Abstract: A structural member comprises a main body formed from a cellular material. The structural member may be a casing for a rotary assembly e.g. a fan of a gas turbine engine. The main body may incorporate strengthening ribs and conduits and may have a random or graduated arrangement of different sized cells forming the cellular material. A recess may be defined on the radially inner face of the main body to receive an abradable material suitable for forming a seal with the blades of the fan.

Abstract: A material (100) formed of a sintered aggregation of ceria particles (106), mullite particles (108) and an alumina matrix material (110). Differential thermal expansion of the ceria and mullite particles generates thermal stress sufficient to create micro-cracking of the ceria particles. The ratio of ceria to mullite may be selected to achieve a desired coefficient of thermal expansion for matching the thermal growth of a mating CMC material (102). The micro cracks provide the material with a desired degree of strain tolerance useful in high temperature applications such as a solid core gas turbine vane (20).

Abstract: In a steam turbine plant in which a turbine casing containing a turbine is constituted of an upper-half casing and a lower-half casing, nozzles are provided to the upper-half casing and a steam supplied through main steam piping lines are deliveried into the upper-half casing. Main steam pipes for supplying a steam from respective main valves to the respective nozzles are each formed so as to be dividable in a position out of the installation area of the upper-half casing.

Abstract: The present invention concerns a wind power installation comprising a ring generator and a housing having a heat-conducting housing portion in the region of the ring generator. Previously known structures suffer from the disadvantage that mechanical vibrations and oscillations of the generator can be perceived as acoustic disturbance and interference. The object of the present invention is very substantially to eliminate that disadvantage. A wind power installation comprising a ring generator and a pod housing, which surrounds the ring generator, of the wind power installation, wherein the pod housing has a heat-conducting housing portion in the region of the ring generator and a predetermined spacing is provided between the outside periphery of the ring generator and the heat-dissipating housing portion.

Abstract: An air turbine starter for use in aircraft or other gas turbine engine applications. In a particular embodiment, the air turbine starter has a titanium unitary inlet structure. The unitary inlet structure has a housing having a longitudinal centerline. The housing defines an air inlet, a mounting surface, and a flow path therebetween. Integrally formed inside the housing and transverse to the longitudinal centerline is a stator for directing the flow of air in to the turbine blades of the turbine starter. The stator has a central circular body with a plurality of angularly spaced circumferentially mounted stator fins. An improved unitary inlet structure and method for making such a unitary inlet and stator are also provided.

Abstract: A system and method is provided for pumping fluid. A pump incorporates composite components that provide a high degree of formability while maintaining wear resistance for use in potentially abrasive environments. The composite components may comprise one or more impellers and/or one or more diffusers.

Abstract: A low solvus, high refractory alloy having unusually versatile processing mechanical property capabilities for advanced disks and rotors in gas turbine engines. The nickel base superalloy has a composition consisting essentially of, in weight percent, 3.0–4.0 Al, 0.02–0.04 B, 0.02–0.05 C, 12.0–14.0 Cr, 19.0–22.0 Co, 2.0–3.5 Mo, greater than 1.0 to 2.1 Nb, 1.3 to 2.1 Ta, 3.0–4.0 Ti, 4.1 to 5.0 W, 0.03–0.06 Zr, and balance essentially Ni aid incidental impurities. The superalloy combines ease of processing with high temperature capabilities to be suitable for use in various turbine engine disk, impeller, and shaft applications. The Co and Cr levels of the superalloy can provide low solvus temperature for high processing versatility. The W, Mo, Ta, and Nb refractory element levels of the superalloy can provide sustained strength, creep, and dwell crack growth resistance at high temperatures.

Abstract: A structural member comprises a main body formed from a cellular material. The structural member may be a casing for a rotary assembly e.g. a fan of a gas turbine engine. The main body may incorporate strengthening ribs and conduits and may have a random or graduated arrangement of different sized cells forming the cellular material. A recess may be defined on the radially inner face of the main body to receive an abradable material suitable for forming a seal with the blades of the fan.

Abstract: A lightweight high temperature bladed turbine disk intended for use in gas turbine engines. The bladed disk comprises a cast integral ring of single crystal airfoils with the primary and secondary crystallographic orientation being the same for each airfoil. Low-angle mismatch boundaries are present in the endwalls that couple adjacent airfoils. The cast ring of single crystal turbine blades is diffusion bonded to a high strength equiaxed disk. The resulting single crystal bladed disk is endowed superior performance, temperature capability, and lower weight and cost, relative to conventional turbines composed of individually cast single crystal blades, which are mechanically inserted into machined slots in the disk, or lower strength cast equiaxed blade rings that are diffusion bonded to a high strength turbine disk.

Abstract: A rotor assembly of an axial flow turbine engine has a bladed ring including a ring, and a plurality of turbine blades affixed to the ring and extending radially outwardly from the ring. There is a solid state weld joint between a central disk hub and the ring of the bladed ring. In one approach, the rotor assembly is prepared by bonding the plurality of turbine blades to the coarse-grain ring so that the turbine blades extend outwardly from the ring, providing the fine-grain central disk hub, and solid-state inertia welding the central disk hub and the ring of the bladed ring at a solid state weld joint.

Abstract: A monolithic rotor comprising first and second rotor regions axially aligned within the monolithic rotor and a transition zone therebetween. The first and second rotor regions are formed of different alloys and the transition zone having a composition that differs from and varies between the first and second rotor regions. The first rotor region is located within a high pressure region of the monolithic rotor and is formed from an alloy chosen from the group consisting of CrMoV low alloy steels, martensitic stainless steels containing about 11 to about 14 weight percent chromium, Fe—Ni alloys, and nickel-base alloys. The second rotor region is located within a low pressure region of the monolithic rotor and is formed from an alloy chosen from the group consisting of NiCrMoV low alloy steels and martensitic stainless steels containing about 11 to about 14 weight percent chromium.

Abstract: To protect an article with an aerodynamic surface, such as an aeroplane propeller or helicopter rotor, from erosive damage caused by flying particulate matter, a thin elastomeric protective covering is provided. This layer covers approximately 15% of a forward face (15) a leading edge (12), and approximately 90% of the rear face (13) of the article. Typically, it is made of polyurethane with hardness between 85 Shore A and 80 Shore D. It is applied by centrifugal casting using a silane log gammaglycidoxporpyl-tri-methoxysilane as a coupling agent when bonding to a metal surface such as aluminum.

Abstract: The invention concerns a casing aggregate for the turbine of an exhaust turbocharger. The invention is identified by the following characteristics: a spiral casing adapted for surround the running wheel of the turbine; a tongue-like wall part (tongue) in the inside of the spiral casing; an inlet connection; an outlet connection; a flange to connect to a bearing casing; wherein the casing aggregate is manufactured of thin-walled precision casting; wherein the casing aggregate is made of at least two parts, so that at least one separation joint is present; and the separation joint is arranged as follows: it runs in an axially perpendicular level; it runs along the apex line of the spiral casing; it extends over an arc of a circle of approximately 270 degrees; it lies outside of the area of the tongue.

Abstract: A high pressure centrifugal blower having vertically split casing and aluminum or steel impellers mounted on a common shaft housed within the casing, and at least two oil-enclosing bearing housings to rotatably support the rotors, where an integral gearbox is formed as part of the blower casing so as to increase the impeller rotational speed to achieve higher pressure, and axial impeller eye seals are utilized to reduce the clearance and enhance reliability for higher pressure applications.

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: An impeller for a magnetic-drive centrifugal pump includes a core for supporting a magnetic assembly of magnets. An inner barrier covers at least part of the magnets. The inner barrier hermetically isolates the magnetic assembly within the impeller. For example, in one embodiment the inner barrier may be sealed or hermetically connected to the core at one or more seams. An outer barrier overlies the inner barrier.

Abstract: Methods for repairing and manufacturing a gas turbine blade, and the gas turbine blade repaired and manufactured with such methods are presented with, for example, the repair method comprising providing a gas turbine blade, the blade comprising a blade tip and a blade body; removing at least one portion of the blade tip; providing at least one freestanding tip insert; and disposing the at least one tip insert onto the gas turbine blade body such that the at least one tip insert replaces the at least one removed portion of the blade tip.

Abstract: A turbine wall includes a metal substrate having front and back surfaces. A thermal barrier coating is bonded atop the front surface. A network of flow channels is laminated between the substrate and the coating for carrying an air coolant therebetween for cooling the thermal barrier coating.

Abstract: A mechanical kinetic vacuum pump with a stator (1), a rotor (6, 7) made from an aluminum or magnesium alloy and a rotor (6, 7) and a bearing shaft (3). The shaft (3) and the rotor (6, 7) are connected by a shrink- or screw-fit in a secure permanent connection. The rotor (6, 7) is made by spray forming. The main alloying component in the aluminum or magnesium alloy is silicon which is present in an amount such that the alloy has an expansion coefficient which essentially corresponds to the expansion coefficient of the shaft material.

Abstract: A method for connecting a wheel, such as a turbine wheel or compressor wheel, in a turbine wheel rotor. The method includes providing a shaft made of steel, and pouring a casting alloy around an end of the shaft, wherein the casting alloy includes an intermetallic compound of the system TiAl. The method is particularly well-suited making a connection of the turbine wheel and the shaft of an exhaust-gas turbocharger for motor vehicles using a casting process. In addition, a turbine wheel rotor, that includes a steel shaft, a cast wheel including a casting alloy fixedly connected to an end of the shaft. The casting alloy including an intermetallic compound of the system TiAl. A connection between the cast wheel and the shaft includes at least one of a friction fit, a positive fit, and an integral connection.

Abstract: A lightweight, composite structural element for turbo engines, includes a thin metallic shell and a metallic core structure, of which a large proportion of the volume is empty space, the shell and the core structure being rigidly connected to each other. The core structure has a spatial, felt-like and/or mesh-like construction and is made of one or more wires, strips, shavings, or comparable elements. The core structure is sintered together, and sintered to the shell.

Abstract: A turbine engine shroud segment is provided with a radially outer surface including a pair of spaced apart, opposed first and second edge portion surface depressions, for example spaced circumferentially, having a seal surface shaped to receive, in a surface depression formed between assembled adjacent segments in a shroud assembly, or axially assembled adjacent segments and engine members, a radially outer fluid seal member. The depression portions of a shroud segment are joined with the radially outer surface of the shroud segment through an arcuate transition surface. Stresses generated during engine operation in the shroud material are reduced, enabling practical use of a low ductility material, for example a ceramic matrix composite. The edge portion surface depressions are provided with a first shape and the fluid seal member, disposed at the depression, is provided with a surface of a second shape matched in shape with the first shape.

Abstract: There is provided a rotor for a turbo/drag vacuum pump, the rotor comprising an upstream rotor segment of the turbine type made of metal or alloy, and a downstream rotor segment of Holweck type made of composite material. The downstream segment of the rotor has a reinforcing structure made of long fibers that are distributed in a manner that varies as a function of the section under consideration: in the annular connection region connected to the upstream segment of the rotor, the fibers are inclined and/or spaced apart in order to conserve sufficient flexibility for the composite material to enable it to deform so as to track deformation of the metal of the upstream rotor segment while it is in operation; in contrast, the fibers are close together and form turns that touch in the downstream region of the skirt, thereby guaranteeing greater stiffness in order to withstand the mechanical stresses that occur during high-speed rotation of the rotor in operation.

Abstract: A method for securing a nozzle for a turbine is provided. The nozzle includes an airfoil having a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity is defined within the airfoil, the airfoil extending between an inner band and an outer band. The method includes extending at least one member through the airfoil, and at least one of the inner band and the outer band. The method further includes securing the nozzle assembly in position with at least one fastener such that the at least one member is coupled adjacent to at least one of the inner band and the outer band.

Abstract: One aspect of the invention is directed to an impeller made of a non-metallic, heat resistant material, comprising a generally cylindrical shaped body, first and second generally planar end faces and a side wall extending between the first and second faces. A plurality of passages have inlets circumferentially spaced apart from each other on the first face, outlets at the impeller sidewall, and connecting portions extending between the inlets and the outlets transverse to the central axis. Another aspect of the invention is directed to an impeller comprising a central hub portion and first and second impeller bases, including end faces, transverse to a central axis. Vanes extend from the central hub portion between the impeller bases. Cavities are formed between the impeller bases and between adjacent vanes. Molten metal inlets on the end faces for molten metal to reach the cavities. Pumps are also disclosed using the inventive impellers.

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 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 internal joint peg aperture; a refractory base with a post aperture configured to receive the first end of the refractory post, and with a peg aperture contiguous with the post aperture; and a joint peg with a first end and a second end, the joint peg including a retention shoulder, the joint peg configured to insert through the peg aperture in the refractory base with a retention bar or bolt inserted through an aperture in the joint peg of refractory post, and the retention shoulder engaging the refractory base.

Abstract: An airfoil for an internal combustion engine, such as a gas turbine, formed by use of a preform. The airfoil includes: an outer surface forming the foil shape; and a plurality of craze-free cooling passages extending through the airfoil. In the preferred embodiment, a root on the airfoil joins the airfoil to the hub of a gas turbine vane assembly. Also, in the preferred embodiment, the gas turbine vane assembly is adapted to receive replaceable airfoils.

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: An assembly that includes a CMC article, and a method of forming the assembly, so as to reduce the likelihood during a transient thermal condition of the CMC article becoming interlocked with the worn shank of a fastener used to secure the article to its support structure. The CMC article has oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings. The assembly further includes a support structure adjacent the article, and a fastener received in the hole of the CMC article and securing the CMC article to the support structure. The location of the chamfers at the perimeter of each opening eliminates a relatively sharp edge that could interlock with the worn shank of the fastener during a thermal excursion.

Abstract: A joint assembly for limiting an extension of the joint in the direction of a load path derived from an impact comprising a first member having a portion and a second member having a portion, the portions overlapping one another and arranged generally parallel to one another and secured together via securing means disposed through corresponding holes defined therein. One of the overlapping portions further defines, sequentially in the direction of extension, a shear neck, a pocket and a catcher portion. In the event of a worst-case impact load the securing means shears through the shear neck and the pocket and is arrested by the catcher portion, thereby the extension of the joint assembly is limited and the joint assembly remains integral.

Abstract: A high-pressure turbine nozzle-vane band for a gas turbine engine. The band includes 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 is 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 the cavity to be increased.

Abstract: A novel blade configuration does not exceed the permitted stresses for particular loads, especially as a result of centrifugal forces and which at the same time, allows the turbomachine to function with a high degree of efficiency. To this end, a moving blade for the turbomachine contains at least partially a cellular material, especially a foamed metal. The cellular material can be provided e.g. in the hollowed-out part of the moving blade.

Abstract: A flow-rectifying member comprising a plurality of vanes, an outer platform and an inner platform for having a flow-rectifying function to a fluid flowing thereinto, which is integrally constituted by annularly connecting a plurality of flow-rectifying member units each having an integral structure comprising a vane, an outer platform piece and an inner platform piece, with the adjacent outer platform pieces connected to each other, and with the adjacent inner platform pieces connected to each other; each flow-rectifying member unit comprising (a) a core comprising a web constituting the vane, and flanges integrally connected to both ends of the web for constituting the outer platform piece and the inner platform piece, and (b) a skin layer covering a surface of the core; and the skin layer being made of a rubber or a thermosetting resin having rubber elasticity.

Abstract: A blood pump having rotor and/or stator touch down zones to prevent pump failure or hernolysis which can occur if the rotor comes into contact with the stator due to power failure or mechanical shock. The touch down zones can include forming, or coating, portions of adjacent surfaces of the stator and rotor which can come into contact if a rotor touch down occurs. The materials used to form or coat the touch down zones can have properties which ensure that no consequential damage to the contacting surfaces occurs.

Abstract: A method enables a gas turbine engine compressor including a stator assembly and a rotor assembly to be assembled. The method comprises providing a casing formed from a plurality of rings, and coupling a first of the casing rings around the rotor assembly such that a radially inner surface of the first casing ring is axially aligned with, and radially outward from, a row of rotor blades extending from the rotor assembly. The method also comprises coupling a second of the casing rings to the first casing ring with a fastener assembly, such that the first casing ring radially inner surface facilitates insulating the fastener assembly from the compressor flowpath.

Abstract: A jet aircraft fan case containment design that uses polyurethane to absorb fan blade fragments and uses polyurethane to prevent fan blade fragments from penetrating the fan case. The polyurethane is used in place of or to supplement KEVLAR® and/or fiberglass wraps used to contain fan blade fragments. The polyurethane is also used in place of aluminum alloy and stiffening ribs in the fan case.

Abstract: A turbine engine shroud segment having a body including a circumferentially arcuate radially inner surface defining a circumferential arc and a radially outer surface is provided, at least at one axially spaced apart outer surface edge portion surface, with a surface depression extending circumferentially across the outer edge portion and including a planar seal surface. The planar seal surface is spaced apart radially outwardly from the circumferential arc defining a spaced apart chord of the arc. The planar seal surface is joined with the segment body radially outer surface through an arcuate transition surface. In a circumferential assembly of a plurality of the shroud segments into a turbine engine shroud assembly, at least one of the outer surface edge portions and its respective depression portion and fluid seal surface is distinct axially from an axially juxtaposed engine member by a separation therebetween.

Abstract: A turbine fuel pump includes: a casing for casing an electric motor; a pump housing disposed at the casing, and an impeller rotatably disposed in the pump housing. The pump housing includes a fuel passage between an intake port and a delivery port. The fuel passage includes a flow path defining a cross section S. The impeller has an outer periphery formed with a vane which force feeds the fuel in the fuel passage when the impeller is rotated with the electric motor. The vane defines a height H and a thickness T. The fuel passage defines the following typical dimension Rm: Rm=S/(2H+T). A wall of the flow path defining the cross section S is profiled by a profile length Lp. The profile length Lp divided by the typical dimension Rm makes a dimension ratio Lp/Rm in a first range from 11 to 16.

Abstract: A steam turbine is provided that includes in an exemplary embodiment, a steam inlet pipe coupled to a steam inlet port in a steam turbine housing. At least a portion of the steam inlet pipe is fabricated from at least one of a shape memory alloy having a memorized activated configuration and a negative thermal expansion ceramic having an activated configuration.

Abstract: Small winglets placed at the outer end of each fan blade substantially reduce the vortices created in conventional fans by the pressure differential between the low pressure and high pressure sides of the blade. The winglet acts as a barrier, which substantially blocks leakage around the blade tip, thus suppressing vortices. Technical advantages include noise reduction, because there are no shedding vortices to create noise as the blades pass the struts; increased aerodynamic efficiency of the fan, providing higher air flow for the same fan speed, size, and power, because less energy is lost in vortices; and minimal cost impacts, because housings currently used for fans can still be used with standard finger guards and because winglets and blades can be formed integrally of injection molded plastic.

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 transition portion (58) and a blade containment portion (54) and a downstream portion (60). The upstream portion (56) has a flange (42) connecting the metal casing (40) to a flange (48) on axially adjacent casing (46). The blade containment portion (54) has a greater thickness (T2) than the thickness (T1) of the upstream portion (54) and the downstream portion (60). The downstream portion (60) has impact protection means (64) located on its inner surface (62) to protect the downstream portion (60) of the containment casing (40). The impact protection means (64) comprises a plurality of radially inwardly and circumferentially extending ribs (80) on the inner surface (62) of the downstream portion (60) to act as spacer between an inner portion of a detached fan blade (34) and the downstream portion (60).

Abstract: A turbine blade extends along a major axis from a root region via a blade leaf region capable of being acted upon by hot gas to a head region. The turbine blade is formed essentially from carbon-fiber-reinforced carbon, at least the blade leaf region having a blade outer wall with carbon-fiber-reinforced carbon, the blade outer wall being surrounded by a protective layer.

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: 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 fan outlet guide vane assembly (36) for a turbofan gas turbine engine (10) comprises a fan casing (32) and a plurality of circumferentially spaced radially extending fan outlet guide vanes (34). The fan outlet guide vanes (34) are secured at their radially outer ends to the fan casing (32). A plurality of panels (40) are secured to the fan casing (32). Each panel (40) is arranged between two adjacent fan outlet guide vanes (34) to define the flow path between the fan outlet guide vanes (34). Each panel (40) comprises a perforated skin (42) and a honeycomb structure (44) to form an acoustic treatment structure. The perforated skin (42) defines the flow path between the fan outlet guide vanes (34). The pressure equalization across the panels (40) minimises the possibility of the panels (40) being removed.

Abstract: A blood pump having rotor and/or stator touch down zones to prevent pump failure or hemolysis which can occur if the rotor comes into contact with the stator due to power failure or mechanical shock. The touch down zones can include forming, or coating, portions of adjacent surfaces of the stator and rotor which can come into contact if a rotor touch down occurs. The materials used to form or coat the touch down zones can have properties which ensure that no consequential damage to the contacting surfaces occurs.

Abstract: The invention relates to a steam turbine (3) comprising an optical measuring system (60) for measuring a moving blade vibration. A transmitter (55) produces a light beam (61) which strikes the moving blades (27, 29, 31, 33) and is reflected by these into a receiver (57). By providing that the transmitter (55) is separated from the receiver (56), the invention achieves a measuring angle that actually reduces the scattered light effect of the steam enough to enable reliable optical measurements of the blades vibration. The invention also relates to a method for measuring the vibration of a moving blade (33) in a flow channel (19, 21, 23, 25) of a steam turbine (3).

Abstract: An integrated engineering analysis system that determines at least one final output value in response to at least one initial input value. A first subprocesses provides at least one output value in response to the initial input value. A plurality of subprocesses provide a plurality of output values in response to the output values of the first subprocess. The plurality of output values and the output value of the first subprocess are inputted into at least one of the plurality of subprocesses. A command code executes each of the plurality of subprocesses in response to the output values and determines which one of the plurality of subprocesses to run and a final subprocess provides a final output. The final output is the result of a plurality of calculations executed by the plurality of subprocesses and the command code compares the final output with the initial input.

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.