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公开(公告)号：US20250027427A1
公开(公告)日：2025-01-23
申请号：US18416269
申请日：2024-01-18
Applicant: General Electric Company
Inventor： Jeffrey D. Rambo , Brandon W. Miller , Arthur W. Sibbach , Scott D. Hunter , Ryan T. Roehm
Abstract: A turbine engine having a longitudinal centerline axis. The turbine engine including a fan comprising a plurality of fan blades that rotate about the longitudinal centerline axis and a rotational component coupled to the fan. The turbine engine including a fluid circuit for supplying fuel or lubricant to the turbine engine and a hydraulic fan brake coupled to the fluid circuit to prevent rotation of the rotational component, thus preventing rotation of the fan. The hydraulic fan brake including a hydraulic cylinder fluidly coupled to the fluid circuit and a valve coupled to the hydraulic cylinder and having a first valve position that disengages the hydraulic fan brake to allow rotation of the rotational component and a second valve position that engages the hydraulic fan brake to prevent rotation of the rotational component.
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公开(公告)号：US12253023B1
公开(公告)日：2025-03-18
申请号：US18468198
申请日：2023-09-15
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , Rajesh Kumar , Jeffrey D. Rambo
Abstract: A turbine engine for an aircraft. The turbine engine includes a combustor and a steam system. Fuel and steam are injected into the combustor to mix with compressed air to generate a fuel and air mixture. The fuel and air mixture is combusted in the combustor to generate combustion gases. The steam system is fluidly coupled to the combustor as the steam source to provide steam to the combustor. The steam system includes a hot gas path and a steam hot gas path component. The hot gas path is fluidly coupled to the combustor to receive the combustion gases and to route the combustion gases through the steam system. The steam hot gas path component includes a wall having a combustion-gas-facing surface facing the hot gas path and a hydrophobic coating formed on the combustion-gas-facing surface.
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公开(公告)号：US20240191675A1
公开(公告)日：2024-06-13
申请号：US18065143
申请日：2022-12-13
Applicant: General Electric Company
Inventor： Jeffrey D. Rambo , Scott G. Edens
Abstract: A propulsion system includes a turbine engine, and a ramjet engine arranged in parallel with the turbine engine, a fuel storage tank that stores a fuel, such as an ammonia-based fuel, a heat exchanger through which the fuel passes to obtain gaseous (or supercritical) fuel components of the fuel, and a separator that separates the gaseous fuel components into a first fuel component and a second fuel component. The first fuel component is provided to the ramjet engine for ramjet combustion and/or to the turbine engine for turbine combustion, in a high speed operating state of the propulsion system, while the second fuel component may be provided to an inlet of the turbine engine for the turbine combustion.
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公开(公告)号：US20250092822A1
公开(公告)日：2025-03-20
申请号：US18468198
申请日：2023-09-15
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , Rajesh Kumar , Jeffrey D. Rambo
Abstract: A turbine engine for an aircraft. The turbine engine includes a combustor and a steam system. Fuel and steam are injected into the combustor to mix with compressed air to generate a fuel and air mixture. The fuel and air mixture is combusted in the combustor to generate combustion gases. The steam system is fluidly coupled to the combustor as the steam source to provide steam to the combustor. The steam system includes a hot gas path and a steam hot gas path component. The hot gas path is fluidly coupled to the combustor to receive the combustion gases and to route the combustion gases through the steam system. The steam hot gas path component includes a wall having a combustion-gas-facing surface facing the hot gas path and a hydrophobic coating formed on the combustion-gas-facing surface.
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公开(公告)号：US12221905B1
公开(公告)日：2025-02-11
申请号：US18366256
申请日：2023-08-07
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , Robert R. Rachedi , Brandon W. Miller , Jeffrey D. Rambo , Daniel A. Niergarth
Abstract: A turbine engine for an aircraft. The turbine engine includes a fan, a combustor in a core air flowpath that generates combustion gases, a core shaft, a turbine that receives the combustion gases to rotate the turbine, and a steam system. The steam system extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath. The steam system includes one or more water storage devices that store the water therein. The one or more water storage devices include a first state in which the one or more water storage devices increase or maintain a level of the water as the water flows through the one or more water storage devices, and a second state in which the one or more water storage devices decrease the level of the water in the one or more water storage devices.
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Patent Agency Ranking
公开(公告)号：US20250020070A1
公开(公告)日：2025-01-16
申请号：US18517878
申请日：2023-11-22
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , Brandon W. Miller , Andrew Hudecki , Randy M. Vondrell , Jeffrey D. Rambo
Abstract: A lubrication system for a turbine engine. The turbine engine includes a fan having a fan shaft and one or more rotating components. The lubrication system includes one or more tanks that stores lubricant therein, a primary lubrication system, and an auxiliary lubrication system. The primary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump that is coupled to the fan shaft. The auxiliary lubrication system supplies the lubricant from the one or more tanks to the one or more rotating components based on a pressure of the lubricant in the primary lubrication system. Rotation of the fan shaft causes the auxiliary pump to pump the lubricant to the one or more rotating components.
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公开(公告)号：US12110827B1
公开(公告)日：2024-10-08
申请号：US18311660
申请日：2023-05-03
Applicant: General Electric Company
Inventor： Jeffrey D. Rambo , Scott G. Edens , Michael Joseph Murray
CPC classification number: F02C7/236 , F02C7/32 , F05D2220/323 , F05D2270/07
Abstract: A turbo engine for an aircraft includes a gas turbine engine having a combustion section and a fuel system to provide pressurized fuel to the combustion section. The fuel system includes a fuel tank and a boost pump and a main pump driven by an accessory gearbox that is powered by a shaft of the turbo engine. The boost pump and the main pump are arranged in series. The fuel system also includes an auxiliary pump and a controller to operate the fuel system in (1) a first mode in which the boost pump and the main pump produce pressurized fuel for the turbo engine and the auxiliary pump is deactivated, and (2) a second mode in which the auxiliary pump is activated and produces the pressurized fuel for the turbo engine while bypassing the boost pump and the main pump.
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公开(公告)号：US20250129741A1
公开(公告)日：2025-04-24
申请号：US18417814
申请日：2024-01-19
Applicant: General Electric Company
Inventor： Jeffrey D. Rambo , Bhaskar Nanda Mondal
Abstract: A turbine engine includes a cooling air duct for cooling air positioned radially between a core air flow path for core air and a bypass airflow passage for bypass air. A heat exchanger is positioned in the cooling air duct to transfer heat from a heat source from within the turbine engine. The heat exchanger may be a condenser. The turbine engine may further include a steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flow path, the steam system including the condenser to transfer heat from the combustion gases to the cooling air and to condense the water from the combustion gases. The turbine engine may further include a booster fan to increase the pressure of the cooling air and the core air.
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公开(公告)号：US20250084789A1
公开(公告)日：2025-03-13
申请号：US18463782
申请日：2023-09-08
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , Aaron M. Dziech , Scott Alan Schimmels , Robert R. Rachedi , Jeffrey D. Rambo , Brandon W. Miller
Abstract: A turbine engine for an aircraft. The turbine engine includes a combustor fluidly coupled to a fuel delivery assembly to receive fuel from the fuel delivery assembly. The fuel is injected into the combustor and combusted in the combustor to generate combustion gases. A condenser is located downstream of a turbine to receive the combustion gases and to condense water. The fuel heat exchanger is thermally coupled to the condenser to receive heat from the water condensed by the condenser. The fuel heat exchanger is located in the fuel delivery assembly to receive the fuel and to transfer the heat received from the water to the fuel. The boiler is located downstream of the fuel heat exchanger. The boiler receives the water and is fluidly connected to the combustor to receive the combustion gases and to boil the water to generate steam.
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公开(公告)号：US20240229726A1
公开(公告)日：2024-07-11
申请号：US18152903
申请日：2023-01-11
Applicant: General Electric Company
Inventor： Jeffrey D. Rambo , Brandon W. Miller , Scott G. Edens
CPC classification number: F02C9/18 , F02C3/04 , F02C7/057 , F05D2220/10 , F05D2220/3217 , F05D2220/323
Abstract: A propulsion system includes (a) a turbine engine including a compressor section, a combustor, and a turbine section, (b) a ramjet engine, and (c) an inlet section including a turbine engine inlet portion and a ramjet inlet portion, the inlet section providing an inlet airflow to the turbine engine and to the ramjet engine. The turbine engine inlet portion includes an expansion turbine arranged upstream of the compressor section.
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