General Electric Company patent applications published on December 14th, 2023

Patent applications for General Electric Company on December 14th, 2023

AMORPHOUS DUCTILE BRAZE ALLOY COMPOSITIONS, AND RELATED METHODS AND ARTICLES (18454365)

Main Inventor

Raghavendra Rao Adharapurapu

Brief explanation

The abstract describes a nickel-based braze alloy composition that does not contain silicon. It includes nickel, boron (B) in a weight percentage of about 1% to 5%, and germanium (Ge) in a weight percentage of about 1% to 20%. The abstract also mentions the use of this composition to fill cracks or voids in superalloy articles, along with methods for filling such gaps. The abstract further mentions related articles of manufacture and brazing processes for joining metal components.

• Nickel-based braze alloy composition
• Contains nickel, boron (B), and germanium (Ge)
• No silicon present in the composition
• Can be used to fill cracks or voids in superalloy articles
• Methods for filling gaps with the composition are described
• Related articles of manufacture and brazing processes are disclosed

Potential Applications

• Repairing cracks or voids in superalloy articles
• Joining metal components through brazing processes

Problems Solved

• Provides a nickel-based braze alloy composition without silicon
• Offers a solution for filling cracks or voids in superalloy articles

Benefits

• Improved performance and properties compared to silicon-containing braze alloys
• Enables effective repair and joining of metal components

Abstract

A nickel-based braze alloy composition is described, including nickel, about 1 weight % to about 5 weight % boron (B); and about 1 weight % to about 20 weight % germanium (Ge). The composition is free of any silicon. Superalloy articles that contains a crack or other type of void or gap filled with the nickel-based braze alloy composition are also described, along with methods for filling such a gap. Related articles of manufacture and brazing processes to join metal components are also disclosed.

SLOTTED COATINGS AND METHODS OF FORMING THE SAME (17806608)

Main Inventor

Hrishikesh Keshavan

Brief explanation

The abstract describes a method for forming a slot in a coated part, such as a ceramic coated part, using laser ablation. The method involves focusing a laser beam to a specific depth and irradiating the coating to remove material. The laser beam is scanned in a direction perpendicular to the coating's thickness, and each subsequent pass is deeper than the previous pass.

• The method involves laser ablation to form a slot in a coated part.
• The laser beam is focused to a specific depth and irradiates the coating to remove material.
• The laser beam is scanned in a direction perpendicular to the coating's thickness.
• Each subsequent pass of laser ablation is deeper than the previous pass.

Potential applications of this technology:

• Manufacturing of coated parts with slots, such as ceramic coated parts.
• Precision machining of coated parts with complex curvilinear shapes.

Problems solved by this technology:

• Traditional methods of forming slots in coated parts may damage the coating or result in imprecise cuts.
• Laser ablation allows for precise and controlled removal of coating material without damaging the part.

Benefits of this technology:

• Precise and controlled formation of slots in coated parts.
• Minimizes damage to the coating and the part itself.
• Enables the manufacturing of complex curvilinear parts with slots.

Abstract

A coated part, such as a ceramic coated part, having a slot formed in a coating formed on a curvilinear portion of the part and a method of forming the slot. The method includes performing a plurality of laser ablation passes. Each laser ablation pass includes focusing a laser beam to a focus depth, irradiating the coating of the curvilinear portion with the laser beam focused at the focus depth to remove coating material of the coating by laser ablation, and scanning the laser beam in a scanning direction while irradiating the coating of the curvilinear portion with the laser beam. The scanning direction is a direction transverse to a thickness direction of the coating. The focus depth of each subsequent pass of the plurality of laser ablation passes is deeper in a thickness direction of the coating than the pass preceding the subsequent pass.

PRINTING ASSEMBLIES AND METHODS FOR USING THE SAME (18032263)

Main Inventor

John Sterle

Brief explanation

The patent application describes a printing assembly that includes a manifold assembly with an inlet manifold and an outlet manifold. The inlet manifold has an inlet reservoir and an inlet port, while the outlet manifold has an outlet reservoir and an outlet port. Valves are provided at each port to control the flow of material.

• The printing head is housed within a housing and is in fluid communication with the inlet reservoir and the outlet reservoir.
• The valves at the inlet port and the outlet port can be independently operated to control the flow of material from the inlet reservoir to the print heads and from the print heads to the outlet reservoir.

Potential applications of this technology:

• Printing and graphic design industries
• Manufacturing and production processes that require precise material flow control

Problems solved by this technology:

• Ensures accurate and controlled flow of material to the print heads
• Prevents leakage or wastage of material during printing processes

Benefits of this technology:

• Improved printing quality and accuracy
• Reduced material wastage and cost
• Enhanced efficiency and productivity in printing operations

Abstract

A printing assembly () is provided including a manifold assembly including an inlet manifold () including an inlet reservoir () and an inlet port (), and an outlet manifold () including an outlet reservoir () and an outlet port (). A valve is provided at each of the inlet port of the inlet manifold and at the outlet port of the outlet manifold. The valve is operable between an open position for permitting the flow of material through the port and a closed position for preventing the flow of material through the port. The printing head includes a housing and print heads provided within the housing and in fluid communication with the inlet reservoir via the inlet port and the outlet reservoir via the outlet port. The valves are independently operable to control a flow of material from the inlet reservoir to the print heads, and from the print heads to the outlet reservoir, respectively.

ADDITIVE MANUFACTURING APPARATUSES AND METHODS FOR USING THE SAME (18250859)

Main Inventor

Victor Fulton

Brief explanation

The patent application describes an additive manufacturing apparatus that includes a chassis assembly and a skin covering the chassis assembly. The chassis assembly consists of multiple sections, including a lower chassis section, an upper environmental chassis section, and a high voltage chassis section. There is also a build receptacle carriage that can be adjusted.

• The chassis assembly is made up of multiple sections, including a lower chassis section, an upper environmental chassis section, and a high voltage chassis section.
• The skin covering the chassis assembly includes doors and panels that provide access to different sections of the chassis assembly.
• The doors and panels allow for easy maintenance and adjustment of the apparatus.

Potential applications of this technology:

• Additive manufacturing or 3D printing processes
• Industrial manufacturing processes
• Prototyping and product development

Problems solved by this technology:

• Easy access to different sections of the apparatus for maintenance and adjustment
• Enhanced safety by providing separate access points for low voltage and high voltage sections
• Improved efficiency in manufacturing processes

Benefits of this technology:

• Simplified maintenance and adjustment of the apparatus
• Increased safety for operators by providing separate access points for different voltage sections
• Improved productivity and efficiency in manufacturing processes

Abstract

In embodiments, an additive manufacturing apparatus comprises a chassis assembly and a skin at least partially covering the chassis assembly. The chassis assembly comprises a lower chassis section secured to a low voltage chassis section; an upper environmental chassis section secured to and extending over the low voltage chassis section and the lower chassis section; a high voltage chassis section secured to the upper environmental chassis section and the lower chassis section; and a build receptacle carriage adjustably coupled to the lower chassis section. The skin comprises first and second doors providing access to the low voltage chassis section and the high voltage chassis section; a rear panel providing access to the upper environmental chassis section; a top panel covering a top of the upper environmental chassis section; and at least one hinged door providing access to the lower chassis section.

PRINT AND RECOAT ASSEMBLIES FOR ADDITIVE MANUFACTURING SYSTEMS AND METHODS FOR USING THE SAME (18032259)

Main Inventor

John Sterle

Brief explanation

The abstract describes a method for forming an object using an assembly with an energy source. The method involves heating an initial layer of build material in a build area through forced convection around the energy source. Build material is then spread on the build area, depositing a second layer over the initial layer.

• The method involves using an assembly with an energy source to form an object.
• The initial layer of build material is heated through forced convection around the energy source.
• Build material is spread on the build area to deposit a second layer over the initial layer.

Potential Applications

• 3D printing: This method can be used in 3D printing to form objects layer by layer.
• Manufacturing: The method can be applied in various manufacturing processes to create objects with specific shapes and structures.

Problems Solved

• Efficient heating: The forced convection around the energy source ensures effective heating of the build material, enabling proper layer formation.
• Layer deposition: By spreading build material on the build area, the method allows for the deposition of subsequent layers, resulting in the formation of the desired object.

Benefits

• Precision: The method enables precise layer formation, leading to accurate object creation.
• Versatility: The method can be applied to various materials, allowing for a wide range of object formation possibilities.
• Time-saving: By depositing layers efficiently, the method can reduce the overall production time of objects.

Abstract

A method for forming an object includes moving an assembly including an energy source, heating an initial layer of build material () positioned in a build area via forced convection around the energy source of the assembly, and spreading build material () on the build area, thereby depositing a second layer of build material () over the initial layer of build material ( i, ).

ADDITIVE MANUFACTURING APPARATUSES INCLUDING ENVIRONMENTAL SYSTEMS AND METHODS OF USING THE SAME (18250657)

Main Inventor

Srinivas Pendurti

Brief explanation

The patent application describes an additive manufacturing apparatus that uses a print head and a recoat head to build a three-dimensional object by depositing build and binder materials. 

• The apparatus includes a process chamber that surrounds the print head and recoat head, as well as a linear motion stage that connects them.
• A condenser system is connected to the process chamber to receive a gas stream with a high vapor content and provide a gas stream with a lower vapor content back to the process chamber.
• A blower is also connected to the process chamber and the condenser to create a closed loop that circulates the gas stream through the system.

Potential applications of this technology:

• 3D printing of complex objects with multiple materials
• Rapid prototyping and manufacturing of customized products
• Creation of intricate and precise structures in various industries such as aerospace, automotive, and healthcare

Problems solved by this technology:

• Controlling the vapor content in the process chamber to optimize the printing process and improve the quality of the printed objects
• Preventing excessive vapor buildup that can lead to defects or inconsistencies in the printed objects
• Ensuring a consistent and controlled environment within the process chamber for reliable and repeatable printing results

Benefits of this technology:

• Improved printing quality and accuracy
• Faster printing speeds and increased productivity
• Enhanced control over the printing process and material properties
• Reduced waste and material consumption

Abstract

According to various embodiments, an additive manufacturing apparatus comprises a process chamber surrounding a print head, a recoat head, and a linear motion stage to which the print head and the recoat head are coupled. The print head and recoat head operate within the process chamber to build a three-dimensional object by depositing a build material and a binder material. The additive manufacturing apparatus further comprises a condenser system fluidly coupled to the process chamber to receive a gas stream with a first vapor content from the process chamber and provide the gas stream with a second vapor content to the process chamber. The second vapor content is less than the first vapor content. Additionally, the additive manufacturing apparatus comprises a blower fluidly coupled to the process chamber and the condenser to flow the gas stream through a closed loop comprising the blower, the process chamber, and the condenser.

ADDITIVE MANUFACTURING APPARATUSES AND METHODS FOR OPERATING THE SAME (18034578)

Main Inventor

Vadim Bromberg

Brief explanation

The abstract describes an additive manufacturing apparatus that includes a process chamber, a support, a printing assembly, a vision system, and an electronic control unit. The apparatus is capable of dispensing binder according to a programmed deposition pattern and analyzing the dispensed binder pattern for anomalies.

• The apparatus includes a process chamber with a support and a printing assembly.
• A vision system is used to image the dispensed binder pattern.
• An electronic control unit is responsible for controlling the printing assembly, receiving image data from the vision system, and analyzing the dispensed binder pattern.
• The electronic control unit can adjust the programmed deposition pattern based on the analysis to address any anomalies in the dispensed binder pattern.

Potential applications of this technology:

• Additive manufacturing or 3D printing processes.
• Creating complex and precise structures or objects.
• Rapid prototyping and production of customized products.

Problems solved by this technology:

• Ensures the accuracy and quality of the printed objects by detecting anomalies in the dispensed binder pattern.
• Allows for real-time adjustments to the deposition pattern to address any issues during the printing process.

Benefits of this technology:

• Improved efficiency and reliability in additive manufacturing processes.
• Reduces the need for manual intervention or post-processing to fix errors.
• Enables the production of high-quality and precise objects.

Abstract

An additive manufacturing apparatus includes a process chamber having a length, a support extending along the length of the process chamber, a printing assembly, a vision system configured to image a dispensed binder pattern, and an electronic control unit communicatively coupled to the printing assembly, the first actuator, and the vision system. The electronic control unit is configured to cause the printing assembly to traverse the build zone in a forward or reverse direction while dispensing binder according to a programmed deposition pattern, receive image data from the vision system of the dispensed binder pattern resulting from the programmed deposition pattern, analyze the image data to determine whether there is an anomaly in the dispensed binder pattern, and in response to determining the anomaly in the dispensed binder pattern, adjust the programmed deposition pattern for a subsequent traversal of the printing assembly over the build zone to address the anomaly.

AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE (17835280)

Main Inventor

Keith Edward James Blodgett

Brief explanation

The abstract describes an aircraft with a fuselage and an unducted turbine engine. The fuselage has a divot with an upstream edge and a downstream edge, defined by a straight reference line with a length (L) and a maximum depth (h) relative to the reference line. The unducted turbine engine consists of an engine core, a nacelle, and a set of blades. The first flow ratio (FR1) is calculated as h/L.

• The aircraft has a unique design with a divot in the fuselage.
• The divot is defined by a straight reference line and has a specific length and depth.
• The unducted turbine engine is a key component of the aircraft.
• The first flow ratio is calculated based on the divot dimensions.

Potential applications of this technology:

• This aircraft design could be used in commercial aviation, military aircraft, or private jets.
• It may be suitable for both short-haul and long-haul flights.
• The unique design could offer improved aerodynamics and fuel efficiency.

Problems solved by this technology:

• The divot in the fuselage may help reduce drag and improve overall aircraft performance.
• The specific dimensions of the divot could optimize airflow around the aircraft.

Benefits of this technology:

• Improved aerodynamics could result in reduced fuel consumption and lower operating costs.
• The unique design may enhance the aircraft's speed and maneuverability.
• The divot could potentially contribute to a quieter flight experience for passengers.

Abstract

An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h/L.

AIRCRAFT BIRD STRIKE REDUCTION DEVICE (17806222)

Main Inventor

Kirti Petkar

Brief explanation

The patent application describes a device and engine for preventing bird strikes to an aircraft engine. The device includes a projector mounted on an engine component, which projects an image outside of the engine.

• The device is designed to prevent bird strikes to aircraft engines.
• It includes a projector mounted on an engine component.
• The projector is positioned to project an image outside of the engine.
• The device can be installed on various engine components.
• The projected image serves as a deterrent to birds, preventing them from flying into the engine.

Potential Applications

• Aviation industry: The device can be used in aircraft engines to prevent bird strikes, reducing the risk of engine damage and potential accidents.

Problems Solved

• Bird strikes: The device helps to prevent birds from flying into aircraft engines, reducing the risk of engine damage and potential accidents.

Benefits

• Increased safety: By deterring birds from entering the engine, the device reduces the risk of engine damage and potential accidents caused by bird strikes.
• Cost-effective: The device can be easily installed on existing engine components, providing a cost-effective solution for preventing bird strikes.
• Versatile: The device can be mounted on various engine components, making it adaptable to different aircraft engines.

Abstract

In one aspect, a device for preventing bird strikes to an engine. The device includes a projector mounted on a component of the engine. The projector is positioned to project an image outside of the engine. In another aspect, an engine for an aircraft. The engine includes an engine component and a projector mounted on the engine component. The projector is positioned to project an image outside of the engine.

COMPOSITE COMPONENTS AND METHODS OF DENSIFYING COMPOSITE COMPONENTS (17835083)

Main Inventor

Joseph John Shiang

Brief explanation

The abstract describes a patent application for composite components and methods of densifying them. The composite component includes two plies of fiber tows arranged in different directions. The plies have fluid pathways that improve the penetration of a densification fluid, enhancing the densification of the composite component.

• A composite component with improved densification capabilities is provided.
• The component includes two plies of fiber tows arranged in different directions.
• The plies have fluid pathways that allow for better penetration of a densification fluid.
• The fluid pathways have longer lengths compared to their widths, enhancing the densification process.

Potential Applications

• Aerospace industry: Composite components with improved densification can be used in aircraft structures, reducing weight and improving fuel efficiency.
• Automotive industry: Densified composite components can be utilized in vehicles, enhancing their strength and safety while reducing weight.
• Construction industry: Densification of composite materials can lead to stronger and more durable building materials.

Problems Solved

• Insufficient densification: Traditional methods may not effectively penetrate densification fluids into composite components, resulting in lower strength and performance.
• Inconsistent densification: Uneven distribution of densification fluids can lead to variations in the strength and quality of composite components.

Benefits

• Improved strength: The densification process enhances the strength and durability of composite components.
• Weight reduction: Densified composite components can be lighter than traditional materials, leading to improved fuel efficiency and performance.
• Enhanced performance: The improved densification process ensures consistent and uniform distribution of densification fluids, resulting in higher quality composite components.

Abstract

Composite components and methods of densifying composite components are provided. For example, a composite component includes a first ply having a first plurality of unidirectional arrays of fiber tows extending in a first direction and a second ply having a second plurality of unidirectional arrays of fiber tows extending in a second direction. A first fluid pathway is defined in the first ply that has a first length greater than a first width, and a second fluid pathway is defined in the second ply that has a second length greater than a second width. The first and second fluid pathways may improve densification of the composite component by improving penetration of a densification fluid in the composite component.

BALANCING WEIGHT ENTRY PORT FOR TURBINE ROTOR (18457491)

Main Inventor

Michael Ericson Friedman

Brief explanation

The abstract describes a turbine rotor that includes a rotor body with a balancing weight slot and a balancing weight entry port. The slot has a certain width and a surface at a specific distance from the rotor axis. The entry port is aligned with the slot and has a larger width and a surface at a smaller distance from the axis. The method involves machining the entry port into the rotor with a tool, either for a new rotor or to remove cracks from a previous entry port.

• The turbine rotor includes a balancing weight slot and a balancing weight entry port.
• The slot has a certain width and a surface at a specific distance from the rotor axis.
• The entry port is aligned with the slot and has a larger width and a surface at a smaller distance from the axis.
• The method involves machining the entry port into the rotor with a tool.
• The method can be used for new rotors or to remove cracks from previous entry ports.

Potential Applications

• Turbine systems
• Power generation
• Industrial machinery

Problems Solved

• Balancing weight placement in turbine rotors
• Cracks in entry ports

Benefits

• Improved balance in turbine rotors
• Enhanced durability and performance
• Efficient removal of cracks in entry ports

Abstract

A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body and aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body that is smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

GAS TURBINE ENGINE WITH AN AIRFOIL (17835091)

Main Inventor

Rathakrishnan Bhaskaran

Brief explanation

Abstract:

A turbine engine consists of three sections: a compressor section, a combustion section, and a turbine section. The combustion section burns fuel, which in turn powers the turbine section to drive the compressor section. The airfoils in the turbine section have a specific design near the trailing edge to minimize the shock generated in their wake.

• The turbine engine has a compressor section, combustion section, and turbine section.
• Fuel is burned in the combustion section.
• The combustion process powers the turbine section.
• The turbine section drives the compressor section.
• The airfoils in the turbine section have a unique design near the trailing edge.
• The design includes a linear portion between the pressure side and a curved portion.
• The purpose of the design is to reduce the shock generated in the wake of the airfoils.

Potential Applications:

• Aircraft engines
• Power generation turbines
• Industrial gas turbines

Problems Solved:

• Minimizing shock generated in the wake of airfoils
• Improving the efficiency and performance of turbine engines

Benefits:

• Increased efficiency of turbine engines
• Reduced fuel consumption
• Improved overall performance of the engine

Abstract

A turbine engine includes a compressor section, a combustion section, and a turbine section. Fuel combusted in the combustion section drive stages of airfoils in the turbine section to drive the compressor section. The airfoils can include a geometry near or at the trailing edge with a linear portion provided between the pressure side and a first curved portion, to reduce shock generated in the wake of the airfoils.

TURBINE ENGINE WITH A BLADE (17836023)

Main Inventor

Jonathan Michael Rausch

Brief explanation

The abstract describes a blade for a turbine engine that has a wall separating a cooling fluid flow and a hot gas fluid flow. The blade has a heated surface along which the hot gas fluid flows and a cooled surface facing the cooling fluid flow. There are multiple cooling holes in the blade, each with a passage that extends between an inlet at the cooled surface and an outlet at the heated surface. The outlet of each cooling hole defines a distance between an upstream end and a downstream end with respect to the hot gas fluid flow, and the passage of each cooling hole forms a first angle (θ) with the heated surface.

• The blade has a wall that separates the cooling fluid flow and the hot gas fluid flow.
• The blade has a heated surface where the hot gas fluid flows and a cooled surface facing the cooling fluid flow.
• There are multiple cooling holes in the blade, each with a passage that connects the cooled surface to the heated surface.
• The outlet of each cooling hole defines a distance between an upstream and downstream end with respect to the hot gas fluid flow.
• The passage of each cooling hole forms a first angle (θ) with the heated surface.

Potential Applications

• Turbine engines in aircraft
• Power generation turbines
• Industrial gas turbines

Problems Solved

• Preventing overheating of turbine blades
• Maintaining optimal operating temperatures
• Enhancing the efficiency and performance of turbine engines

Benefits

• Improved cooling of turbine blades
• Increased durability and lifespan of turbine blades
• Enhanced efficiency and performance of turbine engines

Abstract

A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (θ) with the heated surface.

TURBINE ENGINE WITH A BLADE (17836049)

Main Inventor

Jonathan Michael Rausch

Brief explanation

The abstract describes a turbine engine with a temperature sensor and a set of blades that have a cooling system. 

• The turbine engine has a compressor section, a combustor, and a turbine section in sequential order.
• A temperature sensor is installed within the engine to measure the gas temperature.
• The turbine section contains a set of blades, each with an outer wall, an interior, and a cooling conduit.
• The cooling conduit is connected to a plurality of film holes in the blade, allowing for cooling of the blade.

Potential Applications

• This technology can be used in various types of turbine engines, such as aircraft engines, power generation turbines, and industrial turbines.
• It can improve the efficiency and performance of turbine engines by preventing overheating and reducing wear and tear on the blades.

Problems Solved

• The temperature sensor helps monitor the gas temperature within the engine core, allowing for better control and optimization of the engine's performance.
• The cooling system in the blades helps dissipate heat and prevent damage caused by high temperatures, increasing the lifespan of the blades.

Benefits

• Improved engine efficiency and performance.
• Enhanced safety and reliability by preventing overheating and blade damage.
• Extended lifespan of turbine blades, reducing maintenance and replacement costs.

Abstract

A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.

TURBINE ENGINE WITH A BLADE (18354774)

Main Inventor

Jonathan Michael Rausch

Brief explanation

The abstract describes a turbine engine with internal cooling conduits in the compressor and turbine sections. These conduits have bends or terminal ends and are connected to cooling holes on the exterior of the blades.

• The turbine engine has an engine core with a compressor section, a combustor, and a turbine section.
• Blades in the compressor or turbine sections have internal cooling conduits.
• The cooling conduits have bends or terminal ends.
• Cooling holes are provided in the blades, with each hole connected to the cooling conduit.
• The cooling holes allow cooling fluid to flow from the internal conduit to the exterior of the blade.

Potential Applications

• This technology can be applied in various types of turbine engines, including aircraft engines, power generation turbines, and industrial gas turbines.

Problems Solved

• Turbine engines generate high temperatures, which can cause damage to the blades.
• Cooling the blades is crucial to prevent overheating and maintain their structural integrity.
• The internal cooling conduits and cooling holes provide an efficient cooling mechanism for the blades.

Benefits

• Improved cooling system for turbine blades, enhancing their durability and performance.
• Prevents overheating and potential damage to the blades, increasing their lifespan.
• Enables the turbine engine to operate at higher temperatures, improving overall efficiency and power output.

Abstract

A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. One or more blades in the compressor or turbine sections has an internal cooling conduit with at least one of a bend or a terminal end. A plurality of cooling holes are provided in the blade, with each hole having an inlet fluidly coupled to the cooling conduit and an outlet opening onto an exterior of the blade.

SEAL ASSEMBLIES FOR TURBINE ENGINES (18081245)

Main Inventor

Narendra Anand Hardikar

Brief explanation

The abstract describes a rotary machine that includes a stator and a rotor. The rotor is designed to rotate with respect to the stator and has a rotor face at the rotor-stator interface. A seal assembly is present at the rotor-stator interface to prevent undesirable contact between the rotor and the stator. The seal assembly includes at least one seal and a groove formed into the rotor. Additionally, a removable insert is positioned within the groove and defines a portion of the rotor face. If the rotor and stator make undesirable contact, the removable insert gets damaged to protect the rotor and stator from damage.

• A rotary machine with a stator and a rotor that rotates with respect to the stator.
• The rotor has a rotor face at the rotor-stator interface.
• A seal assembly is present at the rotor-stator interface to prevent undesirable contact.
• The seal assembly includes at least one seal and a groove formed into the rotor.
• A removable insert is positioned within the groove and defines a portion of the rotor face.
• The removable insert gets damaged if the rotor and stator make undesirable contact.
• The damaged insert prevents damage to the rotor and stator.

Potential Applications

• Industrial machinery
• Automotive engines
• Power generation equipment
• Aerospace systems

Problems Solved

• Prevents damage to the rotor and stator caused by undesirable contact
• Improves the lifespan and reliability of rotary machines

Benefits

• Enhanced protection for the rotor and stator
• Reduces the need for costly repairs or replacements
• Increases the overall efficiency and performance of rotary machines

Abstract

A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. Further, the rotary machine includes a seal assembly at the rotor-stator interface. The seal assembly includes at least one seal and a groove formed into the rotor at the rotor-stator interface. In addition, the seal assembly includes a removable insert positioned within the groove of the seal assembly and defining at least a portion of the rotor face. As such, during operation of the rotary machine, if the rotor and the stator make undesirable contact at the rotor-stator interface, the removable insert becomes damaged to prevent damage from occurring to the rotor and the stator.

TURBINE COMPONENT WITH HEATED STRUCTURE TO REDUCE THERMAL STRESS (17806317)

Main Inventor

Brandon Lee Cox

Brief explanation

The patent application describes a turbine component that includes two structures: one exposed to hot gas and the other isolated from the hot gas path. The first structure has a fluid passage to deliver a thermal transfer fluid (e.g., air) to cool it. The second structure has a fluid passage in communication with the first structure. 

• The first structure is exposed to hot gas, while the second structure is isolated from it.
• A fluid passage in the first structure delivers a thermal transfer fluid (e.g., air) to cool the first structure.
• The second structure has a fluid passage that is connected to the first structure.
• After heat transfer in the first structure, the thermal transfer fluid becomes hotter than the second structure, increasing its temperature.
• This heat transfer reduces the temperature difference between the two structures, preventing thermal stress.
• The heating of the second structure extends the lifespan of the component and reduces the need for early maintenance.

Potential Applications

This technology can be applied in various turbine components, such as:

• Gas turbines
• Steam turbines
• Wind turbines

Problems Solved

The technology addresses the following problems:

• Thermal stress between turbine structures due to temperature differences
• Early maintenance requirements
• Limited lifespan of turbine components

Benefits

The use of this technology provides the following benefits:

• Reduced thermal stress between turbine structures
• Extended lifespan of turbine components
• Decreased need for early maintenance

Abstract

A turbine component includes a first structure exposed to a hot gas path and a second structure integral with the first structure but isolated from the hot gas path. A first fluid passage in the first structure delivers a thermal transfer fluid, e.g., air, through the first structure to cool the first structure. A second fluid passage is defined within the second structure and is in fluid communication with the first fluid passage. After heat transfer in the first structure, the thermal transfer fluid is hotter than a temperature of the second structure and thus increases the temperature of the second structure. The heat transfer to the second structure reduces a temperature difference between the first structure and the second structure that would, without heating, cause thermal stress between the structures. The heating of the second structure reduces the need for early maintenance and lengthens the lifespan of the component.

SYSTEM AND METHOD FOR PROVIDING COOLING IN A COMPRESSOR SECTION OF A GAS TURBINE ENGINE (18081217)

Main Inventor

Pankaj Dhaka

Brief explanation

The patent application describes a method for cooling the compressor section of a gas turbine engine. 

• The method involves using temperature sensors to measure the temperature at two different locations on a stationary assembly of the compressor section.
• The temperature difference between the two locations is then calculated by a controller.
• If the temperature difference exceeds a predetermined threshold, the controller activates cooling elements located at the first location of the compressor section.

Potential applications of this technology:

• Gas turbine engines used in aircraft, power plants, and other industrial applications could benefit from this cooling method.

Problems solved by this technology:

• Gas turbine engines generate a significant amount of heat, and excessive temperatures in the compressor section can lead to reduced efficiency and potential damage. This cooling method helps to prevent overheating and maintain optimal operating conditions.

Benefits of this technology:

• Improved efficiency: By preventing overheating, the cooling method helps to maintain the optimal performance of the gas turbine engine.
• Increased lifespan: By controlling the temperature in the compressor section, the cooling method can help extend the lifespan of the engine components.
• Enhanced safety: By preventing excessive temperatures, the cooling method reduces the risk of engine failure and potential safety hazards.

Abstract

A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.

MULTI-TEMPERATURE FUEL INJECTORS FOR A GAS TURBINE ENGINE (17805986)

Main Inventor

Hejie Li

Brief explanation

The patent application describes a gas turbine engine that includes a combustor, fuel nozzles, and fuel manifolds. The engine has two fuel circuits, each connected to different fuel manifolds and fuel nozzles. 

• The gas turbine engine has a combustor with a combustion chamber.
• Fuel is injected into the combustion chamber by a plurality of fuel nozzles.
• The engine has a first fuel circuit and a second fuel circuit.
• The first fuel circuit distributes fuel to at least one fuel nozzle through a first fuel manifold at a first temperature.
• The second fuel circuit distributes fuel to at least one fuel nozzle through a second fuel manifold at a second temperature.
• The second temperature is lower than the first temperature.

Potential applications of this technology:

• Gas turbine engines used in power generation.
• Gas turbine engines used in aircraft propulsion.
• Gas turbine engines used in marine propulsion.

Problems solved by this technology:

• Allows for more precise control of fuel temperature in different parts of the engine.
• Helps optimize engine performance and efficiency.
• Reduces the risk of fuel overheating and potential damage to the engine.

Benefits of this technology:

• Improved fuel distribution and combustion efficiency.
• Enhanced engine performance and power output.
• Increased fuel efficiency and reduced emissions.
• Better control over fuel temperature, reducing the risk of engine damage.

Abstract

A gas turbine engine including a combustor, a plurality of fuel nozzles, and at least one fuel manifold. The combustor includes a combustion chamber. The plurality of fuel injects fuel into the combustion chamber of the combustor. The gas turbine engine may include a first fuel circuit and a second fuel circuit. The first fuel circuit includes a first fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a first temperature. The second fuel circuit includes a second fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a second. The second temperature is less than the first temperature.

DIFFERENTIAL GEARBOX ASSEMBLY FOR A TURBINE ENGINE (17806574)

Main Inventor

Ravindra Shankar Ganiger

Brief explanation

The abstract describes a differential gearbox assembly for a turbine engine that connects the fan shaft and the drive shaft. It includes an epicyclic gear assembly with a sun gear, planet gear, and ring gear. The sun gear is connected to the drive shaft, while the planet carrier is connected to the fan shaft. The assembly also includes an electric machine assembly that provides mechanical power to the fan shaft through the epicyclic gear assembly.

• The differential gearbox assembly connects the fan shaft and the drive shaft of a turbine engine.
• It includes an epicyclic gear assembly with a sun gear, planet gear, and ring gear.
• The sun gear is connected to the drive shaft, while the planet carrier is connected to the fan shaft.
• The assembly also includes an electric machine assembly that provides mechanical power to the fan shaft through the epicyclic gear assembly.

Potential Applications

• This technology can be used in turbine engines for various applications such as aircraft propulsion systems, power generation, and industrial machinery.

Problems Solved

• The differential gearbox assembly solves the problem of efficiently transferring power from the drive shaft to the fan shaft in a turbine engine.
• It provides a compact and reliable solution for connecting the two shafts and allows for power transmission through the epicyclic gear assembly.

Benefits

• The use of the epicyclic gear assembly allows for efficient power transmission between the fan shaft and the drive shaft.
• The electric machine assembly provides additional mechanical power to the fan shaft, enhancing the overall performance of the turbine engine.
• The compact design of the differential gearbox assembly saves space and allows for easy integration into turbine engine systems.

Abstract

A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

MONITORING SYSTEMS FOR HYDROGEN FUELED AIRCRAFT (17836681)

Main Inventor

Constantinos Minas

Brief explanation

Methods and apparatus are disclosed for monitoring systems for hydrogen fueled aircraft. The patent application describes a fuel distribution system that includes a first hydrogen fuel tank, a first sensor associated with the tank, a second sensor associated with the combustor, and a controller. The controller is responsible for determining the rate of change in the amount of hydrogen in the tank, the flow rate of hydrogen into the combustor, and the average mass loss rate. If the average mass loss rate exceeds a threshold, the controller determines that a leak is present in the fuel distribution system.

• The patent application describes a method and apparatus for monitoring hydrogen fueled aircraft systems.
• The fuel distribution system includes a hydrogen fuel tank, sensors, and a controller.
• The first sensor measures the rate of change in the amount of hydrogen in the tank.
• The second sensor measures the flow rate of hydrogen into the combustor.
• The controller calculates the average mass loss rate based on the first rate of change and the flow rate.
• If the average mass loss rate exceeds a threshold, the controller determines that a leak is present in the fuel distribution system.

Potential Applications

• This technology can be applied to monitor and detect leaks in the fuel distribution systems of hydrogen fueled aircraft.
• It can be used in the aviation industry to enhance safety and prevent accidents caused by fuel leaks.

Problems Solved

• The technology solves the problem of detecting leaks in the fuel distribution systems of hydrogen fueled aircraft.
• It provides a method for monitoring the fuel system and alerting operators to the presence of a leak, allowing for timely repairs and maintenance.

Benefits

• The technology improves the safety of hydrogen fueled aircraft by detecting fuel leaks.
• It allows for proactive maintenance and repair, reducing the risk of accidents caused by fuel system failures.
• By monitoring the fuel system, it helps optimize fuel efficiency and prevent wastage.

Abstract

Methods and apparatus are for monitoring systems for hydrogen fueled aircraft. An example fuel distribution system distribution system includes a first hydrogen fuel tank, a first sensor associated with the first hydrogen fuel tank, a second sensor associated with the combustor, and a controller to determine a first rate of change in a first amount of hydrogen in the first hydrogen fuel tank based on a first input from the first sensor, determine a flow rate of hydrogen into the combustor based on a second input from the second sensor, determine an average mass loss rate based on the first rate of change and the flow rate and in response to determining the average mass loss rate satisfies a first threshold, determine a leak is present in the fuel distribution system.

COMBUSTOR MIXING ASSEMBLY (18450633)

Main Inventor

Hari Ravi Chandra

Brief explanation

The patent application describes a mixing assembly that includes a pilot mixer and a main mixer. The main mixer consists of a main housing, a fuel manifold, a mixer foot, and a main swirler body with vanes. The main swirler body surrounds the main housing and creates an annular mixing channel. An annular main fuel ring extends into the mixing channel from the mixer foot. Fuel injection ports are positioned in either the mixer foot or the main fuel ring to discharge fuel into the central portion of the mixing channel.

• The mixing assembly includes a pilot mixer and a main mixer.
• The main mixer consists of a main housing, a fuel manifold, a mixer foot, and a main swirler body with vanes.
• The main swirler body surrounds the main housing and creates an annular mixing channel.
• An annular main fuel ring extends into the mixing channel from the mixer foot.
• Fuel injection ports are positioned in either the mixer foot or the main fuel ring to discharge fuel into the central portion of the mixing channel.

Potential Applications

• This mixing assembly can be used in various combustion systems, such as gas turbines, jet engines, and industrial burners.
• It can improve the efficiency and performance of these systems by ensuring proper fuel-air mixing.

Problems Solved

• The mixing assembly solves the problem of inefficient fuel-air mixing, which can lead to incomplete combustion and reduced performance.
• It addresses the challenge of achieving uniform fuel distribution in the mixing channel.

Benefits

• The mixing assembly improves fuel-air mixing, resulting in more efficient combustion and reduced emissions.
• It enhances the performance and reliability of combustion systems by ensuring proper fuel distribution.
• The design of the mixing assembly allows for easy installation and maintenance.

Abstract

A mixing assembly includes a pilot mixer and a main mixer. The main mixer includes a main housing, a fuel manifold positioned between a pilot housing and the main housing, a mixer foot extending outward from a forward end of the main housing, and a main swirler body including a plurality of vanes. The main swirler body surrounds the main housing and defines an annular mixing channel between the main housing and the main swirler body, and being coupled to the mixer foot. An annular main fuel ring extends axially aft from the mixer foot into the annular mixing channel. The mixer foot extends farther from the main housing than the main fuel ring. At least one of the mixer foot or the main fuel ring includes a plurality of fuel injection ports positioned to discharge fuel into a central portion of the annular mixing channel.

COMBUSTOR WITH A VARIABLE VOLUME PRIMARY ZONE COMBUSTION CHAMBER (17805983)

Main Inventor

Ravindra Shankar Ganiger

Brief explanation

The patent application describes a combustor for a gas turbine that includes an outer liner and an inner liner, with a combustion chamber between them. The combustion chamber has a primary combustion zone at the upstream end. The combustor also includes an outer liner expanded primary volume portion and a secondary outer liner portion. One of these portions can be moved to adjust the volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion, thereby increasing or decreasing the volume of the primary combustion zone.

• The patent application describes a combustor for a gas turbine with adjustable primary combustion zone volume.
• The combustor includes an outer liner and an inner liner, with a combustion chamber between them.
• The primary combustion zone is located at the upstream end of the combustion chamber.
• The combustor also includes an outer liner expanded primary volume portion and a secondary outer liner portion.
• The volume of the primary combustion zone can be adjusted by opening and closing access to the outer liner expanded primary volume portion.
• This adjustment allows for increasing or decreasing the volume of the primary combustion zone.

Potential Applications

• Gas turbine power generation systems
• Aircraft engines
• Industrial heating systems

Problems Solved

• Inefficient combustion due to fixed primary combustion zone volume
• Limited control over combustion process
• Difficulty in optimizing combustion efficiency

Benefits

• Improved combustion efficiency
• Enhanced control over combustion process
• Increased flexibility in optimizing combustion performance

Abstract

A combustor for a gas turbine has a combustor liner including an outer liner and an inner liner, a combustion chamber being defined between the outer liner and the inner liner. The combustion chamber includes a primary combustion zone at an upstream end of the combustion chamber. The combustor also includes an outer liner expanded primary volume portion, and a secondary outer liner portion. One of the outer liner expanded primary volume portion and the secondary outer liner portion is movable to adjust a volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion so as to increase and to decrease the volume of the primary combustion zone.

METHODS AND APPARATUS FOR SENSOR-ASSISTED PART DEVELOPMENT IN ADDITIVE MANUFACTURING (17840386)

Main Inventor

Subhrajit Roychowdhury

Brief explanation

The patent application describes methods and apparatus for sensor-based part development in three-dimensional printing.

• The apparatus includes memory, instructions, and processor circuitry.
• The instructions are executed to identify a reference process observable of a computer-generated part.
• Input from at least one sensor is received during three-dimensional printing to identify an estimated process observable using feature extraction.
• At least one three-dimensional printing process parameter is adjusted to reduce an error identified from a mismatch between the estimated process observable and the reference process observable.

Potential Applications

• Three-dimensional printing process optimization
• Quality control in three-dimensional printing
• Real-time monitoring and adjustment of printing parameters

Problems Solved

• Inaccuracies in three-dimensional printing processes
• Lack of real-time feedback during printing
• Difficulty in optimizing printing parameters for desired outcomes

Benefits

• Improved accuracy and precision in three-dimensional printing
• Enhanced quality control and error reduction
• Increased efficiency and optimization of printing processes

Abstract

Methods and apparatus for sensor-based part development are disclosed. An example apparatus includes at least one memory, instructions in the apparatus, and processor circuitry to execute the instructions to identify a reference process observable of a computer-generated part, receive input from at least one sensor during three-dimensional printing to identify an estimated process observable using feature extraction, and adjust at least one three-dimensional printing process parameter to reduce an error identified from a mismatch between the estimated process observable and the reference process observable.

FREQUENCY-BASED COMMUNICATION SYSTEM AND METHOD (18457041)

Main Inventor

Stephen F. Bush

Brief explanation

The patent application describes a communication system that includes multiple nodes and a scheduler device. The nodes receive a signal represented by multiple frequency components in the frequency domain. The scheduler device generates a schedule for transmitting signals within the network, with different slots assigned to discrete frequency sub-bands. The nodes transmit the signal through the network to a listening device within a designated time window according to the schedule.

• The communication system includes multiple nodes and a scheduler device.
• Nodes receive a signal represented by multiple frequency components in the frequency domain.
• The scheduler device generates a schedule for transmitting signals within the network.
• The schedule assigns different slots to discrete frequency sub-bands.
• Nodes transmit the signal through the network to a listening device within a designated time window according to the schedule.
• Frequency components of the signal are transmitted through different slots based on the assigned frequency sub-bands.

Potential Applications

• Time-sensitive networks requiring efficient transmission of signals.
• Wireless communication systems with multiple nodes.
• Industrial automation systems with strict timing requirements.

Problems Solved

• Efficient transmission of time-sensitive signals in a network.
• Coordinating multiple nodes to transmit signals within designated time windows.
• Optimizing frequency allocation for different sub-bands.

Benefits

• Improved reliability and efficiency of time-sensitive communication.
• Enhanced coordination and synchronization of multiple nodes.
• Increased capacity and throughput of the communication system.

Abstract

A communication system includes multiple nodes of a time-sensitive network and a scheduler device. At least one of the nodes is configured to obtain a first signal that is represented in a frequency domain by multiple frequency components. The scheduler device generates a schedule for transmission of signals including the first signal within the time-sensitive network. The schedule defines multiple slots assigned to different discrete frequency sub-bands within a frequency band. The slots have designated transmission intervals. The nodes are configured to transmit the first signal through the time-sensitive network to a listening device such that the first signal is received at the listening device within a designated time window according to the schedule. At least some of the frequency components of the first signal are transmitted through the time-sensitive network within different slots of the schedule based on the frequency sub-bands assigned to the slots.