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| − | ==Patent applications for Raytheon Technologies Corporation on November 30th, 2023==
| + | '''Summary of the patent applications from Raytheon Technologies Corporation on November 30th, 2023''' |
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| − | ===ONE PIECE HIGH TEMPERATURE WASHER ([[US Patent Application 18143135. ONE PIECE HIGH TEMPERATURE WASHER simplified abstract|18143135]])===
| + | Raytheon Technologies Corporation has recently filed several patents related to aircraft propulsion systems and components. These patents cover various aspects such as assembly design, gear systems, gas turbine engines, seal systems, airfoil design, coated fiber structures, and electric machines. |
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| | + | In terms of assembly design, one patent application describes an assembly for an aircraft propulsion system that includes a bladed rotor and a thrust vectoring exhaust nozzle. The nozzle is designed to direct gas propelled by the rotor, with different directions for different modes of operation. |
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| − | '''Main Inventor'''
| + | Another patent application focuses on a gear system for an aircraft propulsion system. This system includes a sun gear, a ring gear, intermediate gears, a carrier, and brakes. The brakes are used to control the rotation of the ring gear and the carrier. |
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| − | Raymond Hayes
| + | A gas turbine engine patent application describes a specific architecture with a propulsor section, compressor section, turbine section, and a geared architecture. The power density ratio of the engine is calculated by dividing the thrust provided by the engine by the volume of the turbine section. |
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| | + | Another patent application discusses a propulsion system with two propulsor rotors and a gas turbine engine core. The core rotates at different speeds to drive the respective rotors for generating thrust and lift. |
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| − | '''Brief explanation'''
| + | A seal system patent application describes a dry face seal system that includes a seal and a seat. The seat has a rim and an outer diameter surface encircled by the seal. |
| − | The abstract describes a washer with a cabinet and a washing zone accessible through a doorway. The washer includes a door with an inflatable door seal that is connected to a pneumatic air system. There is also a clamp for securing a part within the washing zone. The washing zone has a wash nozzle and an air nozzle that are connected to a process water system and a pneumatic system, respectively, for washing and drying the part. The washer also has a safety controller and a process controller. The safety controller is connected to the door, the pneumatic system, and the process water system, while the process controller is connected to the door, the pneumatic system, the process water system, and the clamp. The process controller is responsible for washing the part.
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| − | * Washer with a cabinet and a washing zone accessible through a doorway
| + | An airfoil design patent application focuses on using a ceramic matrix composite (CMC) laminate material for improved performance and efficiency. The design optimizes the distribution of fiber plies within the airfoil section. |
| − | * Door with an inflatable door seal connected to a pneumatic air system
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| − | * Clamp for securing a part within the washing zone
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| − | * Wash nozzle and air nozzle connected to a process water system and a pneumatic system for washing and drying the part
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| − | * Safety controller connected to the door, the pneumatic system, and the process water system
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| − | * Process controller connected to the door, the pneumatic system, the process water system, and the clamp
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| − | * Process controller responsible for washing the part
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| − | '''Abstract'''
| + | A coated fiber structure patent application describes a fiber with a coating system applied around it, including interface, intermediate, and outer layers. The coating layers may contain a metallic element. |
| − | A washer including a cabinet with a washing zone accessible through a doorway; a door with an inflatable door seal for sealing the doorway, the door seal coupled to a pneumatic air system; a clamp for securing a part within the washing zone; a wash nozzle and air nozzle are located within the washing zone and fluidly coupled to a process water system, pneumatic system respectively for washing and drying the part; a safety controller operatively coupled to the door, the pneumatic system and the process water system; and a process controller operatively coupled to the door, the pneumatic system, the process water system and the clamp, the process controller configured to wash the part.
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| − | ===LASER TREATMENT OF MACHINED CERAMIC SURFACE FOR SEALING ([[US Patent Application 18302964. LASER TREATMENT OF MACHINED CERAMIC SURFACE FOR SEALING simplified abstract|18302964]])===
| + | In summary, Raytheon Technologies Corporation has filed recent patents related to various aspects of aircraft propulsion systems and components, including assembly design, gear systems, gas turbine engines, seal systems, airfoil design, coated fiber structures, and electric machines. |
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| | + | Notable applications: |
| | + | * Assembly for an aircraft propulsion system with a bladed rotor and thrust vectoring exhaust nozzle. |
| | + | * Gear system for an aircraft propulsion system with a sun gear, ring gear, intermediate gears, carrier, and brakes. |
| | + | * Gas turbine engine with a specific architecture and power density ratio calculation. |
| | + | * Propulsion system with two propulsor rotors and a gas turbine engine core. |
| | + | * Seal system with a dry face seal design. |
| | + | * Airfoil design using a ceramic matrix composite laminate material. |
| | + | * Coated fiber structure for use in a ceramic matrix composite. |
| | + | * Assembly for an aircraft with a rotating structure, geartrain, propulsor rotor, and electric machine. |
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| − | '''Main Inventor'''
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| − |
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| − | Howard J. Liles
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| − | '''Brief explanation'''
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| − | The patent application describes a method for machining a silicon-containing gas turbine engine article to create a specific feature.
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| − | * The machining process removes the closed-pore surface of the article, resulting in an open-pore machined surface.
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| − | * The open-pore machined surface is then treated with a laser to induce the formation of an oxide in the article.
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| − | * This oxide seals the open-pore machined surface, transforming it into a closed-pore treated surface.
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| − | * The purpose of this method is to improve the performance and durability of the gas turbine engine article.
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| | | | |
| − | '''Abstract'''
| + | ==Patent applications for Raytheon Technologies Corporation on November 30th, 2023== |
| − | A method includes machining a closed-pore surface of a silicon-containing gas turbine engine article to produce a feature. The machining causes removal of the closed-pore surface to produce an open-pore machined surface. The open-pore machined surface is then laser-treated to cause formation of an oxide in the silicon-containing gas turbine engine article that seals the open-pore machined surface to produce a closed-pore treated surface.
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| − | ===MACHINE CONTROL FOR GRINDING MACHINE ([[US Patent Application 18143150. MACHINE CONTROL FOR GRINDING MACHINE simplified abstract|18143150]])=== | + | ===ONE PIECE HIGH TEMPERATURE WASHER ([[US Patent Application 18143135. ONE PIECE HIGH TEMPERATURE WASHER simplified abstract (Raytheon Technologies Corporation)|18143135]])=== |
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| − | '''Brief explanation'''
| + | ===LASER TREATMENT OF MACHINED CERAMIC SURFACE FOR SEALING ([[US Patent Application 18302964. LASER TREATMENT OF MACHINED CERAMIC SURFACE FOR SEALING simplified abstract (Raytheon Technologies Corporation)|18302964]])=== |
| − | The abstract describes a grinding machine that consists of several components and features.
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| − | * The machine includes a support pedestal that holds a drive motor, which in turn supports an abrasive wheel that can rotate.
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| − | * There is a motor drive that is connected to the drive motor, allowing for control and operation.
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| − | * A safety controller is connected to both the drive motor and motor drive, ensuring safe operation of the machine.
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| − | * An emergency stop (E-stop) button is also connected to the safety controller, providing a quick way to halt the machine in case of an emergency.
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| − | * A foot pedal switch is connected to the safety controller, allowing for convenient and hands-free operation of the machine.
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| − | * The machine is powered by a 480 volt alternating current 3 phase electrical power supply, providing the necessary power for the drive motor and other components.
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| − | '''Abstract''' | + | '''Main Inventor''' |
| − | A grinding machine including a support pedestal that supports a drive motor that supports an abrasive wheel rotatably coupled to the drive motor; a motor drive operatively coupled to the drive motor; a safety controller operatively coupled with the drive motor and motor drive; an E-stop operatively coupled to the safety controller; a foot pedal switch operatively coupled to the safety controller; and a 480 volt alternating current 3 phase electrical power supply electrically coupled to the drive motor.
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| − | ===MACHINE CONTROL FOR DYNABRAID MACHINE ([[US Patent Application 18143143. MACHINE CONTROL FOR DYNABRAID MACHINE simplified abstract|18143143]])=== | + | Howard J. Liles |
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| | + | |
| | + | ===MACHINE CONTROL FOR GRINDING MACHINE ([[US Patent Application 18143150. MACHINE CONTROL FOR GRINDING MACHINE simplified abstract (Raytheon Technologies Corporation)|18143150]])=== |
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| − | '''Brief explanation'''
| + | ===MACHINE CONTROL FOR DYNABRAID MACHINE ([[US Patent Application 18143143. MACHINE CONTROL FOR DYNABRAID MACHINE simplified abstract (Raytheon Technologies Corporation)|18143143]])=== |
| − | The abstract describes an abrasive belt machine with several components and features.
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| − | * The machine includes a support housing with a pivoting arm that holds an abrasive belt.
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| − | * The abrasive belt is connected to a drive motor, allowing it to rotate.
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| − | * A safety controller is connected to the drive motor, ensuring safe operation.
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| − | * An emergency stop (E-stop) is also connected to the safety controller, providing a quick way to stop the machine in case of an emergency.
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| − | * A foot pedal switch is connected to the drive motor, allowing the operator to control the machine's operation.
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| − | * The machine is powered by a 480 volt alternating current 3 phase electrical power supply, which is connected to the drive motor.
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| − | '''Abstract''' | + | '''Main Inventor''' |
| − | An abrasive belt machine including a support housing having a pivoting arm that supports an abrasive belt rotatably coupled to a drive motor; a safety controller operatively coupled with the drive motor; an E-stop operatively coupled to the safety controller; a foot pedal switch operatively coupled to the drive motor; and a 480 volt alternating current 3 phase electrical power supply electrically coupled to the drive motor.
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| − | ===AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR ([[US Patent Application 18202733. AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR simplified abstract|18202733]])=== | + | Raymond Hayes |
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| | + | ===AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR ([[US Patent Application 18202733. AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR simplified abstract (Raytheon Technologies Corporation)|18202733]])=== |
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| − | '''Brief explanation'''
| + | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202736. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract (Raytheon Technologies Corporation)|18202736]])=== |
| − | The patent application describes a propulsion system for an aircraft, consisting of a gas turbine engine core, a first propulsor rotor, and a second propulsor rotor.
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| − | * Gas turbine engine core includes compressor, combustor, turbine sections, and a rotating structure with a turbine rotor.
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| − | * The first propulsor rotor is driven by the rotating structure in two modes.
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| − | * The first propulsor rotor has variable pitch blades, including a blade that can pivot between a thrust position and an idle position.
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| − | * The first blade is in the thrust position during the first mode and in the idle position during the second mode.
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| − | * The second propulsor rotor is driven by the rotating structure only during the second mode.
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| − | | |
| − | '''Abstract'''
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| − | A propulsion system is provided for an aircraft. This aircraft propulsion system includes a gas turbine engine core, a first propulsor rotor and a second propulsor rotor. The gas turbine engine core includes a compressor section, a combustor section, a turbine section and a rotating structure. The rotating structure includes a turbine rotor within the turbine section. The first propulsor rotor is rotatably driven by the rotating structure during a first mode and a second mode. The first propulsor rotor includes a plurality of variable pitch blades. The variable pitch blades include a first blade configured to pivot between a thrust position and an idle position. The first blade is in the thrust position during the first mode. The first blade is in the idle position during the second mode. The second propulsor rotor is rotatably driven by the rotating structure during the second mode.
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| − | | |
| − | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202736. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract|18202736]])=== | |
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| − | '''Brief explanation'''
| + | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202734. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract (Raytheon Technologies Corporation)|18202734]])=== |
| − | The patent application describes an assembly for an aircraft that includes a rotating structure, a geartrain, a propulsor rotor, and an electric machine.
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| − | * The rotating structure consists of a turbine rotor.
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| − | * The geartrain is composed of a sun gear, a ring gear, multiple intermediate gears, and a carrier.
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| − | * The sun gear is driven by the rotating structure and is capable of rotation.
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| − | * Each intermediate gear is positioned between the sun gear and the ring gear and is meshed with both gears.
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| − | * The intermediate gears are mounted on the carrier and can rotate.
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| − | * The propulsor rotor is driven by the carrier and is capable of rotation.
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| − | * The electric machine is connected to the ring gear.
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| − | | |
| − | '''Abstract'''
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| − | An assembly is provided for an aircraft. The aircraft assembly includes a rotating structure, a geartrain, a propulsor rotor and an electric machine. The rotating structure includes a turbine rotor. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The sun gear is rotatably driven by the rotating structure. Each of the intermediate gears is between and meshed with the sun gear and the ring gear. Each of the intermediate gears is rotatably mounted to the carrier. The propulsor rotor is rotatably driven by the carrier. The electric machine is coupled to the ring gear.
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| − | | |
| − | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202734. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract|18202734]])=== | |
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| − | '''Brief explanation'''
| + | ===MULTILAYER COATING FOR OXIDATION PROTECTION ([[US Patent Application 18202036. MULTILAYER COATING FOR OXIDATION PROTECTION simplified abstract (Raytheon Technologies Corporation)|18202036]])=== |
| − | The abstract describes an assembly for an aircraft that includes a carrier, a first gear system, a second gear system, and an idler gear.
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| − | * The assembly is designed for use in an aircraft.
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| − | * It includes a carrier, which is a component that supports and holds the other gears.
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| − | * The first gear system consists of a first sun gear, a first ring gear, and multiple first intermediate gears.
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| − | * Each of the first intermediate gears is located between and meshes with the first sun gear and the first ring gear.
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| − | * The first intermediate gears are mounted to the carrier and can rotate.
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| − | * The second gear system also includes a second sun gear, a second ring gear, and multiple second intermediate gears.
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| − | * Similar to the first gear system, each of the second intermediate gears is located between and meshes with the second sun gear and the second ring gear.
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| − | * The second intermediate gears are also mounted to the carrier and can rotate.
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| − | * The idler gear connects the first ring gear to the second ring gear, allowing them to transfer motion between each other.
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| − | | |
| − | '''Abstract'''
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| − | An assembly is provided for an aircraft. This aircraft assembly includes a carrier, a first gear system, a second gear system and an idler. The first gear system includes a first sun gear, a first ring gear and a plurality of first intermediate gears. Each of the first intermediate gears is between and is meshed with the first sun gear and the first ring gear. Each of the first intermediate gears is rotatably mounted to the carrier. The second gear system includes a second sun gear, a second ring gear and a plurality of second intermediate gears. Each of the second intermediate gears is between and is meshed with the second sun gear and the second ring gear. Each of the second intermediate gears is rotatably mounted to the carrier. The idler gear couples the first ring gear to the second ring gear.
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| − | | |
| − | ===MULTILAYER COATING FOR OXIDATION PROTECTION ([[US Patent Application 18202036. MULTILAYER COATING FOR OXIDATION PROTECTION simplified abstract|18202036]])=== | |
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| − | '''Brief explanation'''
| + | ===CMC LAMINATE AIRFOIL WITH PLY DROPS ([[US Patent Application 18319586. CMC LAMINATE AIRFOIL WITH PLY DROPS simplified abstract (Raytheon Technologies Corporation)|18319586]])=== |
| − | The patent application describes a coated fiber structure for use in a ceramic matrix composite.
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| − | * The structure consists of a fiber with a coating system applied around it.
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| − | * The coating system includes an interface coating layer that directly contacts the fiber.
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| − | * The interface coating layer is made of either boron nitride or a boron-doped pyrocarbon.
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| − | * There is at least one intermediate layer that extends coaxially with and directly contacts the interface layer.
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| − | * The intermediate layer is made of either silicon or boron nitride.
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| − | * An outer layer is also present, extending coaxially with and directly contacting the interface layer.
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| − | * The interface coating layer, the intermediate layer(s), and the outer layer may contain a metallic element.
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| − | | |
| − | '''Abstract'''
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| − | A coated fiber structure for use in a ceramic matrix composite comprises a fiber and a coating system applied to and circumscribing the fiber. The coating system comprises an interface coating layer in direct contact with the fiber, the interface coating layer comprising one of boron nitride and a boron-doped pyrocarbon, at least one intermediate layer extending coaxially with and in direct contact with the interface layer, the at least one intermediate layer comprising at least one of silicon and boron nitride, and an outer layer extending coaxially with and in direct contact with the interface layer. At least one of the interface coating layer, the at least one intermediate layer, and the outer layer comprises a metallic element.
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| − | | |
| − | ===CMC LAMINATE AIRFOIL WITH PLY DROPS ([[US Patent Application 18319586. CMC LAMINATE AIRFOIL WITH PLY DROPS simplified abstract|18319586]])=== | |
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| − | '''Brief explanation'''
| + | ===TURBINE ENGINE WITH TOBI SUPPORTING VANES ([[US Patent Application 18302976. TURBINE ENGINE WITH TOBI SUPPORTING VANES simplified abstract (Raytheon Technologies Corporation)|18302976]])=== |
| − | - The patent application describes an airfoil design that uses a ceramic matrix composite (CMC) laminate material.
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| − | - The airfoil section has an internal cavity and is made up of fiber plies embedded in a ceramic matrix.
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| − | - The fiber plies include a skin ply on the outside and at least one inner ply that lines the skin ply.
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| − | - The airfoil wall has fewer fiber plies at the leading and trailing ends compared to the pressure and suction sides.
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| − | - The design aims to optimize the distribution of fiber plies for improved performance and efficiency of the airfoil.
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| − | | |
| − | '''Abstract'''
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| − | An airfoil includes an airfoil section that has an airfoil wall that circumscribes an internal airfoil cavity and defines leading and trailing ends and pressure and suction sides. The airfoil wall is formed of a ceramic matrix composite (CMC) laminate comprised of fiber plies disposed in a ceramic matrix. The fiber plies include a skin fiber ply that defines an exterior of the airfoil section and at least one inner fiber ply that lines the skin fiber ply. At least one inner fiber ply locally terminates at one of the leading end or the trailing end such that the airfoil wall has fewer of the fiber plies in the leading end or the trailing end than in each of the pressure side and the suction side.
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| − | | |
| − | ===TURBINE ENGINE WITH TOBI SUPPORTING VANES ([[US Patent Application 18302976. TURBINE ENGINE WITH TOBI SUPPORTING VANES simplified abstract|18302976]])=== | |
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| − | '''Brief explanation'''
| + | ===Self-Guiding Carbon Seal System ([[US Patent Application 18112094. Self-Guiding Carbon Seal System simplified abstract (Raytheon Technologies Corporation)|18112094]])=== |
| − | The patent application describes a gas turbine engine with a row of vanes arranged around a central axis.
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| − | * The vanes have internal cavities and outlet ports for cooling air.
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| − | * A tangential onboard injector (TOBI) supports the vanes at the inner diameter of the row.
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| − | * The TOBI has fore and aft annular walls and an outer diameter annular wall, creating an annular plenum.
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| − | * The outer diameter annular wall has TOBI inlet ports connected to the vane outlet ports, receiving cooling air from each vane into the plenum.
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| − | * The TOBI has axially-oriented nozzles to discharge the cooling air from the plenum in an aft direction.
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| − | | |
| − | '''Abstract'''
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| − | A gas turbine engine includes a circumferential row of vanes arranged about a central engine axis. The vanes include respective internal cavities and vane outlet ports for conveying cooling air. A tangential onboard injector (TOBI) radially supports the vanes at an inner diameter of the circumferential row. The TOBI includes fore and aft annular walls and an outer diameter annular wall. The fore and aft annular walls and the outer diameter annular wall define an annular plenum. The outer diameter annular wall includes TOBI inlet ports that are connected, respectively, with the vane outlet ports to receive the cooling air from each of the vanes into the plenum. The TOBI includes axially-oriented nozzles for discharging the cooling air from the plenum in an aft direction.
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| − | | |
| − | ===Self-Guiding Carbon Seal System ([[US Patent Application 18112094. Self-Guiding Carbon Seal System simplified abstract|18112094]])=== | |
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| − | '''Brief explanation'''
| + | ===AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE ([[US Patent Application 18202731. AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE simplified abstract (Raytheon Technologies Corporation)|18202731]])=== |
| − | The patent application describes an apparatus with a seal system that includes a seal and a seat.
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| − | * The seal is carried by a first member and has a seal face.
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| − | * The seat is carried by a shaft and has a seat face that slides and seals against the seal face.
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| − | * The seal system is a dry face seal system, meaning it does not require any lubrication.
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| − | * The seat also includes a section with an outer diameter surface encircled by the seal and a rim.
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| − | | |
| − | '''Abstract'''
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| − | 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.
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| − | | |
| − | ===AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE ([[US Patent Application 18202731. AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE simplified abstract|18202731]])=== | |
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| − | '''Brief explanation'''
| + | ===GAS TURBINE ENGINE WITH POWER DENSITY RANGE ([[US Patent Application 18107126. GAS TURBINE ENGINE WITH POWER DENSITY RANGE simplified abstract (Raytheon Technologies Corporation)|18107126]])=== |
| − | The patent application describes a propulsion system that includes two propulsor rotors and a gas turbine engine core.
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| − | * The first propulsor rotor generates propulsive thrust, while the second propulsor rotor generates propulsive lift.
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| − | * The gas turbine engine core consists of a compressor section, a combustor section, a turbine section, and a rotating structure.
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| − | * The rotating structure includes a turbine rotor within the turbine section.
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| − | * In the first mode, the gas turbine engine core rotates the rotating structure at a first speed to drive the first propulsor rotor and generate propulsive thrust.
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| − | * In the second mode, the gas turbine engine core rotates the rotating structure at a second speed to drive the second propulsor rotor and generate propulsive lift.
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| − | * The second rotational speed is less than eighty percent of the first rotational speed.
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| − | | |
| − | '''Abstract'''
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| − | A propulsion system includes a first propulsor rotor, a second propulsor rotor and a gas turbine engine core. The first propulsor rotor is configured to generate propulsive thrust. The second propulsor rotor is configured to generate propulsive lift. The gas turbine engine core includes a compressor section, a combustor section, a turbine section and a rotating structure. The rotating structure includes a turbine rotor within the turbine section. The gas turbine engine core is configured to rotate the rotating structure at a first rotational speed during a first mode to drive the first propulsor rotor to generate the propulsive thrust. The gas turbine engine core is configured to rotate the rotating structure at a second rotational speed during a second mode to drive the second propulsor rotor to generate the propulsive lift. The second rotational speed may be less than eighty percent of the first rotational speed.
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| − | | |
| − | ===GAS TURBINE ENGINE WITH POWER DENSITY RANGE ([[US Patent Application 18107126. GAS TURBINE ENGINE WITH POWER DENSITY RANGE simplified abstract|18107126]])=== | |
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| − | '''Brief explanation'''
| + | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202727. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract (Raytheon Technologies Corporation)|18202727]])=== |
| − | The abstract describes a gas turbine engine with specific components and a power density ratio.
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| − | * Gas turbine engine with a propulsor section, compressor section, geared architecture, and turbine section.
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| − | * Compressor section includes a first and second compressor.
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| − | * Turbine section includes a first turbine and a drive turbine.
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| − | * Power density ratio of the engine is between 4.75 and 5.5 lbf/in.
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| − | * Power density ratio is calculated by dividing the thrust provided by the engine by the volume of the turbine section.
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| − | | |
| − | '''Abstract'''
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| − | A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a first compressor and a second compressor, a geared architecture, a turbine section including a first turbine and a drive turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.
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| − | | |
| − | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202727. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract|18202727]])=== | |
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| − | '''Brief explanation'''
| + | ===THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202709. THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM simplified abstract (Raytheon Technologies Corporation)|18202709]])=== |
| − | The patent application describes an assembly for an aircraft propulsion system.
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| − | * The assembly includes a sun gear, a ring gear, a plurality of intermediate gears, a carrier, a first brake, and a second brake.
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| − | * The sun gear can rotate around a centerline axis.
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| − | * The ring gear surrounds the sun gear and can also rotate around the centerline axis.
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| − | * The intermediate gears are positioned around the centerline axis and are meshed between the sun gear and the ring gear.
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| − | * The carrier can rotate around the centerline axis and each intermediate gear is mounted to the carrier.
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| − | * The first brake is designed to slow down or stop the rotation of the ring gear around the centerline axis.
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| − | * The second brake is designed to slow down or stop the rotation of the carrier around the centerline axis.
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| − | '''Abstract'''
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| − | An assembly is provided for an aircraft propulsion system. This assembly includes a sun gear, a ring gear, a plurality of intermediate gears, a carrier, a first brake and a second brake. The sun gear is rotatable about a centerline axis. The ring gear circumscribes the sun gear and is rotatable about the centerline axis. The intermediate gears are arranged circumferentially about the centerline axis. Each of the intermediate gears is meshed between the sun gear and the ring gear. The carrier is rotatable about the centerline axis. Each of the intermediate gears is rotatably mounted to the carrier. The first brake is configured to slow and/or stop rotation of the ring gear about the centerline axis. The second brake is configured to slow and/or stop rotation of the carrier about the centerline axis.
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| − | ===THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202709. THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM simplified abstract|18202709]])=== | |
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| | Paul R. Hanrahan | | Paul R. Hanrahan |
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| − | '''Brief explanation'''
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| − | - The patent application describes an assembly for an aircraft propulsion system.
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| − | - The assembly includes a bladed rotor and a thrust vectoring exhaust nozzle.
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| − | - The bladed rotor can rotate around an axis.
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| − | - The thrust vectoring exhaust nozzle is designed to direct gas propelled by the bladed rotor.
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| − | - During the first mode, the gas is directed along a first direction, which is either parallel to the axis or angularly offset by no more than five degrees.
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| − | - During the second mode, the gas is directed along a second direction, which is angularly offset from the axis by at least seventy-five degrees.
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| − | - The thrust vectoring exhaust nozzle has a larger exit area during the second mode compared to the first mode.
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| − |
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| − | '''Abstract'''
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| − | An assembly is provided for an aircraft propulsion system. This assembly includes a bladed rotor and a thrust vectoring exhaust nozzle. The bladed rotor is rotatable about an axis. The thrust vectoring exhaust nozzle is configured to direct gas propelled by the bladed rotor out of the aircraft propulsion system along a first direction during a first mode and along a second direction during a second mode. The first direction is parallel with the axis or angularly offset from the axis by no more than five degrees. The second direction is angularly offset from the axis by at least seventy-five degrees. The thrust vectoring exhaust nozzle has a first exit area during the first mode and a second exit area during the second mode that is greater than the first exit area.
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