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公开(公告)号：US20230407793A1
公开(公告)日：2023-12-21
申请号：US18068031
申请日：2022-12-19
Applicant: General Electric Company
Inventor： Mohan Kannaiah Raju , Subramani Adhiachari , Ravindra Shankar Ganiger , Arvind Namadevan , Prasant Bilaiya , Scott Alan Schimmels
CPC classification number: F02C7/24 , F02C7/222 , F02C7/06 , F05D2240/15 , F05D2260/231 , F05D2300/603
Abstract: An insulation assembly for use in a gas turbine engine is provided. The insulation assembly defines a hot side and an insulated side and includes: a heat shield layer positioned proximate the hot side; and a thermal absorption layer positioned proximate the insulated side, the thermal absorption layer comprising a phase change material, the insulation assembly defining an air gap positioned between the heat shield layer and the thermal absorption layer.
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公开(公告)号：US20210246849A1
公开(公告)日：2021-08-12
申请号：US16788384
申请日：2020-02-12
Applicant: General Electric Company
Inventor： Arvind Namadevan , Hari Shanker Thakur , Jeffrey Douglas Rambo , Arnab Sen , Siddhartha Pal
Abstract: An ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, a secondary nozzle in fluid communication with a secondary fluid inlet, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area. A gas turbine engine includes a source of high pressure air, a region of low pressure air, and an ejector assembly, the ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, the primary fluid inlet in fluid communication with the source of high pressure air, a secondary nozzle in fluid communication with a secondary fluid inlet, the secondary fluid inlet in fluid communication with the region of low pressure air, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area.
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公开(公告)号：US11293375B2
公开(公告)日：2022-04-05
申请号：US16788384
申请日：2020-02-12
Applicant: General Electric Company
Inventor： Arvind Namadevan , Hari Shanker Thakur , Jeffrey Douglas Rambo , Arnab Sen , Siddhartha Pal
Abstract: An ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, a secondary nozzle in fluid communication with a secondary fluid inlet, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area. A gas turbine engine includes a source of high pressure air, a region of low pressure air, and an ejector assembly, the ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, the primary fluid inlet in fluid communication with the source of high pressure air, a secondary nozzle in fluid communication with a secondary fluid inlet, the secondary fluid inlet in fluid communication with the region of low pressure air, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area.
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公开(公告)号：US11092024B2
公开(公告)日：2021-08-17
申请号：US16155107
申请日：2018-10-09
Applicant: General Electric Company
Inventor： Arvind Namadevan , Weize Kang , Hari Shankar Thakur , Arnab Sen , Mayur Ghawat
Abstract: The present disclosure is directed to a system for mitigating rotor bow at a turbine engine. The system includes a casing circumferentially surrounding a rotor assembly in which a heat pipe is attached to the casing and extended circumferentially around the rotor assembly.
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公开(公告)号：US20210171211A1
公开(公告)日：2021-06-10
申请号：US16705384
申请日：2019-12-06
Applicant: General Electric Company
Inventor： Bhaskar Nanda Mondal , Arvind Namadevan , Shankar Jayaraman , Keith EJ Blodgett , Arnab Sen
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.
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Patent Agency Ranking
公开(公告)号：US12221899B2
公开(公告)日：2025-02-11
申请号：US18210347
申请日：2023-06-15
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Dharmaraj Pachaiappan , Nageswar Rao Ganji , Arvind Namadevan , Jeffrey D. Carnes , Charles Eric Lavender , Steven Mark Ballman
Abstract: A lock lug for inhibiting movement of a plurality of rotor blades includes a body and an engagement mechanism. The body is sized and configured to be received within the rim slot of the rotor disk and defines a dovetail receiving aperture. The engagement mechanism extends from the body and has a retracted configuration configured to allow entry and exit of a dovetail of at least one or more of the plurality of rotor blades into and out of the dovetail receiving aperture and an extended configuration configured to block the dovetail from entering the dovetail receiving aperture.
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公开(公告)号：US20220010727A1
公开(公告)日：2022-01-13
申请号：US16923198
申请日：2020-07-08
Applicant: General Electric Company
Inventor： Arvind Namadevan , Jeffrey Douglas Rambo , Arnab Sen
IPC: F02C7/18
Abstract: An aspect of the present disclosure is directed to a system for reducing thermal gradient at a heat engine. The heat engine includes a rotor assembly with a rotor disk and a seal assembly is provided. An interfacing structure at least partially surrounds the rotor assembly at the seal assembly. The seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition. A fluid supply manifold is connected to the rotor assembly and is extended at least partially along a radial direction from the first cavity to an outlet opening in thermal communication with the rotor disk of the rotor assembly.
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公开(公告)号：US20210388739A1
公开(公告)日：2021-12-16
申请号：US16902480
申请日：2020-06-16
Applicant: General Electric Company
Inventor： Arvind Namadevan , Arnab Sen , Wendy Wenling Lin , Shivam Mittal , Peeyush Pankaj , Shashank Suresh Puranik , Narayanan Payyoor , Praveen Sharma
IPC: F01D25/24
Abstract: A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin, wherein one or more of the plurality of core layers of reinforcing fibers comprises a shear thickening fluid. The core layer may include at least one fabric sheet comprising the reinforcing fibers.
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公开(公告)号：US20240418092A1
公开(公告)日：2024-12-19
申请号：US18210347
申请日：2023-06-15
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Dharmaraj Pachaiappan , Nageswar Rao Ganji , Arvind Namadevan , Jeffrey D. Carnes , Charles Eric Lavender , Steven Mark Ballman
Abstract: A lock lug for inhibiting movement of a plurality of rotor blades includes a body and an engagement mechanism. The body is sized and configured to be received within the rim slot of the rotor disk and defines a dovetail receiving aperture. The engagement mechanism extends from the body and has a retracted configuration configured to allow entry and exit of a dovetail of at least one or more of the plurality of rotor blades into and out of the dovetail receiving aperture and an extended configuration configured to block the dovetail from entering the dovetail receiving aperture.
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公开(公告)号：US20240001323A1
公开(公告)日：2024-01-04
申请号：US18054735
申请日：2022-11-11
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Thomas D. Woodrow , Scott Alan Schimmels , Arvind Namadevan , Mohan Raju , Subramani Adhiachari , Prasant Bilaiya , Rajesh Kumar
CPC classification number: B01J19/0026 , F16N39/00 , F16N2210/02
Abstract: A self-cleaning conduit for a hydrocarbon fluid. The conduit includes a tube and a mesh. The tube has an interior surface defining a flow passage for the hydrocarbon fluid. The mesh is positioned within the flow passage to abut the interior surface and movable along the interior surface to break-up deposits on the interior surface. The mesh is characterized by a mesh activation parameter (MAP) from one ten thousandths to six tenths.
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