An improved turbine spring clip seal (10) for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal (10) may include an inner housing (14) and an outer housing (12). The inner housing (14) or the outer housing (12), or both, may be shortened relative to conventional clips and may include a cooling channel (26) proximate to a point of attachment to the combustor basket.
The present invention provides for high thermal conductivity paper that comprises a host matrix (10), and high thermal conductivity materials (12) added to a surface of the host matrix in a specific pattern (12). The high thermal conductivity materials are comprised of one or more of nanofillers, diamond like coatings directly on the host matrix, and diamond like coatings on the nanofillers. In particular embodiments the specific pattern comprises one or more of a grid, edging, banding centering and combinations thereof and the high thermal conductivity materials cover 15-55% of the surface of the host matrix. Multiple surfaces, including sub layers my have patterning.
D21H 17/67 - Water-insoluble compounds, e.g. fillers or pigments
D21H 19/68 - Coatings characterised by a special visual effect, e.g. patterned or textured uneven, broken or discontinuous
B32B 29/06 - Layered products essentially comprising paper or cardboard specially treated, e.g. surfaced, parchmentised
B32B 29/02 - Layered products essentially comprising paper or cardboard next to a fibrous or filamentary layer
H01B 3/52 - Insulators or insulating bodies characterised by the insulating materialsSelection of materials for their insulating or dielectric properties mainly consisting of organic substances fibrous materials woodInsulators or insulating bodies characterised by the insulating materialsSelection of materials for their insulating or dielectric properties mainly consisting of organic substances fibrous materials paperInsulators or insulating bodies characterised by the insulating materialsSelection of materials for their insulating or dielectric properties mainly consisting of organic substances fibrous materials pressboard
3.
GAS TURBINE COMBUSTION TRANSITION DUCT PROVIDING TANGENTIAL TURNING OF THE FLOW
A transition duct (122) for routing a gas flow from a combustor (124) to the first stage (126) of a turbine section in a combustion turbine engine has an internal passage from an inlet (140) to an outlet (142) that is offset from the inlet (140) in the longitudinal, radial and tangential directions. The offset outlet (142) and the curved internal passage discharge the gas flow toward the first stage blade array (126) at an angle (150) in the tangential direction (146) relative to the longitudinal direction (148). This angled discharge (150) can be presented directly to the blades (128), thus avoiding the need for first stage vanes and the associated costs and complexity
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
4.
HIGH POWER DENSITY SEAL-LESS TUBULAR SOLID OXIDE FUEL CELL BY MEANS OF A WIDE INTERCONNECTION
The present invention is a solid oxide fuel cell that includes at least one flat support tube having a first side, a second side, and an outer surface and at least one interconnection (3) deposited to the full surface of the outer surface of at least one side of the tube. At least one support tube comprises a solid electrolyte layer (4) that is deposited over an outer surface of the support tube. At least a portion of the interconnect is covered with electrolyte and at least one anode (5) is applied over the electrolyte.
The present invention provides for a resin mixture that comprises a highly structured resin 40 and a less structured resin 50. The highly structured resin 40 and the less structured resin 50 are mixed to a ratio of between 1:9 and 4:1 by volume, with a more particular ratio of 1:5 to 3:1. The highly structured resin forms ordered micro regions and the ordered micro regions impose order on surrounding less structured resin molecules. The micro regions are essentially groups of the HS resin that will naturally form order structures.
C08L 101/00 - Compositions of unspecified macromolecular compounds
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
H01B 3/00 - Insulators or insulating bodies characterised by the insulating materialsSelection of materials for their insulating or dielectric properties
The present invention provides for a sulfur detector (8) that comprises a gaseous flow (2), and a zeolite material disposed in the gaseous flow. Although various types of sulfur can be detected, the present invention is particularly suited for dimethyl sulfide and organic sulfur. The zeolite material changes color in the presence of sulfur by physically binding sulfur from the gaseous flow (2), which is also referred to as physical adsorption. The zeolite material is regenerable, and regenerating the zeolite material releases sulfur and returns to an original color.
G01N 21/78 - Systems in which material is subjected to a chemical reaction, the progress or the result of the reaction being investigated by observing the effect on a chemical indicator producing a change of colour
In one embodiment the present invention provides for a regenerable sulfur remover that comprises a gaseous flow 2, a first layer in line with the gaseous flow 6, and a second layer 8 in line with the first layer. The first layer comprises a physical absorber of sulfur; the second layer comprises a pyrophoric material capable of being reduced by the gaseous flow. To regenerate the adsorbing layer, a blower 22 blows air first over the second layer, the air flow is heated by passing over the second layer, and then over the first layer. The heated air flow removes sulfur from the first layer, and the air flow is exhausted after removing sulfur from the first layer.
In one application the mix grafted and non grafted invention provides for high thermal conductivity resin that comprises a host resin matrix 32 with a first class of grafted 31 high thermal conductivity particles that are grafted to the host resin matrix. Also a second class of non-grafted 30 high thermal conductivity particles that are not directly grafted the host resin matrix 32. The first class and the second class comprise approximately 2-60% by volume of the high thermal conductivity resin. The first class of grafted particles and the second class of non-grafted particles are high thermal conductivity fillers are from 1-1000 nm in length, and have an aspect ratio of between 3-100.
In one embodiment the present invention provides for a method of forming HTC dendritic fillers 40 within a host resin matrix that comprises adding HTC seeds 42 to the host resin matrix. The HTC seeds have been surface functionalized to not substantially react with one another. The seeds then accumulate HTC building blocks 42, and the HTC building blocks have also been surface functionalized to not substantially react with one another. Then assembling the HTC building blocks with the HTC seeds to produce HTC dendritic fillers 40 within the host resin matrix.
In one embodiment of the present invention as used for impregnating a composite tape (56) with HTC particles provides for permeating a fabric layer (51) of the composite tape with HTC particles and impregnating an impregnating resin into the composite tape through the fabric layer (51). At least 5% of the HTC particles permeated into the fabric layer are carried out of the fabric layer and into a mica layer (52) bound to the fabric layer by the impregnating resin. In some embodiments the impregnating resin itself contains HTC particles.
B32B 27/20 - Layered products essentially comprising synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
B32B 29/02 - Layered products essentially comprising paper or cardboard next to a fibrous or filamentary layer
H01B 3/00 - Insulators or insulating bodies characterised by the insulating materialsSelection of materials for their insulating or dielectric properties
11.
INTEGRATED GASIFICATION COMBINED CYCLE WITH PREHEATING OF NITROGEN / OXYGEN FROM AIR SEPARATOR
A system and method for increasing the efficiency and/or power produced by an integrated gasification combined cycle system by increasing the integration between the air separation unit island (200) of the integrated gasification combined cycle system and the remainder of the system. By integrating one or more of the nitrogen and oxygen gas product streams (220, 205) from the air separation unit (200) in the remainder of the integrated gasification combined cycle system, heat may be utilized that helps to increase the efficiency of the combustion reaction and/or the gasification reaction used to produce the syngas utilized in the system.
F01K 23/06 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
F02C 3/28 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being solid or pulverulent, e.g. in slurry or suspension using a separate gas producer for gasifying the fuel before combustion
C10J 3/00 - Production of gases containing carbon monoxide and hydrogen, e.g. synthesis gas or town gas, from solid carbonaceous materials by partial oxidation processes involving oxygen or steam
12.
REFRACTORY COMPONENT WITH CERAMIC MATRIX COMPOSITE SKELETON
Aspects of the invention relate to a construction system and method for components in high temperature environments, such as the hot gas path components of a turbine engine. Such a component includes a skeleton (12) and a coating (14). The skeleton (12) is formed by a plurality of interconnected frame members (16), which give the component its general shape. The frame members (16) are made of ceramic matrix composite. A coating (14) is provided around at least a portion of the skeleton (12). The coating (14) is a refractory material, such as refractory ceramic. Examples of turbine engine components that can be constructed according to aspects of the invention are airfoils (10) with or without platforms (38), ring segments (66), combustor tiles and heat shields. A component according to aspects of the invention can be made using low cost fabrication and construction methods.
A system and method for increasing the efficiency and/or power produced by an integrated gasification combined cycle system by increasing the integration between the air separation unit island, the heat recovery steam generator and the remainder of the system. By integrating heat produced by the heat recovery steam generator in the remainder of the integrated gasification combined cycle system, heat may be utilized that may have otherwise been lost or used further downstream in the system. The integration helps to increase the efficiency of the combustion reaction and/or the gasification reaction used to produce the syngas utilized in the integrated gasification combined cycle system.
F01K 23/06 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
F01K 23/10 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
F02C 3/28 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being solid or pulverulent, e.g. in slurry or suspension using a separate gas producer for gasifying the fuel before combustion
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
14.
A-TIG WELDING OF COPPER ALLOYS FOR GENERATOR COMPONENTS
The present invention provides for the welding of copper using activated TIG welding (8). In particular, the copper coils (6) of electrical generators (2) are welded using the present invention.
B23K 35/00 - Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
B23K 35/22 - Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
B23K 35/36 - Selection of non-metallic compositions, e.g. coatings, fluxesSelection of soldering or welding materials, conjoint with selection of non-metallic compositions, both selections being of interest
B23K 9/167 - Arc welding or cutting making use of shielding gas and of a non-consumable electrode
B23K 9/23 - Arc welding or cutting taking account of the properties of the materials to be welded
The present invention comprises a seamless flat solid oxide fuel cell that comprises an anode layer (10), an electrolyte layer (8), and a cathode. The cathode contains a series of ellipsoidal annular spaces (2) and the series of ellipsoidal annular spaces have an open end and a closed end. Ribs (6) separate the ellipsoidal annular spaces (2) and the closed end has exclusively rounded edges.
The present invention provides a method of depositing a stepped-gradient fuel electrode onto a fuel cell support 2 and the resulting fuel cell, that comprises placing a solid oxide fuel cell support that has at least an air electrode layer 4 and an electrolyte layer 6 into an atmospheric plasma sparying chamber and measuring spray parameters of an atmospheric plasma spray to obtain reactive oxides, conductive metal and graphite phases. Then spraying the spray parameters onto the solid oxide fuel cell support to produce multiple sub-layers 8 on the solid oxide fuel cell support, and adjusting usage of the atmospheric plasma spray. The adjusting of the hydrogen usage comprises using high hydrogen levels for the initial spraying of the sub-layers producing a first gradient region, and as lower hydrogen level for subsequent spraying of the sub-layers, producing a second gradient region.
H01M 8/12 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte
C23C 4/12 - Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
A method of forming a ceramic matrix composite (CMC) article (30) or a composite article (60) that minimizes the risk of delaminations while simultaneously maintaining a desired degree of porosity in the material. A pressure P applied against a surface of the article during a sintering process is controlled to be high enough to resist a separation force between the plies (66) of the CMC material (62) caused by anisotropic shrinkage of the material and/or to resist a separation force caused by differential shrinkage between the CIVIC material and an adjoined monolithic ceramic material (64). The pressure is also controlled to be low enough to avoid undue consolidation of the materials and to provide a desired degree of porosity in the sintered article. The pressure may be applied by delta-alpha tooling, and it may be varied verses the time of the sintering heating and/or across the article surface.
Aspects of the invention are directed to systems for reducing the cooling requirements of a ring seal in a turbine engine. In one embodiment, the ring seal (54) can be made of a ceramic material, such as a ceramic matrix composite. The ceramic ring seal (54) can be connected to metal isolation rings (40, 42) by a plurality of pins (76, 78). The hot gas face (72) of the ring seal (54) can be coated with a thermal insulating material (74). In another embodiment, a ring seal (120) can be made of metal, but it can be operatively associated with a ceramic heat shield (122). The metal ring seal (120) can carry the mechanical loads imposed during engine operation, and the heat shield (122) can carry the thermal loads. By minimizing the amount of ring seal cooling, the ring seal systems according to aspects of the invention can result in improved engine performance and emissions
In one embodiment the present comprises an air inlet 2, a series of fuel cells 6, a new fuel inlet 14, a fuel distributor 16, a recirculation plenum 19, and an exhaust 12. Fresh fuel from the fuel distributor 16 enters the fuel cell stack in a middle-third section of the fuel cell stack, and the fresh fuel is divided into an exhaust fuel 12 flow and a recirculation fuel flow 18. The exhaust fuel flow passes along a first portion of the series of fuel cells to the exhaust, and the recirculation fuel flow passes along a second portion of the series of fuel cells to the recirculation plenum and mixes with new fuel from the new fuel inlet in the fuel distributor. The recirculation plenum is located at an opposite end of the fuel cell stack from the exhaust, and the fuel-cell stack is of a seal-less design.
Aspects of the invention are directed to an interface (10) between an exhaust cylinder (20) and an exhaust diffuser (22) in a turbine engine. The interface (10) allows relative radial movement of the exhaust diffuser (22) and the exhaust cylinder (20). According to aspects of the invention, the diffuser (22) and the cylinder (20) are operatively connected about their peripheries by a plurality of connecting members, which can be tie rods (40). Each connecting member can be pivotally connected at a first end (42) to a joint bolt (80) affixed to the exhaust cylinder (20) and at a second end (44) to an exhaust diffuser (22). Thus, the connecting members can join the cylinder (20) and the diffuser (22) in the axial direction, while allowing for the differential thermal expansion of the two components. Relative circumferential movement between the cylinder (20) and the diffuser (22) can be reduced by positioning neighboring connecting members at opposing angles in relation to one another.
F02K 1/04 - Mounting of an exhaust cone in the jet pipe
21.
ELECTRIC POWER GENERATION SYSTEM USING A PERMANENT MAGNET DYNAMOELECTRIC MACHINE FOR STARTING A COMBUSTION TURBINE AND FOR GENERATING UNINTERRUPTIBLE EXCITATION POWER
An electric power generation system (10) with a combustion turbine (12) as a prime mover for a main generator (16) is provided. The power generation system includes a dynamoelectric machine (30) that may be used both as the starting motor and as a generator to provide a source of excitation power that is essentially independent of a local power system and thereby not susceptible to voltage fluctuations and/or power interruptions.
H02P 9/08 - Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
H02P 9/30 - Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices
F02N 11/04 - Starting of engines by means of electric motors the motors being associated with current generators
F02N 11/06 - Starting of engines by means of electric motors the motors being associated with current generators and with ignition apparatus
H02M 5/458 - Conversion of AC power input into AC power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into DC by static converters using discharge tubes or semiconductor devices to convert the intermediate DC into AC using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
22.
CMC WITH MULTIPLE MATRIX PHASES SEPARATED BY DIFFUSION BARRIER
A ceramic matrix composite (CMC) material (10) with increased interlaminar strength is obtained without a corresponding debit in other mechanical properties. This is achieved by infusing a diffusion barrier layer (20) into an existing porous matrix CMC to coat the exposed first matrix phase (19) and fibers (12), and then densifying the matrix with repeated infiltration cycles of a second matrix phase (22). The diffusion barrier prevents undesirable sintering between the matrix phases and between the second matrix phase and the fibers during subsequent final firing and use of the resulting component (30) in a high temperature environment.
A method for optimizing the availability of a technical object, comprises the steps of providing a serviceable technical object; defining a service plan; defining a setpoint availability (230); maintaining the serviceable technical object according to the service plan (200); determining the actual availability of the serviceable technical object (220); and automatically adjusting the service plan according to a difference between the setpoint availability and the actual availability.
A method for maintaining a system consisting of a plurality of components, comprises the steps of collecting maintenance information for each component of the system for which maintenance information is available (220), providing a maintenance schedule for components of the system (230); operating the system (240); and maintaining the system wherein during scheduled maintenance of a component information about the status of that component is acquired, during a failure of a component information about the failure of that component is acquired (240), and modifying the maintenance schedule according to the acquired information (250).
A trailing edge attachment (10) for a composite turbine airfoil. The trailing edge attachment (10) may include an attachment device (28) for attaching the trailing edge attachment (10) to the airfoil. The attachment device (28) may include a plurality of pins (40) extending through the attachment device (28) and into the trailing edge (32) of the turbine airfoil. The trailing edge attachment (10) may also include a spanwise cooling channel for feeding a plurality of cooling channels (38) extending between a leading edge (18) of the trailing edge attachment (10) and a trailing edge (20) of the attachment device (28). The attachment device (28) may be configured to place the leading edge (18) of the composite airfoil in compression, thereby increasing the strength of the composite airfoil.
An attachment device (10) for coupling one or more removable turbine components (12) to a carrier of a turbine engine. The attachment device (10) may include a securement structure (22) rotatable about an axis of rotation (56) and including one or more arms (30) for grasping an arm (26) extending from a support structure (18). A fastener (16) may extend from the support structure (18) and be inserted into a fastener (16) receiving recess (46) in the securement structure (22) for preventing the securement structure (22) from rotating and becoming disengaged from the support structure (18). The attachment device (10) may also include a fastener retaining device (50) for preventing the fastener (16), which may be a threaded bolt, from becoming disengaged from the attachment device (10), traveling downstream in a turbine, and damaging a turbine assembly.
Aspects of the invention relate to a system for attaching a ring seal (52) to a vane carrier (40) in a turbine engine such that the ring seal (52) can radially expand and contract at least partially independently of the vane carrier (40). The system can also be configured to substantially restrict axial and/or circumferential movement of the ring seal (52). In one embodiment, the ring seal (52) can include a plurality of radial slots (70) circumferentially spaced about the ring seal (52). A pin (76) can extend substantially through each of the slots (70) and into operative engagement with isolation rings (44, 46), which are connected to the vane carrier (40). In another embodiment, the ring seal (52) and the isolation rings (44, 46) can include a series of axially-extending protrusions (90, 92) extending substantially circumferentially about each component. The protrusions (92) on the ring seal (52) can substantially matingly engage the protrusions (90) on the isolation rings (44, 46). The protrusions (90, 92) can be configured as a Hirth coupling (93)
A seal assembly is provided to be positioned about a rotor shaft 24 of an electric power generator 22 to prevent leakage of cooling fluid from a generator housing. A bracket 26 is affixed to the housing. The bracket includes an inlet connectable to power plant piping external to the generator for receiving a supply of sealing fluid. The power plant piping is connectable along a radial position that may vary from plant-to-plant. The inlet is in communication with a bracket passageway 32 for admitting the sealing fluid in a radially inner section of the bracket. A sealing cartridge 28 is mountable in an annulus defined by the bracket. The sealing cartridge includes at least one cartridge passageway 44 in communication with the bracket passageway for admitting the supply of sealing fluid and passing the supply of sealing fluid to establish a sealing boundary about the rotor shaft. At least one of the bracket or the sealing cartridge includes a first sealing fluid-distribution channel 30 extending along a radial direction for providing fluid communication between the bracket passageway and the at least one passageway in the sealing cartridge regardless of a variable installation position of the bracket to accommodate variation in the radial position of the power plant piping for receiving the supply of sealing fluid.
A system and method for early detection of a failure of a gas turbine engine airfoil (10), such as but not restricted to a burn through of the airfoil outer skin (12). A sensor (52) provides a signal (54) responsive to a condition of fluid flowing through an outer cooling chamber (24) of the airfoil. A detected change in the condition of the fluid is correlated to a failure of the airfoil, which for example can be detected by measuring the static fluid pressure. An increase in the static pressure of fluid in the outer cooling chamber may indicate a breach in the region of the leading edge of the airfoil. A decrease in the static pressure of fluid in the outer cooling chamber may indicate a breach along other portions of the profile of the airfoil outer skin. Both pressure and temperature parameters of the fluid may be measured and coincident changes thereof correlated to a condition of failure of the airfoil
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
F01D 21/12 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to temperature
F01D 21/14 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
30.
METHOD OF REPAIRING A THREADED GENERATOR ROTOR BLOWER ASSEMBLY
A method of repairing a generator blower hub assembly (12) and rotor blade (10) removed from the generator blower hub assembly (12) where the rotor blade (10) has fatigued material in threads of a threaded blade root (14). The method may include removing (32) at least a portion of the fatigued material to form the blade root (14) to a first or new diameter. Threads may be formed (36) on the diameter of the blade root (14) using a roll forming process. A collar (20) may be secured within a threaded hole (16) formed in the generator blower hub assembly (12) where the collar (20) includes internal threads (35) for receiving the threads formed on the diameter of the blade root (14), which may be threaded into the collar (20). Collar (20) may be fabricated of steel alloy and include relief groove (40) for improving the fatigue resistance of the threaded blade root (14) when reassembled into the generator blower hub assembly (12).
A gasification power plant (10) includes a compressor (32) producing a compressed air flow (36), an air separation unit (22) producing a nitrogen flow (44), a gasifier (14) producing a primary fuel flow (28) and a secondary fuel source (60) providing a secondary fuel flow (62). The plant also includes a catalytic combustor (12) combining the nitrogen flow and a combustor portion (38) of the compressed air flow to form a diluted air flow (39) and combining at least one of the primary fuel flow and secondary fuel flow and a mixer portion (78) of the diluted air flow to produce a combustible mixture (80). A catalytic element (64) of the combustor (12) separately receives the combustible mixture and a backside cooling portion (84) of the diluted air flow and allows the mixture and the heated flow to produce a hot combustion gas (46) provided to a turbine (48). When fueled with the secondary fuel flow, nitrogen is not combined with the combustor portion.
F23C 13/06 - Apparatus in which combustion takes place in the presence of catalytic material in which non-catalytic combustion takes place in addition to catalytic combustion, e.g. downstream of a catalytic element
F02C 3/28 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being solid or pulverulent, e.g. in slurry or suspension using a separate gas producer for gasifying the fuel before combustion
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
A method of instrumenting a first component (210) for use in a combustion turbine engine (10) wherein the first component (210) has a surface contacted by a second component during operation of the combustion turbine engine (10). The method may include depositing an insulating layer (260) on the surface of the first component (210) and depositing a first conductive lead (232, 254) on the insulating layer (260). A piezoelectric material (230) may be deposited in electrical communication with the first conductive lead (232, 254) and a second conductive lead (236, 256) may be deposited in electrical communication with the piezoelectric material (230) and be insulated from the first conductive lead (232, 254) to form a sensor (50) for detecting pressure exerted on the surface of the first component (210) during operation of the combustion turbine engine (10)
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
H01L 41/113 - Piezo-electric or electrostrictive elements with mechanical input and electrical output
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
G01P 15/09 - Measuring accelerationMeasuring decelerationMeasuring shock, i.e. sudden change of acceleration by making use of inertia forces with conversion into electric or magnetic values by piezoelectric pick-up
33.
GAS TURBINE COMBUSTOR BARRIER STRUCTURES FOR SPRING CLIPS
A barrier structure (302) blocks exit of spring clip fragments (317) that may break off from a spring clip assembly disposed between a gas turbine engine combustor (300) and a transition piece component (360). The barrier structure (302) may additionally comprise an aspect (326) effective to restrict a spring clip's (310, 311) radially inward compression, thereby reducing or eliminating damage to the spring clip (310, 311) during shipping and handling. The barrier structure (302) additionally may comprise an aspect (330) to restrict access by a human hand to the free ends (318) of the spring clips (310, 311). This aspect (330) reduces or eliminates the undesired lifting of the compressor by grabbing the spring clips (310, 311) during combustor transport, installation or removal. Accordingly, barrier structure embodiments are provided that reduce stress on spring clips, and that prevent the exit of spring clips from a containment space partly formed by the barrier structure.
An inspection head (10,140,206,250) where non-destructive inspection is structured to fit into narrow spaces, and to accurately and repeatably move an inspection probe (138,298) along a surface to be inspected. Movement of the inspection head (10,140,206,250) along an X, Y, Z, and Φ-axis is precisely controlled by individual drive mechanisms.
G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details
G01N 29/265 - Arrangements for orientation or scanning by moving the sensor relative to a stationary material
G01N 27/90 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
35.
INSPECTION OF COMPOSITE COMPONENTS USING MAGNETIC RESONANCE IMAGING
Embodiments of the invention relate to a system and method for non-destructively inspecting a component (20) that is at least partially made of a composite material. In one embodiment, the composite component (20) can be a ceramic matrix composite vane or a liner for a turbine engine. Aspects of the invention involve imaging the component (20) using a magnetic resonance imaging (MRI) apparatus (14). To enhance the image, the component (20) can be infiltrated with at least one contrast media (24), which can be in liquid or gas form. By imaging the component (20) using the MRI apparatus (14), internal and/or external defects of the component can be revealed. In addition, external and/or internal features (19, 25) of interest can examined for dimensional accuracy, among other things.
G01N 24/08 - Investigating or analysing materials by the use of nuclear magnetic resonance, electron paramagnetic resonance or other spin effects by using nuclear magnetic resonance
G01R 33/44 - Arrangements or instruments for measuring magnetic variables involving magnetic resonance using nuclear magnetic resonance [NMR]
A transition duct (30) for a gas turbine engine (2) having improved cooling and reduced stress levels. The transition duct may be formed of two panels ((36, 38) joined together with welds (40) disposed remote from the bent corner regions (34) of the panels. Cooling channels (32) extending longitudinally in the direction of flow of the hot combustion gas carried by the duct are formed within each panel, including the corner regions. Because the entire annular width (W) of the transition duct is cooled, the gap (G) separating adjacent ducts around the inlet to the turbine (4) may be reduced when compared to prior art designs. Two-panel construction with welds remote from the corner regions is facilitated by maintaining the minimum bend radius in the corners (R2) and in the direction of flow (R4) to be greater than in prior art designs.
patents