Abstract: A flexible shield for fluid connectors of a gas turbine engine is disclosed. The flexible shield may comprise a flexible sleeve adapted to surround the fluid connector, and a coupling configured to secure the flexible sleeve onto a fluid tube proximate the fluid connector. A gas turbine engine employing such a flexible shield is also disclosed, as is a method of enclosing a fluid connector in a gas turbine engine using such a flexible shield.

Abstract: A combustor liner (30) for a can-annular gas turbine engine (10) and a method for constructing such a liner are provided. The combustor liner includes an annular wall member (32) A cooling channel (34, 42, 50, 54, 56, 58) is formed through the wall member and extends from an inlet end of the liner to an outlet end of the liner A property of the cooling channel may be varied along a length of the cooling channel. The cooling channel may be formed through the combustor liner using an electro-chemical machining (ECM) process or a three dimensional printing process (3DP).

Abstract: A method includes forming a sheet of material having first, second, third, and fourth ends. The third and fourth ends extend longitudinally between the first and second ends. First and second protrusions are formed at the first end. The first and second protrusions extend longitudinally outwardly from an edge of the first end. The third and fourth ends are coupled to one another to create a longitudinally extending compressor shell having a stepped region at the edge of the first end where the third and fourth ends meet.

Abstract: The present invention provides a method of producing a common rail having a common rail body and a holder which include chemical components of 0.01-0.3 mass % of C, 0.01-0.5 mass % of Si, 0.01-3.0 mass % of Mn, 0.0003-0.01 mass % of B, 0.001-0.01 mass % of N, over 0.01-0.5 mass % of Al, 0.01-0.05 mass % of Ti, P limited to 0.03 mass % or less, S limited to 0.01 mass % or less, O limited to 0.01 mass % or less, a total content of As, Sn, Sb, Pb, and Zn limited to 0.015 mass % or less, the balance including Fe and inevitable impurities, in which the TLB value is 0.001% or more, the method including: inserting an insert metal; performing liquid phase diffusion bonding; performing laser-peening; and removing a surface layer.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan.

Abstract: Embodiments of the invention provide an apparatus for damping or attenuating acoustic vibrations in an air induction system of a motor vehicle, the apparatus defining a passageway through which induction air may be drawn to an engine of the vehicle, the apparatus comprising: damping means, the damping means being provided around the passageway for damping or attenuating acoustic vibrations in the induction air; and hydrocarbon trapping means, the hydrocarbon trapping means comprising a sheet of trapping material provided around at least a portion of the passageway, the trapping means being arranged to provide a flow-past hydrocarbon trap for trapping hydrocarbon vapours entering the passageway from the engine.

Abstract: A method of observing an airflow passage within a gas turbine engine includes locating a support in view of an airflow passage and housing an optical fiber within the support.

Abstract: A heat exchanger assembly comprises a heat exchanger body including a first fluid circuit and a second fluid circuit. The first circuit includes a first bypass valve in flow communication with a first fluid circuit inlet channel. The first fluid circuit also includes a plurality of cooling channels in flow communication with the first bypass valve. The first bypass valve is configured to channel a first fluid to the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the first fluid. The second fluid circuit includes a second bypass valve configured to facilitate a flow of a second fluid through at least a portion of the heat exchanger body during the first mode of operation.

Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.

Abstract: A method of installing a hybrid drive system in a drive train system includes the preliminary step of providing a cradle, a plurality of components of a hybrid drive system, and a drive train system. The cradle and the plurality of components are initially assembled together to provide an integrated cradle and hybrid drive module. Then, the integrated cradle and hybrid drive module are subsequently installed in the drive train system. The hybrid drive system may be actuated hydraulically, electrically, or otherwise as desired.

Abstract: A direct driven wind turbine with a plain bearing and a service method for this bearing is provided. A rotor is directly connected with a rotatable drive train, which is directly connected with a rotor of an electrical generator. The rotatable drive train is connected with a stationary part via at least one bearing, which allows the rotation of the drive train in relation to the stationary part. The generator provides a support structure to which the stationary side of the at least one bearing is mounted. The at least one bearing is a plain bearing and the plain bearing comprises a wear-and-tear-part, which is an object to be exchanged. The rotatable drive train is prepared to be fastened to the stationary part and at least one wear-and-tear-part of the plain bearing is exchangeable while the rotatable drive train is fastened to the stationary part.

Abstract: A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region.

Abstract: A turbine engine including a casing, a turbine engine shaft extending axially, a guide bearing for guiding the turbine engine shaft in the casing, the guide bearing including an inner circumferential ring rigidly connected to the turbine engine shaft, an outer circumferential ring fitted in a housing of the casing, and gripping rolling members, and a damping cavity configured to receive a damping fluid to form a damping fluid film for damping the guide bearing, the cavity being delimited radially between an outer surface of the outer ring and an inner surface of the housing. The outer surface of the outer ring and the inner surface of the housing are conical surfaces.

Abstract: A system to install a mask onto a component of a gas turbine engine includes a drive movable along an axis with respect to a movable base.

Abstract: A vehicle, in particular, a military vehicle, includes a self-supporting vehicle body (2) and a drive assembly (3) for driving the vehicle. The drive assembly (3) is connected to the vehicle body (2) via an assembly support (6, 7), the assembly support (6, 7) forming a part of the support structure of the vehicle body (2). In a method for mounting a drive assembly (3) in a vehicle (2) that has a self-supporting vehicle body (2), the drive assembly (3) is connected to the vehicle body (2) via an assembly support (6, 7) and the assembly support (6, 7) forms a part of the support structure of the vehicle body (2) in the mounted state.

Abstract: A seal for placement in a slot between two turbine components of a gas turbine to seal a gap between the components may include a sealing element sized so as to be capable of placement within the slot and of substantially sealing the gap during operation of the gas turbine. A sacrificial coating may be located on the sealing element. The sacrificial coating may be configured with a size substantially conforming to a size of the slot, the sacrificial coating including a material that is removable from the sealing element via heating to a temperature achieved during operation of the gas turbine. Related gas turbine assemblies and methods of assembly are also disclosed.

Abstract: A fuel nozzle for use in a turbine engine is provided. The fuel nozzle includes at least one premixer tube including a tube wall and a plurality of perforations defined therein and extending through the tube wall. The plurality of perforations are configured to channel a flow of air therethrough. The fuel nozzle also includes a liquid fuel plenum positioned upstream from the premixer tube, and at least one fuel injector coupled in flow communication with the liquid fuel plenum and the at least one premixer tube. The at least one fuel injector is configured to channel a flow of liquid fuel from the liquid fuel plenum into the premixer tube.

Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines a flexible support lateral stiffness with respect to the support lateral stiffness. An input to the gear system defines an input lateral stiffness with respect to the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.

Abstract: An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.

Abstract: A method for assembling a variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member.

Abstract: A cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79£DoutDin£0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.

Abstract: A gas turbine engine component assembly according to an exemplary aspect of the present disclosure includes, among other things, a nacelle including a moveable portion. A generator is configured to be received within a space established by the nacelle. A plurality of cables are at least partially supported on the moveable portion of the nacelle, the plurality of cables being selectively electrically coupled with the generator.

Abstract: An annular injector is described. The injector includes a first bayonet assembly and a second bayonet assembly each including a terminal end and a tip end. The second bayonet assembly is configured to be concentrically coupled at least partially about the first bayonet assembly. An outer diameter of the first bayonet assembly and an inner diameter of the second bayonet assembly vary at the tip end to define a first substantially annular nozzle. The first bayonet assembly includes a maximum outer diameter that is greater than a minimum inner diameter of the second bayonet assembly and at least a portion of at least one of the first bayonet assembly and the second bayonet assembly extends from the tip end to the terminal end. The injector includes a third bayonet assembly configured to be concentrically coupled at least partially about the second bayonet assembly to define a second substantially annular nozzle.

Abstract: A liner wall insert is provided for a compressor rotor stage of a gas turbine engine. Several liner wall inserts are provided radially outboard of the tips of the rotor blades. The liner wall inserts have bleed flow channels formed therein. The bleed flow channels are arranged to remove flow from a trailing edge region of the stage and re-inject the bleed flow at an upstream region. The re-injected bleed flow alters the flow field around the tips of the rotor blades, for example the tip leakage flow. Thus, the bleed flow is used to improve the efficiency of the compressor rotor stage, and thus of the gas turbine engine.

Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a core gas turbine engine including a first rotatable drive shaft, a first low-pressure turbine section in serial flow communication with the gas turbine engine, a gear assembly coupled to the first low-pressure turbine section through a second rotatable drive shaft, and a second low-pressure turbine section in serial flow communication with the core gas turbine engine. The first low-pressure turbine section is configured to rotate in a first rotational direction, and the second low-pressure turbine section is configured to rotate in a second rotational direction opposite the first rotational direction. The first and second low-pressure turbine sections are spaced axially apart from each other. The turbine engine assembly also includes a fan assembly coupled to the first low-pressure turbine section through the gear assembly, and coupled to the second low-pressure turbine section through a third rotatable drive shaft.

Abstract: The disclosure relates to a combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension, which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper.

Abstract: The disclosure relates combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and an downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. The combustor transition is, characterized in that at least one side wall has a side wall extension, which is extending in a downstream direction beyond the outlet. Besides the combustor transition a gas turbine includes such a combustor transition, a method for retrofitting a gas turbine with such a combustor transition as well as a method for borescope inspection of a GT with such a combustor transition are disclosed.

Abstract: A piston pump assembly in which a piston-forming element to be received in a piston chamber of a piston chamber-forming member carries a removable stop flange member which may be secured to the piston chamber-forming member to provide a retention stop to prevent the piston-forming element from being removed from the piston chamber.

Abstract: In a method and system for forming tubing to achieve at least one predetermined performance characteristic relating to the flow of a flowable material therethrough, a relationship is determined between at least one material characteristic of the tubing material, at least one operating parameter of the tube forming machine, and the at least one predetermined performance characteristic of the tubing. Based on this relationship, at least one operating parameter for operation of the tube forming machine to achieve the at least one predetermined performance characteristic is determined. The at least one operating parameter is input into the tube forming machine and the machine is operated to achieve the at least one predetermined performance characteristic.

Abstract: The compressor includes a first constituent element and a first slider. The first constituent element is capable of being laser welded. The first slider is composed of cast iron capable of being laser welded and having a carbon content of from 2.0 wt % or more to 2.7 wt % or less. This first slider is joined to the first constituent element by laser welding without using a filler.

Abstract: A disclosed probe assembly includes a sensor member and an outer holder including a main bore for the sensor member, the outer holder including a first coefficient of thermal expansion. The sensor member is held within a sensor bore of an inner holder. The inner holder is held within the main bore of the outer holder by an interference fit. The inner holder includes a second coefficient of thermal expansion greater than the first coefficient of thermal expansion. Expansion of the inner holder is constrained by the outer holder to maintain the sensor member within the probe bore of the inner holder at elevated temperatures.

Abstract: Some embodiments relate to a catalytic assembly for an engine. The catalytic assembly includes a cooling housing that receives a coolant (e.g., seawater). A catalyst housing is disposed within the cooling housing such that the coolant flows between the catalyst housing and the cooling housing. A catalyst substrate is positioned within the catalyst housing such that exhaust gases from the engine flows through the catalyst substrate. The catalyst substrate serves to covert harmful emissions found in the exhaust gases to less harmful emissions. The catalyst housing includes a first fitting and cooling housing includes a second fitting that mates with the first fitting to prevent rotation of the catalyst housing relative to the cooling housing.

Abstract: A gas turbine engine turbine diaphragm (460) includes an inner cylindrical portion (461), a mounting portion (463), and a disk portion (462). The mounting portion (463) is located radially outward from the inner cylindrical portion (461). The disk portion (462) extends radially between the inner cylindrical portion (461) and the mounting portion (463). The disk portion (462) includes a plurality of angled holes (464). Each angled hole (464) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular to a radial extending from an axis of the diaphragm (460). The component of the vector is angled relative to an axial direction of the diaphragm (460).

Abstract: A method for top-loaded assembly of an internal combustion engine includes providing a carrier base having a lower portion configured as a crankcase and an upper portion having a number of upwardly directed assembly provisions such as a crankshaft bay and at least one cylinder deck. Arranging the crankshaft bay and cylinder deck so that the engine may be assembled from a position above the engine, without the necessity of attaching connecting rods or crankshaft main bearing bolts from underneath the engine.

Abstract: A vane cluster for a gas turbine engine includes multiple singlet vanes and a forward wear liner connecting a forward edge of each singlet vane, thereby allowing the vane cluster to be manipulated as a single component.

Abstract: A thermal/electrical power converter includes a gas turbine with an input couplable to an output of an inert gas thermal power source, a compressor including an output couplable to an input of the inert gas thermal power source, and a generator coupled to the gas turbine. The thermal/electrical power converter also includes a heat exchanger with an input coupled to an output of the gas turbine and an output coupled to an input of the compressor. The heat exchanger includes a series-coupled super-heater heat exchanger, a boiler heat exchanger and a water preheater heat exchanger. The thermal/electrical power converter also includes a reservoir tank and reservoir tank control valves configured to regulate a power output of the thermal/electrical power converter.

Abstract: A method and associated apparatus are described for addressing blow-back when a hydrogen generator is attached to a combustion engine to enhance performance. The method involves positioning a filter with a porous flame tolerant core upstream of the combustion engine on a supply line leading from the hydrogen generator to the combustion engine. The method also involves surrounding the porous flame tolerant core with a hydrophilic filter medium. The hydrophilic filter medium serves as a trap for water vapour passing through the filter in a first direction and the hydrophilic filter medium moistened by water vapour assists in retarding flames passing through the filter in a second direction.

Abstract: The present invention relates to a heat exchanger for cooling a gas which can mainly be applied in EGR systems with a floating core. The differences in temperature achieved during operation of the casing and the core of gas ducts housed therein give rise to degrees of expansion which are also different. If the ends of both components were fixed to each other, stresses which would cause the breakage thereof would occur. The common solution applied is to leave one of the ends of the core of ducts floating, i.e., with capacity for longitudinal displacement with respect to the casing to prevent the occurrence of stresses. The floating end of the core has an attachment by means of O-ring gaskets. The O-ring gaskets are made of an elastomer that cannot reach very high temperatures, hence in the state of the art the floating attachment is on the side where the already cooled gas exits.

Abstract: A micropump with a deformable membrane, including: a first chamber, one wall of which includes a first deformable membrane portion and an actuator of the first membrane portion; a second chamber including a second deformable membrane portion and a third chamber, including a third deformable membrane portion, the second chamber and the third chamber being connected together through a first channel, at least one of the second and third chambers being connected through a second channel to the first chamber; each of the second chamber and third chamber including a mechanism forming a detection gauge, but not including an activation mechanism.

Abstract: The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.

Abstract: The method for retrofitting a double flow steam turbine includes opening an outer casing of the steam turbine, removing the blade carriers and the stator blades, removing the inner casing with inlet belt, removing the double flow rotor and the rotor blades. Thus, the method includes the further steps of providing a new single flow rotor and new rotor blades different from the rotor blades connected to the double flow rotor, providing balancers connected to the single flow rotor, to balance the axial thrust, providing new stator blade carriers and new stator blades different from the stator blades associated to the double flow rotor, providing a new inner casing with inlet belt, providing a passage between the inner casing and the outer casing, closing the outer casing.

Abstract: A method for manufacturing a micropump, which may be for the metered delivery of insulin, multiple layers being situated on the front side of a first carrier layer, which has a front side and a rear side, and microfluidic functional elements being formed by structuring at least one of the layers. It is provided that the structuring of the at least one layer for manufacturing all microfluidic functional elements is exclusively performed by front side structuring. Furthermore, a micropump is disclosed.

Abstract: A liner for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A plurality of hanger assemblies is disposed within the radial space between the liner and the duct for supporting the liner relative to the duct. Each of the hanger assemblies includes a cable having a first end attached to the duct and a second end attached to the liner.

Abstract: An article of manufacture includes a housing having three input ports and an output port. An electronic sensor operationally coupled to an exhaust flowpath is coupled to the first input port via an electrical conduit. A first fluid conduit fluidly couples the second input port to the exhaust flowpath upstream of a particulate filter, and a second fluid conduit fluidly couples the third input port to the exhaust flowpath downstream of the particulate filter. A differential pressure sensor in the housing determines a differential pressure in response to a first pressure at the second input port and a second pressure at the third input port. The article includes a communication module that provides electronic information representative of the differential pressure and output from the electronic sensor at the output port, wherein the communication module is disposed in the housing.

Abstract: A fan drive gear system for a gas turbine engine includes a carrier supporting circumferentially arranged gears within gear mount sections spaced circumferentially about a periphery. A shelf is disposed between each of the gear mounting sections. A torque frame is attached to the carrier and includes circumferentially arranged finger sections. Each of the finger sections includes first and second ends that are spaced apart to receive the shelf. A pin extends through openings in the shelf and first and second ends to secure the torque frame to the carrier.

Abstract: A method and device for modifying a gas turbine engine is disclosed herein. The method for modifying a gas turbine engine includes accessing a first outward end of a first tube installed in the gas turbine engine, the first tube having a tube axis. Then attaching an extraction tool to the first outward end of the first tube, and applying an axial force to the first tube using the extraction tool, the axial force relative to the tube axis, thus breaking a first interference seal between a first interface surface on a first inward end of the first tube and a receiving member of the gas turbine engine. The method continues with removing the first tube from the gas turbine engine.

Abstract: An apparatus for simulation of an anatomical structure may include a left ventricle component having an inlet port configured to receive fluid flow therethrough, an aortic arch component having an outlet port configured to receive fluid flow therethrough, an aortic annulus component attached to and disposed between the left ventricle component and the aortic arch component, and an introducer configured to receive an elongated catheter assembly therethrough. The aortic annulus component may have an inner surface including simulated stenotic nodules. The introducer may be in fluid communication with at least one of the left ventricle component and the aortic arch component.

Abstract: A micromixer assembly of a turbine system includes a plate having at least one aperture comprising a receiving diameter. Also included is at least one tube having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor, wherein the at least one tube includes an inner diameter and an outer diameter, wherein the outer diameter is configured to fit within the receiving diameter of the at least one aperture, wherein the at least one tube is operably coupled at a location on the outer diameter to the receiving diameter of the at least one aperture by exerting a radial force on the inner diameter of the tube.

Abstract: A combustion system for a gas turbine includes a combustion chamber with a wall section separating an outside of the combustion chamber from an inside of the combustion chamber. The wall section has a passage for injecting a combustion medium into the combustion chamber. The combustion system further includes a resonator with a neck section and a resonator chamber, wherein the neck section and the resonator chamber form a resonator volume reducing vibrations within the combustion chamber. The resonator chamber has a first inlet for injecting gaseous medium into the resonator chamber and a second inlet for injecting fuel into the resonator chamber such that a fuel/gas mixture is generated inside the resonator chamber. The neck section is connected from the outside of the combustion chamber to the passage of the wall section such that the combustion medium comprising the fuel/gas mixture is injectable into the combustion chamber.

Abstract: A component includes a substrate having outer and inner surfaces, where the inner surface defines at least one hollow, interior space. The outer surface defines pressure side and suction side walls, which are joined together at leading and trailing edges of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer substrate surface. The coating comprises at least a structural coating that extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge. A method of forming cooling channels in the vicinity of the trailing edge is also provided.