General Electric Company patent applications published on October 5th, 2023

Patent applications for General Electric Company on October 5th, 2023

CASTING MOLD (17713540)

Inventor Evin Nathaniel Barber

Brief explanation

The abstract describes an intermediate investment casting mold that consists of a shell and a core. The shell has an outer surface and an inner surface, which creates an interior space. The core is positioned inside the shell but is not in direct contact with the inner surface, leaving a void between them. The mold may also contain multiple anchors.

Abstract

An intermediate investment casting mold includes at least a shell and a core. The shell has an outer surface and an inner surface, with the inner surface defining an interior for the shell. The core is located in the interior of the shell and is at least partially spaced from the inner surface of the shell. A void can be defined as the space between the core and the inner surface. The intermediate investment casting mold can include a plurality of anchors.

METHOD AND APPARATUS FOR ROBOTIC ARM NAVIGATION (17712403)

Inventor Andrew Crispin Graham

Brief explanation

The abstract describes a system where a robotic arm is used to examine a part. The operator provides instructions for the arm's tip motion, and the arm also receives sensor readings and an environmental map. These inputs are used by a machine learning model that has been trained previously. The model generates control signals that are sent to an actuator on the arm, allowing it to move automatically and gain traction in the passage. The arm moves according to the specified movement instructions.

Abstract

A robotic arm is inserted into a passage of a part to be examined. Operator instructions defining a tip motion for a tip of the robotic arm, sensor readings, and an environmental map are received. The operator instructions, the environmental map and sensor readings are applied to a previously trained machine learning model to produce control signals. The control signals to an actuator on the arm to control a movement of the robotic arm allowing the robotic arm to automatically gain traction in the passage and automatically move according to the movement.

Apparatus and Method for Tool Monitoring (17713371)

Inventor Todd William Danko

Brief explanation

The abstract describes an apparatus that consists of a tool with two separate parts connected by a joint. The tool has two inertial measurement units (IMUs) attached to each part. A control circuit is connected to the IMUs and receives information about the tool's position. The control circuit processes this information to determine the position of each part of the tool. It does this by first calculating the absolute orientation of each part and then calculating the difference in position between the two parts.

Abstract

An apparatus comprises a tool having a first portion and a second portion that are separated by at least a first area of articulation. A first inertial measurement unit is affixed with respect to that first portion and a second inertial measurement unit is affixed with respect to that second portion. A control circuit operably couples to those inertial measurement units and receives corresponding information regarding those portions of the tool. The control circuit can then process that received information to generate positional proprioception information as regards those monitored tool portions. By one approach, the control circuit generates that positional proprioception information by first determining an absolute orientation of each of the tool portions independent of one another and then calculating a differential pose as a function of the determined absolute orientation of those tool portions.

TOOLING ASSEMBLY FOR DECREASING POWDER USAGE IN A POWDER BED ADDITIVE MANUFACTURING PROCESS (18330476)

Inventor Hongqing Sun

Brief explanation

The abstract describes a tooling assembly designed for a powder bed additive manufacturing machine. This assembly is used to mount multiple components, specifically compressor blades, in order to facilitate a repair process. The tooling assembly consists of component fixtures that hold each compressor blade, a mounting plate that holds the component fixtures, and a complementary fixture with voids where the compressor blades are placed. By using this assembly, less powder is needed to fill the powder bed during the manufacturing process.

Abstract

A tooling assembly for mounting a plurality of components, such as compressor blades, in a powder bed additive manufacturing machine to facilitate a repair process is provided. The tooling assembly includes component fixtures configured for receiving each of the compressor blades, a mounting plate for receiving the component fixtures, and a complementary fixture defining a plurality of voids within which the compressor blades are received when the complementary fixture is mounted to the mounting plate such that less powder is required to fill the powder bed.

YTTRIA-STABILIZED ZIRCONIA SLURRY AND METHODS OF APPLICATION THEREOF (17841861)

Inventor Atanu Saha

Brief explanation

The abstract describes coated components and the methods used to create them. These components have a coating that consists of three different sizes of micrograins: coarse, medium, and fine. Each type of micrograin contains a yttria-stabilized zirconia (YSZ) constituent. The abstract also provides the chemical formula for the YSZ constituent.

Abstract

Coated components, along with methods of their formation, are provided. The coating may include a component having a surface and a coating over the surface of the component. The coating may include a first plurality of coarse micrograins having an coarse median grain size of greater than 10 μm to 20 μm, a second plurality of medium micrograins having a medium median grain size of 4 μm to 10 μm, a third plurality of fine micrograins having a fine median grain size of 0.001 μm to less than 4 μm. Each of the coarse micrograins, medium micrograins, and fine micrograins may include, independently, a yttria-stabilized zirconia (YSZ) constituent having a chemical formula of (ZrO)(YO)with x is from greater than 0 to less than 1.

AIRFOIL ASSEMBLY WITH A STRUCTURALLY REINFORCED FOAM CORE (17712701)

Inventor Raghuveer Chinta

Brief explanation

The abstract describes an airfoil assembly that includes a central spar, a blade skin, and a support structure. The central spar extends in the radial direction and the blade skin surrounds it to form an airfoil shape. The airfoil has a pressure side and a suction side that extend between a leading edge and a trailing edge. The blade skin and central spar create at least one cavity, and the support structure is located within this cavity. The support structure consists of a foam material with a foam reinforcement structure embedded within it.

Abstract

An airfoil assembly comprising a central spar extending along the radial direction; a blade skin positioned around the central spar to define an airfoil that has a pressure side and a suction side extending in the axial direction between a leading edge and a trailing edge, wherein at least one cavity is defined between the blade skin and the central spar; and a support structure positioned at least partially within the at least one cavity. The support structure comprises: a foam; and a foam reinforcement structure embedded within the foam.

FAN BLADE WITH INTRINSIC DAMPING CHARACTERISTICS (18329467)

Inventor Ravindra Shankar Ganiger

Brief explanation

The abstract describes a fan blade design that has built-in damping characteristics. The fan blade consists of an exterior body with two sides. It also includes two hairpin structures, one on each side of the exterior body. These hairpin structures have different stiffness levels, which helps in reducing vibrations and increasing stability of the fan blade.

Abstract

Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure corresponds to a first stiffness and the second hairpin structure corresponds to a second stiffness different than the first stiffness.

CERAMIC MATRIX COMPOSITE COMPONENT INCLUDING COOLING CHANNELS AND METHOD OF PRODUCING (18322856)

Inventor Thomas Earl Dyson

Brief explanation

The abstract describes a ceramic matrix composite component and a method of making it. The component consists of multiple layers of ceramic matrix composite material stacked together to form a solid structure. Within this structure, there are elongated functional features that are aligned with the layers. These features have an inlet that allows cooling fluid to flow into them from a fluid source. The layers are cut through to create bores that connect the functional features to an outlet on the outer surface of the component. Additionally, there are film cooling throughholes that are cut through the layers from the inner surface of the component to an outlet on the outer surface.

Abstract

A ceramic matrix composite component and method of fabrication including a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration forming a densified body and one or more elongate functional features formed therein and in alignment with the plurality of longitudinally extending ceramic matrix composite plies. Each of the elongate functional features includes an inlet configured to be in fluid communication with a flow of cooling fluid from a fluid source. One or more bores cut through the plurality of ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite component. One or more film cooling throughholes cut through the ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component.

COOLING PASSAGE EXIT OPENING CROSS-SECTIONAL AREA REDUCTION FOR TURBINE SYSTEM COMPONENT (17657420)

Inventor Kyle J. Lewis

Brief explanation

The abstract describes a component of a turbine system that has a cooling passage to regulate its temperature. The component includes a hollow member made of a material with a high melt temperature, which is placed in the cooling passage to reduce its cooling capabilities. This is done by creating a smaller exit opening for the cooling passage, which helps identify and address any excess cooling in certain passages.

Abstract

A turbine system component includes a body having an exterior surface, and a cooling passage defined in the body. The cooling passage has a first cross-sectional area in the body. The component also includes a hollow member defining a first exit opening at the exterior surface of the body and coupled in the cooling passage. The hollow member, at the first exit opening, has a second cross-sectional area that is less than the first cross-sectional area, creating an exit opening with a smaller dimension than the original cooling passage. The hollow member is made of a material having a melt temperature higher than an operating temperature of the turbine system. The hollow member(s) reduces the cooling capabilities of the cooling passage. A cooling profile of the component can be generated to identify those cooling passages having excess cooling so they can have their exit openings reduced in cross-sectional area.

ADJUSTABLE INLET GUIDE VANE ANGLE MONITORING DEVICE (17657637)

Inventor Daniel CARTER

Brief explanation

The abstract describes a device that can monitor the angle of an inlet guide vane in a gas turbine engine. The device includes a position sensor attached to the vane, a sensor plate attached to the position sensor, and a limit switch that stops the vane from moving when the sensor plate is detected. The position sensor determines the angle of the vane, allowing for monitoring and control of the engine's performance.

Abstract

The present application provides an adjustable inlet guide vane angle monitoring device for monitoring an angular position of an inlet guide vane mounted about a compressor of a gas turbine engine. The adjustable inlet guide vane angle monitoring device may include a position sensor attached to the inlet guide vane, a sensor plate attached to the position sensor, and a limit switch positioned about the sensor plate. The position sensor determines the angular position of the inlet guide vane and the limit switch prevents movement of the inlet guide vane upon detection of the sensor plate.

TURBINE ENGINE SERVICING TOOL AND METHOD FOR USING THEREOF (17707380)

Inventor Ambarish J. Kulkarni

Brief explanation

The abstract describes a tool and method for servicing a turbine engine. The tool is inserted into the engine through an access opening and is used to remove material from the engine's blades. The tool includes a wiper mount and a wiper with a surface designed to contact and remove material from the blades. The tool also has a body, an actuator, and fluid flowpaths for deploying the wiper and providing fluid to the engine's blades.

Abstract

A servicing tool for a turbine engine and a method for using thereof are provided. A method includes inserting the tool into an access opening of the turbine engine, contacting a blade of the turbine engine, and removing material from the blade. The tool may comprise a wiper mount and a wiper, including a wiper surface, configured to contact and remove material from the blades. The tool may further comprise a body, an actuator, and fluid flowpaths for deploying the wiper and providing fluid locally to the blades of the turbine engine.

VIBRATIONAL DAMPING ASSEMBLY FOR USE IN AN AIRFOIL (17731653)

Inventor Karol Filip Leszczynski

Brief explanation

The abstract describes three different components: vibrational damping assemblies, turbomachine airfoils, and exhaust diffusers. It focuses on the vibrational damping assembly, which includes a pin connected to a turbomachine component. The pin has a body and a disk attached to it. There is also a plate placed between the disk and the turbomachine component. This plate can move relative to the pins and the turbomachine component to reduce vibrations experienced by the turbomachine component.

Abstract

Vibrational damping assemblies, turbomachine airfoils, and exhaust diffusers are provided. A vibrational damping assembly includes at least one pin coupled to the turbomachine component. The at least one pin has a pin body and a disk coupled to the pin body. The vibrational damping assembly further includes at least one plate disposed between the disk and the turbomachine component. The at least one plate is movable between the disk and the turbomachine component relative to the plurality of pins and relative to the turbomachine component to dampen vibrations experienced by the turbomachine component.

SYSTEM AND METHOD FOR ALIGNING CASING WALL OF TURBOMACHINE (17709389)

Inventor Kyle Vanceton Mote

Brief explanation

The abstract describes a system that helps align the inner and outer walls of a multi-wall casing in a turbomachine. This system includes a positioner that pushes one side of the inner wall towards the direction of rotation of the rotor inside the casing. The positioner can be powered by a spring, fluid, electricity, or a combination of these. It is designed to push the inner wall into a recess next to a flanged coupling between two sections of the outer wall.

Abstract

A system includes a casing alignment system configured to align an inner wall with an outer wall of a multi-wall casing of a turbomachine having a rotor. The casing alignment system includes a first alignment positioner configured to bias a first lip of the inner wall in a direction of rotation of the rotor disposed within the multi-wall casing. The alignment positioner may include a spring, a fluid-driven alignment positioner, an electric-driven alignment positioner, or a combination thereof. The alignment positioner may be configured to bias the first lip within a first recess adjacent a first flanged coupling between first and second wall sections of the outer wall.

SHROUD PIN FOR GAS TURBINE ENGINE SHROUD (17713515)

Inventor Mark Anthony Holleran

Brief explanation

The abstract describes a shroud assembly for a gas turbine engine. The assembly includes a shroud segment with a shroud wall and a hanger assembly with a hanger wall. An attachment pin assembly connects the shroud segment and the hanger assembly. The attachment pin assembly consists of a first member that fits tightly with the hanger wall and extends through the shroud attachment opening. The first member has a hollow core. A second member extends through the hollow core of the first member and has a rim at one end and a secondary attachment member at the other end.

Abstract

A shroud assembly is provided for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction. The shroud assembly includes: a shroud segment extending substantially along the circumferential direction and including a shroud wall, the shroud wall defining a shroud attachment opening; a hanger assembly including a hanger wall defining a hanger attachment opening; and an attachment pin assembly including a first member defining an interference fit with the hanger wall through the hanger attachment opening and including a shoulder contacting the hanger wall, the first member further extending through the shroud attachment opening and defining a hollow core; and a second member extending through the hollow core of the first member, the second member extending between a first end and a second end, the second member including a rim at the first end and a secondary attachment member at the second end.

ECCENTRIC GUTTER FOR AN EPICYCLICAL GEAR TRAIN (17657685)

Inventor Xiaohua Zhang

Brief explanation

The abstract describes a gearbox for a gas turbine engine. The gearbox consists of a rotor and a gutter. An oil system is designed to supply oil to the gearbox. The rotor can rotate around a central axis and when it does, it expels oil in a radial direction. The gutter is located outside the rotor and is positioned eccentrically, meaning it is not centered with respect to the rotor. Its purpose is to collect the oil that is expelled by the rotor during rotation.

Abstract

A gearbox for a gas turbine engine. The gearbox including a rotor and a gutter. The oil system is configured to supply oil to the gearbox. The rotor is rotatable about a rotation axis. The rotor expels oil radially outward when the rotor rotates. The gutter is positioned radially outward of the rotor to collect oil expelled by the rotor when the rotor rotates. The gutter is positioned eccentrically with respect to the rotor.

AIR-TO-AIR HEAT EXCHANGER POTENTIAL IN GAS TURBINE ENGINES (17706814)

Inventor Eyitayo James Owoeye

Brief explanation

The abstract describes an air-to-air heat exchanger that is connected to a gas turbine engine. The heat exchanger's efficiency is determined by a calculation involving the surface area of the heat transfer and the airflow capacity of the engine. The potential of the heat exchanger falls within a range depending on the bypass ratio (a measure of the amount of air that bypasses the engine) and the surface area density. The potential ranges from 6.7 to 19.5 for a bypass ratio between 3 and 10, and from 2.9 to 12.2 for a bypass ratio between 10 and 20. The surface area density ranges from 3,000 to 10,000 m/m² for the first range, and from 1,000 to 10,000 m/m² for the second range.

Abstract

An air-to-air heat exchanger in flow communication with a gas turbine engine is provided. The air-to-air heat exchanger has an air-to-air heat exchanger potential defined by a product raised to a half power, the product being a heat transfer surface area density associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine. The air-to-air heat exchanger potential is between about 6.7 and 19.5 for a bypass ratio associated with the gas turbine engine between about 3 and 10 and the heat transfer surface area density being between about 3,000 m/mand 10,000 m/mand is between about 2.9 and 12.2 for a bypass ratio associated with the gas turbine engine between about 10 and 20 and the heat transfer surface area density being between about 1,000 m/mand 10,000 m/m.

FUEL NOZZLE VALVE SEALS FOR HIGH TEMPERATURE (17657182)

Inventor Christopher E. Wolfe

Brief explanation

The abstract describes a fuel nozzle valve that controls the flow of fuel. It consists of a liner with a channel and an opening for fuel to pass through, as well as a seat. There is also a plunger with a stud and a base, which can move to either seal or open the opening of the valve. Additionally, there is a metal resilient member that comes into contact with the base of the plunger and the seat of the liner to create a seal when the plunger is moved to seal the valve.

Abstract

A fuel nozzle valve includes a fuel nozzle valve liner having a channel with an opening for allowing fuel to flow therethrough and a seat. A plunger has a stud and a base substantially perpendicular to the stud, the plunger being configured to move relative to the fuel nozzle valve liner to seal or to open the opening of the fuel nozzle valve. The fuel nozzle valve further includes a metal resilient member configured to contact the base of the plunger and the seat of the fuel nozzle valve liner to seal the opening of the fuel nozzle valve when the plunger is moved to seal the fuel nozzle valve.

GAS TURBINE ENGINE WITH FUEL CELL ASSEMBLY (17712747)

Inventor Honggang Wang

Brief explanation

This abstract describes a method for operating a gas turbine engine. The method involves supplying a primary fuel to the combustor of the engine, which includes a compressor, a turbine, and a spool that rotates with the compressor and turbine. The method also includes receiving data about a parameter of the spool and adjusting the flow of a secondary fuel to the combustor based on this data.

Abstract

A method of operating a gas turbine engine is provided. The method includes: providing a flow of a primary fuel to a combustor of a turbomachine, the turbomachine including a compressor, a turbine, and a spool rotatable with the compressor and the turbine; receiving data indicative of a spool parameter of the spool; and modifying a flow of a secondary fuel to the combustor in response to the received data indicative of the spool parameter of the spool.

CASCADE THRUST REVERSER ASSEMBLY FOR A GAS TURBINE ENGINE (17713597)

Inventor Trevor Howard Wood

Brief explanation

The abstract describes a design for a thrust reverser assembly used in gas turbine engines. The assembly includes a nacelle assembly, which is a protective housing around the engine, and a cascade assembly. The cascade assembly is enclosed by the nacelle assembly and consists of one or more movable cascade members. These cascade members can be adjusted between a stowed configuration, where they have a smaller size, and a deployed configuration, where they have a larger size. In the deployed configuration, the cascade members form a cascade segment. The second radial extent, or size, of the cascade members in the deployed configuration is greater than the first radial extent in the stowed configuration.

Abstract

A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.

METHOD AND SYSTEM FOR DETERMINING AND TRACKING WIND TURBINE TOWER DEFLECTION (17712321)

Inventor Bernard P. Landa

Brief explanation

The abstract describes a system and method for measuring the deflection of a wind turbine tower. The system includes a nacelle with a machine head and rotor on top of the tower. A fixed location on the tower is established, and the total deflection of that location is determined. The system then calculates the deflection components caused by non-thrust loads on the tower and subtracts them from the total deflection to determine the deflection caused by operational thrust loads on the rotor.

Abstract

A system and method are provided for determining deflection of a tower of a wind turbine, the wind turbine including a nacelle with a machine head and a rotor atop of the tower. A fixed location relative to the tower is established, and a total deflection of a geographic location (“geo-location”) of the fixed location is determined. Components of the total deflection are determined that are generated by non-thrust loads acting on the tower. The non-thrust loads deflection components are subtracted from the total deflection to determine a thrust loads deflection component corresponding to deflection of the tower from operational thrust loads on the rotor.

MULTISIPHON PASSIVE COOLING SYSTEM WITH LIQUID BRIDGE (18009088)

Inventor Naveenan Thiagarajan

Brief explanation

The abstract describes a passive cooling system that uses multiple siphons to cool a heat-generating component. The system includes a heat exchanger, a distribution manifold, a condensing unit, and two conduits. A liquid bridge connects the conduits and allows a two-phase cooling medium to circulate through the system. The liquid bridge transfers the cooling medium in a liquid state from one conduit to the other or to the distribution manifold.

Abstract

A multisiphon passive cooling system includes a heat exchanger thermally connected to a heat-generating component located within an enclosure, a distribution manifold located below the heat exchanger, a condensing unit located external to the enclosure and above the heat exchanger, and a first conduit thermally connected to the heat exchanger. The first conduit is fluidly connected to the distribution manifold and the condensing unit. The cooling system also includes a second conduit fluidly connected to the condensing unit and the distribution manifold, a liquid bridge fluidly connected to the first conduit and the second conduit or the distribution manifold, and a two-phase cooling medium that circulates through a loop defined by the first conduit, the liquid bridge, the condensing unit, the second conduit, the heat exchanger, and the distribution manifold. As such, the liquid bridge transfers the cooling medium in a liquid state from the first conduit to the second conduit or the distribution manifold.

OIL SCAVENGE SYSTEM FOR A GEARBOX (17657683)

Inventor Xiaohua Zhang

Brief explanation

This abstract describes a gearbox that consists of a gear and a gutter. The gear can rotate in a specific direction around an axis and when it rotates, it expels oil outward in a radial direction. The gutter is positioned outside the gear and is designed to collect the oil expelled by the gear during rotation. The gutter has different surfaces, including an axial surface and radial surfaces. It also has openings that allow the collected oil to flow through. The radial surfaces are oriented in a way that intersects the axial surface, and the openings are present on both the axial surface and one of the radial surfaces.

Abstract

A gearbox including a gear and a gutter. The gear is rotatable about a rotational axis in a rotational direction. The gear has a radial direction and an axial direction, and the gear expels oil radially outward when the gear rotates. The gutter is positioned radially outward of the gear in the radial direction of the gear to collect oil expelled by the gear when the gear rotates. The gutter includes an axial surface, a plurality of radial surfaces including a first radial surface and a second radial surface, and at least one opening to allow the oil collected in the gutter to flow therethrough. Each of the first radial surface and the second radial surface is oriented in a direction intersecting the axial surface, and the at least one opening is formed on both the axial surface and one of the first radial surface and the second radial surface.

CHECK VALVE ASSEMBLY (17657511)

Inventor Victor Moreno Patan

Brief explanation

The abstract describes a check valve assembly that consists of two flappers and an internal passage. There is also a nozzle within the passage that generates a flow inside. When fluid flows through the assembly, the flappers can move between an open position, allowing flow through the passage, and a closed position, blocking flow. In the open position, the internal flow has lower pressure than the flow outside the passage, which keeps the flappers open.

Abstract

A check valve assembly includes a first flapper, a second flapper, an internal passage formed by the first flapper and the second flapper, and a nozzle disposed within the internal passage and configured to generate an internal flow in the internal passage. In response to a fluid flow through the check valve assembly, the first flapper and the second flapper are configured to move between an open position allowing the internal flow through the internal passage and an outer flow outside the internal passage, and a closed position preventing flow through the internal passage. When the first flapper and the second flapper are operably in the open position, the internal flow has a lower pressure than the outer flow outside of the internal passage, such that the first flapper and the second flapper are maintained in the open position.

LINER ASSEMBLY FOR A COMBUSTOR (17811771)

Inventor Ranganatha Narasimha Chiranthan

Brief explanation

The abstract describes a liner assembly for a combustor, which is a device used in combustion engines. The liner assembly includes a liner that forms the combustion chamber of the combustor. At the front end of the liner, there is a looped section with bends, creating a flexible joint. This joint allows for the absorption of vibrations, preventing them from traveling downstream through the liner.

Abstract

A liner assembly for a combustor. The liner assembly includes a liner defining a combustion chamber of the combustor. The liner includes a looped section at a forward end of the liner. The looped section includes one or more bends such that the looped section forms a compliant joint and vibrations are dampened through the liner downstream of the looped section.

AMMONIA FIRED COMBUSTOR OPERATING METHOD (17708860)

Inventor Hatem M. Selim

Brief explanation

This method involves delivering a mixture of fuel and oxidant to a combustion chamber. The fuel used is ammonia (NH), which is burned in the first zone of the chamber, producing nitrogen oxides (NOx) as combustion gases. To reduce the NOx emissions, a second portion of oxidant is introduced into the second zone of the chamber, where unburned ammonia is broken down into ammonia intermediates. The NOx reacts with these intermediates, reducing their concentration. As a byproduct of this process, hydrogen is produced. Finally, a third portion of oxidant is delivered to the third zone, where the byproduct hydrogen is burned. The amount of oxidant delivered in the third zone is greater than the amounts delivered in the first and second zones.

Abstract

A method includes delivering fuel and a first portion of oxidant as a rich mixture to the first zone of the combustion chamber. The fuel includes ammonia (NH). The method further includes burning the rich mixture in the first zone. Combustion gases containing nitrogen oxides (NOx) are produced. The method further includes delivering a second portion of oxidant into the second zone to break down unburned ammonia into ammonia intermediates in the second zone. The nitrogen oxides (NOx) are consumed by reacting with the ammonia intermediates in the second zone. Byproduct hydrogen is produced as a result of breaking down the unburned ammonia into the ammonia intermediates. The method further includes delivering a third portion of oxidant into the third zone. The byproduct hydrogen is burned in the third zone. The third portion of oxidant is greater than the first portion of oxidant and the second portion of oxidant.

ANNULAR DOME ASSEMBLY FOR A COMBUSTOR (17811762)

Inventor Ranganatha Narasimha Chiranthan

Brief explanation

The abstract describes an annular dome assembly for a combustor. The assembly consists of an annular dome made up of dome panels, with one panel having a surface facing upstream and another panel having a surface facing downstream. The dome also has arms extending from the upstream surface and apertures that go through the dome from the upstream to the downstream surface. The assembly also includes a deflector assembly made up of deflector panels. One panel has an upstream surface and a downstream surface, with arms extending from the upstream surface. These arms are mounted within the apertures of the annular dome.

Abstract

An annular dome assembly for a combustor. The annular dome assembly includes an annular dome including one or more dome panels defining the annular dome. A first dome panel includes a dome upstream surface and a dome downstream surface opposite the dome upstream surface. One or more dome arms extend from the dome upstream surface. One or more apertures extend from the dome upstream surface to the dome downstream surface. The annular dome assembly also includes a deflector assembly including one or more deflector panels defining the deflector assembly. A first deflector panel includes a deflector upstream surface and a deflector downstream surface opposite the deflector upstream surface. One or more deflector arms extend from the deflector upstream surface. Each of the one or more deflector arms are mounted within a respective aperture of the annular dome.

COMMUNICATING SECURELY WITH DEVICES IN A DISTRIBUTED CONTROL SYSTEM (18206194)

Inventor Jeffrey S. Gilton

Brief explanation

This abstract describes a method for secure communication between a server and a device. The server generates a unique code and sends it, along with its public key and a signature, to the device. The device verifies the server's public key, signs the code with its own private key, generates another unique code, and sends both codes, along with its public key, signature, and the second code, back to the server. The server verifies the codes and the device's public key, generates a secret key, encrypts it with the device's public key, signs the second code and the secret key with its own private key, and sends all this information back to the device. The device then verifies the second code, decrypts the secret key with its private key, and verifies the decrypted key. This method ensures secure communication between the server and the device.

Abstract

A method comprises a server generating a server nonce and transmitting a server public key, a key signature and the server nonce to a device, the device verifying the server public key, signing the server nonce with a device private key, generating a device nonce, and transmitting the server nonce, the server nonce signature, a device public key, a device key signature, and the device nonce to the server, the server verifying the server nonce and the device public key, generating a session key, encrypting the session key with the device public key, signing the device nonce and the session key with a server private key, and transmitting the device nonce, the signed device nonce and session key, and the encrypted session key to the device, and the device verifying the device nonce, decrypting the encrypted session key with the device private key, and verifying the decrypted session key.