Patent application number | Description | Published |
20100177903 | Hybrid Derivation of Surround Sound Audio Channels By Controllably Combining Ambience and Matrix-Decoded Signal Components - Ambience signal components are obtained from source audio signals, matrix-decoded signal components are obtained from the source audio signals, and the ambience signal components are controllably combined with the matrix-decoded signal components. Obtaining ambience signal components may include applying at least one decorrelation filter sequence. The same decorrelation filter sequence may be applied to each of the input audio signals or, alternatively, a different decorrelation filter sequence may be applied to each of the input audio signals. | 07-15-2010 |
20110249819 | AUDIO CHANNEL SPATIAL TRANSLATION - M audio input channels, each associated with a spatial direction, are translated to N audio output channels, each associated with a spatial direction, wherein M and N are positive whole integers, M is three or more, and N is three or more, by deriving the N audio output channels from the M audio input channels, wherein one or more of the M audio input channels is associated with a spatial direction other than a spatial direction with which any of the N audio output channels is associated, and at least one of the one or more of the M audio input channels is mapped to a respective set of at least three of the N output channels. At least three output channels of a set may be associated with contiguous spatial directions. | 10-13-2011 |
20130317833 | Methods and Systems for Generating Filter Coefficients and Configuring Filters - Methods for generating a palette of feedback (IIR) filter coefficient sets and using the palette to configure (e.g., adaptively update) a prediction filter which includes a feedback filter, and a system for performing any of the methods. Examples of the system include an encoder, including a prediction filter and configured to encode data indicative of a waveform signal (e.g., samples of an audio signal), and a decoder. In some embodiments, the prediction filter is included in an encoder operable to generate (and assert to a decoder) encoded data including filter coefficient data indicative of the selected IIR coefficient set with which the prediction filter was configured during generation of the encoded data. In some embodiments, the timing with which adaptive updating of prediction filter configuration occurs or is allowed to occur is constrained (e.g., to optimize efficiency of prediction encoding). | 11-28-2013 |
20140119570 | Equalization of Speaker Arrays - Methods and apparatus are described by which equalization and/or bass management of speakers in a sound reproduction system may be accomplished. | 05-01-2014 |
20150163614 | EMBEDDING DATA IN STEREO AUDIO USING SATURATION PARAMETER MODULATION - In some embodiments, a method for embedding data (e.g., metadata for use during post-processing) in a stereo audio signal comprising frames. Each of the frames has a saturation value, and data are embedded in the stereo audio signal by modifying the signal to generate a modulated stereo audio signal comprising a sequence of modulated frames having modulated saturation values indicative of the embedded data. Typically, one data bit is embedded in each frame of an input stereo audio signal by modifying the frame to produce a modulated frame whose modulated saturation value matches a target value indicative of the data bit. In other embodiments, a method for extracting data from a stereo audio signal in which the data have been embedded in accordance with an embodiment of the inventive embedding method. Other aspects are systems (e.g., programmed processors) configured to perform any embodiment of the inventive method. | 06-11-2015 |
20150187362 | Multichannel Audio Coding - Multiple channels of audio are combined either to a monophonic composite signal or to multiple channels of audio along with related auxiliary information from which multiple channels of audio are reconstructed, including improved downmixing of multiple audio channels to a monophonic audio signal or to multiple audio channels and improved decorrelation of multiple audio channels derived from a monophonic audio channel or from multiple audio channels. Aspects of the disclosed invention are usable in audio encoders, decoders, encode/decode systems, downmixers, upmixers, and decorrelators. | 07-02-2015 |
20150243289 | Multi-Channel Audio Content Analysis Based Upmix Detection - Forensic audio upmixer detection is described. Feature sets are extracted from an audio signal that has two or more individual channels. Based on the extracted feature sets, it is determined whether the audio signal was upmixed from audio content that has fewer channels. | 08-27-2015 |
20150365775 | AUTOMATIC LOUDSPEAKER POLARITY DETECTION - In some embodiments, a method for automatic detection of polarity of speakers, e.g., speakers installed in cinema environments. In some embodiments, the method determines relative polarities of a set of speakers (e.g., loudspeakers and/or drivers of a multi-driver loudspeaker) using a set of microphones, including by measuring impulse responses, including an impulse response for each speaker-microphone pair; clustering the speakers into a set of groups, each group including at least two of the speakers which are similar to each other in at least one respect; and for each group, determining and analyzing cross-correlations of pairs of impulse responses (e.g., pairs of processed versions of impulse responses) of speakers in the group to determine relative polarities of the speakers. Other aspects include systems configured (e.g., programmed) to perform any embodiment of the inventive method, and computer readable media (e.g., discs) which store code for implementing any embodiment of the inventive method. | 12-17-2015 |
20160005413 | Audio Signal Enhancement Using Estimated Spatial Parameters - Received audio data may include a first set of frequency coefficients and a second set of frequency coefficients. Spatial parameters for at least part of the second set of frequency coefficients may be estimated, based at least in part on the first set of frequency coefficients. The estimated spatial parameters may be applied to the second set of frequency coefficients to generate a modified second set of frequency coefficients. The first set of frequency coefficients may correspond to a first frequency range (for example, an individual channel frequency range) and the second set of frequency coefficients may correspond to a second frequency range (for example, a coupled channel frequency range). Combined frequency coefficients of a composite coupling channel may be based on frequency coefficients of two or more channels. Cross-correlation coefficients, between frequency coefficients of a first channel and the combined frequency coefficients, may be computed. | 01-07-2016 |
Patent application number | Description | Published |
20100296693 | SYSTEM AND PROCESS FOR ROOF MEASUREMENT USING AERIAL IMAGERY - The present disclosure shows creating a first layer and a second layer, in computer memory and substantially overlapping at least a segment of line from said first layer with at least a segment of another line from said second layer. A first non-dimensional attribute is different from said second non-dimensional attribute of the two lines. A user length field enabling a client with said interactive file to override at least one of said length numeric values, where said area operator may automatically recalculate area based on said length field override is shown. Also, providing a visual marker that is moveable on said computer monitor around said aerial imagery region, which may be moved, to more precisely identify the location of the building roof structure is shown. | 11-25-2010 |
20130138401 | System and Process for Roof Measurement Using Aerial Imagery - The present disclosure shows creating a first layer and a second layer, in computer memory and substantially overlapping at least a segment of line from said first layer with at least a segment of another line from said second layer. A first non-dimensional attribute is different from said second non-dimensional attribute of the two lines. A user length field enabling a client with said interactive file to override at least one of said length numeric values, where said area operator may automatically recalculate area based on said length field override is shown. Also, providing a visual marker that is moveable on said computer monitor around said aerial imagery region, which may be moved, to more precisely identify the location of the building roof structure is shown. | 05-30-2013 |
20130147802 | System and Process for Roof Measurement Using Aerial Imagery - The present disclosure shows creating a first layer and a second layer, in computer memory and substantially overlapping at least a segment of line from said first layer with at least a segment of another line from said second layer. A first non-dimensional attribute is different from said second non-dimensional attribute of the two lines. A user length field enabling a client with said interactive file to override at least one of said length numeric values, where said area operator may automatically recalculate area based on said length field override is shown. Also, providing a visual marker that is moveable on said computer monitor around said aerial imagery region, which may be moved, to more precisely identify the location of the building roof structure is shown. | 06-13-2013 |
20130170694 | System and Process for Roof Measurement Using Aerial Imagery - Processes and systems are disclosed for determining attributes of a roof structure of real-world three-dimensional building(s), including providing computer input field(s) for a user to input location data generally corresponding to the location of the building, providing visual access to a nadir image of a region including the roof structure of the building; on the nadir image of the region, providing a visual marker that is moveable on the computer monitor around the region, the visual marker initially corresponding to the location data but which may be moved to a final location, having location coordinates, on top of the building to more precisely identify the location of the building roof structure; providing a computer input capable of signaling user-acceptance of the final location of the marker; and, providing visual access to one or more oblique images of an aerial imagery database corresponding to location coordinates of the final location. | 07-04-2013 |
20130212536 | SYSTEM AND PROCESS FOR ROOF MEASUREMENT USING AERIAL IMAGERY - The present disclosure shows creating a first layer and a second layer, in computer memory and substantially overlapping at least a segment of line from said first layer with at least a segment of another line from said second layer. A first non-dimensional attribute is different from said second non-dimensional attribute of the two lines. A user length field enabling a client with said interactive file to override at least one of said length numeric values, where said area operator may automatically recalculate area based on said length field override is shown. Also, providing a visual marker that is moveable on said computer monitor around said aerial imagery region, which may be moved, to more precisely identify the location of the building roof structure is shown. | 08-15-2013 |
20140003707 | System and Process for Roof Measurement Using Aerial Imagery | 01-02-2014 |
20140237430 | SYSTEM AND PROCESS FOR ROOF MEASUREMENT USING AERIAL IMAGERY - The present disclosure shows creating a first layer and a second layer, in computer memory and substantially overlapping at least a segment of line from said first layer with at least a segment of another line from said second layer. A first non-dimensional attribute is different from said second non-dimensional attribute of the two lines. A user length field enabling a client with said interactive file to override at least one of said length numeric values, where said area operator may automatically recalculate area based on said length field override is shown. Also, providing a visual marker that is moveable on said computer monitor around said aerial imagery region, which may be moved, to more precisely identify the location of the building roof structure is shown. | 08-21-2014 |
Patent application number | Description | Published |
20080214732 | PROCESS FOR THE PREPARATION OF ARYLENE FLUORINATED SULFONIMIDE POLYMERS AND MEMBRANES - Aromatic sulfonimide ionene polymers useful as membranes in electrochemical cells are prepared. | 09-04-2008 |
20090068528 | HEAT TREATMENT OF PERFLUORINATED IONOMERIC MEMBRANES - A process for the conditioning of fully hydrated fluorinated membranes. The hydrated membrane is heated while under pressure, and allowed to cool before the pressure is released. | 03-12-2009 |
20090136817 | ARYLENE FLUORINATED SULFONIMIDE POLYMERS AND MEMBRANES - Aromatic sulfonimide ionene polymers useful as membranes in electrochemical cells are prepared. | 05-28-2009 |
20090171067 | BRIDGED ARYLENE FLUORINATED SULFONIMIDE COMPOSITIONS AND POLYMERS - Aromatic sulfonimide ionene compositions useful as monomers for polymers in electrochemical cells are prepared. | 07-02-2009 |
20100292351 | PROCESS TO PREPARE CROSSLINKABLE TRIFLUOROSTYRENE POLYMERS AND MEMBRANES - Described herein is a process to prepare crosslinkable polymers based on trifluorostyrene, and their use as polymer electrolyte membranes. | 11-18-2010 |
20110031441 | ELECTRICALLY CONDUCTIVE POLYMER COMPOSITIONS - There are provided electrically conducting polymer compositions comprising an electrectically conductive polymer or copolymer and an organic solvent wettable fluorinated acid polymer. Electrically conductive polymer materials are derived from thiophene, pyrrole, aniline and polycyclic heteroaromatic precursor monomers. Non-conductive polymers derived from alkenyl, alkynyl, arylene, and heteroarylene precursor monomers. The organic-solvent wettable fluorinated acid polymer is fluorinated or highly fluorinated and may be colloid-forming. Acidic groups include carboxylic acid groups, sulfonic acid groups, sulfonimide groups, phosphoric acid groups, phosphonic acid groups, and combinations thereof. The compositions can be used in organic electronic devices. | 02-10-2011 |
20110046247 | CROSSLINKABLE MONOMER - Described herein is a trifluorostyrene compound that can be used as a monomer to form crosslinkable polymers. | 02-24-2011 |
20110207859 | COPOLYESTERS WITH ENHANCED TEAR STRENGTH - This invention relates to aliphatic-aromatic copolyesters that can exhibit improved tear strength and improved rate of biodegradation. Particularly to an aliphatic-aromatic copolyester having a dicarboxylic acid component and a glycol component. The invention also relates to articles and blends using the copolyesters. | 08-25-2011 |
20110213055 | COPOLYESTERS WITH ENHANCED TEAR STRENGTH - This invention relates to aliphatic-aromatic copolyesters that can exhibit improved tear strength and improved rate of biodegradation. Particularly to an aliphatic-aromatic copolyester having a dicarboxylic acid component and a glycol component. The invention also relates to articles and blends using the copolyesters. | 09-01-2011 |
20110213056 | COPOLYESTERS WITH ENHANCED TEAR STRENGTH - This invention relates to aliphatic-aromatic copolyesters that can exhibit improved tear strength and improved rate of biodegradation. Particularly to an aliphatic-aromatic copolyester having a dicarboxylic acid component and a glycol component. The invention also relates to articles and blends using the copolyesters. | 09-01-2011 |
20110218255 | ARYLENE-FLUORINATED-SULFONIMIDE IONOMERS AND MEMBRANES FOR FUEL CELLS - The preparation of aromatic sulfonimide polymers useful as membranes in electrochemical cells is described. | 09-08-2011 |
20110229674 | POLYMERIZATION OF ALIPHATIC-AROMATIC COPOLYETHERESTERS - The polymerization processes described herein provide methods for controlling the dehydration of glycols such that dimers are formed as glycol ethers and incorporated into aliphatic-aromatic copolyetheresters during polycondensation. Control over this phenomenon provides unique polymer compositions with a range of thermo-mechanical properties, crystallinity, bio-content and biodegradability. | 09-22-2011 |
20110230575 | CROSSLINKABLE TRIFLUOROSTYRENE POLYMERS AND MEMBRANES - Described herein is a crosslinkable polymer based on trifluorostyrene, and its use in polymer electrolyte membranes thereof. | 09-22-2011 |
20120004387 | POLYARYLENE POLYMERS AND PROCESSES FOR PREPARING - Provided are sulfone-containing polyarylene polymers. Also provided are monomers and processes for preparing the polymers. The polyarylene polymers are suitable for use as engineering polymers. | 01-05-2012 |
20120289678 | METHOD OF MAKING POLYARYLENE IONOMERS AND MEMBRANES - Described herein is the preparation of polyarylene ionomers copolymers, both polysulfones and sulfonimide containing, useful as membranes in electrochemical cells. | 11-15-2012 |
20120296065 | POLYARYLENE IONOMERS MEMBRANES - Described herein is the preparation of polyarylene ionomeric copolymers, copolymers containing polysulfone, sulfonic acid, and sulfonimide repeat units, and useful membranes made from such polyarylene ionomeric copolymers, in particular as membranes in electrochemical cells such as fuel cells. | 11-22-2012 |
20120302725 | POLYARYLENE IONOMERS - Described herein is the preparation of polyarylene ionomeric copolymers containing polysulfone, sulfonic acid, and sulfonimide repeat units, and such polyarylene ionomeric copolymers that are useful as membranes in electrochemical cells. | 11-29-2012 |
20120322973 | POLYARYLENE POLYMERS AND PROCESSES FOR PREPARING - Provided are sulfone-containing polyarylene polymers, and processes for preparing the polymers. The polyarylene polymers are suitable for use as engineering polymers. | 12-20-2012 |
20130079440 | COPOLYESTER BLENDS WITH ENHANCED TEAR STRENGTH - This invention relates to aliphatic-aromatic copolyesters that can exhibit improved tear strength and improved rate of biodegradation. Particularly to an aliphatic-aromatic copolyester having a dicarboxylic acid component and a glycol component. The invention also relates to articles and blends using the copolyesters. | 03-28-2013 |
20130158168 | ALIPHATIC-AROMATIC COPOLYETHERESTERS - Provided are aliphatic-aromatic copolyetheresters that can exhibit biodegradation with improved physical properties. The copolyetheresters can be blended with other polymeric materials, and are useful for making a variety of shaped articles. The aliphatic-aromatic copolyetheresters can include combinations of terephthalic acid or ester with linear aliphatic, or a non-linear dicarboxylic acid or ester, that is condensed with a linear glycol and a polyalkylene ether glycol. | 06-20-2013 |
20130158196 | ALIPHATIC-AROMATIC COPOLYETHERESTERS - Provided are aliphatic-aromatic copolyetheresters that can exhibit biodegradation and improved physical properties. The copolyetheresters can be blended with other polymeric materials, and are useful for making a variety of shaped articles. | 06-20-2013 |
20130172456 | COPOLYESTER BLENDS WITH IMPROVED MELT STRENGTH - Blends comprising 65-95 wt % poly(trimethylene terephthalate-co-sebacate), 5 to 35 wt % polylactic acid and a chain extender are provided that exhibit greatly increased melt strength compared to that of poly(trimethylene terephthalate-co-sebacate) alone. Such improvements allow these compositions to be processed readily by melt-blowing, which is useful for packaging and for preparing items such as biodegradable garbage bags. | 07-04-2013 |
20140020857 | FREEZE DRIED PULP AND METHOD OF MAKING - A method for making a dry pulp comprising the steps of
| 01-23-2014 |
20140128560 | PROCESS TO PREPARE CROSSLINKABLE TRIFLUOROSTYRENE POLYMERS AND MEMBRANES - Described herein is a trifluorostyrene compound that can be used as a monomer to form crosslinkable polymers, and their use as polymer electrolyte membranes. | 05-08-2014 |
20150197876 | GRAFTED PARA-ARAMID FIBER AND METHOD OF MAKING - A fiber comprising poly(p-phenylene terephthalamide) having monomers such as N-(4-vinylphenyl)maleimide grafted onto the fiber surface. | 07-16-2015 |
20150197886 | GRAFTED PARA-ARAMID FIBER AND METHOD OF MAKING - A method of making a fiber comprised of poly(p-phenylene terephthalamide) having monomer groups grafted onto the fiber surface, the method comprising the steps of (i) providing a fiber of poly(p-phenylene terephthalamide) that has been dried to remove adsorbed moisture, (ii) treating the fiber, in a non-polar solvent that will not dissolve the fiber, with a phosphazene base that exhibits a pKa in dimethylsulfoxide of at least 21 so as to generate anions at the amide sites on the surface of the poly(p-phenylene terephthalamide) fiber, (iii) washing the base-activated fiber with an aprotic solvent, (iv) grafting a monomer onto the anion sites so as to introduce reactive functional groups onto the surface of the poly(p-phenylene terephthalamide) fiber, and (v) washing the grafted fiber of step (iv) with a protic solvent to extract any residual base compounds and grafting agents that are unbound to the surface of the fibers. | 07-16-2015 |
Patent application number | Description | Published |
20130170963 | HYBRID BLADE OUTER AIR SEAL FOR GAS TURBINE ENGINE - A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face. | 07-04-2013 |
20130205786 | COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE - A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge. | 08-15-2013 |
20130205787 | TRI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE - A gas turbine engine component includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section positioned between the inlet and the outlet. The diffusing section includes a first lobe, a second lobe adjacent the first lobe and a third lobe adjacent the second lobe. The first lobe and the second lobe meet at a first ridge and the second lobe and the third lobe meet at a second ridge. | 08-15-2013 |
20130205790 | MULTI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE - A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet. | 08-15-2013 |
20130205792 | COOLING HOLE WITH ASYMMETRIC DIFFUSER - A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. | 08-15-2013 |
20130205801 | MULTI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE - A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet at the first wall surface, an outlet at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally from the metering section, a third lobe adjacent the second lobe and diverging longitudinally and laterally from the metering section, and a transition region having an end adjacent the outlet and a portion that extends between the lobes and the outlet. The first and third lobes each include a curved outer portion. | 08-15-2013 |
20130206733 | EDM METHOD FOR MULTI-LOBED COOLING HOLE - A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges. | 08-15-2013 |
20130209232 | MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS - A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed. | 08-15-2013 |
20130209269 | GAS TURBINE ENGINE COMPONENT WITH MULTI-LOBED COOLING HOLE - A component for a gas turbine engine includes a wall and a cooling hole extending through the wall. The wall has a first surface and a second surface. The cooling hole includes a metering section extending downstream from an inlet in the first surface of the wall and a diffusion section extending from the metering section to an outlet in the second surface of the wall. The diffusion section includes a first plurality of lobes diverging longitudinally and laterally from the metering section on a first side of a centerline axis of the cooling hole and a second plurality of lobes diverging longitudinally and laterally from the metering section on a second side of the centerline axis. | 08-15-2013 |
20130243575 | COOLING PEDESTAL ARRAY - A turbine engine component includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals. | 09-19-2013 |
20130251536 | HYBRID AIRFOIL FOR A GAS TURBINE ENGINE - A hybrid airfoil for a gas turbine engine according to an exemplary embodiment of this disclosure can include a leading edge portion, a trailing edge portion, and an intermediate portion between the leading edge portion and the trailing edge portion. The leading edge portion can be made of a first material, the trailing edge portion can be made of a second material, and the intermediate portion can be made of a third material. At least two of the first material, the second material and the third material are different materials. | 09-26-2013 |
20130280081 | GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS - A core for an airfoil includes a refractory metal structure having a variable thickness. An airfoil includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness, and the second thickness is less than 0.060 inch (1.52 mm). A method of manufacturing a refractory metal core includes depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of a refractory metal core, and producing the core having a variable thickness. | 10-24-2013 |
20130280091 | GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING - An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil. | 10-24-2013 |
20130280093 | GAS TURBINE ENGINE CORE PROVIDING EXTERIOR AIRFOIL PORTION - A core has a body that includes a cooling passage portion with a film cooling passage portion extending there from to a film cooling hole portion. An exterior airfoil portion is connected to the film cooling hole portion and is spaced apart from the cooling passage portion to provide a space surrounding the film cooling hole portion that corresponds to an exterior airfoil wall. | 10-24-2013 |
20130323079 | TURBOMACHINERY COMPONENT COOLING SCHEME - A turbomachinery component includes a surface exposed to hot working fluid flow. The surface has an undulating contour formed from a series of alternating protuberances and troughs. A set of three cooling outlets is associated with each trough. | 12-05-2013 |
20130323080 | VORTEX GENERATORS FOR IMPROVED FILM EFFECTIVENESS - An airfoil includes a suction surface, a pressure surface, a first showerhead cooling hole and a second showerhead cooling hole. The suction surface and the pressure surface both extend axially between a leading edge and a trailing edge, as well as radially from a root section to a tip section. The first showerhead cooling hole and the second showerhead cooling hole both extend into pressure surface near the leading edge. The first showerhead cooling hole and the second showerhead cooling hole are angled in opposing directions. | 12-05-2013 |
20140000282 | TURBINE BLADE PLATFORM WITH U-CHANNEL COOLING HOLES | 01-02-2014 |
20140010650 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall. | 01-09-2014 |
20140047844 | GAS TURBINE ENGINE COMPONENT HAVING PLATFORM TRENCH - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench. | 02-20-2014 |
20140075754 | SYSTEM METHOD FOR MACHINING AIRCRAFT COMPONENTS - A method for manufacturing an aircraft component according to one embodiment of this disclosure includes providing a machining system including a controller, at least one sensor, and a tool for machining. The method further includes providing an aircraft component, and machining the aircraft component with the tool based on feedback from the at least one sensor. | 03-20-2014 |
20140127013 | GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core. | 05-08-2014 |
20140140829 | TURBINE ENGINE COOLING SYSTEM WITH AN OPEN LOOP CIRCUIT - A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit. | 05-22-2014 |
20140271101 | MODULATED TURBINE VANE COOLING - A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity. | 09-18-2014 |
20140321961 | MATE FACE COOLING HOLES FOR GAS TURBINE ENGINE COMPONENT - A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage. | 10-30-2014 |
20150160097 | LONG WAVE INFRARED SENSING FOR TURBOMACHINE - A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade. | 06-11-2015 |
20150252682 | HYBRID BLADE OUTER AIR SEAL FOR GAS TURBINE ENGINE - A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face. | 09-10-2015 |
20150345304 | GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE - A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. | 12-03-2015 |
20150345319 | DUAL WALLED SEAL ASSEMBLY - A seal assembly that may be for turbine engine includes a first wall defining in-part a first flowpath and a second wall defining in-part a second flowpath having a pressure that is greater than the first flowpath. The second wall has a plurality of metering apertures in fluid communication between the second flowpath and a cavity defined by and between the first and second walls. The walls may be convoluted and generally, resiliently compressed between two substantially opposing surfaces for providing a seal between the two flowpaths. | 12-03-2015 |
20150345396 | GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE - A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure. | 12-03-2015 |
20150354365 | GAS TURBINE ENGINE AIRFOIL WITH LARGE THICKNESS PROPERTIES - An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location. | 12-10-2015 |
20150354465 | TURBINE STAGE COOLING - A turbine cooling air generation system for a gas turbine engine includes a first fluid pathway connecting a compressor bleed outlet and a mixing valve, a second fluid pathway connecting the compressor bleed outlet and an input of a heat exchanger, and a third fluid pathway connecting an output of the heat exchanger and the mixing valve. The mixing valve is further connected to an input of a turbine stage active cooling system. | 12-10-2015 |
20160003068 | METHOD FOR DETECTING A COMPROMISED COMPONENT - A method for providing visually detectable changes to a surface that has been subjected to a temperature in excess of a predetermined temperature. A coating is applied to the surface, wherein the coating will melt when the predetermined temperature has been reached. Centrifugal forces acting on the melted coating will cause it to be displaced such that the disturbed surface is visibly detectable upon inspection after solidifying. | 01-07-2016 |
20160003477 | SELF-COOLED ORIFICE STRUCTURE - A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls. | 01-07-2016 |
20160024944 | TRANSIENT LIQUID PAHSE BONDED TURBINE ROTOR ASSEMBLY - A rotor assembly for a turbine engine includes a rotor disk constructed of a first material. Multiple rotor blades constructed of a second material are connected to the rotor disk via a diffusion material. | 01-28-2016 |
20160025006 | SELF-COOLED ORIFICE STRUCTURE - A self-cooled orifice structure, that may be for a combustor of a gas turbine engine includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous first wall extending axially between the hot and cold side panels and spaced radially outward from a centerline. The structure may further include a first plurality of helical vanes projecting laterally, radially, inward from the first wall for flowing cooling air in a spiraling fashion through the cold side panel, then through the hot side panel. | 01-28-2016 |
20160032416 | GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING - A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another. The layers are joined to one another with reference to CAD data relating to a particular cross-section of an airfoil. The airfoil is produced with leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. An exterior wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the exterior wall to provide an impingement cavity between the exterior wall and the impingement wall. Multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. | 02-04-2016 |
20160032732 | GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS - An airfoil for a gas turbine engine includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness. The second thickness is less than 0.060 inch (1.52 mm). | 02-04-2016 |
20160047251 | COOLING HOLE HAVING UNIQUE METER PORTION - A gas turbine engine component has a cooling hole with a metering section. The metering section includes a convex surface and a concave surface, with a first arcuate channel connecting an end of the convex surface and an end of the concave surface. The end of the convex surface and the end of the concave surface define a dimension that is smaller than a diameter of the arcuate channel. | 02-18-2016 |
20160069198 | CASTING OPTIMIZED TO IMPROVE SUCTION SIDE COOLING SHAPED HOLE PERFORMANCE - A gas turbine engine component includes a pressure side, a suction side, a leading edge, a trailing edge, an outer surface and an inner surface. The inner surface is positioned within the outer surface and defines a core. The inner surface has a first protrusion. | 03-10-2016 |
20160084090 | METHOD AND ASSEMBLY FOR REDUCING SECONDARY HEAT IN A GAS TURBINE ENGINE - A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage. | 03-24-2016 |
20160090844 | GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE CONFIGURATION - A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another. The first pass includes first and second portions nested relative to one another and overlapping in a thickness direction. The first and second portions are adjacent to one another by sharing a common wall. The first portion is provided on the suction side. The second portion is provided on the pressure side. | 03-31-2016 |