Abstract: This disclosure describes embodiments of a method of repairing a diaphragm found in a turbine, and a diaphragm assembly resulting from the same, that does not require welds in between the partitions. The method inserts a replacement part in place of certain machine-removed portions of the existing partitions on the diaphragm. The replacement part includes coupons that work in combination with the remaining portions of the partitions to form the aerodynamic shape of the original partitions.

Abstract: A method and system adapted for removing one or more shells from an assembly of multiple annular shells, for example, turbine shells of a gas turbine engine. The method includes removing an upper shell positioned in an upper position relative to a lower shell of the assembly of multiple annular shells, and then positioning and securing a counterweight in the upper position and securing the counterweight to the lower shell as a replacement for the upper shell in the upper position. The counterweight and the lower shell are then rotated in unison until the lower shell is in the upper position and the counterweight is in a lower position previously occupied by the lower shell. Thereafter, the lower shell can be removed from the assembly.

Abstract: A turbine repair process, a repaired coating, and a repaired turbine component are disclosed. The turbine repair process includes providing a turbine component having a higher-pressure region and a lower-pressure region, introducing particles into the higher-pressure region, and at least partially repairing an opening between the higher-pressure region and the lower-pressure region with at least one of the particles to form a repaired turbine component. The repaired coating includes a silicon material, a ceramic matrix composite material, and a repaired region having the silicon material deposited on and surrounded by the ceramic matrix composite material. The repaired turbine component a ceramic matrix composite layer and a repaired region having silicon material deposited on and surrounded by the ceramic matrix composite material.

Abstract: A remanufactured pump includes a casing and a pumping mechanism positioned within the casing having a rotatable pump shaft and an impeller mounted upon the pump shaft and rotatable within a pumping chamber in the casing. A first insert is held fast within a first bore in the casing, and a second insert is held fast within a second bore in the casing, each via an interference fit. Sealing mechanisms are positioned within the first and second inserts to form a first seal about the pump shaft to prevent leakage of a working fluid from the pumping chamber, and a second seal about the pump shaft to prevent leakage of a lubricating fluid from a bearing chamber in the casing. Related methodology is also disclosed.

Abstract: A thrust reverser system for a gas turbine engine includes a duct including a cowling movable between an open position and a closed position in a direction transverse to a centerline of the gas turbine engine. The thrust reverser is supported within the cowling and movable between an axial closed position, an axial intermediate position and an axial open position. A controller is actuateable to command movement of the thrust reverser from the axial closed position to the axial intermediate position such that the cowling is free to move to the open position.

Abstract: A compressor for a gas turbine having a rotor rotating about an axis and a housing coaxially surrounding the rotor, thereby defining a flow channel between the rotor and the housing for a fluid to be compressed. Alternating rows of vanes and blades are arranged within the flow channel, with the vanes being mounted in the inner wall of the housing, and the blades being mounted in the outer wall of the rotor.

Abstract: During the repair of welded two-stage or multi-stage compressor or turbine drums, which after welding are machined in the weld area down to a height A, a first material coating with a height B extending on both sides from the root face is applied to the machined weld area, and a second and lesser material coating is applied by laser welding to the area of plasma pockets formed on the intact rotor disk, with the sum of the heights A and B corresponding to an original height C in the weld area prior to its final machining. Then the defective rotor disk is detached in the root face and through the middle of the first material coating, and after that a new rotor disk already validated in the new construction with the root face validated in the new construction is welded on using appropriate welding parameters, and the weld area is machined, in line with the parameters already used for the new construction, down to the original height A.

Abstract: A turbine includes a rotor and a casing that circumferentially surrounds at least a portion of the rotor. The rotor and the casing at least partially define a gas path through the turbine. A last stage of rotating blades is circumferentially arranged around the rotor and includes a downstream swept portion radially outward from the rotor. A method for reducing shock losses in a turbine includes removing a last stage of rotating blades circumferentially arranged around a rotor and replacing the last stage of rotating blades with rotating blades having a downstream swept portion radially outward from the rotor.

Abstract: A longitudinally-split compressor case of a gas turbine engine is overhauled to inhibit leakage between case segments that have been distorted. Grooves are machined in mating surfaces of the case segments. Seal wires are located at the grooves.

Abstract: A terminal box cover for a ram air fan assembly includes a body defining a top wall having an outer surface. The body extends between a forward end and a rearward end. An opening is formed in a forward wall at the forward end. The opening allows electric supply feeders to move into an internal space defined by the cover when mounted on a terminal box base. The outer surface extends from the forward end to the rearward end such that the forward wall is thicker than a rear wall at the rearward end. The thickness is defined as a distance extending away from the top wall. A separator wall is defined extending from the inner surface. The separator wall extends from the front wall toward the rear wall, but is spaced from the rear wall. The separating wall has a curved inner lip at a rearwardmost end. In addition, a ram air fan assembly, a system including a heat exchanger, and a method of replacing a box cover are also described.

Abstract: A compressor guide-vane stage for a turbine engine, the stage comprising two coaxial shrouds, respectively an inner shroud (120) and an outer shroud, with vanes (124) extending between them, the radially inner ends of the vanes being engaged with clearance (125) in orifices in the inner shroud and being secured to the inner shroud by means of a polymerizable sealing resin (126), the guide-vane stage being characterized in that a gasket (140) is mounted on the radially inner end of each vane, the gasket including a slit through which the vane passes and bearing against the radially inside surface of the shroud or in the proximity of said surface, in order to limit the passage of resin through the above-mentioned clearance while the resin is being applied to the inside surface of the shroud.

Abstract: A turbine nozzle may be repaired by severing the inner band from the vanes and outer band, which may then be discarded. A replacement nozzle is cast to include replacement vanes extending between a replacement outer band and an inner web, with the replacement outer band and vanes conforming with the original outer band and vanes. The new web is configured differently than the old inner band and includes a tie bar. The inner band is machined to form vane seats. The web is machined to form plinths atop the tie bar at each of the replacement vanes. The plinths and tie bar are assembled through the vane seats and bonded to the machined inner band to collectively form the repaired turbine nozzle.

Abstract: An engine assembly comprising a cylinder head, turbocharger in fluid communication with the cylinder head and exhaust conduit in fluid communication with the turbocharger and method of making the assembly using a single human assembler includes: mounting the turbine to the cylinder head; using a first assembly aid to form a slidable joint between the exhaust conduit and head; using a second assembly aid to form a movable joint between the turbine and exhaust conduit and align the turbine outlet flange and exhaust conduit inlet flange; using a third assembly aid to pilotingly engage the flanges; disposing a clamp about the turbine outlet flange and the exhaust conduit inlet flange; tightening the second assembly aid sufficiently to form an immovable joint; tightening the clamp to form a sealed joint between the flanges; and tightening the first assembly aid to form a fixed joint.

Abstract: A surface pump assembly having a thrust chamber with a telescoping shaft. In some embodiments, the surface pump assembly has a pump with a pump shaft, a thrust chamber with a telescoping shaft extending therein, the telescoping shaft extendable to engage the pump shaft and retractable to disengage the pump shaft, and a motor coupled to the telescoping shaft and operable to rotate the telescoping shaft. In some embodiments, the telescoping shaft has a rotatable shaft member, an adjusting nut threadably disposed thereabout, wherein the adjusting nut is moveable axially relative to the shaft member by rotation, and a first sleeve translatably disposed about the shaft member.

Abstract: A seal for a pump includes a seal housing configured to be received in a housing of the pump and a seal assembly received in the seal housing. The seal further includes a seal holder receiving at least a portion of the seal assembly, the seal holder being configured to rotate with respect to the seal housing. The seal also includes a guide coupled to the seal housing and retaining the seal holder, such that the seal holder rotates with respect to the seal housing, wherein during operation of the pump, the seal holder and a portion of the seal assembly rotate. A pump includes the pump seal, and a method for refurbishing a pump seal includes removing and replacing at least a portion of a seal assembly of the pump seal, wherein refurbishing the pump seal does not require removing a pump shaft from the pump.

Abstract: A cryopump includes a housing, an electrical control unit which controls the cryopump, a purge valve provided on a passage between an external purge gas source and the inside of the housing, a rough valve provided on a passage between an external pump and the inside of the housing, a vent valve provided on a passage between the inside and the outside of the housing, and a Pirani gauge which measures a pressure inside the housing. The electrical control unit is connected to each of the purge valve, rough valve, vent valve, and Pirani gauge via a wire. Each of the wires is provided with a connector on the component side and a connector on the electrical control unit side. The connector on the component side is configured to be attachable to and detachable from the connector on the electrical control unit side.

Abstract: The present application provides a stage of a gas turbine engine. The stage may include a bucket, a shroud facing the bucket, and a forward step honeycomb seal on the shroud. The forward step honeycomb seal may include a forward step portion and one or more linear portions.

Abstract: A valve assembly in a reciprocating compressor used in oil and gas industry is provided. The valve assembly comprises an actuator configured to a valve actuating motion and a valve. The valve has a valve seat comprises an inlet port configured to allow a fluid to flow through the valve seat, a counter-seat comprising an outlet port configured to allow the fluid to flow through the counter-seat, and a valve closing member attached to the counter-seat and configured to cover the inlet port when the counter-seat is in a closed position. The counter-seat is configured to receive the valve actuating motion and to move between the closed position and an open position in which the valve closing member does not cover the inlet port thereby selectively allowing the fluid to flow on a flow path which comprises the inlet port and the outlet port.

Abstract: A gas turbine engine 10 is provided with rigid raft assemblies 290, which may be electrical harness raft assemblies 290 comprising electrical conductors embedded in a rigid composite material. The rigid raft assemblies 290 can be provided with engine dressings, such as pipework and ECUs to produce an electrical raft assembly. In order to assemble or dress the gas turbine engine 10, the rigid raft assemblies can be pre-prepared to incorporate at least a part of at least one gas turbine engine system/component before being installed on the gas turbine engine 10. During maintenance, whole raft assemblies can be removed and replaced with corresponding, pre-prepared assemblies. This can save considerable time during engine build and maintenance.

Abstract: A gas turbine engine 10 comprises at least one rigid raft assembly that has a fluid passageway 210 at least partially embedded therein. The fluid passageway 210 is at least a part of a fluid system. In addition to the fluid passageway 210, the rigid raft assembly 200 also has at least a part of another system. For example, the rigid raft assembly may also include electrical conductors 252, which are part of an electrical system. The rigid raft assembly 200 may be lighter, easier to assemble, more robust and more compact than conventional solutions for providing systems to gas turbine engines.

Abstract: An endcover for a turbine combustor adapted to support one or more combustor nozzles, includes a plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel cavity is formed in the plate; and a fuel restrictor insert is formed with at least one flow orifice located within the fuel cavity for supplying fuel to at least one combustor nozzle. The fuel restrictor insert is adjustable along a length dimension of the fuel cavity.

Abstract: Embodiments of the invention can provide systems and methods for adjusting clearances in a turbine. According to one embodiment, there is disclosed a turbine system. The system may include one or more turbine blades, a turbine casing encompassing the one or more turbine blades, a thermoelectric element disposed at least partially about the turbine casing, a cooling system in communication with the thermoelectric element, and a controller in communication with the cooling system and the thermoelectric element. The controller may be operable to control the expansion or contraction of the turbine casing by heating or cooling at least a portion of the turbine casing with the thermoelectric element and by adjusting the cooling system such that a clearance between the one or more turbine blades and the turbine casing is adjusted.

Abstract: A maintenance method of a gas turbine unit, having a first stator element provided with first connecting holes contemplates replacing a second stator element, provided with second connecting holes and connected to the first stator element by means of coupling pins insertable into the first and the second connecting holes, with a third spare stator element provided with third connecting holes; and coupling the first stator element to the third spare stator element by means of eccentric coupling pins and eccentric bushes, each of which is selectively insertable in the first and the third connecting holes.

Abstract: A pump has a pump fluid end and a manifold that is detachable from the fluid end. A device is attachable to the pump, and has a manifold support beam portion adapted to affix to the pump fluid end at a location adjacent a manifold mating surface of the pump fluid end and extend outward from the pump fluid end. A support is provided on the manifold support beam portion that, when the manifold support beam portion is affixed to the fluid end of the pump, engages the manifold detached from the fluid end and supports the weight of the manifold.

Abstract: A first valve head is selected for removal from a piston cylinder. The first valve head has been configured to house at least a one way intake valve assembly in an intake chamber of the head and at least a one way exhaust valve assembly in an exhaust chamber of the head. The intake and exhaust chambers are sealed off from each other. The first valve head is removed from the piston cylinder. A second valve head is selected. A bottom of the second valve head is removably coupled to the piston cylinder. A concentric two way valve is seated within the second valve head. The concentric valve is secured within said second valve head with a valve clamp having a top cover. The top cover is removably coupled to the second valve head.

Abstract: A cost effective method for revamping a low pressure distillate hydrotreating process unit to a high pressure distillate hydrotreating process unit. A high pressure hot-feed pump is added, the furnace is retubed for higher pressures, the low pressure reactor is replaced with a high pressure reactor, a high pressure let-down valve is added at the reactor outlet, and the low pressure recycle compressor is replaced with a high pressure recycle compressor.

Abstract: A quick disengaging field joint connects a first component of an exhaust system of a gas turbine engine to a second component of the exhaust system. The field joint includes a pair of opposed stepped liners connected via exterior-facing connecting flanges. The field joints can be disassembled entirely from outside the exhaust housing without requiring access to the interior of the exhaust housing.

Abstract: A method is provided for extending useful life of tubing of a peristaltic pump. The method can comprise switching inlet and discharge hoses between respective inlet and outlet ends of the tubing of the peristaltic pump, and reversing a direction of rotation of a rotor of the peristaltic pump. In implementations of methods disclosed herein, the useful life of the tubing of a peristaltic pump can be approximately doubled.

Abstract: Described is a power generating apparatus and a rotor locking method for the apparatus, which is capable of locking the rotor without using a huge braking mechanism. The power generating apparatus of renewable energy type includes a blade, a rotor including a hub and a main shaft, a hydraulic pump of variable displacement type driven by rotation of the rotor, a hydraulic motor driven by operating oil pressurized by the hydraulic pump, and a generator coupled to the hydraulic motor. The rotor locking method for the power generating apparatus may include the steps of: decelerating the rotor by adjusting a pitch angle of the blade: after the decelerating step, stopping the rotor by applying a braking force by the hydraulic pump to the rotor; and locking the rotor so that the rotor is immovable in a rotation direction.

Abstract: A compressor assembly having a tank seal which seals a tank gap between a portion of a housing of the compressor assembly and a portion of a compressed gas tank and a method for controlling the sound level of a compressor assembly by configuring a tank seal to seal a gap between the housing of a compressor assembly and a compressed gas tank. The sound level of the compressor assembly can be controlled by sealing a tank gap between at least a portion of a compressor assembly housing and at least a portion of a compressed gas tank.

Abstract: A pump body is pre-compressed by expanding a displacement plug in a cavity to pre-compress a portion of a pump body comprising a piston bore, an inlet bore and an outlet bore spaced from said cavity, and connected in a pump assembly. A fluid pump assembly is made up of a plurality of pump bodies connected side by side between opposing end plates with a plurality of fasteners tightened to compress the pump bodies between the end plates, wherein each pump body comprises a piston bore, an inlet bore, an outlet bore and an expanded displacement plug in a cavity; and wherein the expanded displacement plug applies a pre-compressive force at the cavity on each of the pump bodies.

Abstract: A retrofit kit for an emergency eyewash station and method of retrofitting a plumbed emergency eyewash station is disclosed. The kit includes a sterile eyewash fluid source. A pump assembly having an input port and an output port is also included. The input port is configured to connect to a dispensing structure of a plumbed eyewash station and the output port is configured to connect to the sterile eyewash fluid source. A drive assembly is configured to drive the pump assembly to draw sterile eyewash fluid from the sterile eyewash fluid source and discharge it through the dispensing structure of the plumbed eyewash station. The eyewash fluid discharged from the dispensing structure is configured to drain through a discharge of the plumbed eyewash station and away from the plumbed eyewash station.

Abstract: A jig and a method for modifying a casing in a turbine system are disclosed. The jig includes a body and a protrusion extending from the body. The protrusion is configured for engaging a hole defined in a spot face on the casing. The jig further includes at least one machining passage defined in the body, the machining passage provided for machining the casing therethrough, and at least one alignment feature configured on the body, the at least one alignment feature provided for aligning the jig with respect to the casing. The method includes engaging a jig with a hole defined in a spot face on the casing, aligning the jig with respect to the casing, and machining at least one installation hole into the casing through the spot face.

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for modifying a turbine casing. According to an example embodiment of the invention, a method is provided for modifying a turbine casing. The method can include providing one or more casing retention pin bores in the turbine casing; inserting a retention pin in the one or more casing retention pin bores; providing one or more patch ring segments configured to be radially constrained by at least a portion of the turbine casing and further configured to slide circumferentially in cooperation with at least a portion of the turbine casing, wherein the one or more patch ring segments comprise at least one retention pin locking bore; installing the one or more patch ring segments in the turbine casing to radially constrain the one or more patch ring segments; and engaging the retention pin in the at least one retention pin locking bore to circumferentially constrain the one or more patch ring segments to the turbine casing.

Abstract: A method of processing turbine airfoils includes depositing a protective coating on first and second turbine airfoils, and bonding the first and second turbine airfoils together after the deposition such that there is an open throat between the first and second turbine airfoil and at least portions of surfaces in the open throat are coated with the protective coating.

Abstract: A method for refurbishing wicket gates by applying a sheet material to at least a portion of the vane surface of the wicket gate, thus forming a new face. This sheet material may be applied by wrapping the sheet material around the vane surface. The method may further include applying sheet material to the end surfaces of the wicket vane. If end material is applied, it may be sealed to the sheet material of the vane surface.

Abstract: A method of repairing a damaged coated vane from a turbine module without removing the vane from the module is taught. The method includes locally removing the coating in the vicinity of the damage as well as any underlying damage in the superalloy substrate. A diffusible coating precursor is then applied to the damage site. A heat treating fixture is then mounted on the vane and repair site is heated to up to 2000° F. in an inert environment to interdiffuse the coating precursor and the substrate. After the diffusion anneal, the vane is cleaned and the module is returned to service.

Abstract: A suction pump coupler for replacement of the immersible one-way valve with the pump coupler securable to the inlet end of a suction pump for forming a leakproof connection to an intake pipe to enable use of the suction pump in a location wherein the suction pump is remote from the fluid being pumped with the pump coupler operable for securing an inlet pipe to the suction pump in a leakproof condition through rotational engagement of pump coupler with respect to the inlet pipe even with the presence of the suction pump cantileverly mounted thereon.

Abstract: The life of an actuator such as a turbocharger VTG actuator is extended by reducing heat conduction from the turbine housing along the control linkage to the actuator link and into the actuator, thereby protecting sensitive electronic components. To this end, the control linkage may be equipped with cooling fins, or be made hollow rather than solid, or be made of a thermal energy retarding material in order to retard heat from the turbine housing assembly reaching the actuator.

Abstract: A method of reducing the fluid flow effects of one or more flow modifiers (19) in a passage (16), the method comprising: providing a plurality of aerofoil structures (15) in the passage (16), wherein the geometry of each aerofoil structure (15) is initially substantially the same; and shortening the trailing edge (18) of one or more selected aerofoil structures (17) in a chordwise direction and over at least a spanwise portion of the one or more selected aerofoil structures such that, when in use, the direction of the fluid flow (20a, 20e) in the vicinity of the one or more selected aerofoil structures is altered and the fluid flow effects of the one or more flow modifiers (19) in the passage are reduced.

Abstract: A method for retrofitting a fossil-fueled power station having a multiple-casing steam turbine with a carbon dioxide separation device is provided. The maximum flow rate of the steam turbine is adjusted to the process steam that is to be removed for the operation of the carbon dioxide separation device and the carbon dioxide separation device is connected via a steam line to an overflow line that connects two steam turbine casings.

Abstract: A pump has a pump fluid end and a manifold that is detachable from the fluid end. A device is attachable to the pump, and has a manifold support beam portion adapted to affix to the pump fluid end at a location adjacent a manifold mating surface of the pump fluid end and extend outward from the pump fluid end. A support is provided on the manifold support beam portion that, when the manifold support beam portion is affixed to the fluid end of the pump, engages the manifold detached from the fluid end and supports the weight of the manifold.

Abstract: The invention relates to a gasket part for a pump to be used in conjunction with a bearing part (1) of the pump, through which there is arranged a drive shaft (2). According to the invention, the gasket part includes a mechanical gasket (7) and a detachable part (4) of the drive shaft, which detachable part is arranged substantially in conjunction with the bearing part (1) and can be detachably connected between the other parts (3, 5) of the drive shaft; the gasket (7) is arranged in conjunction with the detachable part (4) of the drive shaft; and the detachable part (4) of the drive shaft includes means (8) for arranging it so as to be compacted in the longitudinal direction. Moreover, the invention concerns a method for detaching the gasket part and use of the gasket part.

Abstract: An arrangement for the repair of BLISK blades damaged at their leading and trailing edges by use of laser deposition welding, includes a laser source and laser optics for generating a focused laser beam (26) and a powder line (35) connected to a powder reservoir for supplying metal powder to be melted by the laser beam to the weld area. A modular, tubularly elongated welding apparatus (7) with a connection module (13) which is connected to a laser source and in which the entering laser beam is deflected in longitudinal direction and parallelized, and to the one side of the connection module (13) is connected to a camera module for a CCD camera (12) enabling the precise positioning of the welding apparatus and the deposition of the molten metal powder on the respective blade to be monitored and controlled.

Abstract: A motor compressor system in which the motor is configured to activate the compressor. The system includes a common casing; a motor cartridge housing a motor, the motor cartridge detachably provided inside the common casing; and a compressor cartridge housing a compressor detachably connected to the motor, the compressor cartridge detachably provided inside the common casing.

Abstract: When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur since the load on rear stage side vanes of a compressor increases. An object of the present invention is to suppress the degradation of the aerodynamic performance and of reliability of an axial compressor. The axial compressor includes a rotor; a plurality of rotor blade rows installed on the rotor; a casing located outside of the rotor blade rows; a plurality of stator vane rows installed on the casing; and exit guide vanes installed on the downstream side of a final stage stator vane row among the stator vane rows. An incidence angle of a flow toward the final stage stator vane row is equal to or below a limit line of an incidence operating range.

Abstract: A method for reducing pulsation effects associated with the compressor nozzle of a positive displacement compressor system. A pulsation absorber, having a design like that of a side branch absorber, is installed on the cylinder valve cap or on the cylinder nozzle. The acoustic dimensions and placement of the pulsation absorber are designed to reduce the amplitude of the pulsations associated with the peak resonant frequency of the compressor nozzle response.

Abstract: A method for restoring the registry of opposed shafts that carry meshing pump teeth inside a polymer pump that contains polymer without removing polymer from within the pump, the method using an asymmetric pattern of apertures in the shaft ends and a template having a pattern of holes that matches the pattern of apertures, and dowels that closely fit the holes and apertures.

Abstract: A method of refurbishing a seal land on a transition piece of a turbomachine includes applying a wear strip to a wall surface of the seal land, and covering the wear strip with a slot protector.

Abstract: A method of assembling and repairing an internal-rotation type gear pump has a preparing step, a disassembling step, a taking step, a repairing step and an assembling step. The preparing step includes preparing an internal-rotation type gear pump with a bearing mount device, a gland-sealing device and a pump device with a casing, a side cover, a driven gear and a driving gear. The disassembling step includes disassembling the side cover from the casing and disassembling and separating the gears from the driving shaft. The taking step includes separating and taking the gland-sealing device from the casing. The repairing step includes repairing the mechanisms inside the internal-rotation type gear pump and replacing with a new one if one of the mechanisms is broken. The assembling step includes putting the gland-sealing device into the casing, assembling the driving gear on the driving shaft and assembling the side cover on the casing.