Abstract: A method and replacement detail for use in processing a stator vane for a rotary machine are disclosed. Various steps and construction details are developed which promote the ease of carrying out the process and improve the fatigue life of the processed stator vane. In one particular embodiment, a portion of the airfoil and the platform are removed in a region adjacent the leading edge of the airfoil and replaced with a replacement detail having new material at a location where cracks are known to form.

Abstract: A stator suitable for high-pressure compressors in gas turbine engines includes two points of ventilation at different temperatures. It is recommended that the upstream section of the stator be constructed with a casing and a shroud, both of which are unbroken around a circumference and made of a material with a low degree of thermal expansion. Downstream the shroud is, however, constructed using angular sectors in a material with a higher degree of thermal expansion.

Abstract: A light, cheap, and high-performance regenerative pump for pumping a methanol-water fuel of a fuel cell, which is adapted to the fuel. At least one of an impeller of the regenerative pump and an inner wall of the pump is made of polyphenylene sulfide or polyphenylene sulfide containing a filler. A thrust clearance formed between the pump chamber inner wall and an impeller peripheral face is set so as to be assured even in a state where the impeller swells.

Abstract: A frangible cover is provided for a recess in a containment case for turbofan engine blade removal and access. The recess provided in the containment case allows outward radial movement of the engine fan blade when the engine fan blade is to be removed from the containment case. The present invention proposes a frangible component to cover the recess. A plurality of initiation points, notched in the frangible cover at intersections of surfaces encourages brittle fracture of the frangible component.

Abstract: A steam turbine that passes more turbine driving steam by off-setting the turbine moving blade throat-pitch ratio before operation and, when a blade untwist is generated during operation, causing more turbine driving steam to flow by maintaining an appropriate value, and, at the same time causing the turbine moving blade throat-pitch ratio to swell by giving the blade untwisting angle to the blade cross-sections in regions where the aerodynamic loss is small. The steam turbine is one in which the throat-pitch ratio (S/T) distribution of a turbine moving blade is offset by forming a curve providing at least one minimal value and maximal value by giving blade twist angle to the blade cross-sections in the blade height direction from blade root to blade tip and, at the same time, the distribution of throat-pitch ratio (S/T) taking into consideration blade untwist generated during operation.

Abstract: Disclosed is a shaft system particularly adapted for use in molten metal applications, such as injecting impellers, submersible molten metal pumps, and others. Embodiments of the shaft system contemplated by this invention very generally including a base shaft with an outer surface, a shaft sleeve composed of material adapted to be used in a molten metal environment, the shaft sleeve having an inner surface approximately corresponding in size to the outer surface of the shaft and located approximately concentrically around the shaft; and a shaft coupler between the outer surface of the shaft and the inner surface of the shaft sleeve; wherein the shaft sleeve is securely attached to the shaft by the expansion of the shaft coupler relative to the shaft and the shaft sleeve.

Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular hook (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular hook (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade (34). The metal casing (40) has a containment portion (A) downstream of the annular hook (54) and substantially in the plane of the leading edge of the tip (37) of the fan blade (34). The containment portion (A) of the casing (40) has a greater diameter than the diameter of the casing (40) at the annular hook (54) to restrain upstream movement of a detached fan blade (34).

Abstract: A steam turbine includes a turbine high pressure section, a turbine intermediate pressure section and a turbine low pressure section, in which at least two or more of these pressure sections are combined together, and a turbine rotor which is subjected to a gradient thermal treatment at different thermal treating temperatures at respective pressure sections is rotatably supported by bearings and accommodated in a turbine casing, and in a case where an axial distance from a setting position of a turbine movable blade of a final stage of the turbine low pressure section to a setting position of a partition plate disposed at a time when the gradient thermal treatment is performed to each of the pressure sections at different thermal treating temperature is defined as A, a blade length of the turbine movable blade is defined as B, and an axial distance from a prior stage of the final stage of the turbine low pressure section to the setting position of the partition plate is defined as C, the setting position of t

Abstract: A fan case for a turbofan engine having a fan including plurality of fan blades mounted to a rotor disk and a decoupler that fails in response to a predetermined load includes a substantially annular shell. The shell has a forward section, an intermediate section, and an aft section. The fan case further includes an aft facing step formed at the forward end of the intermediate section to prevent blade fragments from being ejected forward. The intermediate section is axially aligned with the fan and has a large inside diameter. The intermediate section thus defines an annular space around the fan blades that is sufficiently large to allow the fan to orbit when the decoupler fails. The intermediate section and the aft section are aligned radially to allow blade fragments to be ejected aft, avoiding additional secondary blade damage.

Abstract: A compact steam turbine power-generation plant has a compact steam turbine that operates at a high temperature in a range of 600 to 660° C. Ferrite based heat resisting steels provide for thermal efficiency. The main steam temperature and the reheated steam temperature can be set in a range of 600 to 660° C. by making the main parts exposed to the high temperature atmosphere, such as the rotor shaft, from ferrite based forged steels and cast steels and by making a final stage blade of a low pressure turbine from a martensite steel. The final stage blade is made from a ferrite based forged steel having a tensile strength of 120 kgf/mm2 or more; the rotor shaft is made from a ferrite based forged steel having a 105 h creep rupture strength of 11 kgf/mm2 or more; and the inner casing is made from a ferrite based cast steel having a 105 h creep rupture strength of 10 kgf/mm2 or more.

Abstract: Apparatus for moving a stream of molten metal in a bath of molten metal, includes a pump disposed in the met. The pump has a lower inlet opening with a strainer and a slinger rib to prevent the entry of debris that exceeds a predetermined diameter from passing through the pump.

Abstract: A solid-solution strengthened superalloy weld composition, includes: about 10 to about 15 wt % Co; about 18 to about 22 wt % Cr; about 0.5 to about 1.3 wt % Al; about 3.5 to about 4.5 wt % Ta; about 1 to about 2 wt % Mo; about 13.5 to about 17.0 wt % W, up to about 0.08 wt % C; up to about 0.06 wt % Zr; up to about 0.015 wt % B; about 0.4 to about 1.2 wt % Mn; about 0.1 to about 0.3 wt % Si; and balance Ni.

Abstract: A turbine shaft, in particular for a steam turbine, is oriented along an axis of rotation. The turbine shaft has a first region with a maximum radius R1 and a second region adjoining the first region and having a maximum radius R2>R1. The first region includes a first base material for use at a temperature of over 550° C. and the second region includes a second base material for use at a temperature below 550° C. An alloy steel used for the first and the second base materials in each case has a chromium content of between 8.0% by weight and 12.5% by weight at a substantially identical austenitizing temperature. A method is provided for producing the turbine shaft.

Abstract: The present invention relates to a turbine housing (1) having an inner housing (2) which is surrounded by an outer housing (3), the inner housing (2) and the outer housing (3) each having a first, upper partial region (5) and a second, lower partial region (6), and having an inner-housing outer surface (7) and an outer-housing inner surface (8) which are positioned opposite one another, with a distance between them. At least in a part of the first partial region (5), the inner-housing outer surface (7) has a lower heat transfer through radiation to the opposite outer-housing inner surface (8) than at least in a part of the second partial region (6) of the inner-housing outer surface (7). This can be achieved by means of suitable surface coatings in the respective regions which have different absorption and/or emission coefficients (a1, a2).

Abstract: There is provided a hydraulic turbomachine comprising a housing, one or more impellers arranged rotatably around an axis within the housing, one or more resin-made diffusers provided around the one or more impellers for defining diffuser channels around the impellers, respectively, one or more support members provided within the housing and engaged under pressure with corresponding ones of the diffusers for securely supporting the corresponding diffusers in the direction of the above-noted axis within the housing, and elastic members held between surfaces of the support members and the diffusers in the above-noted direction. An O-ring receiving groove is formed in each of the surfaces of the diffusers in such a manner that the groove surrounds the axis, and an O-ring is placed in the groove as the elastic member.

Abstract: A high-pressure fan comprising a blade wheel (3, 4), a fan housing (5, 6) surrounding the blade wheel and an electric motor (1) to operate the blade wheel. To eliminate the problems related to the mounting of the blade wheel, the blade wheel (3, 4) at least mainly consists of light carbon fiber based composite material and is directly mounted on the shaft (2) of the electric motor.

Abstract: A Mg alloy member with an anticorrosive coating free from any enviromental load can be produced by using a solution for chemical conversion treatment for anticorrosive coating, which comprises 0.05 to 1 mol/l of an oxoacid compound of heavy metal selected from Mo, W and V and has a pH of 2 to 6 adjusted by sulfuric acid or nitric acid, and is characterized by contacting the surface of Mg alloy preferably containing 2 to 10% Al with the solution, thereby forming a specific oxide film and, if necessary further forming a fluorine-containing organic film on the film, the resulting Mg alloy member being used in electrically driven blowers, note-type personal computers, various household electrical appliances, etc.

Abstract: A movable blade of a turbine, which has a plurality of stages each provided with movable and stationary blades mounted to a turbine rotor, comprises a movable blade body having a leading edge portion, with respect to a turbine steam flow, and an erosion protective piece which is formed to be continuously integrally with the leading edge portion of the movable blade body so as to be protruded therefrom. The leading edge portion and the erosion protective piece are subjected to a surface hardening treatment such as flame hardening treatment.

Abstract: A high temperature repairable airfoil having a plurality of flow path cover tiles coupled to a single crystal spar member. In one embodiment, the plurality of flow path cover tiles include an attachment portion that is received within a groove formed in the outer surface of the spar. The attachment portion slides into a retaining feature within the groove so as to limit movement of the plurality of flow path cover tiles. Upon rotation of the airfoil, the plurality of flow path cover tiles become centrifugally loaded with a portion of the spar member. In one embodiment, the plurality of flow path cover tiles are formed of a material selected from the group consisting of ceramics, intermetallic, and thermal barrier coated single crystal alloy material.

Abstract: The main object of the present invention is to provide a steam turbine rotor shaft whose high-temperature strength is excellent at a selected temperature of 650 degrees C.

Abstract: A turbine inner shroud and a turbine assembly. The turbine assembly includes a turbine stator having a longitudinal axis and having an outer shroud block with opposing and longitudinally outward facing first and second sides having open slots. A ceramic inner shroud has longitudinally inward facing hook portions which can longitudinally and radially surround a portion of the sides of the outer shroud block. In one attachment, the hook portions are engageable with, and are positioned within, the open slots.

Abstract: A frangible cover is provided for a recess in a containment case for turbofan engine blade removal and access. The recess provided in the containment case allows outward radial movement of the engine fan blade when the engine fan blade is to be removed from the containment case. The present invention proposes a frangible component to cover the recess. A plurality of initiation points, notched in the frangible cover at intersections of surfaces encourages brittle fracture of the frangible component.

Abstract: A molten metal pumping device is disclosed that comprises a pump base including at least one input port, a pump chamber, a chamber wall, and a discharge leading to an output port. A rotor is retained within the chamber and is connected to a rotor shaft. The device further includes a superstructure attached to and positioned above the pump housing, a motor on the superstructure, a drive shaft connected to the motor and a coupling connecting the drive shaft to the rotor shaft. The rotor is a dual-flow (or mixed-flow) rotor, directing molten metal both into the chamber and towards the chamber wall, where it ultimately exits the chamber through the discharge. The dual-flow rotor can also be used with a scrap melter.

Abstract: A solid-solution strengthened superalloy weld composition, includes: about 0 to about 10 wt % Co; about 18 to about 22 wt % Cr; about 0.2 to about 0.7 wt % Al; about 15 to about 28 wt % of the sum of refractory elements; up to about 0.09 wt % C; up to about 0.06 wt % Zr; up to about 0.015 wt % B; about 0.4 to about 1.2 wt % Mn; about 0.2 to about 0.45 wt % Si; and balance Ni.

Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a blade containment portion (54) and a transition portion (58). The upstream portion (56) has a flange (52) connecting the metal containment casing (40) to an axially adjacent casing ( ). The upstream portion (56) of the casing (40) has a greater diameter (D1) than the diameter (D2) of the blade containment portion (54) and the blade containment portion (54) has a greater thickness (T2) than the thickness (T1) of the upstream portion (54). The transition portion (58) connects the blade containment portion (54) and the upstream portion (56) to transmit loads from the blade containment portion (54) to the upstream flange (52).

Abstract: An impeller for a molten metal pump having a cylindrical body comprised of a refractory material. The cylindrical body includes generally coplanar top and bottom surfaces. A central bore is provided in the top surface to provide a point for mating with a shaft. A plurality of circumferentially spaced passages extend from the top or bottom surface to a side wall of the impeller, each of the passages being separate and preferably having an inlet opening which is equal to or less than the corresponding outlet opening in size. A recess being optionally formed in the top or bottom surface, forming the initial inlet to the passages.

Abstract: A liquid pump includes a rotor, a rotor shaft, and a split cage for accommodating the rotor. A stator assembly is situated outside the split cage, and a pump casing has a pump-casing bottom and top part, a flange part, and a plug-in holder. The pump casing accomodates a pump impeller on the shaft, and the pump-casing top part has a plug-in holder. A method for assembling the liquid pump includes axially pressing a bearing into a bearing holder. O-rings are mounted on the split cage. The rotor is axially inserted into the split cage, which is axially pressed into the plug-in holder of the pump casing. The rotor shaft is simultaneously pressed into the pump impeller. The bearing holder has another supporting part and is axially pressed into the split cage. A cap together with the stator assembly are axially mounted onto the plug-in holder. The pump-casing bottom part is connected to the pump-casing top part, preferably with a pump-casing seal in between.

Abstract: The invention relates to a housing part for a ventilating fan with an axial rotation shaft, wherein a number of housing parts can be placed radially round the ventilating fan so as to form a substantially cylindrical housing, which housing part comprises:

Abstract: A formulation used in the construction of lightweight aircraft engine fan blades. The formulation comprises a polyurethane elastomer composition, which is formed from a prepolymer, a curative and an antioxidant and molded into the blades. Optionally, a hindered amine light stabilizer and/or an ultraviolet absorber may be added to the formulation. The aircraft engine fan blade is formed from a metal, such as titanium alloy. Pockets are machined into the fan blade, so as to lessen the amount of metal used to construct the blade, thereby lowering the total weight of the blade. The formulation of the present invention is positioned in the pockets of the fan blade, so as to maintain the structural integrity of the blade against bird strikes and the like, while at the same time providing a fan blade which is significantly lighter than all-metal fan blades.

Abstract: An article is formed of a gas turbine component having a substrate, an internal passage through the substrate defining an internal surface of the substrate, and an internal protective layer overlying the internal surface of the substrate. The internal protective layer has a composition of aluminum, plus, in weight percent, on average from about 0.1 to about 5.0 percent of a modifying element selected from the group consisting of hafnium, yttrium, zirconium, chromium, and silicon, and combinations thereof, and elements found in the substrate.

Abstract: A method and shield assembly 12 for use in processing a flow directing assembly 10, such as a stator vane or rotor blade, is disclosed. Various details are developed for the construction of the shield assembly and for the method of masking the flow directing assembly. The shield assembly has a shield having two sides 52, 56 and at least one tab 56 which extends from one of the sides and through the other side and is pressed against the other side. In one embodiment, the method includes exerting a force against the shield to block movement of the shield from the installed position. The shield assembly might include a locking member for this purpose which has a projection 106a which is attached to the shield or a locking member 42 which is not attached to the shield and which has a tab 114 which engages the shield and a projection 112 which engages the airfoil. Alternatively, the shield assembly might include a clamp 92 which presses the shield against the airfoil.

Abstract: A sheet metal casing for multistage pump and its manufacturing method, the casing includes an outer shell and an inner shell. The outer shell is integrally formed and includes a front end ring, a step positioning ring, an outer shell surface and a positioning end. The inner shell is fixed to the inner side of the outer shell and includes an inner end, an inner shell surface and a step positioning rim. The step positioning rim forms a closed holding space with the outer shell surface for holding and squeezing a seal ring therein. When a plurality of casings being serially mounted on a spindle, the positioning end of a front casing may make contact with the step positioning ring of a rear casing, and the positioning rim of the front inner shell may make contact with the front end ring of the rear outer shell for axially positioning the casings on the spindle.

Abstract: A thrust reverser cascade flow directing element (28) for a gas turbine engine (10) comprises a plurality of plates (30) and a plurality of flow directing vanes (40). At least one vane (40) extends between each pair of plates (30), the plurality of plates (30) are formed from sheet material and a single integral piece of ductile sheet material (32) forms the plurality of flow directing vanes (40). The single integral piece of ductile sheet material (32) has a plurality of longitudinally spaced apart apertures (36) and a plurality of longitudinally spaced apart sheet material portions (38) between the apertures (36) and the ductile sheet material (32) is bent at a plurality of longitudinally spaced positions such that each sheet material portion (38) defines one of the plurality of flow directing vanes (40).

Abstract: A ceramic nozzle for a gas turbine stage of a turbomachine (e.g., a turbopump) includes a splined mounting surface. Ceramic splines on the nozzle mounting surface are interlocked with metal mating splines on a surface of a turbine housing to prevent the nozzle from rotating relative to the housing. Both sets of splines extend in a radial direction, are straight and have trapezoidal shapes in transverse cross-section. These splines maintain a constant contact angle during large temperature excursions, when inherent thermal growth mismatches between ceramic and metal occur.

Abstract: A turbine blade, in particular a gas-turbine blade, which extends along a main axis from a root region over a blade body region to a tip region. The turbine blade has a cavity in the blade body region, at least regions of the cavity being surrounded by a blade wall having a small wall thickness. The blade wall is formed of a metallic material having a small average grain size. In addition, a method of producing the turbine blade is further disclosed.

Abstract: An impeller for a molten metal pump having a cylindrical body comprised of a refractory material. The cylindrical body includes generally coplanar top and bottom surfaces. A central bore is provided in the top surface to provide a point for mating with a shaft. A plurality of circumferentially spaced passages extend from the top or bottom surface to a side wall of the impeller, each of the passages being separate and preferably having an inlet opening which is equal to or less than the corresponding outlet opening in size. A recess being optionally formed in the top or bottom surface, forming the initial inlet to the passages.

Abstract: An engine, according to an exemplary embodiment of the invention, comprises a compressor which compresses inlet air; a combustor in which a mixture of fuel and air is combusted; a turbine which is driven by gases from the combustor; and a dielectric coating applied to a surface of at least one of: the compressor and the turbine, the dielectric coating having a dielectric constant of at least 3.0 and a loss tangent of at most 0.1, wherein the dielectric coating reduces the magnitude of an electrostatic force which attracts particles flowing through the engine to the surface of the engine. In operation, only a thin layer of particles typically accumulates on the dielectric coating. While the dielectric coating reduces the magnitude of the electric field which attracts particles, the repulsive force produced by the accumulated particles repels additional particles of the same charge.

Abstract: A molten metal impeller having a base portion including a circumferential notch. The notch having a generally radial wall and a generally axial wall, at least one of the radial or axial walls including a plurality of grooves. A ceramic bearing ring is cemented into the notch.

Abstract: A portable working machine provided with a centrifugal air blower, which is featured in that a prime mover (50) for driving the air blower (20) is mounted via a supporting coupling member (30) on a volute case (22) of the air blower (20) which is mounted in an upright state; and that an air inlet port of the air blower (20) is positioned on the side of the volute case (22) which is closer to the prime mover (50).

Abstract: The invention relates to a radial blower for a work apparatus and especially for a suction/blower apparatus. The radial blower has a blower wheel (2) and a blower housing (1) which at least partially surrounds the blower wheel (2). The blower housing (1) includes a peripheral wall (3) and a side wall (4). The housing includes an intake opening (6) in the region of the blower wheel axis (5) as well as a discharge stub (7) peripherally of the blower wheel (2) in the region of the peripheral wall (3). The peripheral wall (3) and the side wall (4) are lined on the side facing toward the blower wheel (2) with a wear insert (8) configured as one piece.

Abstract: A locking member for engaging a shield 40 which is disposed during processing about an airfoil 24 of a flow directing assembly 10, such as a stator vane or rotor blade, is disclosed. Various details are developed for the construction of the locking member. In one embodiment, the locking member is separate from the shield and has projections 112, 116 that each engage an opening 36a, 36b in the airfoil and tabs 114, 118 which engage an opening 78, 84 in the shield. In another embodiment, the shield has a projection 106a which is attached to the shield.

Abstract: Described is a turbine blade with a metal blade body and a protective coating constructed of a porous intermetallic felt, and in the blade body of the turbine blade cooling air channels are constructed that end at the intermetallic felt in order to supply it with cooling air. The intermetallic felt is based on an iron or nickel aluminide alloy with mixing ratios of Fe:Al or Ni:Al of approximately 50:50, and that the protective coating has cooling channels that are facing the blade body and end in the area of the cooling channels. The design of the turbine blades permits their cooling with a smaller amount of cooling air, and, due to improved aerodynamics and a lower cooling air supply, the degree of effectiveness of the turbine is significantly increased.

Abstract: Transmission torque converter reactor thrust washer segments (12) comprising a surface hardenable aluminum alloy are subjected to electrical discharge machining (EDM) using an electrode (26) and under conditions effective to impart a hydrodynamic bearing surface profile to the segment surfaces (12a), reduce segment surface roughness, and increase segment surface hardness. Torque converter reactors (10) having integrated thrust washer segments machined in this manner exhibit improved wear resistance and hydrodynamic lift when compared to as cast thrust washer segments.

Abstract: There is provided a hardwall fan case for encasing a forward fan in a gas turbine engine. The fan case has a stiff annular shell spaced radially outward from the tips of the fan blades and a flexible ring which is an integral structural part of the shell. The flexible ring has a frusto-conical shape with a lip adjacent to the blade trailing edge. The ring extends axially rearwardly from the fixed root to the free inner edge forming a cantilevering resilient ring. A hollow cavity defined between an inner surface of the shell and an outer surface of the flexible ring provides clearance for the flexible ring to deform radially outwardly on impact with a released blade, or to elastically flex on contact with the trailing edge blade tip during bird strike events.

Abstract: A steam turbine comprising a rotor shaft integrating high and low pressure portions provided with blades at the final stage thereof having a length not less than 30 inches, wherein a steam temperature at first stage blades is 530° C., a ratio (L/D) of a length (L) defined between bearings of the rotor shaft to a diameter (D) measured between the terminal ends of final stage blades is 1.4 to 2.3. This rotor shaft is composed of heat resisting steel containing by weight 0.15 to 0.4% C, not more than 0.1% Si, 0.05 to 0.25% Mn, 1.5 to 2.5% Ni, 0.8 to 2.5% Cr, 0.8 to 2.5% Mo and 0.15 to 0.35% V and, further, the heat resisting steel may contain at least one of Nb, Ta, W, Ti, Al, Zr, B, Ca, and rare earth elements.

Abstract: A nonmetallic pump for pumping molten metal includes a base with an impeller chamber, at least one molten metal inlet opening to the base, at least one molten metal outlet opening from the base, and an impeller connected to one end of a motor driven shaft and rotatable in the impeller chamber. The base includes an impeller opening in which the impeller is disposed and a wall extending so as to form a spiral-shaped opening around the impeller opening. An egress channel extends from the spiral-shaped opening toward the molten metal outlet opening.

Abstract: A coating for a portion of the flowpath of a diffuser of a centrifugal compressor. The coating covers a portion of the diffuser against which flows high velocity air from the compressor blades. The coating is a smooth, tenacious, heat-resistant powder paint that reduces the aerodynamic drag of the diffuser walls on the high velocity air thus increasing the efficiency of the compressor.

Abstract: There is provided a steam turbine blade made of Ti-base alloy comprising an &agr;+&bgr; type phase in which a difference of a tensile strength is small between a blade portion and a dovetail portion, a tensile strength at a room temperature of the dovetail portion is equal to or more than 100 kg/mm2 and a suitable toughness is commonly provided together with a strength, as a steam turbine blade having a length of 43 inch or more, a method of manufacturing the same, a steam turbine power generating plant and a low pressure steam turbine.

Abstract: An pump casing for a sheet metal pump includes a pump body made by pressing or roll forming a sheet metal, a reinforced member which includes a water guide unit and a flange unit separately made by casting or CNC machining and a seal ring engaged with the water guide unit. The pump body is a simple basin shape which can be produced with less stress concentration. The water guide unit may be made with a more precise volute for achieving better pumping efficiency. The reinforced member may increase structural strength of the pump casing for withstanding greater pumping pressure and external forces. The seal ring may be positioned precisely without dislocation because it engages with the water guide unit rather than the pump casing. The gap between the seal ring and the impeller may be kept small and constant, thus obtaining better pumping efficiency, lower operation noise and greater durability.

Abstract: System for repairing worn surfaces of steam turbine components and especially high pressure turbine rotors, are disclosed. These systems include depositing a first layer of weld metal on a worn surface of the component, whereby a heat-affected zone is created. A second layer of weld metal is then deposited over the first layer using a greater amount of heat to temper at least a portion of the heat-affected zone produced by the first layer. The preferred embodiments include the use of gas tungsten arc welding for providing fine-grain size and more creep resistance, especially in the weld and heat-affected zone. The resulting build-up can be machined, for example into a blade fastening to produce a component having properties equal to or better than the base-metal alloy. The invention also provides a longer lasting turbine system, including rotors which have serrated steeples that are more resistant to failure.