (201). A plurality of rotor connecting shafts (6), each shaft having a foot (602) and a head (601). The root (201) of each blade is mounted on the head (601) of a rotor connecting shaft via a pivot (8) in such a way as to allow each blade (2) to rotate according to the blade rotational axis (A1), in which each blade (2) has a blade pitch, such that the blade rotational axis (A1) is inclined relative to a radial axis (A2) passing through the foot (602) of the corresponding shaft.

Abstract: A gas turbine engine may have a blade receiver for holding a fan blade, wherein the blade receiver is rotatable about a radial axis of the gas turbine engine. The gas turbine engine may also include a variable pitch mechanism comprising an actuation arm. The gas turbine engine may also include a splined index ring disposed between the actuation arm of the variable pitch mechanism and the blade receiver. The splined index ring may include an outer spline and an inner spline.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile, and a first endwall section with which the airfoil section is attached. First and second airfoil pieces form different portions of the airfoil profile. The first and second airfoil pieces include respective first ends. The first ends interlock with the first endwall section such that the first and second airfoil pieces are retained with the first endwall section.

Abstract: A component for a gas turbine engine includes a hot side wall, a plurality of connection walls, and a cold side wall. The hot side wall is exposed to a core air flowpath defined by the gas turbine engine. The cold side wall is spaced from the hot side wall and rigidly connected to the hot side wall through the plurality of connection walls. The hot side wall, connection walls, and cold side wall together define a cooling air cavity. The cold side wall defines a thermal stress relief slot for at least partially accommodating a relative thermal expansion between the hot side wall and the cold side wall to reduce an amount of thermal stress within the component during operation of the component.

Abstract: A nozzle guide vane for a gas turbine engine includes an integrally formed angled nozzle with radially outer and inner platforms and an airfoil extending therebetween. An internal cooling air passage extends between the platforms. A cooling air outlet in the inner platform communicates with the air passage and opens to an inter stage cavity between stages of the engine and is formed as part of the nozzle with an outlet axis angled with respect to a radial direction of the engine. A transition area between a radially outwards facing part of the nozzle and an approximately linear outlet part including the outlet axis is formed as a curved conduit bend. An investment casting core member includes a cone-shaped part that defines the bend, a support part attached to the cone-shaped part and a cylindrical part which extends to the surface of the inner platform.

Abstract: An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal.

Abstract: Aspects of the disclosure are directed to a system for maintaining a seal about an engine centerline, comprising: a first component, a second component, and a dog-bone seal coupled to the first component and the second component, wherein the first component is configured with at least one spline that is configured to engage a slot in the dog-bone seal to radially center the dog-bone seal relative to the first component and the second component.

Abstract: A rotatable arrangement for a gas turbine engine comprises a plurality of blades having an aerofoil profile with a suction side, a pressure side, a leading edge and a trailing edge. A plurality of annulus fillers are provided between adjacent blades. A pressure side seal extends between a blade and an annulus filler on the pressure side of the blade, and a suction side seal extends between the blade and an annulus filler on the suction side of the blade. The suction side seal comprises a blocking member provided at an end of the suction side seal proximal to the trailing edge of the blade, the blocking member being configured to restrict recirculation of flow along the suction side of the blade.

Abstract: A seal assembly includes an annular base, a spring, a shoe, a first channel, a seal cover, and a seal. The spring includes a beam and is connected to the annular base. The shoe is disposed radially inward of the annular base and connected to the spring. The shoe includes an upstream portion, a downstream portion, and a lip connected to and extending radially outward from the upstream portion of the shoe. The spring extends from the annular base to the shoe. The first channel is positioned between the shoe and the beam of the spring. The seal is disposed between the seal cover and the shoe such that a downstream face of the seal is in contact with an upstream face of the shoe.

Abstract: A seal arc segment includes a body including a radially inner surface and a radially outer surface. The radially inner surface and the radially outer surface are located between a first circumferential end and a second circumferential end. A recessed portion defines a cavity in the radially outer surface. A notch is located in an edge of the recessed portion adjacent the first circumferential end.

Abstract: A gas turbine engine includes a turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case.

Abstract: A fluid flow assembly may include an orifice plate having a set of orifices and a plenum defined by a blade outer air seal. The set of orifices may be aligned with and in fluid communication with the plenum. A gas turbine engine may include a vane outer support having an orifice plate, wherein the orifice plate includes a plurality of sets of orifices. The gas turbine engine may also include a blade outer air seal defining a plurality of plenums. Each set of orifices of the plurality of sets of orifices may be forward relative to and substantially axially aligned with a respective plenum of the plurality of plenums.

Abstract: A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft. The shaft has a shaft body that extends between a first end that is operatively connected to the motor assembly and a second end that is operatively connected to the blade outer air seal.

Abstract: A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. Each actuator may be in operable communication with a blade outer air seal (BOAS) segment or a BOAS mounting block. The actuators may be configured to move the BOAS segment and/or the BOAS mounting block in a radial direction from a first position to a second position to control tip clearance.