-
公开(公告)号：US11308249B2
公开(公告)日：2022-04-19
申请号：US16457147
申请日：2019-06-28
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Ananda Barua , Evan Dozier , Joseph Block , Brendon Leary , Prabhjot Singh , Arvind Rangarajan , Changjie Sun , Dean Robinson
IPC: G06F30/20 , B29C64/393 , B29C64/40 , B33Y40/00 , B33Y50/02 , G06F119/08 , G06F119/18
Abstract: A method, medium, and system to receive a specification defining a model of a part to be produced by an additive manufacturing (AM) process; execute an AM simulation on the model of the part to determine a prediction of thermal distortions to the part; execute a topology optimization (TO) to create TO supports that counteract the predicted thermal distortions; generate at least one rule-based support based on a geometry of the part to interface with the part at one or more regions other than the TO supports; combining the TO supports and the at least one rule-based support to generate a set of hybrid supports; save a record of the set of hybrid supports; and transmit the record of the set of hybrid supports to an AM controller to control an AM system to generate a support structure for an AM production of the part.
-
公开(公告)号：US11182520B2
公开(公告)日：2021-11-23
申请号：US16456333
申请日：2019-06-28
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Ananda Barua , Prabhjot Singh , Arvind Rangarajan , Changjie Sun , Dean Robinson
IPC: G06F30/20 , B29C64/393 , B29C64/40 , B33Y40/00 , B33Y50/02 , G06F119/08 , G06F119/18
Abstract: A method, medium, and system to execute an additive manufacturing (AM) simulation on a model of a part; determine, based on the AM simulation, a prediction of a temperature and displacement distribution in the part at a particular time in the AM process; apply the predicted temperature and displacement distributions in the part as a boundary conditions on a support design space to determine a temperature distribution throughout the support design space; and execute a thermal-structural topology optimization based on the determined temperature and displacement distributions throughout the support design space to determine a distribution of material in the design space for a thermal support structure to interface with the part that optimally reduces a thermal gradient in the part with a minimum of material and results in the generation of an optimized AM support structure.
-
33.发明授权公开(公告)号：US11174752B2
公开(公告)日：2021-11-16
申请号：US16723011
申请日：2019-12-20
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Daniel Gene Dunn , Changjie Sun , Christopher Jon Potokar , Douglas Glenn Decesare
Abstract: A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features formed in multiple fiber plies of the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet and an outlet to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The one or more elongate functional features are configured in multiple plies of the plurality of longitudinally extending ceramic matrix composite plies to form a plurality of cooling channels in multiple plies of the ceramic matrix composite component.
-
公开(公告)号：US10927693B2
公开(公告)日：2021-02-23
申请号：US16263596
申请日：2019-01-31
Applicant: General Electric Company
Inventor： Sathyanarayanan Raghavan , Gautam Suresh Naik , Prabhjot Singh , Zachary John Snider , Changjie Sun
Abstract: A turbine shroud for turbine systems may include a unitary body including a support portion coupled directly to a turbine casing of the turbine system, and forward hook(s) and aft hook(s) formed integral with the support portion. The unitary body may also include an intermediate portion formed integral with and extending from the support portion. The intermediate portion may include a non-linear segment extending from the support portion, and a forward segment formed integral with the non-linear segment. The forward segment of the intermediate portion may be positioned axially upstream of the forward hook(s). Additionally the unitary body may include a seal portion formed integral with the intermediate portion, opposite the support portion. The seal portion may include a forward end formed integral with the intermediate portion. The forward end may be positioned axially upstream of the forward hook(s).
-
公开(公告)号：US10415579B2
公开(公告)日：2019-09-17
申请号：US15278860
申请日：2016-09-28
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Larry Steven Rosenzweig , Sathyanarayanan Raghavan , Changjie Sun , Ananda Barua , Jinjie Shi
Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include a ceramic material disposed along the compressor blade tip and may be used with a bare compressor casing. The ceramic coating is harder than the bare compressor casing and can reduce the rub ratio thereby increasing the lifetime of the compressor blades. Methods are also provided for applying the coating system onto a compressor blade.
-
Patent Agency Ranking
公开(公告)号：US20190249570A1
公开(公告)日：2019-08-15
申请号：US15892735
申请日：2018-02-09
Applicant: General Electric Company
Inventor： Ananda Barua , Joshua Tyler Mook , Raymond Floyd Martell , Changjie Sun , Gautam Naik , Jordan Paule Tesorero , Aigbedion Akwara
Abstract: Turbine center frames are provided. For example, a turbine center frame comprises an annular outer case and an annular hub. The hub is defined radially inward of the outer case such that the outer case circumferentially surrounds the hub. The turbine center frame further comprises an annular fairing extending between the outer case and the hub, a ligament extending from the fairing to the outer case to connect the fairing to the outer case, a plurality of struts extending from the hub to the outer case, and a boss structure defined on an outer surface of the outer case. The outer case, hub, fairing, ligament, plurality of struts, and boss structure are integrally formed as a single monolithic component. For instance, the turbine center frame is additively manufactured as an integral structure, and methods for manufacturing turbine center frames also are provided.
-
公开(公告)号：US20190041280A1
公开(公告)日：2019-02-07
申请号：US15667091
申请日：2017-08-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arun Karthi Subramaniyan , Ananda Barua , Daniel J. Erno , Darren L. Hallman , Changjie Sun
Abstract: A component has a first structural configuration and a second structural configuration. The component includes a sensor assembly including a plurality of interconnected structural members defining a plurality of load paths. A first structural member and a second structural member define a first load path when the component is in the first structural configuration. The first structural member and a third structural member define a second load path when the component is in the second structural configuration. The second load path is configured to bypass the second structural member. The sensor assembly is configured to detect a characteristic of the component that changes when the component switches between the first structural configuration and the second structural configuration.
-
公开(公告)号：US20180187773A1
公开(公告)日：2018-07-05
申请号：US15399291
申请日：2017-01-05
Applicant: General Electric Company
Inventor： Darren Lee Hallman , Donald Albert Bradley , Changjie Sun , Bugra Han Ertas
CPC classification number: F16H57/08 , F02C7/36 , F02K3/06 , F05D2220/323 , F05D2240/54 , F05D2260/40311 , F16H1/28 , F16H2057/0087 , F16H2057/085 , Y02T50/671
Abstract: A planet gear includes a pin and an annular planet gear rim. The pin has a pin radius. The pin includes a pin outer surface. The annular planet gear rim has an inner radius and an outer radius. The annular planet gear rim includes an inner surface and an outer surface. The inner surface and the pin outer surface define a clearance therebetween. The clearance is greater than 0 when a radial force is applied to the planet gear.
-
公开(公告)号：US20180135638A1
公开(公告)日：2018-05-17
申请号：US15353182
申请日：2016-11-16
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Luc Stephane Leblanc , Sathyanarayanan Raghavan , Changjie Sun , Ananda Barua
CPC classification number: F04D29/023 , F04D29/526 , F05D2300/20
Abstract: Coating systems for components of a gas turbine engine, such as a compressor casing, are provided. The coating system can include a ceramic material disposed along the compressor casing on a surface to be adjacent to a rotating compressor blade. The coating system is harder than the compressor blade and can reduce the rub ratio between the casing and blade. The coating system can thereby increase the lifetime of the compressor casing and blades. Methods are also provided for applying the coating system onto a compressor casing.
-
公开(公告)号：US12123308B2
公开(公告)日：2024-10-22
申请号：US17702101
申请日：2022-03-23
Applicant: General Electric Company
Inventor： Li Zheng , Nicholas Joseph Kray , Changjie Sun
CPC classification number: F01D11/22 , F01D11/122 , F05D2240/11 , F05D2260/232 , F05D2260/606 , F05D2300/505
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine; a fan including a plurality of fan blades rotatably driven by the turbomachine; a nacelle surrounding at least in part the plurality of fan blades of the fan; and a clearance control system including a control ring positioned at least partially within the nacelle, coupled to the nacelle, or both for control of a clearance gap between the plurality of fan blades and the nacelle.
-
-
-
-
-
-
-
-
-
Search Results
53
records
(took 0.024 seconds)
