| Raytheon Technologies Corporation Patent applications |
| Patent application number | Title | Published |
|---|
| 20220298921 | Self-Guiding Carbon Seal System - An apparatus has a first member, a shaft rotatable relative to the first member about an axis, and a seal system. The seal system has: a seal carried by the first member and having a seal face; and a seat carried by the shaft and having a seat face in sliding sealing engagement with the seal face. The seal system is a dry face seal system. The seat further includes a section having: an outer diameter surface encircled by the seal; and a rim. | 09-22-2022 |
| 20220298645 | LASER INDUCED, FINE GRAINED, GAMMA PHASE SURFACE FOR NiCoCrAlY COATINGS PRIOR TO CERAMIC COAT - A process for forming a thermal barrier coating on a part comprising depositing an aluminum containing bond coat on the part, the bond coat comprising a surface; cleaning the surface to remove oxides and debris from the surface of the bond coat; forming a gamma phase layer proximate the surface of the bond coat; forming an aluminum oxide layer on the surface of the bond coat; and depositing a ceramic topcoat on the aluminum oxide layer on the bond coat. | 09-22-2022 |
| 20220290322 | SYSTEMS, FORMULATIONS, AND METHODS FOR REMOVAL OF DIFFUSION COATING FROM AIRFOILS - A method of removing an aluminide diffusion coating from a gas turbine engine component having a nickel alloy base material may comprise: disposing the gas turbine engine component in a solution, the solution including an acid between 5% and 15% vol./vol. and water between 85% and 95% vol./vol.; placing the gas turbine engine component in electrical contact with a graphite plate; and removing the aluminide diffusion coating from the gas turbine engine component in response to placing the gas turbine engine component in electrical contact with the graphite plate and disposing the gas turbine engine component in the solution. | 09-15-2022 |
| 20220288674 | Arcuate Seed Casting Method - A casting method includes forming a seed. The seed has a first end and a second end and an inner diameter (ID) surface and an outer diameter (OD) surface. The seed second end is placed in contact or spaced facing relation with a chill plate. The first end is contacted with molten material. The molten material is cooled and solidified so that a crystalline structure of the seed propagates into the solidifying material. At least a portion of the seed contacted with the molten material has a solidus higher than a solidus of at least an initial pour portion of the molten material. | 09-15-2022 |
| 20220281050 | FLOW DIRECTORS AND SHIELDS FOR ABRASIVE FLOW MACHINING OF INTERNAL PASSAGES - An insert apparatus for protecting a curved inner surface within a passageway from abrasion during an abrasive machining operation is disclosed. In various embodiments, the insert apparatus includes a shield having a shell shaped to match a curved portion of the curved inner surface of the passageway and a shaft having a first end connected to the shell and a second end connected to a member configured to maintain the shaft within the passageway and the shell positioned against the curved inner surface during the abrasive machining operation. | 09-08-2022 |
| 20220281025 | SYSTEMS AND METHODS FOR CASE REPAIR - A method for repairing a pocket of a case for a variable stator assembly may comprise: receiving, via a processor, a plurality of wear depths, each wear depth in the plurality of wear depths corresponding to a wear portion in a stator pocket in a plurality of stator pockets; determining, via the processor, a plurality of thicknesses of a coating to be deposited based on the plurality of wear depths, each thickness of the coating in the plurality of thicknesses corresponding to the wear portion for each stator pocket in the plurality of stator pockets; and commanding, via the processor, a coating spray torch to deposit the coating in the wear portion of each stator pocket in the plurality of stator pockets. | 09-08-2022 |
| 20220276205 | MICROTEXTURE REGION CHARACTERIZATION SYSTEMS AND METHODS - The present disclosure provides methods and systems for the characterization of a microtexture of a sample, component, or the like. The methods may include methods of determining a service life limiting region of a component, determining a treatment method for a component, and/or selecting components from a batch of components for use in production. The characterization may include calculating a microtexture level indicator from ultrasonic C-scan images for various samples, regions, components, or the like. The microtexture level indicator may include at least one of an average peak factor, a standard deviation of peak amplitude, and/or a baseband bandwidth. | 09-01-2022 |
| 20220276006 | SYSTEMS AND METHODS FOR VACUUM FURNACE POST-PROCESSING - A method of generating a loaded layout in a vacuum furnace corresponding to an actual layout in the vacuum furnace during operation of the vacuum furnace may comprise receiving, via a processor, a visual data of a loading process of the vacuum furnace from a camera; comparing, via the processor, the visual data to a predetermined maximum capacity layout for the vacuum furnace; and arranging, via the processor, the visual data into the loaded layout in response to comparing the visual data. | 09-01-2022 |
| 20220275758 | PLUMBING WITH INTERNAL FLOW GUIDES - A conduit assembly may comprise: a pipe; a plurality of hollow passages disposed through the pipe; and a plurality of flow guides disposed in the pipe, each flow guide in the plurality of flow guides at least partially defining a respective hollow passage in the plurality of hollow passages. The conduit assembly may act as a heat exchanger. | 09-01-2022 |
| 20220266333 | SYSTEMS, FORMULATIONS, AND METHODS FOR REMOVAL OF CERAMIC CORES FROM TURBINE BLADES AFTER CASTING - A solution is provided and includes a strong base, a corrosion inhibitor, wherein the strong base is an alkali metal hydroxide, wherein the corrosion inhibitor is at least one of an organic acid having a-COOH functional group or an alkali metal salt of one of an organic acid having a-COOH functional group. | 08-25-2022 |
| 20220259980 | SYSTEM FOR AN IMPROVED STATOR ASSEMBLY - An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine. | 08-18-2022 |
| 20220252013 | Hybrid Seal Dual Runner - A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward. | 08-11-2022 |
| 20220251972 | ROTOR STACK BUSHING WITH ADAPTIVE TEMPERATURE METERING FOR A GAS TURBINE ENGINE - A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole. | 08-11-2022 |
| 20220243616 | ASYMMETRY IN ANNULAR CENTERING SPRING - An assembly for use in a bearing compartment having an axis includes a bearing outer race configured to be located in the bearing compartment. The assembly further includes at least one annular spring positioned in the bearing outer race and being asymmetric in at least one of the axial direction or the circumferential direction relative to the axis to reduce the likelihood of amplification of vibration experienced by the at least one annular spring. | 08-04-2022 |
| 20220228507 | INNER SHROUD ASSEMBLY FOR GAS TURBINE ENGINE VARIABLE VANE SYSTEM - An inner shroud assembly of a variable vane actuation system for a gas turbine engine includes a shroud assembly comprising a multiple of forward shroud segments and a respective multiple of aft shroud segments. A multiple of variable vanes are rotationally retained at an inboard trunion between the forward and aft shroud segments of the shroud assembly. A retainer assembly includes a multiple of retainer ring segments that retain the forward and aft shroud segments together. The inner shroud assembly is assembled into an engine case with an inboard extending feature that engages with an outer diameter feature of each of the multiple of retainer ring segments. | 07-21-2022 |
| 20220221056 | NON-METALLIC ENGINE CASE INLET COMPRESSION SEAL FOR A GAS TURBINE ENGINE - A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section. | 07-14-2022 |
| 20220098988 | Turbine Blade Trailing Edge Cooling Feed - A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn. | 03-31-2022 |
| 20220097132 | Additive Manufactured Powder Processing System - A system for treatment of atomized powder including a fluidized bed operable to treat feedstock alloy powders. A method of treating atomized powder including communicating an inert gas into a fluidized bed; communicating an atomized powder into the fluidized bed; and heating the atomized powder in the fluidized bed, eject the treated powders out of the fluidized bed to quench the powders. | 03-31-2022 |
| 20220010731 | ACOUSTICALLY TREATED PANELS - A system for dampening noise generated by a gas turbine engine is disclosed. In various embodiments, the system includes a fan exit guide vane having a leading edge, a trailing edge and a pocket that extends in a chordwise direction between the leading edge and the trailing edge; and an acoustic panel configured to be received within the pocket, the acoustic panel including a back sheet, a face sheet and a core disposed between the back sheet and the face sheet, the core having a first cavity extending between a first wall and a second wall and a second cavity disposed within the first cavity. | 01-13-2022 |
| 20220003125 | WEAR RESISTANT, SELF-LUBRICATING STATIC SEAL - A seal assembly for a gas turbine engine includes a seal composed of a nickel-based superalloy; a component in contact with the seal and defining a seal-counterface; and a coating on the seal at the seal-counterface, wherein the coating is a ternary oxide. | 01-06-2022 |
| 20220003119 | FILM COOLING DIFFUSER HOLE - An airfoil for a gas turbine engine is disclosed. In various embodiments, the airfoil includes a cooling passage; an outer wall separating a core flow path from the cooling passage; a diffuser in fluid communication with the cooling passage and opening into the core flow path, the diffuser being characterized by a linear ridge on a downstream end of the diffuser; and a thermal barrier coating covering the outer wall and the linear ridge. | 01-06-2022 |
| 20220002209 | Protective Coating for Ceramic Matrix Composites - An article has a substrate and a layer atop the substrate. The layer has: a matrix comprising at least one of hafnium silicate (HfSiO | 01-06-2022 |
| 20220001508 | SMOOTHING ROUND INTERNAL PASSAGES OF ADDITIVELY MANUFACTURED PARTS USING METALLIC SPHERES - A method for smoothing surface roughness within an internal passageway is disclosed. In various embodiments, the method comprises developing a first sphere progression through a length of the internal passageway, each sphere within the first sphere progression having a first sphere diameter greater than or equal to a diameter of the internal passageway; and developing a second sphere progression through the length of the internal passageway, each sphere within the second sphere progression having a second sphere diameter greater than the first sphere diameter, whereby the inner surface of the internal passageway is smoothed, first by the first sphere progression and then by the second sphere progression. | 01-06-2022 |
| 20210404659 | MULTI-DIRECTION HOLE FOR RAIL EFFUSION - A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice. | 12-30-2021 |
| 20210402423 | FIXTURE ASSEMBLY FOR COATING COMBUSTOR PANELS - A fixture assembly for supporting workpieces in a coating process includes a shaft; and a plurality of fixtures each having a workpiece support surface and a shaft mount defining a shaft mounting structure, wherein the shaft mounting structure extends from the workpiece support surface such that, when the shaft mounting structure is engaged with the shaft, workpiece support surfaces of the fixtures are positioned facing radially outwardly away from the shaft. | 12-30-2021 |
| 20210396388 | DILUTION HOLES WITH RIDGE FEATURE FOR GAS TURBINE ENGINES - A grommet may define a dilution hole in a combustor panel. The grommet may comprise a ridge having a stepped geometry formed about an inner diameter of the grommet, the ridge comprising a passage. The passage may comprise an outlet. The ridge may further comprise a fillet about the inner diameter of the grommet, wherein the outlet is configured to direct a cooling flow circumferentially along the fillet and fill the ridge with the cooling flow. | 12-23-2021 |
| 20210396151 | MONOLITHIC COMBUSTOR FOR ATTRITIABLE ENGINE APPLICATIONS - A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange. | 12-23-2021 |
| 20210381387 | NEEDLED CERAMIC MATRIX COMPOSITE COOLING PASSAGES - A method for forming a passage in a ceramic matrix composite component incudes forming a core for a ceramic matrix composite component; embedding a hollow member into the core at a desired location for a passage in the ceramic matrix composite component; wrapping the core with a ceramic material; and inserting a rod through the hollow member and into the core. | 12-09-2021 |
| 20210372622 | MAIN MIXER IN AN AXIAL STAGED COMBUSTOR FOR A GAS TURBINE ENGINE - A main mixer including a swirler along an axis, the swirler including an outer swirler with a multiple of outer vanes, and a center swirler with a multiple of center vanes and a swirler hub along the axis, the swirler hub including a fuel manifold and an inner swirler with a multiple of inner vanes that support a centerbody, the multiple of inner vanes interconnect the fuel manifold and the centerbody. | 12-02-2021 |
| 20210372525 | HIGH PRESSURE COMPRESSOR SEAL-RING WITH IMPROVED WEAR RESISTANCE - A compressor seal-ring assembly includes a seal formed of a nickel, cobalt or iron-based superalloy; a counterface positioned for sealing interaction with the seal; and a lubricant coating on the seal, the lubricant coating being formed of a CoCrAlY-containing material. | 12-02-2021 |
| 20210370447 | PISTON SEAL ASSEMBLY GUARDS AND INSERTS FOR SEAL GROOVE - A method of repairing a piston seal assembly comprises removing worn material from a piston seal groove to generate a worked seal groove, applying a groove buildup member to the worked seal groove, and disposing a seal member proximate the groove buildup member. | 12-02-2021 |
| 20210363896 | LOW FRICTION, WEAR RESISTANT VARIABLE VANE BUSHING - A variable vane assembly includes a variable vane; a trunnion arranged on one end of the variable vane; a bushing mated to the trunnion to define an interface between the trunnion and the bushing; and a surface modification on at least one of the trunnion and the bushing at the interface, whereby frictional heating at the interface during operation of the assembly is reduced. | 11-25-2021 |
| 20210355838 | Substrate Edge Configurations for Ceramic Coatings - In a method for manufacturing an article, the article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface. Each of the first channels are machined in the body by plunging a rotating bit into the first surface and drawing the rotating bit down the bevel surface. The coating is thereafter applied. | 11-18-2021 |
| 20210348761 | PANEL BURN THROUGH TOLERANT SHELL DESIGN - A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path. | 11-11-2021 |
| 20210348562 | THERMAL BARRIER COATING WITH REDUCED EDGE CRACK INITIATION STRESS AND HIGH INSULATING FACTOR - A thermal barrier coating disposed on a substrate comprising a plurality of surface features formed on the substrate proximate an inner side of the substrate, each of the plurality of surface features comprising a metallic column having a top with rounded edges; a dense layer disposed in a valley located between each of the plurality of surface features, and the dense layer disposed on the top and covering the rounded edges; a thermally insulating topcoat disposed over the plurality of surface features. | 11-11-2021 |
| 20210348523 | REDUCED RADIAL CLEARANCE SEAL SYSTEM - A seal system for a gas turbine engine includes a seal runner manufactured of a Molybdenum alloy material that provides a first coefficient of thermal expansion and a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion. | 11-11-2021 |
| 20210348278 | Solution Based Corrosion Inhibitors for Aluminum Alloy Thermal Spray Coatings | 11-11-2021 |
| 20210348077 | ABRADABLE COATING hBN FILLER MATERIAL AND METHOD OF MANUFACTURE - A process for solid lubricant filler powder used in abradable coating manufacture comprising mixing a bentonite clay and a hexagonal boron nitride powder to form a mixture of the bentonite clay and the hexagonal boron nitride powder; consolidating the bentonite clay and the hexagonal boron nitride powder to form a composite material; heat treating the composite material to at least 500 degrees centigrade; breaking up the composite material into a variety of sizes; and segregating the composite material to produce a final product of free flowing, low dust powder of composite hexagonal boron nitride and calcined bentonite. | 11-11-2021 |
| 20210347700 | PRECERAMIC IONIC SYSTEMS - A process of forming a Si-containing ceramic comprises forming a Si-based polymeric composition. The process includes neutralizing a charge of said Si-based polymeric composition. The process includes adding thermal energy under a controlled atmosphere to the Si-based polymeric composition. A turbine engine component comprises an airfoil and the airfoil comprises a Ceramic Matrix Composite (CMC) material. | 11-11-2021 |
| 20210340956 | SYSTEMS AND METHODS FOR OPTIMAL SPEED PROTECTION FOR POWER TURBINE GOVERNING - A control system for limiting power turbine torque (QPT) of a gas turbine engine includes a controller including a processor and memory configured to control the gas turbine engine, the controller including an engine control module that provides an effector command signal to a gas generator of the gas turbine engine; a power turbine governor module that outputs a preliminary torque request (QPT_req_pre); and a power turbine torque (QPT) optimal limiter module that outputs a maximum torque topper (QPT_max) to limit a power turbine speed overshoot of the gas turbine engine; wherein the controller outputs a minimum value between the preliminary torque request (QPT_req_pre) and the maximum torque topper (QPT_max) to the engine control module. | 11-04-2021 |
| 20210332979 | EXTENDED BULKHEAD PANEL - A combustor may comprise an outer combustor panel and an inner combustor panel radially inward of the outer combustor panel. A bulkhead panel may extend radially between the outer combustor panel and the inner combustor panel. An outer spacer may be located between an outer flange of the bulkhead panel and the outer combustor panel. An inner spacer may be located between an inner flange of the bulkhead panel and the inner combustor panel. | 10-28-2021 |
| 20210332757 | PLUMBING WITH INTERNAL FLOW GUIDES - A conduit assembly may comprise: a pipe; a plurality of hollow passages disposed through the pipe; and a plurality of flow guides disposed in the pipe, each flow guide in the plurality of flow guides at least partially defining a respective hollow passage in the plurality of hollow passages. The conduit assembly may act as a heat exchanger. | 10-28-2021 |
| 20210332715 | PROCESS AND MATERIAL CONFIGURATION FOR MAKING HOT CORROSION RESISTANT HPC ABRASIVE BLADE TIPS - An abrasive coating system for a substrate of an airfoil in a turbine engine high pressure compressor, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, the matrix material consisting of unalloyed chromium and unalloyed aluminum distributed throughout the matrix material, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material. | 10-28-2021 |
| 20210324800 | REFLECTIVE COATING AND COATING PROCESS THEREFOR - A process for coating a component includes applying a bond coat on a substrate of a component; applying a thermal barrier material to the bond coat; and applying a conforming reflective layer to the thermal barrier material, the conforming reflective layer conforming to porous microstructure of the ceramic coating. | 10-21-2021 |
| 20210324499 | METALLIC ALLOY - An alloy that may include nickel, aluminum from 4.8 wt. % to 5.15 wt. %; cobalt from 18 wt. % to 19 wt. %, chromium from 11.9 wt. % to 12.9 wt. %, molybdenum from 2.8 wt. % to 3.6 wt. %, and niobium from 0.05 wt. % to 0.1 wt. %. The alloy may further include tungsten from 0.05 wt. % to 0.1 wt. %. The alloy may further include tantalum from 0.05 wt. % to 0.1 wt. %. | 10-21-2021 |
| 20210323685 | SYSTEMS AND METHODS FOR HYBRID ELECTRIC GAS TURBINE ENGINES - A hybrid electric gas turbine propulsion system may comprise: a first propulsion system, a second propulsion system, and a third propulsion system. The first propulsion system may comprise a first fan, a first turbine, a first compressor, and a first electric motor, the first fan operably coupled to the first turbine and the first compressor by a first shaft, the first shaft coupled to the first electric motor, the first shaft configured to be disposed radially inward of a fuselage of an aircraft. The second propulsion system and the third propulsion system may be in accordance with the first propulsion system. The hybrid electric gas turbine propulsion system may be symmetric about a vertical plane extending through a neutral aerodynamic axis. | 10-21-2021 |
| 20210323128 | TOOL SYSTEM FOR INSTALLATION/REMOVAL OF INTERFERENCE FIT COMPONENTS - A tool system to install an interference fit component within a bore of a component, includes a guide bushing that at least partially fits within a bore of a component. A drive screw is of a length to extend through the guide bushing and the bore. A threaded insert is receivable at least partially within the bore, the threaded insert receivable at least partially within the interference fit component. | 10-21-2021 |
| 20210318071 | Aircraft Heat Exchanger Panel Attachment - A heat exchanger for providing thermal energy transfer between a first flow along a first flowpath and a second flow along a second flowpath has at least one plate bank having a plurality of plates, each plate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. An inlet manifold has a first face to which the plurality of plates are mounted along their respective proximal edges. An inlet plenum has at least one inlet port and at least one outlet port. An outlet plenum has at least one outlet port and at least one inlet port. The first flowpath passes from the at least one inlet port of the inlet plenum, through the at least one passageway of each of the plurality of plates, and through the at least one outlet port of the outlet plenum. For each plate, the manifold first face has a respective associated slot capturing a portion of the plate along the proximal edge thereof to prevent extraction of the plate normal to the face. | 10-14-2021 |
| 20210180605 | TOOL FOR SIMULTANEOUS LOCAL STRESS RELIEF OF EACH OF A MULTIPLE OF LINEAR FRICTION WELDS OF A ROTOR FORGING - A tool for simultaneous local stress relief of each of a multiple of linear friction welds includes a columnar track defined along an axis, the columnar track having a helical slot; and a support structure engaged with the helical slot to translate and rotate a heat treat fixture portion along the axis. | 06-17-2021 |
| 20210010804 | CALIBRATION FOR LASER INSPECTION - A method of calibrating a laser measurement device includes positioning a calibration part, having known geometric specifications, at varying distances from the laser measurement device (within a measurement depth-of-field of the laser measurement device). The detected geometric specifications, measured at these different positions, are compared with the known specification(s) of the calibration part in order to improve the accuracy of the calibration. A calibration standoff fixture having a plurality of adjustable legs may be used in conjunction with the method to facilitate changing the position of the calibration part relative to the laser measurement device. | 01-14-2021 |
| 20210008669 | Abrasive Preforms and Manufacture and Use Methods - A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate. | 01-14-2021 |
| 20200408406 | COMBUSTOR DILUTION HOLE ACTIVE HEAT TRANSFER CONTROL APPARATUS AND SYSTEM - Systems and methods are described herein whereby an air jet is configured to manipulate local aerodynamics and/or boundary layer flows associated with a dilution hole. A gas turbine component including a combustor panel, a dilution hole located within the combustor panel and an air jet located within the combustor panel positioned in close proximity to the dilution hole is described. The dilution hole is configured to produce a flow of cooling fluid. An air flow from the air jet is configured to deflect secondary flows produced within a combustor. The air jet is located close enough to a leading edge of the dilution hole such that the air flow from the air jet manipulates a pressure gradient of the dilution hole. The air jet extends through a wall defining the dilution hole to provide an air jet inlet fed by an air flow passing through the dilution hole. | 12-31-2020 |
| 20200408169 | NACELLE - A nacelle may comprise an inlet cowling defining an inlet of the nacelle, wherein the inlet cowling comprises an inlet cowling maximum point and an inlet cowling aft edge, wherein the inlet cowling aft edge comprises an aft edge length; and a boat tail cowling disposed aft of the inlet cowling, wherein the boat tail cowling comprises a boat tail cowling forward edge having a forward edge length, and wherein the boat tail cowling forward edge is disposed adjacent to the inlet cowling aft edge. The forward edge length may be smaller than the aft edge length, forming a step, the step being defined by a portion of the inlet cowling aft edge that is radially outward of the boat tail cowling forward edge. | 12-31-2020 |
| 20200408104 | SYSTEM AND METHOD FOR CONTROLLING DUAL STARTER AIR VALVE - A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor. | 12-31-2020 |
