Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a turbine nozzle. The surface reflects radiation back into the hot gas flow path.

Abstract: A method for the early detection of aerodynamic instability in a turbomachine compressor is described which involves collecting and normalizing signals from sensors distributed uniformly around the circumference of the compressor and detecting events for which the normalized signals do not pass through a zero value during a length of time Tz which is at least greater than the time taken for two successive moving blades to travel past the sensor. A decision regarding the imminence of aerodynamic instability is then taken after the detected events have been analyzed and decision criteria have been applied. The decision criteria may be based on the event detection rate and/or on the spatio-temporal position of the events detected across all the sensors.

Abstract: An impeller for a molten metal pump includes a base and a plurality of vanes having openings for flow of molten metal there through during pumping. Alternatively, or in combination with the vane openings, a single drain opening extending through the base of the impeller may be provided remote of the rotational axis of the impeller. In another embodiment, an impeller provides axial and radial pumping. The multiflow impeller includes at least one pumping chamber inclined into the direction of rotation to provide axial pumping.

Abstract: A steam turbine component coated with a protective layer can be exposed to hot vapor. The component has a metallic base body, to which the protective layer is bonded by diffusion in order to increase the resistance of the base material to oxidation. The protective layer contains aluminum and has a thickness of less than 50 &mgr;m. The protective coating can be formed by applying an aluminum pigment to the base body and maintaining the component at a predetermined temperature.

Abstract: Articles produced by laser shock processing exhibit various compressive residual stress distribution profiles. A gas turbine engine airfoil includes an asymmetrical stress profile formed through the thickness of its thin section. The articles include plural laser shock peened surfaces and plural regions having deep compressive residual stresses imparted by laser shock peening extending into the article from the laser peened surfaces. One article includes at least one set of simultaneously formed, adjacent non-overlapping laser shock peened surfaces. Another article includes at least one set of opposing laser shock peened surfaces formed at different times at opposite sides of the article. Another article includes at least one set of opposing laser shock peened surfaces formed simultaneously at opposite sides of the article using laser beams having different pulse lengths.

Abstract: Electronic system components are cooled using a field configurable pump comprising a selectable plurality of identical or nearly identical modular pump units. The pump units are disposed in a stacked arrangement and are fluidly connected to adjacent modular pump units via a removable coupling, preferably one of the quick-disconnect variety. Each modular pump unit comprises a housing, an impeller and a sealing mechanism. When disposed in a stack the combined pump structure is driven by a single motor. In this fashion, pump structures may be employed which are adaptable to heat flux demands imposed by the electronic components.

Abstract: An impeller system for use in a molten metal pump, the impeller system including a generally cylindrical outer wall with outlets therein, an impeller lid mounted on the impeller walls, the impeller lid including a plurality of inlets, with the shaft being mounted directly into a base, which is mounted relative to the outer wall. The impeller system has an open interior defined by the outer wall, the lid and the base, and the impeller shaft mounts directly into the base without the need for a collar or attachment to the impeller lid.

Abstract: Rotor blades for wind power installations are known in many different forms. In a wind power installation the rotors or the rotor blades thereof represent the main source of sound. For reasons relating to acceptance and noise prevention laws, the aim should/must be that of minimizing the levels of sound emission as wind power installations are often also set up in the proximity of residential accommodation. The levels of sound emission which hitherto occur with a wind power installation or a wind power converter also mean that wind power installations are faced with resistance from populated areas because of the sound they produce and for that reason such installations can be accepted sometimes with difficulty or not at all as authorities responsible for planning permission refuse permission for wind power installations because of the existing environmental requirements, noise also being an environmentally polluting factor.

Abstract: A molten metal pump system which generally provides a refractory connection joint for connecting a refractory pump post to a pump base, the pump post including a refractory post with a first end, the first end including an internally threaded joint screw aperture; a refractory base with a post aperture configured to receive the first end of the refractory post, and with a screw aperture contiguous with the post aperture; and a joint screw with a first end and a second end, the joint screw including a threaded external surface and a retention shoulder, the joint screw configured to insert through the screw aperture in the refractory base with the threaded external surface engaging the internally threaded joint screw aperture of the refractory post, and the retention shoulder engaging the refractory base.

Abstract: A gas turbine having a metallic outer shroud and a ceramic inner shroud. The ceramic inner shroud being secured to the outer shroud by hooks carried on the outer shroud. The hooks on the outer shroud being coated with TBC. A pin and spring system being provided to hold the ceramic inner shroud against the forward hook of the outer shroud. An anti-rotation pin being provided to trap the aft bend of the ceramic inner shroud against the aft hook of the outer shroud. The gas turbine further including a damping spring and pin system, disposed between a heat shield, within the outer shroud, and the ceramic inner shroud, to provide damping of the inner shroud.

Abstract: A flexible jacket for a vacuum blower having rotatable blades in a blade housing. The jacket is made from heavy duty, substantially impenetrable, bullet resistant material such as KEVLAR brand sheet material which is placed about the blade housing to prevent any severed and flying rotor blades from entering the atmosphere through the blade housing. The configuration of the jacket is formed to match the blade housing and to enable the jacket to be easily retrofitted onto existing vacuum blowers or other blade housings and secured in place about the blade housing.

Abstract: The invention describes a temperature-stable protective coating over a metallic substrate surface (1), which coating includes at least one layer of material (4) consisting of MCrAlY, where M represents at least one of the elements selected from the group of materials consisting of Fe, Co and Ni. The invention also describes a production process for this coating.

Abstract: An air boost device such as a turbocharger, wherein the compressor wheel thereof is re-designed to permit die inserts (20), which occupy the air passage and define the blades (4, 5) during a process of forming a wax pattern (21) of a compressor wheel, to be pulled without being impeded by the blades. This modified blade design enables the automated production of wax patterns (21) using simplified tooling. The compressor wheel improves low cycle fatigue, withstands high temperatures and temperature changes, and permits operation at high boost pressure ratio while, on the other hand, having low weight, low inertial drag, and high responsiveness.

Abstract: A hybrid vane (50) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member (52) bonded to a substantially solid core member (54). The airfoil member and core member are cooled by a cooling fluid (58) passing through cooling passages (56) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond ((70) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation (72) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.

Abstract: An impeller shaft assembly, coupler and molten metal pump are described, in which a coupling member is configured to be secured to a pump drive shaft and includes a socket part that is defined by a socket wall formed about and extending along an axis. The socket wall includes a plurality of coupling shaft engaging surfaces and a plurality of socket corner surfaces joining the shaft engaging surfaces. The socket corner surfaces are disposed radially outward from adjacent shaft engaging surfaces with respect to the axis.

Abstract: A ceramic matrix composite (CMC) component for a combustion turbine engine (10). A blade shroud assembly (30) may be formed to include a CMC member (32) supported from a metal support member (32). The CMC member includes arcuate portions (50, 52) shaped to surround extending portions (46, 48) of the support member to insulate the metal support member from hot combustion gas (16). The use of a low thermal conductivity CMC material allows the metal support member to be in direct contact with the CMC material. The gap (42) between the CMC member and the support member is kept purposefully small to limit the stress developed in the CMC member when it is deflected against the support member by the force of a rubbing blade tip (14). Changes in the gap dimension resulting from differential thermal growth may be regulated by selecting an angle (A) of a tapered slot (76) defined by the arcuate portion.

Abstract: A turbine engine shroud segment, preferably a low ductility material, for example a ceramic matrix composite, comprises a segment body extending between body circumferential ends. The body includes a body radially inner surface arcuate at least circumferentially, and a body radially outer surface from which a plurality of hooks extend generally radially outwardly. Each hook comprises a generally radially outwardly extending hook arm with a generally axially extending hook end having a generally radially inner surface in spaced apart juxtaposition with a portion of the body radially outer surface. Such body outer surface includes at least two body contact surfaces each matched in shape and in juxtaposition at least at body circumferential ends with a cooperating hanger contact surface. The radially inner surface of each hook end includes a hook end contact surface matched in shape with a cooperating hanger contact surface at least in a circumferential middle portion of such surface.

Abstract: A method for controlling distortion of a turbine case (“case”) includes measuring a temperature distribution for the case that includes thermal gradients. The method further includes modeling thermal stresses on the case induced by the thermal gradients, calculating an out of roundness index (“index”) resulting from the thermal stresses, and comparing the index with at least one distortion limit to determine whether the case has a satisfactory or an unsatisfactory index. The temperature distribution is controlled for an unsatisfactory index to produce the satisfactory index. A system for controlling distortion of the turbine case includes a thermal measurement system, for measuring the temperature distribution, and a computer configured for modeling the thermal stresses, calculating and comparing the index with the distortion limit, and controlling the temperature distribution for an unsatisfactory index to produce the satisfactory index.

Abstract: A turbomachine stator flap including a structural beam which is formed integrally with a structural core for a vane, and fastening portions, and a composite envelope surrounding the structural core and forming at least the aerodynamic profile of the vane.

Abstract: A part is used that constitutes a platform web and that has a shape close to the shape of the platform with an inside face and an outside face that are opposite each other. Fiber reinforcement plies are draped on a blade core and at least some of these plies extend beyond an end of the blade that is to be connected to the platform so as to form ply extensions. The ply extensions are folded down against the inside and outside faces of the platform to form flaps securing the blade to the platform, and fiber reinforcement plies are draped around the platform web and over the flaps so as to form a platform box retaining the flaps.

Abstract: An exhaust-gas turbine for a turbocharger includes a rotor mounted rotatably in a turbine casing having a spiral inlet duct which is followed by an annular space surrounding the rotor. A guide-blade cascade is capable of being pushed axially into the annular space near the outer circumference of the rotor. The guide-blade cascade includes guide blades, is guided in an annular gap between an inner part and the turbine casing and is axially displaceable via an axial slide by a sliding sleeve. The guide-blade cascade with the axial slide, the inner part and/or the sliding sleeve are produced from an austenitic cast steel material having the following components: C≦0.2%; Si 1.5-2.5%; Mn≦2.00%; P≦0.045%; S≦0.03%; Cr 24.0-26.0%; Ni 19-22%; and W≦5%.

Abstract: Impeller 21 is rotatably disposed within a pump housing that includes pump cover 5 and pump body 18. Inlet port 19, body groove 31, partition 33 and blocking wall 37 are formed in the pump body 18. The body groove 31 defines a first pump channel 35, and the blocking wall 37 defines a enlarged channel portion 38. Outlet port 20, cover groove 32 and partition 34 are formed in the pump cover 5. The cover groove 32 defines a second pump channel 36. Distance {circle around (1)} between a terminal end of the first pump channel 35 and a terminal end of the outlet port 20, distance {circle around (2)} between a starting end of the enlarged channel portion 38 and a starting end of the second pump channel 36, length {circle around (3)} of the partition 34 and length {circle around (4)} of the partition 33 each are chosen to be optimum values such that the amount of fluid that is discharged through the outlet port 20 and the amount of fluid that flows in though the inlet port 19 increase.

Abstract: A fan blade fragment containment assembly for a gas turbine engine having a fan case surrounding the fan and having a circumferential axially extending blade fragment impact zone. An inner relatively slack or low tension deformable layer of Kevlar™ or Zylon™ fabric is mounted to the fan case outer surface and envelopes the impact zone. A compressible (ex. metal foam or honeycomb) layer is mounted on an outer surface of the deformable layer. A friction reduction layer of Teflon™ is mounted on an outer surface of the compressible layer and an outer relatively taut higher tension containment layer of Kevlar™ or Zylon™ fabric is mounted on an outer surface of the friction reduction layer. The friction reduction layer enhances the distribution of impact forces about the circumference of the compressible layer by reducing local shear stresses between the compressible layer and the containment layer.

Abstract: The invention relates to a gas turbine seal, comprising a metallic component (1) with a durable or erosion-resistant ceramic coating (2) and an abradable ceramic layer (18) which is arranged thereon in locally delimited fashion, a bond layer (5) being arranged on the surface (4) of the metallic component (1), to which bond layer the durable or erosion-resistant ceramic coating (2) is applied as a covering layer. The invention is characterized in that the bond layer (5) comprises separate, adjacent spherical rivets (6) or mushroom-shaped rivets (6) which have a web (7) and a head (8). These rivets form individual metal islands with numerous undercuts (12), around which there is a continuous ceramic network. It is possible to produce very thick layers which have a good bond strength, the ceramic not being flaked away even in the event of introduction of radial/tangential forces, sickle-shaped contact or locally high overheating/frictional heat, and a good sealing action being achieved.

Abstract: A turbine blade or turbine vane includes a metallic nonfoam region, and a ceramic foam region joined to the metallic region. The ceramic foam region is an open-cell solid ceramic foam made of ceramic cell walls having an intracellular volume therebetween. The ceramic is preferably alumina. The intracellular volume may be empty porosity, or an intracellular metal such as an intracellular nickel-base superalloy.

Abstract: A ceramic matrix composite material (CMC) vane for a gas turbine engine wherein the airfoil member (12) and the platform member (14) are formed separately and are then bonded together to form an integral vane component (10). Airfoil member and the platform member may be bonded together by an adhesive (20) after being fully cured. Alternatively, respective joint surfaces (16, 18) of the green body state airfoil member and platform member may be co-fired together to form a sinter bond (30). A mechanical fastener (38) and/or a CMC doubler (42) may be utilized to reinforce the bonded joint (40). A matrix infiltration process (50) may be used to create or to further strengthen the bond.

Abstract: A pump station for transferring radioactive particle containing waste water, includes: (a.) an enclosed sump having a vertically elongated right frusto conical wall surface and a bottom surface and (b.) a submersible volute centrifugal pump having a horizontally rotating impeller and a volute exterior surface. The sump interior surface, the bottom surface and the volute exterior surface are made of stainless steel having a 30 Ra or finer surface finish. A 15 Ra finish has been found to be most cost effective. The pump station is used for transferring waste water, without accumulation of radioactive fines.

Abstract: A on-line method is provided for detecting wear and/or damage to gas turbine parts. Preferred embodiments of the invention provide a gas turbine comprising parts with smart coatings and collection and detection means to measure wear and erosion of gas turbine parts. In other preferred embodiments, smart coatings are provided comprising chemical taggants that can be collected and detected downstream, thus providing an on-line or in situ evaluation technology for wear and damage to gas turbine parts.

Abstract: A spiral casing for a turbine of a turbocharger is made from thin (0,2 to 2 mm thick) sheet metal. The spiral casing can be made from two matching parts and can be insulated.

Abstract: A method and apparatus for casting a near-net-shape article from a high temperature material, such as a refractory metal intermetallic composite material. The apparatus includes: a means for forming a molten material comprising at least one of a metal and an alloy; a means for pouring the molten material; a mold assembly comprising a solid shell having a face coat interposed between the solid shell and molten material; and a heater assembly for maintaining the solid shell at a temperature. The molten material solidifies within the solid shell to form a near-net shape of the article. The near-net shape article may be a turbine assembly component, such as, but not limited to, a vane or airfoil.

Abstract: A wear resistant fuel pump for a vehicle includes a pump section having a rotatable impeller and a plurality of plates disposed axially adjacent to and cooperating with the impeller to pump fuel therethrough. The wear resistant fuel pump also includes a motor section disposed adjacent the pump section and having a motor to rotate the impeller. The wear resistant fuel pump further includes an outlet section disposed adjacent the motor section to allow pumped fuel to exit therethrough. The impeller is made of a first compound and the plates are made of a second compound having an abrasion wear resistance on a surface thereof that improves abrasion wear characteristics therebetween.

Abstract: A low-pressure turbine is provided with stationary and rotating blades, and the blades have a coating that is hydrophobic or water-repellant and has a smooth surface. The coating preferably contains amorphous carbon. The hydrophobic property of the coating has the result that small droplets contained in the steam phase, upon impacting a coated blade, roll off across the blade in the form of small droplets and further follow the steam path. This prevents moisture losses and increases the efficiency of the turbine. It also prevents the small droplets on the blades from coalescing into larger droplets or into a fluid film. This prevents droplet impingement erosion caused by the impact of large droplets on the blading and other components of the turbine.

Abstract: A gas turbine airfoil and methods for manufacturing and repair of an airfoil, the airfoil comprising a wall, the wall defining the perimeter of the airfoil and comprising a leading edge section and a trailing edge section, wherein a majority of the surface area of the wall comprises a first material, the first material having an oxidation resistance and a melting temperature, and at least one portion of the wall comprises a second material, the second material having an oxidation resistance that is greater than the oxidation resistance of the first material and a melting temperature that is at least about 83 degrees Celsius (about 150 degrees Fahrenheit) greater than the melting temperature of the first material, the at least one portion of the wall located in at least one section of the wall selected from the group consisting of the leading edge section and the trailing edge section.

Abstract: To provide a corrosion-resisting and wear resisting alloy including cobalt, nickel or iron as a base used for a sliding part or a valve seat for a machine, and restraining erosion and corrosion caused by eutectic carbide constituting the alloy in an atmosphere with dissolved oxygen.

Abstract: A molten metal pump system which includes a particle relief passageway between the vanes on the impeller and the pump base, the particle relief passageway being a predetermined size to allow particles of a predetermined size to pass between the plurality of vanes and the interior walls of the impeller aperture of the pump base. Part or all of the particle relief passageway may, but need not, be as a result of a shoulder on the radially outward end of the plurality of vanes in the inlet side of the impeller.

Abstract: A high-pressure turbine nozzle-vane band for a gas turbine engine, the band comprising an inside surface supporting at least one guide vane having a trailing edge that is directed towards a downstream end of the band, and an outside surface, opposite the inside surface, from which a flange extends radially, defining firstly, upstream from the flange, a passage for cooling-air, and secondly, downstream from the flange, a cavity, the inside surface of the band being provided, between the trailing edge of the guide vane and the downstream end of the band, with a coating forming a thermal barrier enabling a temperature gradient generated in the band by the air spinning in said cavity to be increased.

Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (62) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (62) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine (10) but has unimpaired stiffness and penetration resistance.

Abstract: A coaxial wind turbine apparatus which includes a pair of rearward-mounted, spring-loaded fins to orient the air inlet opening to face the direction of the oncoming wind and close a damper panel or shutter array at the air inlet opening during very high wind conditions. Thereby, the pair of rearward-mounted, spring-loaded fins stabilizes the apparatus during strong ambient wind conditions and minimizes damage to the rotating turbine wheel in the presence of a strong wind.

Abstract: A turbo-molecular pump includes a casing having an intake port, a stator fixedly mounted in the casing, and a rotor supported in the casing for rotation relatively to the stator. The stator and the rotor make up a turbine blade pumping section and a groove pumping section for evacuating gas. A scattering prevention member is provided for preventing fragments of the rotor from being scattered through the intake port.

Abstract: An exhaust-gas turbine for a turbocharger includes a rotor mounted rotatably in a turbine casing having a spiral inlet duct which is followed by an annular space surrounding the rotor. A guide-blade cascade is capable of being pushed axially into the annular space near the outer circumference of the rotor. The guide-blade cascade includes guide blades, is guided in an annular gap between an inner part and the turbine casing and is axially displaceable via an axial slide by a sliding sleeve.

Abstract: The invention relates to a method of manufacturing a gas-trubine blade and to a turbine blade. First, a hollow, supporting metal blade body is made, in particular by casting, with a multiplicity of, in particular peg-like, elevations on an outer surface of a blade airfoil of the metal blade body. Impact cooling bores are bored between the elevations from the outer surface to the hollow interior space of the metal blade body. A coating is applied which fills the intermediate spaces between the elevations and closes the impact cooling bores. The coating is made of a heat-resistant, removable material. Then, a covering coat is adhered to the metallically bright top sides of the elevations, and the material in the intermediate spaces between the elevations of the metal blade body and the covering coat is then removed.

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 (34) comprises a generally annular, or frustoconical, cross-section casing (52). At least one corrugated sheet metal ring surrounds the casing (52) wherein the corrugations extend with axial and/or circumferential components.

Abstract: A steam turbine blade made of a martensite steel having high strength and high toughness, and a low pressure steam turbine and a steam turbine power generating plant using the steam turbine blades. The steam turbine blade is made of a martensite steel containing C of 0.13-0.40%; Si less than 0.5%; Mn less than 1.5%; Ni of 2-3.5%; Cr of 8-13%; Mo of 1.5-4%; at least one kind of Nb and Ta of 0.02-0.3% in total; V of 0.05-0.35; and N of 0.04-0.15%.

Abstract: A rotor (38) for a gas turbine engine (10) has a low emissivity surface finish, or high emissivity surface finish (44), on at least a portion of its surface (42) to reduce temperature differentials between an upper portion and a lower portion of the rotor (38). This reduces bowing of the rotor (38) to allow the gas turbine engine (10) to be started without harmful vibrations of the rotor (38).

Abstract: A gas turbine has circumferential arrays of nozzles and shrouds and a plurality of combustors for flowing hot gases of combustion through respective sets of adjacent nozzles and shrouds. First and second nozzles of each set of nozzles are subject to different known inlet conditions of the hot gases of combustion flowing from the associated combustor and transition piece. The first nozzle in each set is preferentially located relative to the second nozzle of that set at a circumferential location relative to the associated combustor based on the known different inlet conditions. The first and second nozzles are therefore qualitatively different from one another dependent on those different inlet conditions. Similarly, the shrouds are subject to different inlet conditions and are preferentially designed and located based on those known inlet conditions.

Abstract: A disk pump assembly having a transparent housing and a transparent disk assembly within. The disks of the disk assembly have apertured bosses and indents corresponding to one another for registering the disks into single assembly. The rear disk has a rearward extension with an imbedded a metal insert having a central threaded bore. The rear housing component of the housing has a flanged rear which attaches to a corresponding square-flanged front end of an external motor having an extending shaft with a threaded end and an internally reverse-threaded central bore. The housing components are connected together with v-clamps; the suction port and discharge port each are flanged and also connected to external components with a v-clamp. A securing fastener further fastens the rear disk to the shaft through the internally reverse-threaded central bore at the end of the shaft.

Abstract: A molten metal pump and impeller system including an impeller body with a center portion with a shaft aperture therein, a plurality of vanes extending outward from the center portion, each vane including a radially inward end, a radially outward end, an input side, an output side, a leading surface, a trailing surface, a vane width between the leading surface and the trailing surface, and wherein the vane width is tapered from the input side to the output side. In another embodiment, the leading surface is convex notwithstanding whether the vane width is tapered.

Abstract: Methods for repairing and manufacturing a gas turbine airfoil, and the airfoil repaired and manufactured with such methods are presented with, for example, the repair method comprising providing an airfoil having specified nominal dimensions, the airfoil comprising a first material, the first material having a creep life and a fatigue life, the airfoil further comprising a leading edge section and a trailing edge section; removing at least one portion of at least one section of the airfoil to create at least one deficit of material for the airfoil relative to the specified nominal dimensions, the at least one section selected from the group consisting of the leading edge section and the trailing edge section; providing at least one insert comprising a second material, the second material having a creep life that is at least substantially equal to the creep life of the first material, and a fatigue life that is at least substantially equal to the fatigue life of the first material; and disposing the at least o

Abstract: The blood pump according to the present invention comprises a casing having a blood inlet and a blood outlet, and an impeller for circulating blood by rotating inside the casing, wherein both the casing's and the impeller's surfaces in contact with blood are formed of a biocompatible metal, and onto the surfaces in contact with blood a coating film of a hemocompatible material comprising a phospholipid polymer is formed. According to the present invention, the blood pump effectively suppresses the development of thrombi without activating blood coagulation factors such as thrombocites (blood platelets) in the blood, thanks to a coating film of a hemocompatible material made of a phospholipid polymer being formed onto the surfaces in contact with blood of the casing and the impeller composing the main part of the blood pump.

Abstract: A turbine nozzle includes ceramic outer and inner bands and an integral ceramic vane aft segment. A metal vane forward segment adjoins the aft segment in a hybrid assembly.