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公开(公告)号：US12258923B2
公开(公告)日：2025-03-25
申请号：US18182613
申请日：2023-03-13
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor Howard Wood , Kishore Ramakrishnan
Abstract: A propulsor is provided having a power source; a fan section coupled to the power source and configured to provide thrust opposite a downstream direction; and a cowl assembly at least partially enclosing the power source and the fan section, the cowl assembly including: a forward cowl component; a first aft cowl component disposed in the downstream direction relative to the forward cowl component and movable to vary a first aft cowl displacement from the forward cowl component in the downstream direction; and a second aft cowl component disposed in the downstream direction relative to the first aft cowl component and movable to vary a second aft cowl intermediate displacement from the first aft cowl component.
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公开(公告)号：US11840987B2
公开(公告)日：2023-12-12
申请号：US17713597
申请日：2022-04-05
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Justin John Gambone, Jr. , Darren Lee Hallman , Thomas Malkus , Jixian Yao , Keith Edward James Blodgett
CPC classification number: F02K1/72 , F02K1/766 , F05D2220/323 , F05D2240/129 , F05D2240/14 , F05D2260/606
Abstract: A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.
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公开(公告)号：US20230323815A1
公开(公告)日：2023-10-12
申请号：US17717402
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Gregory Alexander Natsui , Giridhar Jothiprasad , Lana Maria Osusky , Thomas Malkus
CPC classification number: F02C7/18 , F01D25/12 , F05D2260/213 , F05D2220/32 , F02C7/141
Abstract: A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.
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公开(公告)号：US20230313754A1
公开(公告)日：2023-10-05
申请号：US17713597
申请日：2022-04-05
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Justin John Gambone, JR. , Darren Lee Hallman , Thomas Malkus , Jixian Yao , Keith Edward James Blodgett
CPC classification number: F02K1/72 , F02K1/766 , F05D2220/323 , F05D2240/14 , F05D2260/606 , F05D2240/129
Abstract: A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.
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公开(公告)号：US20230212989A1
公开(公告)日：2023-07-06
申请号：US17569293
申请日：2022-01-05
Applicant: General Electric Company
Inventor： Thomas Malkus , Jeffrey D. Carnes , Giridhar Jothiprasad , Christopher E. LaMaster , Michael Macrorie , Trevor H. Wood , Steven M. Taylor , Mitchell J. Headley , Paul J. Trimby
Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly includes a variable bleed valve (VBV) door corresponding to a bleed port, an intermediary device operatively coupled to the VBV door, and a first actuator operatively coupled to the intermediary device, the first actuator to move between a first position and a second position, the first actuator to cause the intermediary device to move between the first position and the second position to cause the VBV door to move between the first position and the second position.
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Patent Agency Ranking
公开(公告)号：US12286941B2
公开(公告)日：2025-04-29
申请号：US18299102
申请日：2023-04-12
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Thomas Malkus , Kishore Ramakrishnan
Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.
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公开(公告)号：US20250075664A1
公开(公告)日：2025-03-06
申请号：US18952677
申请日：2024-11-19
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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公开(公告)号：US12092034B2
公开(公告)日：2024-09-17
申请号：US17958549
申请日：2022-10-03
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Ramakrishna Venkata Mallina , Giridhar Jothiprasad , Kishore Ramakrishnan , Thomas Malkus
CPC classification number: F02C7/24 , F01D11/08 , F02C3/06 , F02C7/045 , F05D2240/14 , F05D2250/184 , F05D2260/96
Abstract: A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
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公开(公告)号：US20240117768A1
公开(公告)日：2024-04-11
申请号：US17958549
申请日：2022-10-03
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Ramakrishna Venkata Mallina , Giridhar Jothiprasad , Kishore Ramakrishnan , Thomas Malkus
CPC classification number: F02C7/24 , F01D11/08 , F02C3/06 , F05D2240/14 , F05D2250/184 , F05D2260/96
Abstract: A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
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公开(公告)号：US20230340927A1
公开(公告)日：2023-10-26
申请号：US18299102
申请日：2023-04-12
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Thomas Malkus , Kishore Ramakrishnan
IPC: F02K1/66
CPC classification number: F02K1/66
Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.
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