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公开(公告)号：US20250073829A1
公开(公告)日：2025-03-06
申请号：US18536780
申请日：2023-12-12
Applicant: General Electric Company
Inventor： Atanu Saha , Hrishikesh Keshavan , Sanat Chandra Maiti , Scott Allen Jones
Abstract: A method of repairing a multi-layer component of an engine in-module includes identifying a damage location on the multi-layer component. The damage location extends at least partially into a ceramic-based top layer of the multi-layer component. The method further includes depositing a material composition onto the damage location at a first temperature range so as to cover the damage location. The material composition includes one or more sintering additives. Further, the method includes applying localized curing to the material composition deposited at the damage location at a second temperature range, the second temperature range being higher than the first temperature range.
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公开(公告)号：US20240157336A1
公开(公告)日：2024-05-16
申请号：US18319714
申请日：2023-05-18
Applicant: General Electric Company
Inventor： Karthick Gourishankar , Lawrence B. Kool , Byron A. Pritchard , Sanjay Kumar Sondhi , Narayanan Janakiraman , Arundhati Sengupta , Atanu Saha , Bernard P. Bewlay
CPC classification number: B01J23/10 , B01J23/42 , B01J23/50 , B01J35/023 , F02C7/30
Abstract: A mixer assembly for a gas turbine engine. The mixer assembly includes a housing and a fuel injection port. The housing has a passage formed therein, and the housing includes a passage wall facing the passage. The fuel injection port is fluidly connected to a fuel source and is configured to inject a hydrocarbon fuel into the passage. At least a portion of the passage wall is a coated passage wall. The coated passage wall is (i) coated with a layer of catalyst particles comprising a rare earth oxide component and (ii) located downstream of the fuel injection port.
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公开(公告)号：US20240026820A1
公开(公告)日：2024-01-25
申请号：US17871146
申请日：2022-07-22
Applicant: General Electric Company
Inventor： Vaishnav Raghuvaran , Atanu Saha , Rajesh Kumar , Scott Alan Schimmels
CPC classification number: F02C7/06 , F02C9/18 , F16N7/30 , F05D2260/98 , F05D2260/606 , F16N2210/02
Abstract: A gas turbine engine including a compressor section including a compressor and a turbine section located downstream of the compressor section. The turbine section including a high pressure turbine, a low pressure turbine, a sump positioned between the high pressure turbine and the low pressure turbine, and a rotating cross flow arrangement defining a plurality of guiding passages fluidly coupling the compressor to the sump.
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公开(公告)号：US11859547B2
公开(公告)日：2024-01-02
申请号：US17826321
申请日：2022-05-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joseph G. Rose , Atanu Saha , Bhaskar Nanda Mondal , Craig W. Higgins , Darek Zatorski , Vaibhav Deshmukh M
CPC classification number: F02C7/06 , F02C3/06 , F05D2240/52 , F05D2260/15 , F05D2260/213 , F05D2260/232 , F05D2260/605 , F05D2260/607
Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.
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公开(公告)号：US11719168B2
公开(公告)日：2023-08-08
申请号：US17188780
申请日：2021-03-01
Applicant: General Electric Company
Inventor： Steven Mitchell Taylor , Vishnu Das K , Manish Singhal , Atanu Saha , Michael Anthony Thomas
CPC classification number: F02C9/18 , F02C3/06 , F02C6/08 , F04D29/547 , F05D2220/32 , F05D2240/12 , F05D2240/14
Abstract: An example compressor bleed slot apparatus includes an annular compressor casing, a blade row mounted for rotation about a centerline axis inside the compressor casing, a bleed slot passing through the forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row, an array of struts interconnecting the inboard and outboard walls, and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange includes a necked-down portion adjacent the forward section of the compressor casing, the necked-down portion positioned axially between an inlet of the bleed slot and an outlet of the bleed slot.
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Patent Agency Ranking
公开(公告)号：US20230101282A1
公开(公告)日：2023-03-30
申请号：US17487507
申请日：2021-09-28
Applicant: General Electric Company
Inventor： Mamatha Nagesh , Atanu Saha , Srinivasan Swaminathan
Abstract: A corrosion resistant coating including a matrix, corrosion resistant particles dispersed throughout the matrix, and a glass-forming additive is disclosed. The glass-forming additive and one or more materials in the matrix form a glassy-phase when cured. Coated gas turbine engine components and methods for coating components are also disclosed.
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公开(公告)号：US10934943B2
公开(公告)日：2021-03-02
申请号：US15499743
申请日：2017-04-27
Applicant: General Electric Company
Inventor： Steven Mitchell Taylor , Vishnu Das K , Manish Singhal , Atanu Saha , Michael Anthony Thomas
Abstract: A compressor bleed slot apparatus includes: an annular compressor casing; a stator vane row disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing, axially downstream of the stator row; a bleed slot passing through the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot having an inlet positioned axially between the stator vane row and the blade row, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row; an annular array of struts interconnecting the inboard and outboard walls; and an annular supplemental flange extending radially outward from the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot.
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公开(公告)号：US10316681B2
公开(公告)日：2019-06-11
申请号：US15168581
申请日：2016-05-31
Applicant: General Electric Company
Inventor： Jagata Laxmi Narasimharao , Thomas Ory Moniz , Mohamed Musthafa Thoppil , Bhaskar Nanda Mondal , Atanu Saha
Abstract: A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.
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公开(公告)号：US10126025B2
公开(公告)日：2018-11-13
申请号：US14904961
申请日：2014-07-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Mamatha Nagesh , Atanu Saha , Francis Johnson
IPC: F25B21/00
Abstract: A magneto-caloric assembly can include a first region including a first magneto-caloric material, a second region disposed on the first region and including a second magneto-caloric material and a first matrix material, and a third region disposed on the second region and including a thermally conductive material.
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公开(公告)号：US20170268535A1
公开(公告)日：2017-09-21
申请号：US15447565
申请日：2017-03-02
Applicant: General Electric Company
Inventor： Bhaskar Nanda Mondal , Kenneth Edward Seitzer , Monty Lee Shelton , Thomas Ory Moniz , Atanu Saha
CPC classification number: F04D29/642 , F01D11/24 , F02K3/06 , F04D19/02 , F04D29/5846 , F04D29/5853 , F05D2220/32 , F05D2260/201 , Y02T50/671
Abstract: The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.
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