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公开(公告)号：US10982554B2
公开(公告)日：2021-04-20
申请号：US15796494
申请日：2017-10-27
Applicant: General Electric Company
Inventor： Ganesh Seshadri , Pranav Kamat , Mahendran Manoharan , Dhananjaya Gottapu , Ravikanth Avancha
IPC: F01D5/22
Abstract: A turbine engine with a tip shroud and method for shaping the tip shroud where at least one pair of airfoils including a first and second airfoil each having an outer wall bounding an interior. Each airfoil extending between a pressure side and a suction side to define a circumferential direction and extending between a leading edge and a trailing edge to define an axial direction. Each airfoil extending between a root and a tip to define a radial direction. The first and second airfoils are circumferentially spaced to define an inlet between the leading edges and an outlet between the trailing edges where each airfoil is coupled to an inner platform at the root. A tip shroud circumscribing the airfoil operably coupled to the tip extending in the axial direction between axially spaced first and second planes where the tip shroud includes at least one scalloped portion.
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公开(公告)号：US20190122401A1
公开(公告)日：2019-04-25
申请号：US16222586
申请日：2018-12-17
Applicant: General Electric Company
Inventor： Robert F. Senzig , Ravikanth Avancha , Bijan Dorri , Sandeep Dutta , Steven J. Gray , Jiang Hsieh , John Irvin Jackson , Giridhar Jothiprasad , Paul Edgar Licato , Darin Robert Okerlund , Toshihiro Rifu , Saad Ahmed Sirohey , Basel Taha , Peter Michael Edic , Jerome Knoplioch , Rahul Bhotika
Abstract: A system and method for estimating vascular flow using CT imaging include a computer readable storage medium having stored thereon a computer program comprising instructions, which, when executed by a computer, cause the computer to acquire a first set of data comprising anatomical information of an imaging subject, the anatomical information comprises information of at least one vessel. The instructions further cause the computer to process the anatomical information to generate an image volume comprising the at least one vessel, generate hemodynamic information based on the image volume, and acquire a second set of data of the imaging subject. The computer is also caused to generate an image comprising the hemodynamic information in combination with a visualization based on the second set of data.
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公开(公告)号：US11557069B2
公开(公告)日：2023-01-17
申请号：US16222586
申请日：2018-12-17
Applicant: General Electric Company
Inventor： Robert F. Senzig , Ravikanth Avancha , Bijan Dorri , Sandeep Dutta , Steven J. Gray , Jiang Hsieh , John Irvin Jackson , Giridhar Jothiprasad , Paul Edgar Licato , Darin Robert Okerlund , Toshihiro Rifu , Saad Ahmed Sirohey , Basel Taha , Peter Michael Edic , Jerome Knoplioch , Rahul Bhotika
Abstract: A system and method for estimating vascular flow using CT imaging include a computer readable storage medium having stored thereon a computer program comprising instructions, which, when executed by a computer, cause the computer to acquire a first set of data comprising anatomical information of an imaging subject, the anatomical information comprises information of at least one vessel. The instructions further cause the computer to process the anatomical information to generate an image volume comprising the at least one vessel, generate hemodynamic information based on the image volume, and acquire a second set of data of the imaging subject. The computer is also caused to generate an image comprising the hemodynamic information in combination with a visualization based on the second set of data.
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公开(公告)号：US11274563B2
公开(公告)日：2022-03-15
申请号：US15002782
申请日：2016-01-21
Applicant: General Electric Company
Inventor： Mohsin Hasan Khan , Sarasija Sudharsan , Ganesh Seshadri , Ravikanth Avancha , Lyle Douglas Dailey
Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.
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公开(公告)号：US20180355763A1
公开(公告)日：2018-12-13
申请号：US15620264
申请日：2017-06-12
Applicant: General Electric Company
Abstract: An apparatus and method for diffusing an airflow in a turbine engine can include a turbine center frame positioned between a high pressure turbine and a low pressure turbine of a turbine section of the engine. The turbine center frame can include two or more diffusion sections for diffusing the airflow. A stabilization section can be provided between the two or more diffusion sections to stabilize the airflow.
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Patent Agency Ranking
公开(公告)号：US20250146418A1
公开(公告)日：2025-05-08
申请号：US19013045
申请日：2025-01-08
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Jeffrey Donald Clements , Paul Hadley Vitt , Francesco Bertini , Aspi Rustom Wadia , Ganesh Seshadri , Mahendran Manoharan , Ravikanth Avancha
Abstract: A turbomachinery apparatus 10 includes: a turbine 22, including: a turbine component 36 defining at least one arcuate flowpath surface 40; an array of axial-flow turbine airfoils 46 extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils 146 extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.
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公开(公告)号：US20240003543A1
公开(公告)日：2024-01-04
申请号：US17853200
申请日：2022-06-29
Applicant: General Electric Company
Inventor： Ravikanth Avancha , Ravish Karve , Jeffrey Donald Clements , Hiranya Kumar Nath , Timothy Richard DePuy
CPC classification number: F02C7/24 , F23R3/002 , F23R2900/00014
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order and together defining a working gas flowpath, the turbomachine including an acoustic liner, the acoustic liner having: a flowpath wall exposed to the working gas flowpath, the flowpath wall defining an opening; and a duct wall extending from the flowpath wall defining at least in part an acoustic passage defining a volume, the acoustic passage operable to attenuate noise through the working gas flowpath during an operating condition of the gas turbine engine.
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公开(公告)号：US20170211399A1
公开(公告)日：2017-07-27
申请号：US15002782
申请日：2016-01-21
Applicant: General Electric Company
Inventor： Mohsin Hasan Khan , Sarasija Sudharsan , Ganesh Seshadri , Ravikanth Avancha , Lyle Douglas Dailey
CPC classification number: F01D9/041 , F01D5/141 , F01D5/143 , F01D25/162 , F01D25/246 , F02C7/20 , F05D2220/32 , F05D2240/90 , F05D2250/71 , Y02T50/673
Abstract: A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.
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公开(公告)号：US12221898B2
公开(公告)日：2025-02-11
申请号：US16490416
申请日：2018-03-06
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Jeffrey Donald Clements , Paul Hadley Vitt , Francesco Bertini , Aspi Rustom Wadia , Ganesh Seshadri , Mahendran Manoharan , Ravikanth Avancha
Abstract: A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils (146) extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.
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公开(公告)号：US11828226B2
公开(公告)日：2023-11-28
申请号：US17827180
申请日：2022-05-27
Applicant: General Electric Company
Inventor： Sesha Subramanian , Ravikanth Avancha , Atanu Saha
Abstract: In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.
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