Abstract: An x-ray-based casing imaging tool, defined by a combination of source collimators, located cylindrically around an X-ray source and a rotatable two-dimensional per-pixel collimated imaging detector array, is provided, the tool including at least an x-ray source; a radiation shield to define the output form of produced x-rays; a direction controllable two-dimensional per-pixel collimated imaging detector array; an imaging window within the tool housing that reduces attenuation of x-rays passing through said tool housing; sonde-dependent electronics; and a plurality of tool logic electronics and PSUs.

Abstract: Systems and methods for determining the resistance of a power cable of an ESP. The nameplate resistance of the motor is determined prior to installation of the ESP in the well, and the temperature is determined for a point in the well at which the motor will be positioned. The downhole temperature and nameplate resistance are used to calculate an initial downhole resistance of the motor. After the ESP is installed, but before operation of the ESP is initiated, the electric drive for the system generates a measurement voltage and applies the measurement voltage to the power cable and motor. The corresponding current is then measured and is used to calculate the resistance of the string (the combined power cable and motor). The calculated initial downhole resistance of the motor is then subtracted from the resistance of the string to obtain the resistance of the power cable.

Abstract: Systems, devices, and methods for directing the operation of a drilling system are provided. The location of a bottom hole assembly (BHA) of a drilling rig may be determined using survey data. One or more steering objective locations may be defined and one or more sets of directional motor instructions are generated to drive the BHA to the one or more steering objective location.

Abstract: A method, device, terminal and computer readable storage medium for determining a cross-sectional shape of a borehole involves obtaining a plurality of logging data items as measured at a same depth of a well via a multi-arm caliper. The logging data items include pad coordinates which use a center of the multi-arm caliper as a reference point. Coordinates of a borehole center and a borehole radius at the depth of the well are obtained by using a least squares objective function with a constraint condition and according to the pad coordinates. The constraint condition is that a distance from a pad of a caliper tool to the borehole center is larger than or equal to the borehole radius. The pad positions are located outside a circle or on the circle obtained by fitting according to the least squares objective function, such that a real borehole cross-sectional shape is obtained.

Abstract: A method, system, and apparatus for determining the location of a tool traveling down a wellbore by measuring a first borehole magnetic anomaly with respect to time at two known locations on a tool, comparing the time difference between the two measurements, then calculating the velocity of the tool based on the comparison and then further calculating the distance traveled by the tool in the wellbore based on the velocity calculation.

Abstract: An integrated and rigless method of determining the location and the type of damage in casing or tubing of a wellbore that involves recording a thickness profile of the casing or tubing, a temperature log, and a noise log along the depth of the wellbore, followed by locating the damage from the thickness profile, and determining the type of damage from the temperature log and the noise log.

Abstract: Tools, processes, and systems for in-situ fluid characterization based on a thermal response of a fluid are provided. The thermal response of a downhole fluid may be measured using a downhole thermal response tool and compared with thermal responses associated with known fluids. The properties of the downhole fluid, such as heat capacity, diffusivity, and thermal conductivity, may be determined by matching the thermal response of the downhole fluid with a thermal response of a known fluid and using the properties associated with the known fluid. The composition of the downhole fluid may be determined by matching the viscosity of the downhole fluid to the viscosity of known fluid. A downhole thermal response tool for cased wellbores or wellbore sections and a downhole thermal response tool for openhole wellbores or wellbore sections are provided.

Abstract: The present application describes a rapid burrowing robot (RBR) that can dig tunnels using ultra high temperature rotating plasma torches.

Abstract: There are provided a method for the bottom-side separation of a body which is to be worked out of rock (2000), in which a first part of the bottom surface of the body to be worked out of the rock (2000) is separated by removing the rock (2000) situated below the bottom surface, and a second part of the bottom surface is separated by replacing rock (2000) situated below the bottom surface with a layer system (140, 240, 440, 540) which has two unconnected separating layers (141, 142, 241, 242, 441, 442, 541, 542, 1310, 1320), with the result that the body to be worked out of the rock (2000) is supported in the region of this second part of its bottom surface by the layer system (140, 240, 440, 540), and a system (1000), which is suitable for carrying out such a method, for the bottom-side separation of a body to be worked out of a rock (2000), having an advancing unit (1100) for removing a rock layer, a discharge conveying unit (1200) for conveying away rock (2000) removed by the advancing unit (1100), a laying

Abstract: An apparatus for pre-loading a mechanical constant-resistance single prop includes a rhombic stretchable bracket, a screw rod, a first cylindrical sleeve ring, and a second cylindrical sleeve ring. The screw rod is connected to two opposite apex corners of the rhombic stretchable bracket. A tail end of the screw rod is fixedly connected to one apex corner of the rhombic stretchable bracket. An end head of the screw rod passes through another apex corner of the rhombic stretchable bracket. The remaining two opposite apex corners of the rhombic stretchable bracket are respectively fixedly connected to edges of the first cylindrical sleeve ring and the second cylindrical sleeve ring through connecting rods. The screw rod is threadedly connected to the apex corner of the rhombic stretchable bracket through which the screw rod passes. A method for pre-loading a mechanical constant-resistance single prop is also provided.

Abstract: The present invention discloses a process method for withdrawing and recovering a mechanical constant-resistance single prop, specific steps involving: detecting a working resistance and a degree of deformation of a mechanical constant-resistance single prop, releasing lug clamp bolts of a recoverable base, knocking a lower portion of a cylinder body of the mechanical constant-resistance single prop to disengage the mechanical constant-resistance single prop from the recoverable base, and dismantling the mechanical constant-resistance single prop. Parts are classified and recovered based on degree of deformation thereof. By means of the foregoing method, a process of withdrawing and recovering a mechanical constant-resistance single prop is standardized, simple and fast disengagement of the mechanical constant-resistance single prop is achieved, and parts that can still be used can be sufficiently recovered and reused, thereby achieving the objectives of saving energy and reducing costs.

Abstract: A method and an apparatus for rock reinforcement are described. The method comprises the steps: to inject a first component and a second component through a first channel and a second channel respectively into a rock hole, wherein the first component and the second component are adapted for rock reinforcement and to inject a blocking agent through a third channel into at least said second channel, wherein said blocking agent provides a barrier in at least said second channel.

Abstract: A free piston apparatus includes a piston receptacle in which a piston device having a piston is reciprocable along an axis. The piston receptacle includes or forms a chamber delimited by a wall arrangement forming an inlet opening and an outlet opening. A cooling device is arranged on the piston receptacle for cooling the wall arrangement. The cooling device includes or forms a cooling channel arranged radially outside on the wall arrangement. The cooling channel has first and second cooling regions axially on opposing sides of the outlet opening. The piston receptacle includes or forms an outlet chamber, arranged outside on the wall arrangement, for exhaust gas exiting via the outlet opening. The cooling channel has a third cooling region which flow-connects the first cooling region and the second cooling region along the outlet chamber and is positioned at least in sections radially outside of the outlet chamber.

Abstract: A free piston apparatus includes a piston receptacle in which a piston device having a piston is reciprocable along an axis. The piston receptacle includes or forms a combustion chamber delimited by a wall arrangement forming an inlet opening for the supply of fresh gas and an outlet opening for the removal of exhaust gas. Fresh gas is suppliable via a supply conduit. The free piston apparatus includes a housing for fresh gas which is connected to the supply conduit in a flow direction of the fresh gas being supplied. The housing forms a settling chamber for fresh gas which surrounds the piston receptacle at least in sections in the region of the inlet opening in a circumferential direction of the axis. The settling chamber opens into the combustion chamber via the inlet opening.

Abstract: A free piston apparatus includes a piston receptacle in which a piston device having a piston is reciprocable along an axis. The piston receptacle includes a combustion chamber delimited by a wall arrangement forming an inlet opening for the supply of fresh gas and an outlet opening for the removal of exhaust gas. The free piston apparatus includes an inflow device, which has the inlet opening and is configured such that fresh gas flowing into the combustion chamber is directed to an incident flow region in the combustion chamber arranged offset axially to the inlet opening, which incident flow region is arranged off-center relative to the axis. A method for operating a free piston apparatus includes operating an inflow device which has an inlet opening configured such that fresh gas is directed to an incident flow region in a combustion chamber offset axially to the inlet opening.

Abstract: A free piston apparatus includes a piston receptacle in which a piston device having a piston is linearly reciprocable. The piston receptacle includes or forms a combustion chamber delimited by a wall arrangement forming a first opening and a second opening. The openings include an inlet opening for the supply of fresh gas and an outlet opening for the removal of exhaust gas for a uniflow scavenging of the combustion chamber. Movement of the piston device is controllable by a control device. The bottom dead center of the piston can be adjustable such that when the piston adopts the bottom dead center, the first opening is partially unblocked and partially blocked for adjusting a free cross sectional area of the first opening. An opening duration can also be adjustable. A method for operating a free piston apparatus includes controlling movement of a piston device with a control device.

Abstract: A compressor includes a compressor screen mounted on the outer circumferential surface of a compressor disk or the inner wall of a compressor casing. The compressor screen is positioned between a row of compressor blades and a row of compressor vanes to stabilize airflow by regulating the amount of air flowing in the compressor. The compressor screen is formed of annular plate having openings through which the compressed air flows, arranged in a pattern to smoothly regulate the flow of air. The compressor screen may be variously configured, for example, to facilitate installation or to guide the flow of air using a tapered surface or a directionality of the openings or a flow guide. A gas turbine includes a combustor, a turbine, and a compressor employing the compressor screen.

Abstract: The present disclosure is directed to a gas turbine engine including a torque frame. The torque frame includes an inner shroud defined circumferentially around the axial centerline, an outer shroud surrounding the inner shroud and defined circumferentially around the axial centerline, and a structural member extended along the radial direction and coupled to the inner shroud and the outer shroud. The torque frame is configured to rotate around the axial centerline.

Abstract: A rotor of a member of a turbomachine, for example a rotor of a turbine, the rotor including a first element, a second element defining with the first element a ventilation cavity, the rotor including a spacer that is introduced and secured between the first element and the second element and that includes a row of through-passages that are configured to permit injection of cooling fluid into the ventilation cavity.

Abstract: A blade (10) for a turbomachine is provided. The blade (10) includes an airfoil (16) having at least one thickening (22) on a pressure side (20) of the airfoil (16). The thickening (22) has a region (B) of constant thickness (D). A turbomachine, a compressor and a turbine having stator vanes and/or rotor blades including at least one such blade (10) is also provided.

Abstract: A turbomachine includes a turbine section including a turbine, the turbine having a plurality of turbine rotor blades spaced along the axial direction, each turbine rotor blade extending generally along the radial direction between a radially inner end and a radially outer end. The plurality of turbine rotor blades include a first turbine rotor blade; and a second turbine rotor blade spaced from the first turbine rotor blade along the axial direction, the radially outer end of the first turbine rotor blade coupled to the radially outer end of the second turbine rotor blade. The plurality of turbine rotor blades additionally includes a third turbine rotor blade spaced from the second turbine rotor blade along the axial direction, the radially inner end of the second turbine rotor blade coupled to the radially inner end of the third turbine rotor blade.

Abstract: A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.

Abstract: A turbine blade is provided with a rotatable leading edge to reduce pressure loss as a flow direction of combustion gas varies. The turbine blade includes an airfoil including as separate bodies a trailing-edge portion and a leading-edge portion being linked to the trailing-edge portion and disposed upstream of the trailing-edge portion, the leading-edge portion including a front surface arranged on an upstream side of the leading-edge portion; and a rotary unit connected to the leading-edge portion and configured to rotate the leading-edge portion according to an inflow angle of the combustion gas such that the front surface faces a flow of the combustion gas. A barrier wall extends from a side surface of the leading-edge portion toward an open end of the trailing edge portion, and when the leading-edge portion is rotated, the bather wall portion prevents formation of a gap between the side surface and the open end.

Abstract: A rotor for a gas turbine engine. The rotor includes blades circumferentially distributed around a hub. The blades have airfoils with a span defined between a root and tip, a chord defined between a leading edge and a trailing edge, and a thickness defined between a pressure side surface and suction side surface. The blades include first blades and second blades. The airfoil of the first blades has a first thickness distribution defining a first natural vibration frequency of the airfoils of the first blades. The airfoil of the second blades has a second thickness distribution defining a second natural vibration frequency different than the first natural vibration frequency. The first thickness distribution is different than the second thickness distribution along a radially-inner half of the span, and the first thickness distribution matches the second thickness distribution along a radially-outer half of the span.

Abstract: An apparatus and method relating to a film-hole of a component of a turbine engine. The film-hole can extend from an inlet to an outlet to define a passage. The film-hole can include a laid back section where a coating can be applied. The method can include forming the film-hole in the component and applying the coating to the component to maintain a specific geometry.

Abstract: An airfoil assembly for a turbine engine can include a platform having a fore edge, an aft edge axially spaced from the fore edge, and opposing heated and cooled surfaces. An airfoil can extend from the heated surface of the platform, and a cooling cavity can be positioned interiorly of the platform.

Abstract: A gas turbine engine component has an engine component body and at least one hole formed within the engine component body and extends between a hole inlet and a hole outlet. The hole has a first portion with a first roughness and a second portion having a second roughness that is less than the first roughness. The first portion is upstream of the second portion. A gas turbine engine and a method of forming a cooling hole are also disclosed.

Abstract: A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.

Abstract: A rotor is provided comprising a centre of mass and a rotational axis and a rotor sealing component extending circumferentially around the rotor for sealing between the rotor and a stator, wherein the centre of mass of the rotor is coincident with the rotational axis, and material of the rotor sealing component is not evenly distributed around its circumference. A stator sealing component in which the material is not evenly distributed around its circumference is also provided.

Abstract: The present disclosure is directed to a method of operating an active clearance control system for an interdigitated turbine engine. The method includes flowing air from a compressor section to a rotatable outer shroud of an interdigitated turbine section; and adjusting the flow of air to the outer shroud based at least on an engine condition of the turbine engine. The present disclosure is further directed to a gas turbine engine including a low speed turbine rotor comprising an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The engine further includes a turbine frame at least partially surrounding the low speed turbine rotor; a seal assembly disposed between the outer shroud of the low speed turbine rotor and the turbine frame; and a fifth manifold coupled to the turbine frame.

Abstract: The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.

Abstract: The present disclosure is directed to a gas turbine engine including a turbine rotor assembly that includes a first turbine rotor and a second turbine rotor. The first turbine rotor includes an outer rotor and a plurality of outer rotors extended inwardly along a radial direction from the outer rotor. The second turbine rotor includes an inner rotor and a plurality of inner rotor airfoils extended outwardly along the radial direction from the inner rotor. The plurality of outer rotor airfoils and inner rotor airfoils are disposed in alternating arrangement along a longitudinal direction. One or more rotating seal interfaces are defined between the first turbine rotor and the second turbine rotor.

Abstract: The invention relates to a sealing assembly for a turbine engine, comprising a wheel mounted inside a sectorised ring carrying an abradable material, having at an axial end an annular groove (14) in which a circumferential rail of the casing is engaged, sealing members being partly engaged in a recess (19) of a circumferential edge of a ring sector and another part thereof being engaged in a recess of a circumferential edge circumferentially opposite a circumferentially adjacent ring sector, characterised in that each sealing member comprises an axial end portion (180a) arranged radially between the circumferential rail and two adjacent ring sectors.

Abstract: A turbomachine includes a turbine section including a turbine. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction. The turbomachine also includes a gearbox. The first plurality of turbine rotor blades and the second plurality of turbine rotor blades are each coupled to one of a ring gear, a planet gear, or a sun gear of the gearbox such that the first plurality of turbine rotor blades is rotatable with the second plurality of turbine rotor blades through the gearbox. The turbomachine also includes an electric machine assembly including a rotor coupled to one of the ring gear, the planet gear, or the sun gear of the gearbox such that the rotor rotates relative to a stator during operation.

Abstract: An engine assembly includes an engine including a component and defining an opening and an interior, the component including a first side and an opposite second side, the second side positioned within the interior of the engine. The engine assembly also includes an inspection tool having a first member including at least one of a receiver or a transmitter and directed at the first side of the component. The inspection tool also includes a second member including the other of the receiver or the transmitter and positioned at least partially within the interior of the engine and directed at the second side of the component to communicate a signal with the first member through the component, the second member being a robotic arm extending through the opening of the engine.

Abstract: A turbomachine includes a turbine section including a turbine center frame and a turbine, the turbine including a plurality of low-speed turbine rotor blades and a plurality of high-speed turbine rotor blades alternatingly spaced along the axial direction. The plurality of low-speed turbine rotor blades each extend between a radially inner end and a radially outer end. At least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the radially outer ends. The turbomachine also includes a gearbox aligned with, or positioned forward of, a midpoint of the turbine. The gearbox includes a first gear coupled to the plurality of low-speed turbine rotor blades, a second gear coupled to the plurality of high-speed turbine rotor blades, and a third gear coupled to the turbine center frame.

Abstract: A turbocharger including a pivoting vane (50) aligned with a volute slot (25) of the housing (10) and located proximal a downstream end (57) of a tongue (15) defining an initial inlet throat area (11) of the housing. When the vane is in its fully closed position (60), inlet exhaust gas is prevented from flowing into the volute slot and, therefore, the turbine wheel, until the inlet exhaust gas passes a downstream end (57) of the vane. The vane effectively extends the inlet throat area to define a revised inlet throat area (12). The A/R ratio of the housing progressively varies as the vane pivots between the fully opened and fully closed positions.

Abstract: A gas turbine includes an endwall supporting a vane or blade as a cooling object and having an airflow path through which cooling air is supplied to a leading edge of the cooling object; a curved portion disposed upstream of the leading edge to guide the cooling air supplied through the airflow path to the cooling object; and a guide protrusion formed on an upper surface of the endwall to redirect the movement of the cooling air to a side surface of the cooling object. The guide protrusion, disposed midway between the leading edge and a trailing edge of the cooling object, redirects the cooling air upward, higher along the side surface of the cooling object. A cooling channel formed in the endwall can be separately provided to supply cooling air to the leading edge of the cooling object, separately from the cooling air supplied through the airflow path.

Abstract: A conduction riser is additively manufactured onto thin metal parts, the conduction riser extends in a build direction of the thin metal part and traverses a surface of the thin metal part as the conduction riser extends in the build direction. The conduction riser transfers heat from the upper layers of the additively manufactured part during manufacturing to prevent thermal deflection of the part during the manufacturing process.

Abstract: A turbomachine includes a spool and a turbine section. The turbine section includes a turbine center frame and a turbine, with the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades. The first plurality of turbine rotor blades and second plurality of turbine rotor blades are alternatingly spaced along the axial direction. The turbomachine also includes a gearbox aligned with, or positioned aft of, a midpoint of the turbine. The gearbox includes a first gear coupled to the first plurality of rotor blades, a second gear coupled to the second plurality of rotor blades, and a third gear coupled to the turbine center frame. The turbomachine also includes a support member, the first plurality of turbine rotor blades coupled to the spool through the support member, the support member extending aft of the gearbox.

Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four total bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.

Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.

Abstract: A turbomachine includes a turbine frame and a turbine, the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a first support member assembly including a first support member supporting the first plurality of turbine rotor blades; a second support member assembly including a second support member supporting the second plurality of turbine rotor blades; a frame support member assembly including a frame support member coupled to and extending from the turbine frame; and a bearing assembly including a first bearing and a second bearing. The first bearing is positioned between the first support member and the second support member, and the second bearing is positioned between the frame support member and one of the first support member or the second support member.

Abstract: A turbofan including a low-pressure shaft; a high-pressure shaft; a fan shaft; a reducing mechanism that couples the low-pressure shaft to the fan shaft; and a maximum of six chambers that accommodate the bearings of the low-pressure shaft, the bearings of the high-pressure shaft and the bearings of the fan as well as the reducing mechanism.

Abstract: The present disclosure is directed to a gas turbine engine including a first turbine frame defining one or more first struts extended along a radial direction and a turbine rotor assembly. The turbine rotor assembly defines a rotatable drum surrounding a reduction speed reduction assembly and coupled thereto. The turbine rotor assembly includes a first turbine rotor and a second turbine rotor each disposed on one or more bearing assemblies. The first turbine frame defines a first supply conduit through the first strut providing a flow of fluid to the speed reduction assembly and one or more of the bearing assemblies. The first turbine frame further defines a first scavenge conduit providing an egress of at least a portion of the flow of fluid from one or more of the bearing assemblies.

Abstract: A turbine nozzle for a rotary machine including a centerline axis includes an airfoil including a leading edge and a trailing edge. The airfoil defines a throat location proximate the trailing edge. The turbine nozzle also includes an inner band assembly including a platform portion coupled to the airfoil, and a first flange coupled to the platform portion. The first flange is obliquely oriented with respect to the platform portion, and the platform portion and the first flange intersect at a point axially aligned with the throat location.

Abstract: A turbine stator, into which combustion gas supplied from a combustor of a gas turbine flows, has an improved structure capable of preventing circumferential movement of turbine vanes. The turbine stator, which may be included in a turbine of a gas turbine having the improved structure, includes a casing including first and second casings constituting respective casing halves, the first and second casings having a fastening groove formed on at least one contact surface between the first casing and the second casing; a plurality of vane airfoils configured to be installed on an inner peripheral surface of the casing and arranged in a multi-stage manner in a flow direction of the combustion gas; and a stop configured to be fixed with respect to a vane airfoil of the plurality of vane airfoils and to be inserted into the fastening groove to fix the vane airfoil to the casing.

Abstract: A gas turbine includes a housing; a rotor rotatable by a fluid flowing through the housing; a bearing for rotatably supporting the rotor; and a support structure configured to support the bearing with respect to the housing. The support structure includes an inner casing accommodating the bearing; an outer casing fastened to the housing; and a strut extending between the inner and outer casings, and at least one of the inner casing and the outer casing includes a diaphragm that is deformable in a radial direction of the rotor. Each casing includes a strut root connected to the strut, a strut platform surrounding the strut root and being formed as the diaphragm; and a main body surrounding the strut platform. Damage to the support structure due to thermal expansion can be prevented, and the support structure can be easily designed to avoid resonance between the support structure and the rotor.

Abstract: A turbomachine base plate is disclosed. The base pate includes an upper metal plate and a lower metal plate. The upper metal plate forms a turbomachine supporting surface. The base plate further includes an intermediate layer between the upper metal plate and the lower metal plate and bonded thereto. A frame extends peripherally around the intermediate layer.

Abstract: A turbine support structure supports a turbine casing and is configured to be movable when the turbine casing is thermally deformed while a gas turbine is operated, thus preventing a fatigue fracture of the turbine casing from occurring. The turbine support structure includes a pair of supports, each having an upper and lower end, for supporting respective opposite side surfaces of the turbine casing at the upper end of either support; and a movable unit installed at the lower end of each support and configured to movably support the lower end of the support. The movable unit is spaced outwardly from the corresponding opposite side surface of the turbine casing, so that the corresponding support inclines toward the turbine casing and is rotatable. The lower end of each support is rotatably coupled to the corresponding movable unit so that the support is rotatable toward an axis of the turbine casing.