Difference between revisions of "Raytheon Technologies Corporation patent applications published on November 30th, 2023"
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| + | '''Summary of the patent applications from Raytheon Technologies Corporation on November 30th, 2023''' | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | 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. | ||
| + | |||
| + | |||
| + | |||
| + | |||
==Patent applications for Raytheon Technologies Corporation on November 30th, 2023== | ==Patent applications for Raytheon Technologies Corporation on November 30th, 2023== | ||
| − | ===ONE PIECE HIGH TEMPERATURE WASHER ([[US Patent Application 18143135. ONE PIECE HIGH TEMPERATURE WASHER simplified abstract|18143135]])=== | + | ===ONE PIECE HIGH TEMPERATURE WASHER ([[US Patent Application 18143135. ONE PIECE HIGH TEMPERATURE WASHER simplified abstract (Raytheon Technologies Corporation)|18143135]])=== |
| Line 9: | Line 42: | ||
| − | ===LASER TREATMENT OF MACHINED CERAMIC SURFACE FOR SEALING ([[US Patent Application 18302964. LASER TREATMENT OF MACHINED CERAMIC SURFACE FOR SEALING simplified abstract|18302964]])=== | + | ===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]])=== |
| Line 17: | Line 50: | ||
| − | ===MACHINE CONTROL FOR GRINDING MACHINE ([[US Patent Application 18143150. MACHINE CONTROL FOR GRINDING MACHINE simplified abstract|18143150]])=== | + | ===MACHINE CONTROL FOR GRINDING MACHINE ([[US Patent Application 18143150. MACHINE CONTROL FOR GRINDING MACHINE simplified abstract (Raytheon Technologies Corporation)|18143150]])=== |
| Line 25: | Line 58: | ||
| − | ===MACHINE CONTROL FOR DYNABRAID MACHINE ([[US Patent Application 18143143. MACHINE CONTROL FOR DYNABRAID MACHINE simplified abstract|18143143]])=== | + | ===MACHINE CONTROL FOR DYNABRAID MACHINE ([[US Patent Application 18143143. MACHINE CONTROL FOR DYNABRAID MACHINE simplified abstract (Raytheon Technologies Corporation)|18143143]])=== |
| Line 33: | Line 66: | ||
| − | ===AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR ([[US Patent Application 18202733. AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR simplified abstract|18202733]])=== | + | ===AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR ([[US Patent Application 18202733. AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR simplified abstract (Raytheon Technologies Corporation)|18202733]])=== |
| Line 41: | Line 74: | ||
| − | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202736. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract|18202736]])=== | + | ===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]])=== |
| Line 49: | Line 82: | ||
| − | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202734. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract|18202734]])=== | + | ===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]])=== |
| Line 57: | Line 90: | ||
| − | ===MULTILAYER COATING FOR OXIDATION PROTECTION ([[US Patent Application 18202036. MULTILAYER COATING FOR OXIDATION PROTECTION simplified abstract|18202036]])=== | + | ===MULTILAYER COATING FOR OXIDATION PROTECTION ([[US Patent Application 18202036. MULTILAYER COATING FOR OXIDATION PROTECTION simplified abstract (Raytheon Technologies Corporation)|18202036]])=== |
| Line 65: | Line 98: | ||
| − | ===CMC LAMINATE AIRFOIL WITH PLY DROPS ([[US Patent Application 18319586. CMC LAMINATE AIRFOIL WITH PLY DROPS simplified abstract|18319586]])=== | + | ===CMC LAMINATE AIRFOIL WITH PLY DROPS ([[US Patent Application 18319586. CMC LAMINATE AIRFOIL WITH PLY DROPS simplified abstract (Raytheon Technologies Corporation)|18319586]])=== |
| Line 73: | Line 106: | ||
| − | ===TURBINE ENGINE WITH TOBI SUPPORTING VANES ([[US Patent Application 18302976. TURBINE ENGINE WITH TOBI SUPPORTING VANES simplified abstract|18302976]])=== | + | ===TURBINE ENGINE WITH TOBI SUPPORTING VANES ([[US Patent Application 18302976. TURBINE ENGINE WITH TOBI SUPPORTING VANES simplified abstract (Raytheon Technologies Corporation)|18302976]])=== |
| Line 81: | Line 114: | ||
| − | ===Self-Guiding Carbon Seal System ([[US Patent Application 18112094. Self-Guiding Carbon Seal System simplified abstract|18112094]])=== | + | ===Self-Guiding Carbon Seal System ([[US Patent Application 18112094. Self-Guiding Carbon Seal System simplified abstract (Raytheon Technologies Corporation)|18112094]])=== |
| Line 89: | Line 122: | ||
| − | ===AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE ([[US Patent Application 18202731. AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE simplified abstract|18202731]])=== | + | ===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]])=== |
| Line 97: | Line 130: | ||
| − | ===GAS TURBINE ENGINE WITH POWER DENSITY RANGE ([[US Patent Application 18107126. GAS TURBINE ENGINE WITH POWER DENSITY RANGE simplified abstract|18107126]])=== | + | ===GAS TURBINE ENGINE WITH POWER DENSITY RANGE ([[US Patent Application 18107126. GAS TURBINE ENGINE WITH POWER DENSITY RANGE simplified abstract (Raytheon Technologies Corporation)|18107126]])=== |
| Line 105: | Line 138: | ||
| − | ===SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202727. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract|18202727]])=== | + | ===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]])=== |
| Line 113: | Line 146: | ||
| − | ===THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM ([[US Patent Application 18202709. THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM simplified abstract|18202709]])=== | + | ===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]])=== |
Latest revision as of 06:38, 7 December 2023
Summary of the patent applications from Raytheon Technologies Corporation on November 30th, 2023
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
Contents
- 1 Patent applications for Raytheon Technologies Corporation on November 30th, 2023
- 1.1 ONE PIECE HIGH TEMPERATURE WASHER (18143135)
- 1.2 LASER TREATMENT OF MACHINED CERAMIC SURFACE FOR SEALING (18302964)
- 1.3 MACHINE CONTROL FOR GRINDING MACHINE (18143150)
- 1.4 MACHINE CONTROL FOR DYNABRAID MACHINE (18143143)
- 1.5 AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR (18202733)
- 1.6 SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM (18202736)
- 1.7 SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM (18202734)
- 1.8 MULTILAYER COATING FOR OXIDATION PROTECTION (18202036)
- 1.9 CMC LAMINATE AIRFOIL WITH PLY DROPS (18319586)
- 1.10 TURBINE ENGINE WITH TOBI SUPPORTING VANES (18302976)
- 1.11 Self-Guiding Carbon Seal System (18112094)
- 1.12 AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE (18202731)
- 1.13 GAS TURBINE ENGINE WITH POWER DENSITY RANGE (18107126)
- 1.14 SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM (18202727)
- 1.15 THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM (18202709)
Patent applications for Raytheon Technologies Corporation on November 30th, 2023
ONE PIECE HIGH TEMPERATURE WASHER (18143135)
Main Inventor
Raymond Hayes
LASER TREATMENT OF MACHINED CERAMIC SURFACE FOR SEALING (18302964)
Main Inventor
Howard J. Liles
MACHINE CONTROL FOR GRINDING MACHINE (18143150)
Main Inventor
Raymond Hayes
MACHINE CONTROL FOR DYNABRAID MACHINE (18143143)
Main Inventor
Raymond Hayes
AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR (18202733)
Main Inventor
Paul R. Hanrahan
SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM (18202736)
Main Inventor
Paul R. Hanrahan
SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM (18202734)
Main Inventor
Paul R. Hanrahan
MULTILAYER COATING FOR OXIDATION PROTECTION (18202036)
Main Inventor
Olivier H. Sudre
CMC LAMINATE AIRFOIL WITH PLY DROPS (18319586)
Main Inventor
Russell Kim
TURBINE ENGINE WITH TOBI SUPPORTING VANES (18302976)
Main Inventor
Howard J. Liles
Self-Guiding Carbon Seal System (18112094)
Main Inventor
Joseph H. Polly
AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE (18202731)
Main Inventor
Paul R. Hanrahan
GAS TURBINE ENGINE WITH POWER DENSITY RANGE (18107126)
Main Inventor
Frederick M. Schwarz
SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM (18202727)
Main Inventor
Paul R. Hanrahan
THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM (18202709)
Main Inventor
Paul R. Hanrahan
