-
公开(公告)号：US20190383156A1
公开(公告)日：2019-12-19
申请号：US16012380
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Sezer , Deepak Trivedi
Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.
-
公开(公告)号：US10472980B2
公开(公告)日：2019-11-12
申请号：US15432094
申请日：2017-02-14
Applicant: General Electric Company
Inventor： Gary Michael Itzel , Ibrahim Sezer
Abstract: A seal in a gas turbine for sealing a radial gap defined between rotating and stationary structure. The rotating structure may include a row of rotor blades. The seal may include a pad attached to the stationary structure. The pad may include an abradable structure. The pad may further include a liner attached to and covering an outer surface of the abradable structure. The stationary structure to which the pad is attached may define an axial section of the outer radial boundary of the annular flowpath, the axial section coinciding axially with an axial position of the row of rotor blades.
-
公开(公告)号：US09963985B2
公开(公告)日：2018-05-08
申请号：US14973886
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Gunnar Leif Siden , Andre Borisenko , Ibrahim Sezer
CPC classification number: F01D9/041 , F05D2220/32 , F05D2240/122 , F05D2250/70 , F05D2250/90
Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine includes opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
-
公开(公告)号：US11525397B2
公开(公告)日：2022-12-13
申请号：US17008775
申请日：2020-09-01
Applicant: General Electric Company
Inventor： Brendon James Leary , Frederic Woodrow Roberts, Jr. , Ibrahim Sezer , Tyler Christopher Henson
IPC: F02C7/05
Abstract: A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.
-
公开(公告)号：US20200025026A1
公开(公告)日：2020-01-23
申请号：US16040062
申请日：2018-07-19
Applicant: General Electric Company
Inventor： Travis J Packer , Benjamin Paul Lacy , Ibrahim Sezer , Zachary John Snider , Brad Wilson VanTassel
Abstract: Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.
-
Patent Agency Ranking
公开(公告)号：US09995151B2
公开(公告)日：2018-06-12
申请号：US14828094
申请日：2015-08-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ibrahim Sezer , Gary Michael Itzel , Jaime Javier Maldonado , Sandip Dutta
CPC classification number: F01D5/189 , F01D5/186 , F01D9/02 , F01D25/12 , F02C7/12 , F05D2250/32 , F05D2250/324 , F05D2260/201 , F05D2260/2212 , F23R3/002 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
Abstract: An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.
-
公开(公告)号：US20220065165A1
公开(公告)日：2022-03-03
申请号：US17008775
申请日：2020-09-01
Applicant: General Electric Company
Inventor： Brendon James Leary , Frederic Woodrow Roberts, JR. , Ibrahim Sezer , Tyler Christopher Henson
IPC: F02C7/05
Abstract: A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.
-
公开(公告)号：US11231175B2
公开(公告)日：2022-01-25
申请号：US16012412
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Sezer , Neelesh Nandkumar Sarawate , Deepak Trivedi
Abstract: An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.
-
公开(公告)号：US11047248B2
公开(公告)日：2021-06-29
申请号：US16012380
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Sezer , Deepak Trivedi
Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.
-
公开(公告)号：US20180128174A1
公开(公告)日：2018-05-10
申请号：US15343369
申请日：2016-11-04
Applicant: General Electric Company
Inventor： Daniel Robert Burnos , Ibrahim Sezer
Abstract: A cooled structure of a gas turbine engine having a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and are arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and are arranged along the second side portion. Each set of cooling air micro-channels has at least one transition manifold in fluid communication with an adjacent micro-channel and also in fluid communication with at least one of an intake end, an exhaust end, and mixtures thereof. The cooled structure described above is also embodied in a gas turbine.
-
-
-
-
-
-
-
-
-
Search Results
27
records
(took 0.039 seconds)
