Abstract: This invention relates to a wind turbine of variable speed type including: a wind turbine tower; a nacelle on said wind turbine; a wind turbine rotor hub rotatably mounted at said nacelle, said wind turbine rotor hub having at least one wind turbine blade mounted thereon and a shaft coupled to said wind turbine rotor hub and to, optionally via a gear box, a primary generator which via power lines has a primary stator electrically connected to a grid connection and a primary rotor electrically connected to a back-to-back converter at a generator side converter end wherein the back-to-back converter at a grid side converter end is electrically connected to the grid connection. The wind turbine further includes a secondary generator coupled to the shaft via a mechanical coupling and electrically connected to the primary rotor of the primary generator and the generator side converter end of the back-to-back converter.

Abstract: A micropump device including a first wafer and a second wafer attached to the first wafer. The first and second wafers are configured to define a chamber therebetween having a predetermined volume. A third wafer is attached to the second wafer to define an inlet section and an outlet section in fluid communication with the chamber. At least one of the second and third wafers are formed to define a moveable diaphragm configured to change the predetermined volume of the chamber for pumping a fluid between the inlet section and the outlet section.

Abstract: A borescope plug configuration is disclosed. The borescope plug configuration comprises an inspection path defined through a bore in a first engine structure, a second engine structure, and an opening into the gas path of an engine. The borescope plug configuration further comprises a removable plug for sealing the inspection path. The removable plug is adapted to couple the first engine structure to the second engine structure.

Abstract: A multi-pieces gas turbine engine combustor heat shield is fabricated from sheet metal. The fabrication involves: sheet metal forming a base sheet having opposed hot and cold facing sides, providing cold side details separately from the base sheet, and mounting the cold side details to the cold facing side of the base sheet. The cold side details may be brazed to the base sheet.

Abstract: A method for forming peristaltic pump cassettes includes cutting tubing segments to different lengths based on the physical properties of the individual tubing segments. The size variations compensate for the physical parameters of the tube and improve accuracy in a peristaltic pump using the cassettes.

Abstract: A method of measuring a steam turbine according to an embodiment has: installing a measuring device into the inside of the steam turbine through an inspection hole or a manhole of the steam turbine or an inspection hole or a manhole of a condenser connected to the steam turbine, when the steam turbine is halted; and measuring a position and a dimension of an axial key or a center key of the steam turbine by using the measuring device, without opening a turbine casing of the steam turbine.

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: An apparatus for installing a turbine casing including a first drive subassembly and a member coupled to the first drive subassembly configured for engaging a first segment of the turbine casing. The apparatus may also include a second member coupled to the second drive subassembly configured for engaging the first segment of the turbine casing. The apparatus may be provided with a first retainer connected to the first member and configured for engaging a second segment of the turbine casing, and a second retainer connected to the second member and configured for engaging the second segment of the turbine casing.

Abstract: A system and a method for adjusting an angle of at least one stator vane of a low pressure compressor (LPC) of a two spool gas turbine engine is disclosed. Variable stator vanes are rotatably coupled to a stationary case in one of the stages of the LPC. An actuator is coupled to at least one of the variable stator vanes for imparting rotation of the stator vane about a radius of the case. Various coupling or linkage arrangements may be made so that rotation of one vane results in rotation of the other vanes disposed along the case. The controller includes the stored constraints, the ability to estimate operating condition, and the ability to estimate optimum targets.

Abstract: A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event.

Abstract: An auxiliary member for assembly/disassembly includes a fixing portion which is fixed to one half casing of a lower half casing and an upper half casing, and a jack receiving portion which extends from the fixing portion and faces an outer surface of the other half casing. When an interval between both end portions in the radial direction of the upper half casing is widened due to heat deformation, the fixing portion of the auxiliary member for assembly/disassembly is fixed to the lower half casing, a jack is disposed between the jack receiving portion of the auxiliary member for assembly/disassembly and the outer surface of the upper half casing, and the interval between both end portions of the jack is widened.

Abstract: A flyweight for use in a ram air turbine has a body with a circumferentially enlarged portion extending between flat sides spaced by an angle of between 45 degrees and 150 degrees. A pivot point is defined by a bore at a circumferentially intermediate point in the body, and in a relatively thin inner portion. The relatively thin inner portion extends beyond the pivot point to an end that will be radially inward when the flyweight is mounted in a ram air turbine. A governor, a ram air turbine and a method are also described.

Abstract: A sandwich structure includes a first skin, a second skin, a first hinge member, and a second hinge member. The first hinge member may be movably coupled to the first skin and a first skin joint. The second hinge member may be movably coupled to the second skin and second skin joint. The first hinge member and the second member may be movably coupled to one another and a member joint located between the first and second skin joint.

Abstract: A method of manufacturing a vane component of a gas turbine engine is described, and includes forming a core of the vane component using a rapid manufacturing process, and applying a coating of nanocrystalline metal onto the core, the nanocrystalline metal fully encapsulating the core and defining an outer structural surface of the vane component.

Abstract: A gas turbine engine case has a metallic composite boss mounted thereto. The boss may have a main metal injection molded (MIM) part, and a separately formed flange part integrated to the main MIM part and projecting laterally outwardly therefrom. The MIM part and the flange part may be made of different materials. The material of the flange part is selected to provide a suitable mounting interface with the gas turbine engine case.

Abstract: A method and apparatus for tuning an engine by a modified pod filter or velocity stack using a tunable pod air filter with base and cap members forming a housing that is joined together by a filter membrane to define a plenum or resonance chamber within the housing that contains only air drawn in through the filter. An aperture in the base member passes air to the inlet of an engine. A tuning sleeve is sealingly engaged within the aperture and extends into the plenum to control air flow out of the plenum and into the engine. The tuning sleeve is tubular with a pattern of vents through its surface to control flow rate. The vents may be drilled, punched or otherwise cut through the sleeve to control air flow. After being vented, the sleeve is reinserted into the filter housing and the filter is installed on the engine.

Abstract: An arrangement connectable to an internal combustion engine having a crankshaft, the arrangement including a flywheel, which is connectable to the crankshaft and coupled by a coupling device to output elements. An intermediate piece is arranged in a torque-transmitting manner between the flywheel and the coupling device. A starter generator is arranged within a flywheel housing and operatively connected to the crankshaft. The intermediate piece has in the center thereof an opening in which a shaft body is mounted in an axially movable manner, and the shaft body is connected to the coupling device by means of a flexible transmission element.

Abstract: A system for forming a barrier between a lubrication oil region and an air region of a gas turbine engine comprising a lubrication oil return path, a centrifugal oil slinger on a rotating member fixed to a spool of the gas turbine engine, a spiral groove configured to directs lubrication oil toward an oil return path, a labyrinth seal, and a cavity configured to form a non-contacting seal with the spiral groove and the labyrinth seal.

Abstract: An axial piston machine comprises a cylinder drum in which a multiplicity of pistons are arranged in a longitudinally displaceable manner. The pistons are supported, via sliding blocks, on a running surface which is inclined relative to the cylinder drum axis. The sliding blocks are held, at that side thereof which faces away from the running surface, by means of a retraction plate. The retraction plate is produced from processed sheet metal in a non-cutting punching and stamping process.

Abstract: An apparatus for maintaining engines including a support cradle and neck support for bearing the load of multiple exhaust system components simultaneously during removal, maintenance, and/or reattachment to the engine. The neck support includes one or more separators and cutouts to support exhaust manifold necks and limit lateral movement of the exhaust manifolds during removal and maintenance. The apparatus includes structural supports designed for allowing maneuverability into an engine for proper placement. A method of using the apparatus for removal, maintenance, and/or reattachment of exhaust manifolds to an engine.

Abstract: A gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan about an engine central axis, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled to drive a first spool. The first spool is coupled at a first axial position to a compressor hub that is coupled to drive the first compressor. The first spool is also coupled at a second, different axial position to a fan drive input shaft that is coupled to drive the fan drive gear system. The turbine section also includes a second turbine coupled through a second spool to drive the second compressor. A sensor probe is operable to determine a rotational speed of the first spool. The sensor probe is located at a third axial position that is axially forward of the first axial position and axially aft of the second axial position.

Abstract: A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes a plurality of tube assemblies wherein each of the plurality of tube assemblies includes a plurality of tubes. At least one injection system is coupled to at least one tube assembly of the plurality of tube assemblies. The injection system includes a fuel delivery pipe and a fluid supply member coupled to the fuel delivery pipe, wherein the fluid supply member is positioned a predefined distance upstream from the tube assembly and includes at least one first portion having an annular end portion. The annular end portion includes at least one opening for delivering fluid toward the tube assembly for reducing dynamic pressure oscillations and/or reducing the temperature within a combustor during operation of the turbine engine.

Abstract: An example gas turbine engine includes a housing and first and second spools coaxial with one another and arranged within the housing. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool. First and second bearings support the aft end of the first spool relative to the housing. An example method of assembling the gas turbine engine includes arranging a first spool within a second spool. First and second bearings are mounted between an aft end of the first spool and a fixed housing.

Abstract: An assembly can include vanes and a base configured to seat the vanes at a radial distance about an axis where each vane includes a leading edge and a trailing edge, a pair of lateral surfaces that meet at the leading edge and at the trailing edge, an extension that extends from one of the lateral surfaces and that has a contact surface, and a stop surface to form a contact with a contact surface of another vane to define a minimum flow distance between the vane and the other vane. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: The present invention provides an electrical raft comprising a rigid material having multiple electrical conductors embedded therein. The electrical raft comprises an electrical connector having a first set of electrical contacts connected to at least one of the electrical conductors, a second set of electrical contacts for electrical connection to another component, and a housing having a first end and a second end. The first set of electrical contacts is at the first end and the second set of electrical contacts is at the second end. The first end of the housing is at least partly embedded in the rigid material, and the second end of the housing is accessible from outside the electrical raft, allowing the electrical raft to be electrically connected to said other component. The electrical connector has a back-shell which sealingly encloses the first end of the housing to prevent ingress of contaminants into the connector.

Abstract: An arrangement of components (12, 13, 30) for a wind power plant. A first component (12, 13) has a flange (15, 130) having a flange contact surface (121, 122, 133). A second component (30) has a flange-mounting surface (131, 132) for a flange (15, 130) of the first component (12, 13). Alternatively, the second component (12, 13) has a flange (15, 130) having a flange contact surface (122, 133) and the flange contact surface (122, 133) of the first component (12, 13) and the flange-mounting surface (131, 132) of the second component (30) are arranged opposite each other, or the flange contact surfaces (122, 121) of the components are arranged opposite each other. At least one flange contact surface (121, 122, 133) of a flange (15, 130) and/or the flange-mounting surface (131, 132) of the second component (30) has an outer coating made of a chrome-steel alloy.

Abstract: A device for detecting breaks in a diaphragm of a hydraulically-actuated pump includes a body (21) in which a first chamber (22) is formed, a duct (23) connecting the first chamber to a second end of the body, a check valve (24) arranged in the duct to pass fluid from the second end towards the first chamber, a piston (26) having a first portion (27) that co-operates in sealed manner with the first chamber and that has a hole passing therethrough of diameter greater than the diameter of a free ball (25) of the check valve, and a second portion (33) that is suitable for co-operating in sealed manner with the first portion to form a closed end of the piston. A method of mounting such a device on a pump, and a pump fitted with such a device, are also provided.

Abstract: A method of constructing a bedplate assembly for retention of a crankshaft in an internal combustion engine having an engine block includes forming a bedplate insert in a first pattern tool. The bedplate insert is defined by a height, a width, and a thickness. The bedplate insert also includes a shape having a variation in the width along the height. The method also includes arranging the formed bedplate insert in a second pattern tool. The method additionally includes forming in the second pattern tool a bedplate frame around the formed bedplate insert to generate the bedplate assembly. During forming of the bedplate frame, the variation in the width of the bedplate insert generates an internal rib in the bedplate frame that is configured to fix and retain the bedplate insert inside the bedplate frame and decrease deflection of the bedplate frame under crankshaft loads during operation of the engine.

Abstract: A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes a second mount feature that cooperates with the first mount feature for transferring torque there between. A method of disassembling a front architecture of a gas turbine engine includes the steps of accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon, removing the fasteners, and decoupling first and second mount features respectively provided on the central body support and the flex support.

Abstract: A transition nozzle for use with a turbine assembly is provided. The transition nozzle includes a liner defining a combustion chamber therein, a wrapper circumscribing the liner such that a cooling duct is defined between the wrapper and the liner, a cooling fluid inlet configured to supply a cooling fluid to the cooling duct, and a plurality of ribs coupled between the liner and the wrapper such that a plurality of cooling channels are defined in the cooling duct.

Abstract: Embodiments of the invention provide a hybrid drive system including a power source. The hybrid drive system can include a hydraulic system operatively coupled to the power source. The hydraulic system can include at least one hydraulic module coupled to the power source and at least one accumulator fluidly coupled to the hydraulic module. The drive system can include at least one drive wheel operatively coupled to the hydraulic system. The drive wheel can be configured and arranged to receive power only from the hydraulic system. The hydraulic system can be configured and arranged to supplement power provided by the power source to the drive wheel. The hybrid drive system can include an electronic control unit in communication with the power source, the hydraulic module, and a sensor associated with the accumulator.

Abstract: A damped torsional coupling is utilized to couple a drive shaft to a work shaft while permitting some relative rotation due to torsional vibrations. The coupling includes a second coupler oriented to rotate with respect to a first coupler about an axis through a continuum of negative to positive torque orientations. The first coupler defines a fluted perimeter surface with a number of flutes, distributed with radial symmetry about the axis. The second coupler a number of pistons reciprocally received in respective barrels to define a variable volume chamber fluidly connected to a damping passage. A spring biases the pistons and barrels to extend toward a position in contact with one of the flutes. The contact end may be an edge of a roller that rolls on the fluted perimeter surface in one of the flutes responsive to torques transmitted between the couplers.

Abstract: A hydraulic brake apparatus, a movable barrier apparatus, a hydraulic brake kit, a method of stopping movement of a movable barrier, and a method installing a hydraulic brake assembly are described herein. A selectively operable piston mechanism converts rotation of a drive shaft of a movable barrier into hydraulic pressure used to operate a brake configured to stop movement of the drive shaft.

Abstract: An exemplary component manufacturing method includes scanning a first surface of a component to determine a location of pocket surfaces of the first surface. The method machines apertures in the component from a second, opposite surface of the component. The apertures each have a cooling air inlet within one of the pocket surfaces and a cooling air outlet within the first surface.

Abstract: A method of fabricating a turbine engine drum including at least two rotor disks, the method including: positioning the two disks on a common axis spaced apart from each other and in a predetermined angular position relative to each other; placing a wall forming a body of revolution between the two disks coaxially about their common axis; driving the wall in rotation about its axis; and moving the disks axially towards the wall so as to put the disks into contact with ends of the wall and thus welding the disks to the wall by inertial friction welding.

Abstract: A gas turbine article includes a substrate and a thermally insulating topcoat disposed on a surface of the substrate. The surface of the substrate includes a surface pattern defining first surface regions and second surface regions. The first surface regions include incubation sites that are favorable for deposition of the thermally insulating topcoat and the second surface regions are less favorable for deposition of the topcoat. The topcoat includes segmented portions that are separated by faults extending through the topcoat from the second regions.

Abstract: A centrifugal impeller includes a hub and a plurality of impeller blades extending from the hub. Each impeller blade extends over a chord length between a leading end and a trailing end, over a span from a root at the hub to a tip end and over a thickness between a convex side and a concave side. The blades collectively or individually have profiles that define a circumferential pitch (CP) with regard to a spacing distance between the leading ends of neighboring ones of the blades and blade angles at positions along the convex side of each blade between the leading end and the trailing end. The blades have a solidity value (S) defined as CD/CP that is less or equal to 1.0 and the blade angles (?) of each blade increase from the respective leading end to the corresponding trailing end.

Abstract: An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

Abstract: The invention relates to a casing, particularly of an axial turbomachine compressor. This casing comprises a support of cylindrical overall shape made of composite material, a metal ring fitted by bonding to the internal surface of the support, and a layer of abradable material fitted by plasma spray onto the internal surface of the metal ring. The metal ring is preferably made of stainless steel and is preferably perforated. The perforation allows better keying of the adhesive and allows the degassing thereof. The external surface of the metal ring is preferably sandblasted prior to bonding. Its internal surface is also preferably sandblasted prior to the plasma spraying of the abradable material.

Abstract: A retractable exhaust liner segment between a gas turbine engine and an exhaust duct.

Abstract: A bearing assembly for a gas turbine engine includes a bearing, an outer assembly disposed about an axis and having an angled perimeter, and an inner assembly supporting the bearing and having a surface angled to slide against and attach to the angled perimeter as the bearing is aligned with the axis.

Abstract: A fuel nozzle for use with a turbine engine is described herein. The fuel nozzle includes a housing that is coupled to a combustor liner defining a combustion chamber. The housing includes an endwall that at least partially defines the combustion chamber. A plurality of mixing tubes extends through the housing for channeling fuel to the combustion chamber. Each mixing tube of the plurality of mixing tubes includes an inner surface that extends between an inlet portion and an outlet portion. The outlet portion is oriented adjacent the housing endwall. At least one of the plurality of mixing tubes includes a plurality of projections that extend outwardly from the outlet portion. Adjacent projections are spaced a circumferential distance apart such that a groove is defined between each pair of circumferentially-apart projections to facilitate enhanced mixing of fuel in the combustion chamber.

Abstract: A turbomachine includes an inner casing component having a first end that extends to a second end and a seal member. An outer casing component is coupled to the inner casing component. The annular outer casing component includes a first end portion that extends to a second end portion and a seal element that aligns with the seal member of the annular inner casing component to form a seal passage. A seal is arranged in the seal passage. The seal includes a first end section that extends to a second end section through an intermediate zone. The first end section includes a recessed portion and the second end section includes a connecting portion. The connecting portion is configured and disposed to nest within the recessed portion to form a substantially continuous seal.

Abstract: A heat recovery steam generator uses heat energy extracted from the exhaust gas of a gas turbine to produce steam. The steam is provided to steam turbines of a combined cycle power plant. Intermediate pressure steam generated by an intermediate pressure evaporator is routed to first and second intermediate pressure superheaters. Also, steam exhausted from a high pressure steam turbine of a combined cycle power plant is reheated by first and second reheaters within the heat recovery steam generator. The steam output by the intermediate pressure superheaters is provided to an interstage admission port of an intermediate pressure steam turbine, and steam output by the first and second reheaters is provided as the main input steam for the intermediate pressure steam turbine of the combined cycle power plant.

Abstract: A plunger installation tool that exerts a force on a plunger for a reciprocating pump to install the plunger into a pump cylinder opening. Maintenance of the pump typically includes repacking of the packing that surrounds the plunger and revalving of the pump's inlet and outlet valve. To allow repacking or revalving, the pump is disassembled and the plunger is removed. The plunger installation tool threads onto the pump cylinder opening to provide a reaction point for a threaded rod that is driven at one end by a driver and engages the plunger at an opposite end during installation to push the plunger into the cylinder opening without the use of hammers by personnel.

Abstract: An aero-derivative can annular gas turbine engine having: an aero gas turbine engine core including an aero high pressure compressor (65) interconnected with an aero high pressure turbine (73) by an aero high pressure shaft (142) in a geometric arrangement appropriate for association with an aero annular combustor (84), but with the aero annular combustor (84) and a first row of turbine vanes (38) of the aero high pressure turbine (73) absent; and a can annular combustor assembly (122) assembled with the aero gas turbine engine core and configured to receive compressed air from the aero high pressure compressor (65) and to accelerate and orient combustion gasses directly onto a first row of blades of the aero high pressure turbine (73).

Abstract: A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.

Abstract: A system for repairing holes in a turbine engine component is provided. The system includes a turbine engine component including a front surface, a back surface, and a tapered surface extending from the front surface to the back surface, the tapered surface circumscribing the hole. The system further includes a plug configured to be welded to the turbine engine component, the plug including at least one tapered portion configured to contact the tapered surface when the plug is welded to the turbine engine component, and a die plate positioned on the back surface of the turbine engine component and including an aperture defined therethrough that is configured to collect flash generated when the plug is welded to the turbine engine component.

Abstract: A plate plunger 17 that determines a servo ratio SR of a vacuum booster 1 pertaining to the present invention has, on a corner portion between its outer peripheral surface and its surface that opposes a reaction disc 16, a servo ratio determination surface 17c that is formed by an inclined surface and determines the servo ratio. The servo ratio determination surface 17c comprises a reaction disc contact surface 17f that determines the servo ratio and a reaction disc non-contact surface 17g. Additionally, a variety of different servo ratios are obtained by performing secondary processing such as cutting or grinding on just the servo ratio determination surface 170 to change the outer peripheral diameter of the reaction disc contact surface 17f.

Abstract: A combustion liner for a combustor of a turbine engine includes a plurality of undulations which extend around the exterior circumference of the combustion liner. A plurality of rows of cooling holes are formed through the combustion liner. Each row of cooling holes is located in one of the undulations which extends around the exterior circumference of the combustion liner. The cooling holes admit a flow of cooling air into the interior of the combustion liner. The cooling holes are located and oriented to help the flow of cooling air form a film along the inner surface of the combustion liner.