Abstract: A beacon assembly located at a downhole end of a drill string proximate a boring tool. The beacon assembly transmits data to an above-ground receiver. The beacon has a housing with a housing wall located between its sensors, such as gradiometers, accelerometers, and other orientation sensors, and an antenna assembly. The antenna assembly has a protective covering made of electromagnetically transparent material.

Abstract: A magnetic ranging system, in some embodiments, comprises: a wellbore in a formation; a conductive casing in said wellbore; and excitation and return electrodes electrically coupled to the conductive casing, the excitation electrode positioned downhole relative to the return electrode, the excitation and return electrodes generating a current in the casing, said current resulting in an electromagnetic signal that propagates through said formation toward a sensor in another wellbore.

Abstract: Systems and methods for measuring rate of penetration (ROP) and well depth of a drill string are disclosed. As the drill string is constructed, a pair of rangefinders are positioned near the well site and are configured to measure a distance to points on the drill string without human intervention. The rangefinders calculate a length of drill string segments the measured distances and from the length and an elapsed time calculate an accurate, automatically generated ROP.

Abstract: Various examples are provided for gas leakage detection from geologic storage sites. In one example, a system for detection of gas leakage from a geologic storage site includes permanent down-hole gauges (PDGs) disposed at different depths within a well and an evaluation system that can determine a three-dimensional (3D) location of the gas leakage from the geologic storage site and a leakage indicator. The 3D location and leakage indicator can be determined using pressure data provided by the PDGs. The geologic storage site can store, e.g., CO2, natural gas or other type of gas. In another example, a method for detecting gas leakage from a geologic storage site includes receiving pressure data provided by PDGs disposed within one or more wells associated with the geologic storage site, determining key performance indicators using the pressure data and determining a 3D location and a leakage indicator using the key performance indicators.

Abstract: A technique is provided for modeling flow simulations at downhole reservoir conditions and rock formations after performing wellbore perforations. By utilizing these flow simulations, a user may be able to simulate and compare different scenarios, thereby facilitating a more effective, profitable, and realistic choice of perforating systems and operating conditions.

Abstract: A communication system that is positionable in a wellbore can include a first transceiver positioned externally to a casing string. The first transceiver can be operable to detect a presence or an absence of a surface wave; determine a location of a fluid in the wellbore based on the presence or the absence of the surface wave; and transmit data indicative of the location to a second transceiver. The surface wave can include an electromagnetic wave that has a magnetic field or an electric field that is non-transverse to a direction of propagation of the surface wave. The communication system can also include the second transceiver, which can be positioned externally the casing string and operable to receive the data.

Abstract: A downhole repeater network timing system for a drilling rig including a drillstring extending subsurface downwardly from a surface wellhead. The system includes a node located at the drillstring lower end and including a sensor adapted for providing a signal data set output corresponding to downhole drilling conditions. Multiple nodes are located downhole between the Bottom Hole Assembly (BHA) and the wellhead and are associated with the drillstring. The nodes are adapted for receiving and transmitting the signals. The timing control system is adapted for controlling all times within a timeframe according to pre-configured constants known to all nodes. A downhole low rate linear repeater network timing method uses the system.

Abstract: An embodiment of a system for performing measurements in a downhole environment includes an optical interrogation assembly configured to emit a pulsed optical signal, the pulsed optical signal including a selected wavelength, and an optical fiber configured to be disposed in a borehole in an earth formation and configured to receive the pulsed optical signal, the optical fiber having at least one measurement location disposed therein and configured to at least partially reflect the pulsed optical signal. The optical fiber has a core and a cladding, at least a portion of the core made from at least substantially pure silica, and the optical fiber has a refractive index profile configured to have a zero dispersion wavelength that is greater than the selected wavelength.

Abstract: Methods, apparatus, and articles of manufacture are disclosed to characterize acoustic dispersions in a borehole. An example apparatus includes a dispersion analyzer to characterize an acoustic wave dispersion in a borehole in a formation by calculating a quality indicator corresponding to the acoustic wave dispersion, and a report generator to prepare a report including a recommendation to perform an operation on the borehole based on the quality indicator.

Abstract: The present disclosure generally relates to a real-time synthetic logging method for optimizing one or more operations in a well. The method generally includes receiving measurements of one or more parameters in real time while performing operations in the well, the measurements being captured without using tools that include active nuclear sources. The method further includes providing the measurements as input to a machine learning algorithm (MLA) that is trained using historical or training well data. The method further includes generating, using the MLA and based on the measurements, a synthetic mechanical property log of the well. The method further includes generating, based on the synthetic mechanical property log, optimized parameters for at least one operation selected from the following list: drilling the well in real-time; steering the well in real-time; and stimulating a reservoir in real-time.

Abstract: A formation fluid sampling bottle having a first chamber and a first piston slidably disposed within the first chamber and dividing the first chamber into first and second portions. The sampling bottle has a second chamber and a second piston slidably disposed within the second chamber and dividing the second chamber into third and fourth portions. The third portion of the second chamber is fluidly connected with the second portion of the first chamber, and the fourth portion of the second chamber is fluidly connected with a space external to the sampling bottle.

Abstract: A cutting bit assembly for a mining machine includes a holder having a first surface, a second surface, and a bore extending therebetween, and a bit having a first end and a second end. The bit further includes a tip, a shank, and a shoulder positioned between the tip and the shank. The shank is positioned in the bore of the holder and defines a shank axis. The shoulder engages the first surface of the holder. The shank includes a projection adjacent the second end. The cutting bit assembly also includes a retainer having a groove and a resilient member. The groove engages a portion of the projection. The resilient portion engages the second surface of the holder and biases the retainer along the shank axis and away from the holder.

Abstract: A fractured roof 110 mining method entry-side anti-collapsed structure, one working face of the 110 mining method corresponds to one roadway but without retaining any coal pillar, the roadway retains an entry after the previous working face implements mining top-cutting pressure release, and a roof of the roadway is arch-shape, directional cutting is conducted on one side of the roadway, and the cutting angle is between 15-20 degrees. One working face corresponds to one roadway but without retaining any coal pillar when underground mining is conducted, which can save resources and improve recovery rate of mining. And, the roof of the roadway of the retained entry is arch-shaped, which can improve safety and ensure safety of the coal mining working face. In addition, a cutting angle is 15-20 degrees, which can effectively determine a roof caving direction after top-cutting and reduce affect to the retained entry.

Abstract: Concrete is formed by providing a wet layer of a first concrete 4, applying a second wet layer 6 of concrete on the first layer 4 of wet concrete and setting the layers 4 and 6 to provide a composite concrete structure, wherein at least one of the layers comprises, AACM (Alkali-Activated Cementitious Material). An ionic bond 2 is formed between the two layers. The AACM layer may comprise a reinforcement structure and cathodic protection.

Abstract: A friction bolt assembly, such as for use with a pneumatically actuated drill, with a friction fit tubular sleeve longitudinally extending between a leading end and a trailing end, a rod which longitudinally extends through the sleeve between a first end and a second end, and which projects from either end of the sleeve to define, between the first end of the rod and the leading end of the sleeve and the second end of the rod and the trailing end of the sleeve respectively, a leading part and a trailing part, an expansion element mounted on or formed with the rod, on the leading part, a drill engaging element axially fixed in position on the second end of the bolt and engageable with a chuck or an end of the rock drill, a first load bearing formation mounted on the trailing part of the rod and which engages the trailing end of the sleeve, and a second load bearing formation mounted over the trailing part of the rod between the first load bearing formation and the drill engaging element.

Abstract: The invention provides a fluid working machine comprising: a crankshaft (2) which is rotatable about an axis of rotation (3); adjacent first and second groups (5, 6, 8, 10) of valve cylinder devices (13) spaced from each other about the axis of rotation (3), one or each of the first and second groups (5, 6, 8, 10) of valve cylinder devices having first, second and third valve cylinder devices (13) arranged about and extending outwards with respect to the crankshaft (2), the first and third valve cylinder devices being axially offset from each other, the second valve cylinder device being axially offset from the first and third valve cylinder devices and the second valve cylinder device being offset from the first and third valve cylinder devices about the axis of rotation, wherein the second valve cylinder device has an axial extent which overlaps with the axial extent of one, or the axial extents of both, of the first and third valve cylinder devices.

Abstract: The invention relates to a pump device (10) for pumping a fluid (13), comprising: a pump housing (12) having an annular portion (22); a pump ring (14), which is deformable and defines an annular pump chamber (57) at least in some portions; a first connection (51) and a second connection (52), said first connection (51) and said second connection (52) being in fluid communication with the pump chamber (57); an eccentric (18), which is designed to be rotatable relative to the pump housing (12) and which is arranged such in the pump device (10) that the eccentric (18), depending on a current rotational position of the eccentric (18), deforms the pump ring (14) in such a way that the pump ring (14) presses at least partially against the annular portion (22) in order to pump, by way of a rotation of the eccentric (18), the fluid (13) along the pump chamber (57) from the first connection (51) to the second connection (52) depending on the current rotational position of the eccentric; and a clamping element (114), w

Abstract: A pneumatic motor with dual air intake includes a pneumatic cylinder and a rotor. The pneumatic cylinder includes a cylinder body, and an elliptic-cylinder-shaped accommodating room located in the cylinder body. The cylinder body has two air inletting paths, two air venting paths, two air venting holes and a front axial hole, which communicate with the accommodating room and outside. The rotor includes a rotor body rotatably accommodated in the accommodating room of the pneumatic cylinder, a plurality of grooves parallel provided on the rotor body, a plurality of vanes accommodated in the grooves respectively, and a front axle extended from the rotor body and inserted through the front axial hole. As a result, the pneumatic motor with dual air intake is lowered in friction of the rotor when it rotates, raised in power output, and lowered in vibration when in use.

Abstract: A shear flow turbomachinery device includes a housing having housing walls defining a cavity, a shaft extending into the cavity though a shaft opening in the housing wall at an end of the cavity, a rotor coupled to the shaft within the cavity, the rotor having a plurality of disks extending radially outward from a central axis of the rotor, the disks having a spaced arrangement forming a gap between adjacent disks, and a shroud for shrouding the rotor, the shroud including a pair of end disks coupled to opposing ends of the rotor, a screen extending between outer edges of the pair of end disks, the screen extending around the rotor between the rotor and the housing walls, wherein the shroud is freely rotatable independent of rotation of the rotor to reduce drag on the disks due to the housing walls when the cavity if filled with fluid and the shaft and plurality of disks are rotated.

Abstract: This disclosure provides methods and systems for using coatings to control component dimensions during operations of a mechanical system, such as gas turbine combustion air cooling system. The mechanical system may have a component with a critical dimension defined by at least one surface. Upon detecting a change in the critical dimension, such as from surface erosion, a coating additive is deployed into the mechanical system. The surface is coated with the coating additive to offset at least a portion of the change in the critical dimension.

Abstract: A compressor for a turbine engine includes an annular row of blades including a first blade with an extrados surface and a second blade with an intrados surface; and a connecting surface joining the intrados surface to the extrados surface, the connecting surface having a bulge of volume VB and a recess of volume VC, the bulge and recess forming a contouring 3D. The volume of the bulge VB is greater than four times the volume VC of the recess, the connecting surface includes a flat or axisymmetric band circumferentially separating the bulge from the recess, and the bottom of the recess being formed against the intrados surface.

Abstract: An assembly for receiving in a radially extending bucket groove (31) of a turbine disc (22), the assembly including a turbine blade having an elongate body (26) of aerofoil cross-section, a root portion (24) at one end of the elongate body (26) and a tip at the other. The root portion (24) configured to be retained in the bucket groove (31). A heat shield (27) configured to be received between an end of the root portion (24) and a radially inner surface of the bucket groove (31) and to interlock with the root portion (24) in a manner which deters separation in a radial direction.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade having: an attachment; an airfoil extending from the attachment to a tip; and a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.

Abstract: A method of assembling an airfoil includes depositing a bonding material on a first end of the tip portion and shaping the bonding material to form a first plurality of features. The first plurality of features correspond to a second plurality of features on a second end of the body portion. The method also includes positioning the first end relative to the second end such that the first plurality of features and the second plurality of features interlock. The method further includes coupling the first end of the tip portion to the second end of the body portion.

Abstract: A fan of a gas turbine engine includes a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end, wherein the airfoil comprises pockets filled with an elastomeric composite.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a plurality of blade outer air seals and a plurality of airfoils, at least one of seals and airfoils including at least one cooling passage. The cooling passage includes a first wall and an opposed second wall bounding the cooling passage, a surface contour of the first wall having a plurality of first surface features and a surface contour of the second wall having a plurality of second surface features. The first surface features and the second surface features are arranged such that a width of the cooling passage varies along a length of the cooling passage defined by the first surface features and the second surface features. The first surface features have a first profile, and the second surface features have a second, different profile. A casting core for forming cooling passages in an aircraft component is also disclosed.

Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.

Abstract: A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a leading edge of an airfoil of the turbine vane and in fluid communication with an internal cavity of the turbine vane; and a baffle insert located in the internal cavity, the baffle insert having a plurality of holes formed therein at least some of the plurality of holes of the baffle insert corresponding to the at least some of the plurality of cooling holes located in the leading edge of the turbine vane, the baffle insert being formed from a flat sheet of metal wherein the plurality of holes of the baffle insert are formed in the flat sheet of metal prior to the baffle insert being formed from the flat sheet of metal, the plurality of holes of the baffle insert being formed in the flat sheet of metal according to the coordinates of Table 1.

Abstract: Disclosed herein are a bucket vibration damping structure and a bucket and turbomachine having the same. The bucket vibration damping structure comprises a plurality of blades disposed on a plurality of buckets mounted on an outer peripheral surface of a rotor disk and a variable contact-type vibration damping means disposed on the plurality of blades and performing variable contact according to rotational speed of a rotor for damping vibration. The variable contact-type vibration damping means may comprise a first damping member disposed on one of the blades, and a second damping member disposed at a position corresponding to the first damping member on the other blade. According to the disclosure, it is possible to effectively damp vibration while performing variable contact according to the rotational speed of a turbine.

Abstract: A blade for a gas turbine engine is disclosed herein. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint located at a peripheral edge of the platform, wherein the damper restraint is a raised feature extending along at least a portion of the peripheral edge of the platform.

Abstract: In the method for carrying out work, according to the invention, in order to maintain a metal turbine engine motor, such as a drum, in an operational state: an upstream and/or downstream face (343) of a circumferential groove (34) of the rotor is ground, with said face having recessed marks that the grinding is intended to remove or at least blur, and foils (43) are placed in the groove between the blades of the rotor (24) and the rotor, at least in the area where the face has been ground.

Abstract: Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine, an airfoil having a root and a tip, and a pin extending through the root. The root is coupled to the rotary structure and has a bulbous shape, and the airfoil is formed from a plurality of composite plies. The pin defines both a planar first surface and a planar second surface on a pin body having a generally circular cross-section. Further, the pin includes a first end and a second end that contact the rotary structure. The first and second surfaces together form a point that is oriented toward the tip of the airfoil. In one embodiment, the rotary structure is an outer rotor of an interdigitated rotor assembly and the airfoil extends radially inward.

Abstract: A guide vane ring for a turbomachine minimizes a leakage flow that passes through a recess into which a guide vane disk is inserted. It has a guide vane row having a plurality of guide vanes, each having a vane airfoil and a vane disk, as well as an inner ring having an inner ring surface facing the plurality of guide vanes. Viewed in the direction of a designated primary flow streaming through the turbomachine, the vane disks have a front and a rear surface region. In a nominal and/or a maximum open position of the guide vanes, the front and/or the rear surface region of at least one of the vane disks has an offset from the inner ring surface that is radially disposed (relative to a central axis of the inner ring).

Abstract: A turbine nozzle according to the disclosure is a turbine nozzle that is used in a radial turbine and includes a ring-shaped hub, a plurality of nozzle vanes that are arranged at equal angular intervals on the hub, and a flow path that is formed between the nozzle vanes. The flow path includes a throat that has a smallest flow path cross-sectional area with respect to a flow direction of working fluid. On a downstream side of the throat with respect to the flow direction, the flow path cross-sectional area increases. Heights of the nozzle vanes on the downstream side of the throat with respect to the flow direction are greater than heights of the nozzle vanes in the throat and gradually increase from an upstream side toward the downstream side with respect to the flow direction.

Abstract: The gas turbine has a plurality of inlet guide vanes each having a blade having a leading edge, a trailing edge, a span extending along the leading edge, and pivot members at opposite ends of the leading edge, and being pivotally mounted across the radial-to-axial intake via the pivot members, the pivot axis extending axially across a radial portion of the radial-to-axial intake. The plurality of inlet guide vanes include a plurality of first inlet guide vanes, and a plurality of second inlet guide vanes, the second inlet guide vanes having a trailing edge recess differing from the corresponding portion of the first inlet guide vanes. During operation, when the inlet guide vanes are pivoted past a given angle toward the tangential orientation, a radial flow of gas is allowed through the trailing edge recesses to avoid or impede vortex whistle.

Abstract: An airfoil includes an airfoil section that has radially inner and outer ends and defines an airfoil profile. The airfoil profile has a leading end, a trailing end, a suction side, and a pressure side. The airfoil section includes a ceramic airfoil piece that defines a portion of the airfoil profile. The ceramic airfoil piece includes an exterior wall that has an internal cooling circuit.

Abstract: A seal system for a moving blade system of a gas turbine includes a seal carrier including a ring section extending in the axial direction and the circumferential direction, on which a radially inner seal element is situated. A first flange section and a second flange section extend outwardly from the ring section in the circumferential direction and the radial direction and are situated at a distance from each other in the axial direction. An inner shroud section of at least one guide blade or of at least one guide blade segment includes a sealing section extending inwardly in the radial direction and in the circumferential direction, the sealing section being accommodated between the first flange section and the second flange section of the seal carrier and being connected thereto. A disk-like first seal is situated upstream from the first flange section with respect to the main flow direction of a working medium and partially abuts the first flange section radially inwardly.

Abstract: There is disclosed an axial flow machine (10) comprising an annular flow path (23); a stator ring (38) comprising a plurality of stators mounted at their radially outer ends and extending into the annular flow path (23); a non-rotating body (24) axially adjacent the stator ring (38); and an annular shroud (42) disposed between the radially inner end of the stator ring (38) and the body (24). The shroud (42) is supported on the stator ring (38) and moveable relative the body (24); and the shroud (42) cooperates with the body (24) to inhibit a flow through a clearance pathway (78) therebetween.

Abstract: A seal assembly for a turbine engine having a shaft with a rotary axis and a housing surrounding the shaft; the seal assembly being disposed between the shaft and the housing, the seal assembly comprising: an outer labyrinth seal having multiple outer fins in opposing sealing engagement with a concentric outer seal runner, one of: the outer labyrinth seal fins; and the outer seal runner, engaging the housing, and the shaft engaging an opposing one of: the outer seal runner; and the outer labyrinth seal fins; an inner labyrinth seal, disposed radially inwardly concentric to and axially overlapping the outer labyrinth seal and the outer seal runner, the inner labyrinth seal having multiple inner fins in opposing sealing engagement with a concentric inner seal runner, one of: the inner labyrinth seal fins; and the inner seal runner, engaging the housing, and the shaft engaging an opposing one of: the inner seal runner; and the inner labyrinth seal fins; and an intermediate plenum, defined between the outer fins,

Abstract: A blade outer air seal for a gas turbine engine is provided. The blade outer air seal having: a gas path surface exposed to exhaust gas flow; a first side extending radially outward from the gas path surface; a second side extending radially outward from the gas path surface; and a plurality of film cooling holes disposed on at least one of the gas path surface, the first side and the second side, the film cooling holes disposed at locations described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin.

Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.

Abstract: A stop valve includes: a valve seat in a fluid flow path; a valve disc that contacts the valve seat and that closes the fluid flow path; a valve stem that extends along a center axis includes a first end, in a direction of the center axis, that is connected to the valve disc; a spindle that extends along the center axis and comprises an end surface of a first end, in the direction of the center axis, that faces an end surface of a second end of the valve stem, in the direction of the center axis; and a connector that connects the second end of the valve stem to the first end of the spindle.

Abstract: A variable displacement supercharger includes a turbine having: a turbine housing that forms a scroll flow passage disposed around a turbine impeller; a variable nozzle unit that includes a second nozzle ring that faces the scroll flow passage and forms a part of an inner wall of the scroll flow passage; and an annular seal member that seals the gap between the turbine housing and the second nozzle ring. The seal member has a disc spring structure that is inserted into the gap and biases the turbine housing and the second nozzle ring in an axial direction of rotation, and is arranged further inside than the scroll flow passage in the radial direction of the turbine impeller.

Abstract: A gas turbine engine including a support structure including a conduit coupled to a static support. The conduit defines an end wall between which a fluid is contained within a volume defined by the conduit. An effort variable provided to the support structure modulates a stiffness of the support structure.

Abstract: A monitoring system for monitoring environmental conditions for rotary members includes a plurality of stationary reader antennas positioned proximate rotary members. A first sensor is coupled to a first rotary member and a second sensor is coupled to a second rotary member. Each sensor is configured to generate environmental condition data. A key phasor is coupled to a third rotary member and configured to generate key phasor data. The monitoring system also includes a data integrator communicatively coupled to each stationary reader antenna and configured to determine measurement values for the first and second environmental condition based on raw data from each stationary reader antennas and data from the key phasor.

Abstract: A fan is mounted on a fan shaft which constitutes part of a mainline shaft assembly centered for rotation on an engine axis X-X of a gas turbine engine. When in operation, the fan rotates about the engine axis X-X. A stub-shaft is arranged radially outwardly and concentrically with the fan shaft and adjoins an upstream facing face of a bearing sleeve. A fan catcher arm extends from the stub-shaft through the bearing sleeve and joins a fan catcher ring arranged downstream of the bearing sleeve and having an upstream facing face arranged to abut against a downstream facing face of the bearing sleeve in the event of a fan blade-off. Immediately downstream of the fan catcher ring is formed a shaft end which is configured to couple with an axially adjacent end of a low pressure compressor shaft. Immediately downstream of the bearing sleeve is a shaft end configured to connect with a turbine shaft.

Abstract: An annular rotatable component for a machine includes a first element formed of a composite material, is ring-shaped, and is formed of one or more first ring segments. The first element includes a first interface surface. A second element is formed of a metallic material, is ring-shaped, and is formed of one or more second ring segments. The second element includes a second interface surface complementary to the first interface surface. The annular rotatable component also includes an interface comprising an interface material disposed between the first interface surface and the second interface surface. The interface material, the first element and the second element are co-bonded together to form a unitary structure of the annular rotatable component.

Abstract: An airfoil includes a supply passage to provide a coolant, an airfoil section that has walls that define an internal cavity, a baffle seated in the internal cavity, and a seal proximate the edge of the baffle. The baffle is seated such that there is a gap between the baffle and at least one of the walls. The baffle includes a baffle wall that has cooling holes and that defines an interior baffle region. The seal seals off the gap such that the coolant that exits the supply passage will be directed to flow into the interior baffle region.

Abstract: A turbomachine structure having a first inner casing including a first and second flowpath oriented in opposing axial directions to one another; a second inner casing surrounding the first inner casing and including a third and fourth flowpath, wherein the third flowpath is fluidly connected to the first flowpath and the fourth flowpath is fluidly connected to the second flowpath; an extraction chamber defined between the first and second inner casings; a cooling passage defined between the first and second inner casings; a first extraction port fluidly connected to the cooling passage and to the first flowpath at a location in the first flowpath having a first pressure; and a second extraction port fluidly connected to the extraction chamber and to the second flowpath at a location in the second flowpath having a second pressure less than the first pressure.