Memory controller for heterogeneous configurable integrated circuit

A system including a configurable memory controller, a memory interface, and a configurable high speed communications fabric comprising a plurality of interconnect stations arranged in an array and operable to implement a plurality of pipelined buses, where the configurable memory controller is operably coupled to the configurable high speed communications fabric using a first interconnect station of the plurality of interconnect stations, where the memory interface is operably coupled to the configurable high speed communications fabric using a second interconnect station of the plurality of interconnect stations, where the plurality of interconnect stations are configured to satisfy a timing requirement of the memory interface, and where the configurable memory controller, the memory interface, and the configurable high speed communications fabric are associated with a configurable integrated circuit.

Multi-spectral photon converting imaging apparatus

A multi-spectral photon converting imaging apparatus and method are disclosed. A plurality of photons in a first received band and a plurality of photons in a second received band are received by a first nanoparticle photon conversion material. The first nanoparticle photon conversion material converts the plurality of photons in the first received band to a plurality of photons in a first converted band, and the plurality of photons in the second received band to a plurality of photons in a second converted band. An image sensor receives the plurality of photons in the first converted band and the plurality of photons in the second converted band, and generates a digitized image of the scene based on the plurality of photons in the first converted band and the plurality of photons in the second converted band.

Frangible Gas Turbine Engine Airfoil

An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments. 1. An airfoil for an aircraft engine , the airfoil comprisinga plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base, including at least one discontinuous ply includinga first ply segment,a second ply segment, anda first butt joint disposed between the first ply segment and the second ply segment along a first fragment profile to frangibly attach the first and second ply segments.2. The airfoil of claim 1 , wherein the plurality of composite plies includes at least two discontinuous plies claim 1 , each of the discontinuous plies including a discrete butt joint between them claim 1 , the two butt joints being staggered in the spanwise direction.3. The airfoil of claim 1 , wherein the butt joint extends at least partially along the chordwise direction.4. The airfoil of claim 1 , wherein the first ply segment includes a first composite material and the second ply segment includes a second composite material claim 1 , the first composite material being different from the second composite material.5. The airfoil of claim 1 , wherein the butt joint extends at least partially in the spanwise direction.6. The airfoil of claim 1 , wherein the airfoil defines an overall airfoil height between the airfoil base and airfoil tip claim 1 , and wherein the butt joint is positioned at a first break height claim 1 , the ...

SYSTEM AND METHOD FOR CAPTURING IMAGES USED IN FACIAL RECOGNITION THROUGH EFFECTIVE USE OF EXPOSURE MANAGEMENT

A system and method for capturing images used in a facial recognition system are provided. The system and method are configured to generate a sequential set of control signals configured to cause a camera to capture a corresponding sequential set of probe images of a face of an individual. Each control signal in the sequential set of control signals is configured to cause the camera to capture a probe image of the sequential set of probe images using a different exposure time. The different exposure times associated with the sequential set of control signals together form a predetermined profile configured to enable capture of a usable image from the sequential set of probe images despite variation in at least one of an amount of light and a skin tone of the face of the individual. 1. An article of manufacture , comprising: generating a first sequential set of control signals configured to cause a camera to capture a corresponding first sequential set of probe images of a face of an individual', 'wherein each control signal in the first sequential set of control signals is configured to cause the camera to capture a probe image of the first sequential set of probe images using a different exposure time, the different exposure times associated with the first sequential set of control signals together forming a first predetermined profile configured to enable capture of a usable image from the first sequential set of probe images despite variation in at least one of an amount of light and a skin tone of the face of the individual., 'a non-transitory computer storage medium having a computer program encoded thereon that when executed by a controller is used to capture images for use in a facial recognition system, the computer program including code for2. The article of manufacture of wherein the code for generating the first sequential set of control signals includes code for selecting the first predetermined profile from among a plurality of predetermined profiles ...

Memory Controller For Heterogeneous Configurable Integrated Circuit

A system including a configurable memory controller, a memory interface, and a configurable high speed communications fabric comprising a plurality of interconnect stations arranged in an array and operable to implement a plurality of pipelined buses, where the configurable memory controller is operably coupled to the configurable high speed communications fabric using a first interconnect station of the plurality of interconnect stations, where the memory interface is operably coupled to the configurable high speed communications fabric using a second interconnect station of the plurality of interconnect stations, where the plurality of interconnect stations are configured to satisfy a timing requirement of the memory interface, and where the configurable memory controller, the memory interface, and the configurable high speed communications fabric are associated with a configurable integrated circuit. 1. A method for routing data in a configurable integrated circuit , comprising:programming a plurality of interconnect stations into a station mesh for high speed data transfer;configuring a plurality of programmable logic blocks (“PLBs”) into a PLB array mesh for performing logic functions;programming a plurality of pipelined buses between the station mesh to facilitate high speed data transfer between the interconnect stations; andselectively linking at least a portion of the plurality of interconnect stations to a portion of the plurality of PLB s to merge the station mesh into the PLB array mesh to form a high speed communications fabric.2. The method of claim 1 , further comprising programming a portion of the plurality of PLBs to perform a function of memory control.3. The method of claim 1 , further comprising configuring a special purpose block into the high speed communications fabric.4. The method of claim 1 , wherein programming a plurality of interconnect stations into a station mesh includes arranging interconnect stations in an array configuration.5. ...

METHODS, SYSTEMS, AND COMPUTER READABLE MEDIA FOR REDUCING THE IMPACT OF FALSE DOWNLINK CONTROL INFORMATION (DCI) DETECTION IN LONG TERM EVOLUTION (LTE) PHYSICAL DOWNLINK CONTROL CHANNEL (PDCCH) DATA

Methods, systems, and computer readable media for reducing the impact of false downlink control information (DCI) detection in long term evolution (LTE) physical downlink control channel (PDCCH) data are disclosed. According to one method, an LTE multi-UE simulator receives PDCCH data from an evolved node B (eNode B). The LTE multi-UE simulator applies blind DCI decoding to decode at least one DCI value from channel control elements that carry the PDCCH data. The LTE multi-UE simulator applies at least one false DCI detection countermeasure to identify as true or false DCIs from the DCIs detected using the blind decoding. 1. A method for reducing the impact of false downlink control information (DCI) detection in long term evolution (LTE) physical downlink control channel (PDCCH) data , the method comprising: receiving PDCCH data from an evolved node B (eNode B);', 'applying blind DCI decoding to decode at least one DCI value from channel control elements (CCEs) that carry the PDCCH data; and', 'applying at least one false DCI detection countermeasure to identify true or false DCIs from the DCIs detected using the blind decoding., 'in an LTE multi-UE simulator2. The method of comprising claim 1 , prior to performing the blind DCI decoding claim 1 , filtering the CCEs with energy detection to exclude claim 1 , from the blind DCI decoding claim 1 , CCEs with energy levels below a threshold.3. The method of wherein applying at least one DCI detection countermeasure includes identifying a DCI with a higher aggregation level as true if plural DCIs are decoded for the same UE with at least one overlapping CCE and different aggregation levels.4. The method of wherein applying at least one false detection countermeasure includes identifying as true a DCI with a shorter length if plural different DCIs for different UEs are decoded with the same CCEs and the same aggregation level.5. The method of wherein applying at least one false detection countermeasure includes ...

CERAMIC MATRIX COMPOSITE ARTICLES HAVING DIFFERENT LOCALIZED PROPERTIES AND METHODS FOR FORMING SAME

Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof. 1. A method for use in forming a ceramic matrix composite article , the method comprising:laying up a first plurality of plies comprising ceramic fibers defining a first extent;laying up at least one second ply defining a second extent on and/or in the layup of the first plurality of plies, the second extent being less than the first extent; andwherein the first plurality of plies comprises a first property, the at least one second ply comprises at least one second property, and the first property being different from the at least one second property.2. The method of wherein the laying up the at least one second ply comprises laying up the at least one second ply comprising ceramic fibers.3. The method of wherein the laying up the at least one second ply comprises laying up a plurality second plies claim 1 , and wherein the plurality of second plies comprises a plurality of second properties different from the first property.4. The method of wherein the first property comprises a first fiber volume fraction claim 1 , the at least one second property comprises at least one second fiber volume fraction claim 1 , and the first fiber volume fraction being different from the at least ...

WIND TURBINE ROTOR BLADE WITH FABRIC SKIN AND ASSOCIATED METHOD FOR ASSEMBLY

A rotor blade for a wind turbine includes an internal support structure extending span-wise from a blade root to a blade tip. A plurality of ribs are fixed to and spaced along the internal support structure, with each rib extending in a generally chord-wise direction and having a generally aerodynamic blade contour. A plurality of chord-wise oriented fabric strips are affixed to the ribs in a tensioned state, wherein the fabric strips define an aerodynamic outer skin of the rotor blade. 1. A rotor blade for a wind turbine , the rotor blade comprising:an internal support structure extending span-wise from a blade root to a blade tip;said internal support structure including a plurality of fixed, spaced apart ribs, each said rib extending in a generally chord-wise direction and comprising an outer surface having a generally aerodynamic blade contour;a plurality of chord-wise oriented fabric strips having a span-wise width and opposite transverse edges, said fabric strips affixed to said ribs in a tensioned state; andwherein said fabric strips are adjacently disposed along a span-wise length of said internal support structure and define an aerodynamic outer skin of said rotor blade.2. The rotor blade as in claim 1 , wherein said internal support structure comprises a plurality of span-wise extending support elements interconnecting said ribs.3. The rotor blade as in claim 2 , wherein said span-wise extending support elements comprise a plurality of strip members circumferentially spaced around said aerodynamic contour of said ribs.4. The rotor blade as in claim 3 , wherein said strip members are not directly connected to each other within said rotor blade between a pressure side and a suction side of said rotor blade.5. The rotor blade as in claim 3 , further comprising at least one support member interconnecting at least two of said strip members between a pressure side and a suction side of said rotor blade.6. The rotor blade as in claim 5 , wherein said internal ...

WIND TURBINE BLADES WITH TENSION FABRIC SKIN STRUCTURE

A wind blade with a self-supporting structural framework, having multiple chord-wise members and one or more span-wise members is provided. Each of the multiple chord-wise members and the one or more span-wise members have an aerodynamic contour. The wind blade also comprises a fabric skin located over the self-supporting structural framework in a tensioned state to generate an aerodynamic surface, wherein the fabric skin is attached via multiple tensioning members to both the chord wise members and span wise members. 1. A wind blade comprising:a self-supporting structural framework, having a plurality of chord-wise members and one or more span-wise members, wherein each of the plurality of the chord-wise members and the one or more span-wise members have an aerodynamic contour; anda fabric skin located over the self-supporting structural framework in a tensioned state to generate an aerodynamic surface, wherein the fabric skin is attached via a plurality of tensioning members to both the chord wise members and span wise members.2. The wind blade of claim 1 , wherein the fabric skin comprises reinforcing fibers and stretchable matrix materials.3. The wind blade of claim 2 , wherein the stretchable matrix material has an elongation of greater than 10%.4. The wind blade of claim 2 , wherein the stretchable matrix material is selected from the group consisting of elastomers claim 2 , PTFE claim 2 , ETFE claim 2 , PU claim 2 , PVC claim 2 , silicone claim 2 , nitrile rubber claim 2 , EPDM rubber claim 2 , natural rubber claim 2 , thermoplastic elastomers claim 2 , thermoplastic vulcanizates claim 2 , and combinations thereof.5. The wind blade of claim 2 , wherein the reinforcing fibers include a first layer of woven fabric material or non-crimp woven fabric.6. The wind blade of claim 5 , wherein the reinforcing fibers in the first layer of woven fabric material or non-crimp woven fabric has a modulus greater than 1 msi and7. The wind blade of claim 5 , wherein the ...

BOND COATINGS HAVING A SILICON-PHASE CONTAINED WITHIN A REFRACTORY PHASE

A coated component, along with method of forming the same, is provided. The coated component may include a substrate having a surface, a silicon-based bond coating on the surface of the substrate, and an EBC on the silicon-based bond coating. The silicon-based bond coating may include a silicon-phase contained within a refractory phase. The silicon-phase, when melted, is contained within the refractory phase and between the surface of the substrate and an inner surface of the environmental barrier coating. Such a coated component may be, in particular embodiments, a turbine component. 1. A coated component comprising:a substrate having a surface;a silicon-based bond coating on the surface of the substrate, wherein the silicon-based bond coating comprises a silicon-phase contained within a refractory phase; andan environmental barrier coating on the silicon-based bond coating, wherein the silicon-phase, when melted, is contained within the refractory phase and between the surface of the substrate and an inner surface of the environmental barrier coating.2. The coated component as in claim 1 , wherein the silicon-phase comprises silicon metal claim 1 , a silicon alloy claim 1 , a silicide having a melting point of about 1500° C. or less claim 1 , or a mixture thereof.3. The coated component as in claim 1 , wherein the silicon-phase comprises silicon metal in an amount of about 50% to 100% by weight.4. The coated component as in claim 1 , wherein the silicon-phase melts at temperatures of about 1400° C. or greater.5. The coated component as in claim 1 , wherein the silicon-phase is molten at a temperature of about 1450° C.6. The coated component as in claim 1 , wherein the silicon-phase and the refractory phase form intertwined continuous phases.7. The coated component as in claim 1 , wherein the refractory phase is a continuous phase claim 1 , and wherein the silicon-phase forms a plurality of discrete particulate phases within the refractory phase.8. The coated ...

Bond coatings having a molten silicon-phase contained between refractory layers

A coated component, along with methods of its formation and use, is provided. The coated component may include a substrate having a surface, a first refractory layer on the surface of the substrate, a silicon-based bond coating on the first refractory, and an environmental barrier coating on the silicon-based bond coating. The silicon-based bond coating includes a silicon-phase contained within a refractory phase such that, when melted, the silicon-phase is contained within the refractory phase and between the surface of the substrate and an inner surface of the environmental barrier coating.

LIQUID BOND COATINGSF OR BARRIER COATINGS

A coated component, along with methods of its formation and use, is provided. The coated component may include a substrate having a surface with a plurality of cavities defined therein, a bond coating (e.g., including a silicon material) on the surface of the substrate within the cavities, and an environmental barrier coating over the surface of the substrate and encasing the bond coating within the cavities such that the bond coating, when melted, is contained within the cavities. Such a coated component may be, in one embodiment, a turbine component, such as a CMC component for use in a hot gas path of a gas turbine engine. 1. A coated component comprising:a substrate having a surface, wherein a plurality of cavities are defined within the surface of the substrate;a bond coating on the surface of the substrate within the cavities defined within the surface of the substrate, wherein the bond coating comprises a silicon material having a melting point; andan environmental barrier coating over the surface of the substrate and encasing the bond coating within the cavities such that the bond coating, when melted, is contained within the cavities.2. The coated component as in claim 1 , wherein the bond coating comprises silicon metal claim 1 , a silicon alloy claim 1 , a silicide with a melting point of about 1500° C. or less claim 1 , or mixtures thereof.3. The coated component as in claim 1 , wherein the bond coating melts at temperatures of about 1400° C. or greater.4. The coated component as in claim 1 , wherein each cavity is defined by a plurality of side walls claim 1 , each side wall having a wall height claim 1 , and wherein the bond coating has a thickness that is equal to or less than the wall height.5. The coated component as in claim 4 , wherein a bottom surface within the cavity and between opposing side walls claim 4 , wherein at least one of the side walls and the bottom surface includes a series of alternating peaks and valleys to increase the contact ...

COMPOSITE BOOSTER SPOOL WITH SEPARABLE COMPOSITE BLADES

According to present embodiments or aspects thereof, a composite booster spool with separable composite blades is provided. The blades are inserted radially from within the inner circumference of the spool and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites. 1. A booster assembly , comprising:a non-metallic spool having a forward end and an aft end;a plurality of rows of holes, said holes extending circumferentially about said spool;a plurality of radially removable non-metallic blades extending through said plurality of rows of holes from an internal side of said non-metallic spool to an external side; and,said plurality of radially removable non-metallic blades each having a retention feature retaining said non-metallic blades along an interior side of said spool.2. The booster assembly of wherein said non-metallic blades and said non-metallic spool are formed of the same material.3. The booster assembly of wherein said non-metallic blades and said non-metallic spool are formed of different materials.4. The booster assembly of wherein said non-metallic spool and said non-metallic blades are formed of at least one of ceramic matrix composite claim 1 , ceramic composite claim 1 , carbon composite claim 1 , polymeric composite.5. The booster assembly of claim 1 , said holes extending axially.6. The booster assembly of claim 1 , said holes extending at an angle to an engine axis.7. The booster assembly of claim 1 , said holes having one of constant or varying thickness in a radial direction.8. The booster assembly of further comprising a retention ring disposed within said spool and inhibiting said plurality of blades from falling ...

CERAMIC MATRIX COMPOSITE ARTICLES

A method for forming a ceramic matrix composite article includes laying up a first group of plies; laying up a second group of plies, the first and second groups of plies being adjacent to each other; compacting the first group of plies and the second group of plies in the same processing step; and performing a first infiltration process on the first group of plies. The method also includes performing a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process. 1. A method for forming a ceramic matrix composite article comprising:laying up a first group of plies;laying up a second group of plies, the first and second groups of plies being adjacent to each other;compacting the first group of plies and the second group of plies in the same processing step;performing a first infiltration process on the first group of plies; andperforming a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process.2. The method of claim 1 , wherein the first infiltration process is the melt infiltration process claim 1 , wherein the second infiltration process is the chemical vapor infiltration process claim 1 , and wherein performing the first infiltration process on the first group of plies comprises performing the first infiltration process on the first group of plies prior to performing the second infiltration process on the second group of plies.3. The method of claim 2 , further comprising:providing a barrier between a least a portion of the first group of plies and the second group of plies.4. The method ...

CERAMIC MATRIX COMPOSITE ARTICLES

A ceramic matrix composite article includes a chemical vapor infiltration ceramic matrix composite base portion including ceramic fiber reinforcement material in a ceramic matrix material having between 0% and 5% free silicon. The ceramic matrix composite article further includes a melt infiltration ceramic matrix composite covering portion including a ceramic fiber reinforcement material in a ceramic matrix material having a greater percentage of free silicon than the chemical vapor infiltration ceramic matrix composite base portion. 1. A ceramic matrix composite article comprising:a chemical vapor infiltration ceramic matrix composite base portion comprising ceramic fiber reinforcement material in a ceramic matrix material having between 0% and 5% free silicon; anda melt infiltration ceramic matrix composite covering portion comprising a ceramic fiber reinforcement material in a ceramic matrix material having a greater percentage of free silicon than the chemical vapor infiltration ceramic matrix composite base portion.2. The ceramic matrix composite article of claim 1 , wherein the chemical vapor infiltration ceramic matrix composite base portion has substantially 0% free silicon.3. The ceramic matrix composite article of claim 1 , wherein the melt infiltration ceramic matrix composite covering portion substantially completely surrounds at least a portion of the chemical vapor infiltration ceramic matrix composite base portion.4. The ceramic matrix composite article of claim 1 , wherein the article is configured for use in a gas turbine engine.5. The ceramic matrix composite article of claim 4 , wherein the article is a nozzle claim 4 , wherein the melt infiltration ceramic matrix composite covering portion includes a first melt infiltration ceramic matrix composite covering portion forming a radially inner band of the nozzle and a second melt infiltration ceramic matrix composite covering portion forming a radially outer band of the nozzle claim 4 , and wherein ...

COMPOSITE COMPRESSOR BLADE AND METHOD OF ASSEMBLING

Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein. 1. A compressor blade , comprising: an airfoil having a span extending radially outward with respect to an axis of rotation, and', 'a blade attachment feature radially inward from said airfoil with respect to said axis of rotation, said blade attachment feature being circumferentially oriented with respect to said axis of rotation., 'a composite blade panel comprising;'}2. The compressor blade of claim 1 , wherein said blade attachment feature is arranged to releasably engage a generally circumferentially oriented spool attachment feature.3. The compressor blade of claim 1 , wherein said blade attachment feature is generally shaped as a dovetail and comprises a neck claim 1 , a forward lobe claim 1 , and an aft lobe claim 1 , said forward lobe and said aft lobe being radially inward from said neck with respect to said axis of rotation claim 1 , said blade attachment feature having a substantially uniform cross section in a circumferential direction with respect to said axis of rotation.4. The compressor blade of claim 2 , wherein said spool attachment feature is generally shaped as a circumferential dovetail slot configured to slidably receive said blade attachment feature therein.5. The compressor blade of claim 1 , further comprising a first platform ...

Memory Controller for Heterogeneous Configurable Integrated Circuit

A system including a configurable memory controller, a memory interface, and a configurable high speed communications fabric comprising a plurality of interconnect stations arranged in an array and operable to implement a plurality of pipelined buses, where the configurable memory controller is operably coupled to the configurable high speed communications fabric using a first interconnect station of the plurality of interconnect stations, where the memory interface is operably coupled to the configurable high speed communications fabric using a second interconnect station of the plurality of interconnect stations, where the plurality of interconnect stations are configured to satisfy a timing requirement of the memory interface, and where the configurable memory controller, the memory interface, and the configurable high speed communications fabric are associated with a configurable integrated circuit.

Vibration damping monolithic polymers

The damping performance of an article and a polycarbonate composition is improved and a storage medium for data is provided which comprises the use of at least one ortho-methyl substituted polycarbonate structure.

Vibration damping monolithic polymers

The damping performance of an article and a polycarbonate composition is improved and a storage medium for data is provided which comprises the use of at least one ortho-methyl substituted polycarbonate structure.

Composite compressor blade and method of assembling

Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein.

Identification of a reflective surface as being associated with a threat optic

Identification of reflective surfaces as being associated with optical threats is disclosed. A first laser signal is emitted from a first laser system at a first wavelength and a first emission circular polarization orientation. A first signal reflection of the first laser signal from a reflective surface at the first wavelength having a first return circular polarization orientation that is different from the first emission circular polarization orientation is detected. A first return quantification of the first signal reflection, based at least in part on an amount of circular polarization of the first signal reflection, is determined. It is determined that the reflective surface is associated with a threat optic based at least in part on the first return quantification.

Composite booster spool with separable composite blades

According to present embodiments or aspects thereof, a composite booster spool (31) with separable composite blades (50) is provided. The blades (50) are inserted radially from within the inner circumference of the spool (31) and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites.

Ceramic matrix composite blade having integral platform structures and methods of fabrication

A method of making a ceramic matrix composite blade includes laying up at least one ply of the plurality of fibrous ceramic plies in a preselected ar-rangement to form an airfoil and dovetail preform, laying up at least one additional ply of the plurality of fibrous ceramic plies on the airfoil and dovetail preform in a sec-ond preselected arrangement to form an integral platform as part of the non-rigidized blade preform, rigidizing the blade preform to form a rigidized blade preform, and densifying the rigidized blade preform to form a ceramic matrix composite blade having an integral platform structure A tool for making the ceramic matrix compos-ite blade and a ceramic matrix composite blade are also disclosed.

Cmc articles having small complex features

A ceramic matrix composite (CMC) component for gas turbine engines (10), the component having fine features such as thin edges with thicknesses of less than about 0.030 inches and small radii of less that about 0.030 inches formed using the combination of prepreg plies (40) layed up with non-ply ceramic inserts (650, 680). The CMC components of the present invention replace small ply inserts cut to size to fit into areas of contour change or thickness change, and replace the small ply inserts with a fabricated single piece discontinuously reinforced composite insert (650, 680), resulting in fewer defects, such as wrinkles, and better dimensional control.

Bond coatings for barrier coatings

A coated component (100), along with methods of its formation, is provided. The coated component (100) includes a substrate (102) having a surface (103) with a plurality of cavities (101) defined therein, a bond coating (104) including a silicon material on the surface (103) of the substrate (102) within the cavities (101), and an environmental barrier coating (108) over the surface (103) of the substrate (102) and encasing the bond coating (104) within the cavities (101) such that the bond coating (104), when melted, is contained within the cavities (101). Such a coated component (100) may be, in one embodiment, a turbine (28) component (100), such as a CMC component (100) for use in a hot gas path (78) of a gas turbine (28) engine.

Composite booster spool with separable composite blades

According to present embodiments or aspects thereof, a composite booster spool with separable composite blades is provided. The blades are inserted radially from within the inner circumference of the spool and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites.

Composite blading member and method for making

A composite blading member (10) includes an airfoil (12) and a base (20) of composite material layers (40) and a platform (38) of composite material layers (40) interfused with the airfoil (12) and base (20). The platform (38) comprises a platform shelf (42) and a plurality of spaced-apart platform supports (44,46) integral with the platform shelf (42) and interfused with surfaces (26,28) of the base. Such blading member (10) was made by providing a partially cured airfoil-base preform (36) and a platform perform (38), including an airfoil shaped opening (43) therethrough and preforms of the platform supports (44,46). The airfoil-base preform (36) was inserted through the airfoil shaped opening (43) whereby cooperating surfaces of the platform perform (38) and airfoil-based preform (36) were in juxtaposition. The performs (36,38) were heated to partially cure them together. Then they were interfused with a binder compatible with material of the preforms (36,38) under conditions to substantially fully cure the structures.

Composite booster spool with separable composite blades

According to present embodiments or aspects thereof, a composite booster spool (31) with separable composite blades (50) is provided. The blades (50) are inserted radially from within the inner circumference of the spool (31) and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites.

Ceramic matrix composite articles formation method

A method for forming a ceramic matrix composite article includes laying up a first group of plies; laying up a second group of plies, the first and second groups of plies being adjacent to each other; compacting the first group of plies and the second group of plies in the same processing step; and performing a first infiltration process on the first group of plies. The method also includes performing a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process.

Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components

The present invention is a ceramic matrix composite turbine engine component, wherein the component has a direction of maximum tensile stress during normal engine operation. The component comprises a plurality of biased ceramic plies, wherein each biased ply comprises ceramic fiber tows, the tows being woven in a first warp direction and a second weft direction, the second weft direction lying at a preselected angular orientation with respect to the first warp direction, wherein a greater number of tows are woven in the first warp direction than in the second weft direction, and wherein a number of tows in the second weft direction allows the biased plies to maintain their structural integrity when handled. The plurality of biased plies are laid up in a preselected arrangement to form the component, and a preselected number of the plurality of biased plies are oriented such that the orientation of the first warp direction of the preselected number of biased plies lie about in the direction of maximum tensile stress during normal engine operation. A coating is applied to the plurality of biased plies. The coating is selected from the group consisting of BN, SiC, and combinations thereof. A ceramic matrix material lies in interstitial regions between the tows of each biased ply and the interstitial region between the biased plies.

Method of manufacturing cmc articles having small complex features

A method for forming a ceramic matrix composite (CMC) component for gas turbine engines. The method contemplates replacing a plurality of plies with insert material. The insert material can be partially cured or pre-cured and applied in place of a plurality of small plies or it may be inserted into cavities of a component in the form of a paste or a ply. The insert material is isotropic, being formed of a combination of matrix material and chopped fibers, tow, cut plies or combinations thereof. The use of the insert material allows for features such as thin edges (650) with thicknesses of less than about 0.030 inches and small radii such as found in corners (680, 710). The CMC components of the present invention replace small ply inserts cut to size to fit into areas of contour change or thickness change, and replace the small ply inserts with a fabricated single piece discontinuously reinforced composite insert, resulting in fewer defects, such as wrinkles, and better dimensional control.

Through thickness reinforcement of SiC/SiC CMC's through in-situ matrix plugs manufactured using fugitive fibers

A method of manufacturing a turbine engine component comprising the steps of providing and laying up a plurality of ceramic plies comprising woven ceramic fiber tows to form a turbine engine component shape, inserting a plurality of tows of oxidizable fugitive fibers into the component shape, such that each fugitive fiber tow passes through a preselected number of ceramic plies, burning off the fugitive fiber tows, the burning producing through-thickness void regions, rigidizing the component shape with a layer of BN and a layer of SiC to form a coated component preform using chemical vapor infiltration, and partially densifying the coated component preform using carbon-containing slurry and filling the through thickness void regions, and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component with in-situ ceramic matrix plugs formed where the through-thickness void regions were located.

Orthogonal weaving for fabricating complex shape preforms

Ceramic matrix composite articles

A ceramic matrix composite article includes a chemical vapor infiltration ceramic matrix composite base portion including ceramic fiber reinforcement material in a ceramic matrix material having between 0% and 5% free silicon. The ceramic matrix composite article further includes a melt infiltration ceramic matrix composite covering portion including a ceramic fiber reinforcement material in a ceramic matrix material having a greater percentage of free silicon than the chemical vapor infiltration ceramic matrix composite base portion.

Ceramic matrix composite articles

A method for forming a ceramic matrix composite article includes laying up a first group of plies; laying up a second group of plies, the first and second groups of plies being adjacent to each other; compacting the first group of plies and the second group of plies in the same processing step; and performing a first infiltration process on the first group of plies. The method also includes performing a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process.

Capturing images used in facial recognition through effective use of exposure management

A system and method for capturing images used in a facial recognition system are provided. The system and method are configured to generate a sequential set of control signals configured to cause a camera to capture a corresponding sequential set of probe images of a face of an individual. Each control signal in the sequential set of control signals is configured to cause the camera to capture a probe image of the sequential set of probe images using a different exposure time. The different exposure times associated with the sequential set of control signals together form a predetermined profile configured to enable capture of a usable image from the sequential set of probe images despite variation in at least one of an amount of light and a skin tone of the face of the individual.

Cmc articles having small complex features .

Un componente de compuesto de matriz de cerámica (CMC) para motores de turbina de gas, el componente tiene características finas, tales como bordes delgados con espesores menores que aproximadamente 0.076 cm y radios pequeños de aproximadamente 0.076 cm formados con el uso de una combinación de capas (40) pre-impregnadas tendidas con los insertos (650, 680) de cerámica sin capas. Los componentes CMCC de la presente invención reemplazan insertos de capa pequeños cortados para ajustarse en áreas de un cambio de contorno o cambio de espesor, y reemplazan insertos de capa pequeños con un inserto (60, 680) compuestos reforzado en forma discontinua de una sola pieza, lo que da como resultado menos defectos, tales como arrugas y mejor control dimensional.

Orthogonal weaving for fabricating complex shape preforms

An orthogonal stitch-weave method and fiber architecture (48). The architecture (48) allows near-net-shape composite preforms to be fabricated, thereby reducing costs associated with complex preform shapes and increasing desired strengths of the composite.

SiC/SiC composites incorporating uncoated fibers to improve interlaminar strength

The present invention is a ceramic matrix composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during normal engine operation. The component includes both coated fiber tows and uncoated fiber tows arranged together into a preselected form, wherein the uncoated fiber tows are located at predetermined regions of expected high interlaminate stress. The invention further includes method of manufacturing a CMC such as a composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during engine operation.

Ceramic matrix composite articles

A method for forming a ceramic matrix composite article includes laying up (410) a first group of plies; laying up (412) a second group of plies, the first and second groups of plies being adjacent to each other; compacting (414) the first group of plies and the second group of plies in the same processing step; and performing (420) a first infiltration process on the first group of plies. The method also includes performing (422) a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process.

Ceramic matrix composite articles having different localized properties and methods for forming same

Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

Methods, systems, and computer readable media for reducing the impact of false downlink control information (DCI) detection in long term evolution (LTE)

Method for forming ceramic matrix composite articles

Wind turbine blades with tension fabric skin structure

Ceramic matrix composite articles

A method for forming a ceramic matrix composite article includes laying up (410) a first group of plies; laying up (412) a second group of plies, the first and second groups of plies being adjacent to each other; compacting (414) the first group of plies and the second group of plies in the same processing step; and performing (420) a first infiltration process on the first group of plies. The method also includes performing (422) a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process.

Liquid bond coatings for barrier coatings

A coated component, along with methods of its formation and use, is provided. The coated component may include a substrate having a surface with a plurality of cavities defined therein, a bond coating (e.g., including a silicon material) on the surface of the substrate within the cavities, and an environmental barrier coating over the surface of the substrate and encasing the bond coating within the cavities such that the bond coating, when melted, is contained within the cavities. Such a coated component may be, in one embodiment, a turbine component, such as a CMC component for use in a hot gas path of a gas turbine engine.

Autonomous database defragmentation

Techniques are disclosed relating to performing database defragmentation operations by autonomously rebuilding index objects stored in one or more tablespaces of a database. In various embodiments, the disclosed techniques include autonomously performing defragmentation operations for one or more tablespaces in a database in an online manner such that a server system may continue to service data access requests while performing the defragmentation operations. In one non-limiting embodiment, for example, the disclosed techniques include selecting a first tablespace to defragment based on its level of fragmentation (e.g., relative to the other tablespaces). The server system may then rebuild index objects, from the first tablespace, to a new tablespace such that the index objects are stored in the new tablespace without fragmentation. The server system may then reclaim at least a portion of the storage space used to store the first tablespace and repeat, as desired, to autonomously defragment multiple tablespaces.

Schaufel aus verbundmaterial und verfahren zur herstellung

Verfahren, Systeme und computerlesbare Medien zur Reduzierung der Auswirkung der Erkennung von falschen Abwärtsstrecken-Steuerungsinformationen (Downlink-Control-Informationen, DCI) in LTE-PDCCH-Daten (Long-Term-Evolution-Physical-Downlink-Control-Channel-Daten)

Verfahren, Systeme und computerlesbare Medien zur Reduzierung der Auswirkung der Erkennung falschen Abwärtsstrecken-Steuerungsinformationen (Downlink-Control-Informationen, DCI) in LTE-PDCCH-Daten (Long-Term-Evolution-Physical-Downlink-Control-Channel-Daten) werden offenbart. Gemäß einem Verfahren empfängt ein LTE-Mehrfach-UE-Simulator PDCCH-Daten von einem evolvierten Knoten B (evolved node B, eNode B). Der LTE-Mehrfach-UE-Simulator wendet blinde DCI-Dekodierung an, um mindestens einen DCI-Wert von Kanalsteuerungselementen (CCE, Channel Control Elements) zu dekodieren, die die PDCCH-Daten tragen. Der LTE-Mehrfach-UE-Simulator wendet mindestens eine Gegenmaßnahme gegen die Erkennung von falschen DCI an, um von den mittels der blinden Dekodierung erkannten DCI DCI als wahr oder falsch zu identifizieren.

Verfahren, Systeme und computerlesbare Medien zur Reduzierung der Auswirkung der Erkennung von falschen Abwärtsstrecken-Steuerungsinformationen (Downlink-Control-Informationen, DCI) in LTE-PDCCH-Daten (Long-Term-Evolution-Physical-Downlink-Control-Channel-Daten)

Ein Verfahren zur Reduzierung der Auswirkungen von falschen Abwärtsstrecken-Steuerungsinformationen (Downlink-Control-Informationen, DCI) in LTE-PDCCH-Daten (Long-Term-Evolution-Physical-Downlink-Control-Daten), wobei das Verfahren Folgendes beinhaltet:in einem LTE Mehrfachendgeräte (multi-user-equipment, multi-UE)-Simulator:Simulieren einer Mehrzahl UEs die mit einem evolvierten Knoten B (evolved node B, eNode B) verbunden sind, wobei die UEs verschiedene temporären Funknetz-Kennung (Radio Network Temporary Identfier, RNTI) haben;Empfangen von PDCCH-Daten von dem eNode B;Anwenden blinder DCI-Dekodierung, um mindestens einen DCI-Wert von Kanalsteuerungselementen (CCE, Channel Control Elements) zu dekodieren, die die PDCCH-Daten tragen, wobei das Anwenden blinder DCI-Dekodierung die Verwendung der verschiedenen RNTI-Wertes für alle verschiedenen angeschlossenen UEs, die vom Simulator während eines gegebenen Übertragungszeitintervalls simuliert wird umfasst, um einen Satz PDCCH-Kandidaten zu überwachen und mögliche gültige DCIs für alle verschiedenen angeschlossenen simulierten UEs zu identifizieren; undAnwenden mindestens einer Gegenmaßnahme gegen die Erkennung von falschen DCI, um von den mittels der blinden Dekodierung erkannten DCIs wahre oder falsche DCIs zu identifizieren.

Metodo para fabricar articulos de compuestos de matriz de ceramica (cmc) con caracteristicas complejas menores.

Un método para formar un componente de compuesto de matriz de cerámica (CMC) para motores de turbina de gas. El método contempla reemplazar una pluralidad de capas con material de inserto. El material de inserto puede curarse parcialmente o pre-curarse y aplicarse en lugar de una pluralidad de capas pequeñas o puede ser insertado dentro de cavidades de un componente en la forma de una pasta o una capa. El material del inserto es isotrópico, y se forma de una combinación de material de matriz y fibras trituradas, estopa, capas cortadas o combinaciones de los mismos. El uso del material de inserto permite que ciertas características, tales como bordes (650) delgados con espesores menores que aproximadamente 0.076 cm y radios pequeños como los encontrados en las esquinas (680, 710). Los componentes CMC de la presente invención reemplazan insertos de capa pequeños cortados para ajustarse en área de un cambio de contorno o cambio de espesor, y reemplazan insertos de capa pequeños con un inserto de compuesto reforzado en forma discontinua de una sola pieza, lo que da como resultado menos defectos, tales como arrugas y mejor control dimensional.

耐火層の間に含まれる溶融ケイ素相を有するボンドコーティング

【課題】セラミック構成要素の環境障壁コーティングと共に使用するためのボンドコーティング、ならびにそれらの形成および使用方法を提供する。【解決手段】コーティングされた構成要素（１００）は、表面（１０３）を有する基材（１０２）と、基材（１０２）の表面（１０３）の第１の耐火層（１２０）と、第１の耐火層（１２０）のケイ素系ボンドコーティング（１０４）と、ケイ素系ボンドコーティング（１０４）の環境障壁コーティング（１０８）とを含む。ケイ素系ボンドコーティング（１０４）は、耐火相（１１２）内に含まれるケイ素相（１１０）を含み、それによりケイ素相（１１０）は、溶融すると、耐火相（１１２）内、および基材（１０２）の表面（１０３）と環境障壁コーティング（１０８）の内側表面（１０３）との間に含まれる。【選択図】図１

lâmina de vento, método de fabricação de uma lâmina de vento e turbina eólica

lâmina de vento, método de fabricação de uma lâmina de vento e turbina eólica. [001] trata-se de uma lâmina de vento com uma armação estrutural autossustentada que tem múltiplos membros no sentido da corda e um ou mais membros no sentido da amplitude. cada um dos múltiplos membros no sentido da corda e dos um ou mais membros no sentido da amplitude tem um contorno aerodinâmico. a lâmina de vento também compreende uma película de tecido localizado sobre a armação estrutural autossustentada em um estado tensionado para gerar uma superfície aerodinâmica, em que a película de tecido é fixada por meio de múltiplos membros de tensionamento tanto aos membros no sentido da corda e aosmembros no sentido da amplitude.

Ceramic composite article manufacture using thin plies

Thin plies used to manufacture components having changes in contour and changes in thickness and in fabricating thin cross-sections utilizing scrims. A scrim is applied to the surface of a thin, high temperature CMC prepreg ply. The scrim assists in maintaining the integrity of the thin ply during handling and lay-up operations thereby preventing damage to the thin plies and the lay-up. The scrim is a thin supportive layer applied to the surface of a thin prepreg to improve its handling characteristics. The scrim can be a coarse or fine mesh of thin or heavy fiber applied as a reinforcement. The scrim can be a temporary removable structure or can be incorporated into the component as part of the thin ply. The structure and composition of the scrim will be dependent upon whether the scrim is a temporary removable structure or incorporated permanently into the component.

Method and apparatus for performing analog mode operations when receiving data and signaling tones in a wireless TDMA system

ワイヤレスｔｄｍａシステムにおいてデータとシグナリングトーンとを受信する際にアナログモード動作を実行するための方法および装置

(57)【要約】 【課題】 アナログモード動作が同相（Ｉ）および直交 （Ｑ）値を用いて実行されるようにできるワイヤレスシ ステムの送受信機において用いるための方法および装置 を提供する。 【解決手段】 アナログモードで動作するとき、その装 置は、オーディオあるいはデータ信号に関連するデジタ ルＩ、Ｑ対を受信し、ＦＭ復調を実行して、オーディオ あるいはデータ信号に関連する情報内容を生成するプロ セッサを備える。アナログモードでデータを受信すると き、データは特定のフォーマットをとる。データを復号 化するために、プロセッサは無線リンクワード（ＲＬ Ｗ）の５回の繰返しに対して各ビットを認識し、各ビッ トに関連する確信度を生成し、かつ格納する。確信度 は、その波形が１あるいは０のどちらを近似しているか と、その信号強度とに基づいている。その波形の雑音が 比較的小さく、ＲＦ信号強度が比較的大きい場合には、 プロセッサは、その波形が１を表すか、０を表すかに関 する判定に、より大きな重みを割り当てる。

Combination therapy comprising a composition of mesenchymal stromal cells and hyaluronic acid for use in treatment of osteoarthritis

The present disclosure relates to an ultrasound guided intraarticular administration of a combination of a composition comprising pooled mesenchymal stromal cells, and mid molecular weight hyaluronic acid for treatment of osteoarthritis. The disclosure also provides methods for increasing levels of anti-inflammatory marker and decreasing levels of disease progression marker in a human subject suffering from osteoarthritis through the use of the said combination. The present disclosure accordingly also relates to a kit comprising the said composition and the hyaluronic acid as such for the said use and treatment.

Combination therapy comprising a composition of mesenchymal stromal cells and hyaluronic acid for use in treatment of osteoarthritis

The present disclosure relates to an ultrasound guided intraarticular administration of a combination of a composition comprising pooled mesenchymal stromal cells, and mid molecular weight hyaluronic acid for treatment of osteoarthritis. The disclosure also provides methods for increasing levels of anti-inflammatory marker and decreasing levels of disease progression marker in a human subject suffering from osteoarthritis through the use of the said combination. The present disclosure accordingly also relates to a kit comprising the said composition and the hyaluronic acid as such for the said use and treatment.