Abstract: A pump assembly includes a manifold having an inlet port configured to be coupled to a supply pipe and an outlet port configured to be coupled to a discharge pipe. The pump assembly also includes a cartridge having a pump stack including a plurality of pumping stages. Each pumping stage includes an impeller. The cartridge extends between a first end and a second end. The first end is removably coupled to the manifold. A carrier assembly supports the cartridge. The carrier assembly moves the cartridge between an advanced position and a retracted position. The cartridge engages the manifold in the advanced position and the cartridge is disengaged from the manifold in the retracted position. Optionally, the carrier assembly may include a support frame and at least one rail. The support frame is slidable along the rail and the cartridge is supported by the support frame.

Abstract: A method for supplying a plurality of capacitance values to a plurality of heating, ventilation, air-conditioning, and refrigeration (HVAC/R) components is provided. The method includes configuring a first set of terminals of a connection device to couple a first capacitor to the connection device and configuring the connection device to couple the first capacitor to at least one of the plurality of HVAC/R components. The method further includes configuring a second set of terminals of the connection device to couple a second capacitor to the connection device and configuring the connection device to selectively couple the second capacitor to at least one of the plurality of HVAC/R components.

Abstract: A gasoline pump apparatus comprises one or more pump nozzles, a sensor configured to detect nozzle removal from and replacement to a nozzle storage bay, and a first housing enclosing at least some gas dispensing apparatus. In addition, a second housing encloses at least one video display and at least one video display controller. The at least one video display controller is coupled to the sensor such that the video display output changes with changes in nozzle position. In some embodiments, the second housing is configured to be explosion proof.

Abstract: A multistage pump assembly includes a manifold having an inlet port configured to be coupled to a supply pipe and an outlet port configured to be coupled to a discharge pipe. The inlet and outlet ports define an end suction, radial outlet port configuration. The pump assembly also includes a cartridge having a sleeve and plurality of pumping stages that define a pump stack received within the sleeve. An outer chamber is defined between the pump stack and the sleeve. Each of the pumping stages includes an impeller mounted along a pump shaft that rotates about a rotation axis. The cartridge is aligned horizontally such that the rotation axis is substantially horizontal. An end plate is positioned between the manifold and the cartridge and includes at least one cartridge engagement surface supporting the cartridge. The end plate is removably coupled to the manifold.

Abstract: Embodiments of the invention provide an impeller assembly having a flexible impeller and a method of replacing a removable drive mechanism. The impeller assembly includes an impeller having an outer portion defining a substantially cylindrical shape, at least one flexible blade extending radially outward from the outer portion, and a first bore extending a first axial length. The impeller assembly also includes a tubular insert supported at least partially within the first bore. The tubular insert has a second bore defining a substantially cylindrical shape with a first radial distance from an axis passing through the center of the impeller, and a key portion radially extending from the second bore. The key portion defines a second radial distance from the axis larger than the first radial distance.

Abstract: Embodiments of the invention can provide methods and apparatus to repair a rotor disk for a gas turbine. In one embodiment, a method to repair a rotor disk for a gas turbine is provided, wherein the rotor disk can include a base and at least one dovetail slot between a pair of dovetail walls. The method can include identifying one or more cracks on the base of the rotor disk, and removing one or more cracks by providing one or more fillets on the base of the rotor disk. Further, the method can include providing one or more conic cuts on the base of the rotor disk between the pair of dovetail walls of at least one dovetail slot.

Abstract: A method for peening a component of a gas turbine engine, or a module of a gas turbine engine, without removing the component from the assembled gas turbine engine or module includes blending the damaged area of the component, determining parameters for peening the damaged component, and peening the damaged component without removing it from the engine.

Abstract: A method and apparatus for removing cracks on a gas turbine engine component includes mounting a first pivotable tool to a base, mounting a second pivotable tool to the first pivotable tool, and mounting a fixture holding the gas turbine engine component to the second pivotable tool. The first pivotable tool and the second pivotable tool are adjusted to position the gas turbine engine component in a desired orientation. A linear tool is then moved along an axis to machine at least one crack from a surface of the gas turbine engine component.

Abstract: Methods for repairing the gas turbine engine components are provided. In this regard, a representative method includes: determining the presence of a previous repair to a component; determining a characteristic of the previous repair using X-ray fluorescence analysis; and repairing the component.

Abstract: A compressor has first and second enmeshed rotors: rotating about first and second axes. The first rotor is supported by a bearing system carried by a bearing case. The bearing case has at least a first port to a discharge plenum. A first sound-absorbing material is positioned within the first port.

Abstract: A method for repairing a shroud segment of a gas turbine, in particular of an aircraft engine, having the steps: a) provision of a shroud segment to be repaired; b) removal of a damaged radially inner section of the shroud segment, so that after the removal of the damaged section the shroud segment has an inner radius; c) manufacture of a replacement section for the shroud segment, the replacement section having an outer radius matched to the inner radius of the shroud segment; d) alignment of the replacement section and the shroud segment; and e) joining of the replacement section to the shroud segment, the replacement section and the shroud segment being first welded to one another for this purpose at their edges in gas-tight fashion in a vacuum, and the surfaces of the replacement section and the shroud segment being subsequently diffusion-bonded to one another by hot isostatic pressing.

Abstract: A static gas turbine component includes an inner and an outer annular support member and a plurality of circumferentially spaced radial struts arranged between the support members for transmitting structural loads. Each of a plurality of the struts includes a load carrying core rigidly fixed to both the inner and the outer support member forming a unitary carcass with the support members, an impact resistant shell surrounding the core, and an energy absorbing material arranged between the core and the shell.

Abstract: A method of repairing an airfoil for a gas turbine engine includes removing a damaged portion of the airfoil at a radially outward tip of the airfoil, securing temporarily a portion of a ceramic core stub within an internal cavity of the airfoil, applying new metallic material to the airfoil covering an exposed portion of the ceramic core stub, machining the airfoil to remove an excess portion of the new metallic material, and removing the ceramic core stub from the internal cavity of the airfoil.

Abstract: A collar assembly for inclusion with, or for a retrofit of, a chemical injection pump and method for manufacturing same. The collar assembly secures to a thrust rod of the chemical injection pump and may include a circular member having a central opening and a second opening offset from the central opening. The second opening receives a central portion of a continuous U-shaped member, wherein fingerlike extensions at opposite ends of the U-shaped member flank a toggle element of a switching mechanism. The fingerlike extensions actuate the toggle element so as to stroke the chemical injection pump. The collar assembly includes a reduced number of parts and a simplified manufacturing process.

Abstract: A method of manufacturing an electrical suction unit for use in a vacuum cleaner includes a turbine unit and an electrical motor with a rotor and a stator. The turbine unit is attached to the rotor and forms, together with the rotor, a rotatable part of the suction unit, which is rotatable about an axis of rotation. An amount of material is removed from the rotor and from the turbine unit to torque-balance the rotatable part of the suction unit. In this manner, the amount of material to be removed from the rotor to torque-balance the rotatable part is considerably reduced, so that the adverse influence of the removal of the material from the rotor on the performance of the electrical motor is limited.

Abstract: An apparatus and method are provided for an adaptive machining and weld repair process for repairing airfoils, damage to an airfoil leading edge and tip. First, damaged material is machined away from a damaged airfoil edge so as to expose a weld surface. New material is laser deposited on the weld surface so as to create a weld-repaired airfoil having actual dimensions. The actual dimensions of the weld-repaired airfoil are automatically measured using a CMM system so as to generate an actual geometry. The actual geometry is deformed so as to develop a deformation geometry. The component is then machined according to the deformation geometry.

Abstract: A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator vanes extend between the rotor blades of axially adjacent disks. A knife edge seal segment is supported by each disk backbone extending from the disks and contacts the stator vanes to restrict leakage of compressed air from between the stator vane and the compressor rotor to limit the recirculation of air. Retaining flanges extend from each disk rim to retain the knife edge seal segments to the disk backbone and spacer bridges integral to the knife edge seal segments prevent axial movement of the knife edge seal segments. A plurality of lock assemblies are spaced about the circumference of the disk backbone to prevent circumferential shifting and rotating of the knife edge seal segments during operation.

Abstract: A starter for moving a movable portion of an engine to start the engine includes a gear housing, a gear assembly within the gear housing, an output member at a first end of the gear assembly adapted to operably couple to the movable portion of the engine, a motor housing, and a rotor rotatably mounted within the motor housing. The rotor has a shaft portion and a vane portion that are an integral, unitary piece. The shaft portion has splines for mating with the gear assembly. The splines prevent relative rotational movement between the rotor and the gear assembly and permit relative axial movement. The rotor is formed from aluminum and at least a portion of the rotor includes an anodized coating.

Abstract: A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.

Abstract: A method of repairing a nozzle segment is provided. The nozzle segment includes at least one airfoil extending between an inner band and an outer band, and the airfoil includes a first sidewall and an opposing second sidewall that are joined together at a leading edge and at an axially-spaced trailing edge. The method includes identifying a damaged portion of the airfoil, repairing the damaged portion of the airfoil by at least one of welding weld filler in the area of the damaged portion of the airfoil, and brazing preform in the area of the damaged portion of the airfoil, and blending at least one of the weld filler and the preform to remove excess material to facilitate finishing an outer surface of the airfoil.

Abstract: A compressor apparatus having a check valve (70) having a first condition permitting downstream flow along the flowpath and a second condition blocking a reverse flow. The valve element includes a resonator (112).

Abstract: A compressor includes a housing and one or more working elements. A muffler is located downstream of the discharge plenum and a helmholtz resonator is located in the discharge plenum upstream of the muffler.

Abstract: A method for modifying a multistage compressor (101) involves exchanging the rotor blades of the first compressor rotor blade row (LA1) for modified rotor blades which have an identical blade leaf profile (121) to the original rotor blades and the blade angle (B?11) of which is different from the blade angle (B?10) of the original rotor blades. Furthermore, the blades of at least one further blade row (LAN, LEN) arranged downstream of the second compressor stage are exchanged for modified blades which have an identical blade leaf profile (125, 126) to the original blades and the blade angle (B?N1, B?N1) of which is different from the blade angle (B?NO, B?NO) of the original blades. The method makes it possible to increase the mass flow of a compressor and essentially maintain the stability reserve against stall.

Abstract: A method for making a replacement panel for repairing a liner for a gas turbine engine combustor, the combustor having a combustion zone formed by inner and outer liners, the method comprising the steps of forming a panel from a sheet of material suitable for use in a combustor liner, forming at least one opening in the sheet of material, and applying a thermal barrier material to the replacement panel adjacent to the opening.

Abstract: Disclosed herein is a method comprising creating a weld pool using a laser; wherein the weld pool is created on a part of a turbine; and wherein the weld pool comprises molten metal or ceramic derived as a result of a heat interaction between the laser and the part of the turbine; adding a metal or a ceramic powder or a wire filler to the melt pool; and modifying the part of the turbine in a manner that results in a change of about 0.005 to about 50 volume percent in the part of the turbine, while improving the aerodynamic efficiency of the turbine in an amount of about 0.1 to about 5 percent over a corresponding unmodified turbine.

Abstract: A screw compressor (20) has compressor lubrication network having a lubricant outlet port (242) along a low pressure cusp (244). An unloading slide valve element (102) may be along a high pressure cusp (105).

Abstract: A collar assembly for inclusion with, or for a retrofit of, a chemical injection pump and method for manufacturing same. The collar assembly secures to a thrust rod of the chemical injection pump and may include a circular member having a central opening and a second opening offset from the central opening. The second opening receives a central portion of a continuous U-shaped member, wherein fingerlike extensions at opposite ends of the U-shaped member flank a toggle element of a switching mechanism. The fingerlike extensions actuate the toggle element so as to stroke the chemical injection pump. The collar assembly includes a reduced number of parts and a simplified manufacturing process.

Abstract: A method is provided for repairing a driven compressor housing including a bore having an inner surface configured to engage a shaft-mounted knife seal. The method includes the steps of removing material from the bore inner surface, press-fitting a sleeve into the bore, and plasma-spraying an abradable coating onto the bore inner surface.

Abstract: A method and apparatus are provided for adjusting an impeller in a motor and impeller assembly of a pumping device.

Abstract: A compressor has a housing assembly and at least one rotor held by the housing assembly for rotation about a rotor axis. The rotor has a first face and a first housing element has a second face in facing spaced-apart relation to the first face of the rotor. One or more spacer elements are positioned from the first housing element. The spacer elements are machined. A coating is applied over the first surface around the one or more spacer elements.

Abstract: Stator blade counts of an upper compressor casing for adjacent stages S0 and S1 are changed in the field to provide additional stator vanes and hence an increased vane count. Particularly, the upper casing half of the compressor is removed from the lower casing half. The original stator vanes on opposite axial sides of the first stage buckets are removed from the upper casing half and replaced by an additional sets of stator vanes providing a non-uniform vane spacing as between the upper and lower halves of the compressor as well as between axially adjacent stages S0 and S1. The unequal vane counts reduce the vibratory response of the rotating blades between stages S0 and S1.

Abstract: A method of manufacturing a linear compressor includes measures to account for possible variations in manufacture of the spring connecting between a cylinder part and a piston part. In the method, the piston is located at a predetermined axial position in the bore of the cylinder of the compressor. A spring that is connected with the cylinder part is extended so that a piston connection point of the spring is at a position based on a predetermined displacement of the spring or a position in which the spring exerts a predetermined reaction force. In this position, this piston and the spring connection point are thus separated by a distance that depends on the actual formed dimension of the individual spring. The piston and the piston connection point are subsequently joined to have a rigid axial separation that is fixed according to the separation attained in these steps.

Abstract: A compressor has a housing. One or more working elements cooperate with the housing to define a compression path between suction and discharge locations. An intermediate port is located along the compression path. A branch path extends to the intermediate port. The compressor includes means for limiting pressure pulsations along the branch path.

Abstract: A component assembly is provided for converting a conventional centrifugal pump, of the vortex impeller type for example, to a different type of centrifugal pump, such as a spiral impeller pump. The component assembly enables a resident centrifugal pump to be converted to a more efficient or appropriate type of industrial pump when conditions or application processing requirements change, and avoids the need to entirely replace an installed pump for a new type of pump.

Abstract: A process, apparatus, and kit for horizontally assembling a cryogenic pump with an apparatus generally including a workstand, a plurality of support stands longitudinally spaced apart from the workstand and a roller transport structure. The kit includes the apparatus and a beam crane for attachment to the apparatus for assembling and disassembling the cryogenic pump at the point of use.

Abstract: Methods and apparatuses for aligning the component parts of a drum assembly are disclosed. One aspect of the invention relates to tools for measuring and aligning the component parts of the drum assembly. By way of example, the tools may include indicator tools for measuring the relative position of the component parts, as well as alignment tools for aligning the component parts in accordance with the measurements. Another aspect of the invention relates to methods of measuring and aligning the component parts of the drum assembly. By way of example, some methods may pertain to aligning the upper drum and/or the drum support of the drum assembly.

Abstract: A slurry pump includes a power frame as well as a wet end, and the wet end comprises a casing, an impeller and wear ring in the casing, a stub shaft connected to the impeller, a sleeve assembly for the stub shaft and an adapter for adjusting the wet end to the power frame. The wet end can be attached to and detached from the power frame as a module.

Abstract: A method is provided for repairing a driven compressor housing including a bore having an inner surface configured to engage a shaft-mounted knife seal. The method includes the steps of removing material from the bore inner surface, press-fitting a sleeve into the bore, and plasma-spraying an abradable coating onto the bore inner surface.

Abstract: A bearing assembly (20) for a pump (12), e.g., an internal or external gear pump includes a journal bearing block (20) having a length, a width, and an axial centerline (CL?) passing through a center of the journal bearing block (20) with respect to the length. The journal bearing block (20) includes at least two journal bearing bores (21), the journal bearing bores (21) each having a center (C), wherein a bearing bore centerline (CL) extends between the centers (C) of the journal bearing bores (21) and in parallel with the bearing bore centerline (CL). The bearing bore centerline (CL) is offset with respect to the width of the journal bearing block (20) and the axial centerline (CL?). The bearing assembly (20) is particularly applicable to gear pumps, such as external gear pumps for fuel applications.

Abstract: A water pump having a housing with an opening defined by an axial inner retention surface and a radial outer surface. A plug formed of sheet metal includes a radial closure portion surrounded by a continuous axial flange adapted to be press fitted into the inner retention surface of the housing. Before assembly, an adhesive is applied to either the axial flange of the plug or the inner retention surface of the housing. The plug is then pressed into the housing so that the flange of the plug engages the inner retention surface of the housing. After the adhesive sets, a water tight seal is formed between the plug and the housing adequate to hold pressurized coolant within the housing of the water pump.

Abstract: A device and a process for mounting the rotor of a hermetic compressor, said device comprising a pulling rod (40), which is loosely and coaxially provided through the rotor (30) of the electric motor of the compressor, in order to have a first end coupled to an end of the crankshaft (10) located adjacent to an end face of the rotor (30), and a second opposite end to be seated against an opposite end face of the rotor (30) and to which a driving means (DM) is engaged to move the pulling rod (40), in order to provoke a relative axial displacement of the crankshaft (10), sufficient to fit, by mechanical interference, the extension (11) of the crankshaft (10) inside the rotor (30).

Abstract: A method of attaching a rotor to a shaft is provided to obtain increased motor performance. The increased motor performance is obtained as a result of a high impedance gap that is formed between the rotor bars and the rotor core during the heat shrinking operation to attach the rotor to a shaft. In the heat shrinking operation, the rotor is heated to between 600-800° F. At this temperature the aluminum in the rotor bars expands faster than the steel in the rotor core and causes a deforming or yielding of one or both of the materials. As a result of this deformation of the material, the cooling of the rotor results in the formation of a gap between the rotor bars and the rotor core that operates as a high impedance barrier between the rotor bars and rotor core.

Abstract: A compressor has a housing assembly and at least one rotor held by the housing assembly for rotation about a rotor axis. The rotor has a first face and a first housing element has a second face in facing spaced-apart relation to the first face of the rotor. The housing has a coating on the second face and a plurality of inserts protruding from the second face into the coating.

Abstract: A bearing assembly (20) for a pump (12), e.g., an internal or external gear pump includes a journal bearing block (20) having a length, a width, and an axial centerline (CL′) passing through a center of the journal bearing block (20) with respect to the length. The journal bearing block (20) includes at least two journal bearing bores (21), the journal bearing bores (21) each having a center (C), wherein a bearing bore centerline (CL) extends between the centers (C) of the journal bearing bores (21) and in parallel with the bearing bore centerline (CL). The bearing bore centerline (CL) is offset with respect to the width of the journal bearing block (20) and the axial centerline (CL′). The bearing assembly (20) is particularly applicable to gear pumps, such as external gear pumps for fuel applications.

Abstract: A first steam turbine of a reaction stage design is retrofitted to form a second turbine of a substantially impulse stage design using common components with the first turbine. To retrofit the new steam path into the first turbine, the upper outer and inner shells and rotor of the first turbine are removed leaving the lower outer shell. A lower carrier section is installed in the lower outer shell. A lower inner shell forming part of the new steam path is installed on the lower carrier ring. The rotor forming part of the new steam path is installed. The upper inner shell is bolted to the lower inner shell encompassing the rotor and an upper carrier section is bolted to the lower carrier section. Finally, the upper outer shell is bolted to the lower outer shell. Consequently a new steam path of reduced diameter is retrofitted into a prior turbine using the prior turbines outer shell.

Abstract: The apparatus includes a track mounted in the inlet of a compressor. A manipulator is mounted for movement about the track and carries three modules, the last of which mounts a tool head for movement in a Cartesian coordinate system and about the track. A measuring head measures the location of the airfoil surface. An abrading tool mounted on the third module removes surface material from the airfoil. Subsequently, a shot-peening device, either a flapper with embedded shot or free shot is impacted against the abraded surface to strengthen the surface. Final inspection is performed by a light and camera head mounted on the third module.

Abstract: A seal is provided for controlling flow of a fluid in a fluid path in a rotary machine. The seal comprises a brush seal carrier having a front plate and a back plate disposed therein. A brush seal is disposed between the front plate and the back plate. In addition, a flexible member is disposed between the brush seal and the back plate for reducing stress in the brush seal.

Abstract: A method of removing a sensing rod from a hydraulic water pump includes an access plug, a sealing o-ring, and an end block modified to receive the access plug. The access plug preferably includes a front flange, a threaded body, and a rear tapered end. An o-ring groove is formed adjacent the front flange to retain the sealing o-ring. An internal thread is preferably formed in the modified end block to threadably receive the access plug. An opening is formed through the length of the access plug which is sized to receive the sensing rod. The access plug is unthreaded to allow the sensing rod to be removed. A nut removal tool inserted through the internal threads of the modified end block to unscrew a rod nut. Once the rod nut has been unscrewed, the sensing rod may be removed.

Abstract: A device and a process for mounting the rotor of a hermetic compressor, said device comprising a pulling rod (40), which is loosely and coaxially provided through the rotor (30) of the electric motor of the compressor, in order to have a first end coupled to an end of the crankshaft (10) located adjacent to an end face of the rotor (30), and a second opposite end to be seated against an opposite end face of the rotor (30) and to which a driving means (DM) is engaged to move the pulling rod (40), in order to provoke a relative axial displacement of the crankshaft (10), sufficient to fit, by mechanical interference, the extension (11) of the crankshaft (10) inside the rotor (30).

Abstract: An existing water-lifting pump is converted into a reversible pump-turbine which functions as not only a water-lifting pump, but also a pump-turbine capable of generating electric power. An existing pump runner is modified or replaced with a replacement runner. Movable guide vanes are disposed, or the rotational speed of the runner is increased. Alternatively, water passages in the stationary parts are modified. A pumping station can be given with the function as an urgent power plant in the event of an electric power shortage. A converted pump-turbine having good pump-turbine characteristics can be economically obtained.