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公开(公告)号：US10815824B2
公开(公告)日：2020-10-27
申请号：US15478321
申请日：2017-04-04
Applicant: General Electric Company
Abstract: A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.
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2.发明公开公开(公告)号：US20240328343A1
公开(公告)日：2024-10-03
申请号：US18327026
申请日：2023-05-31
Applicant: General Electric Company
Inventor： Shishir Paresh Shah , Subramani Adhiachari , Stephanie Glynn Cotten , Daniel A. Niergarth , Sanjeev Sai Kumar Manepalli , Donald G. Thompson , Inenhe Mohammed Khalid
CPC classification number: F01P11/18 , G06F17/12 , F01P2031/20 , F05D2260/213 , F05D2260/80
Abstract: Methods, apparatus, systems and articles of manufacture to monitor health of a closed loop system in a turbine engine are disclosed. An example apparatus includes non-linear solver circuitry to: iteratively determine a volume of a gas in a system of a turbine engine based on a pressure measurement, a temperature measurement and a constant that corresponds to the gas, the non-linear solver circuitry to iteratively determine the volume of the gas using a thermodynamic state model; and determine a mass of the gas based on the volume of the gas and a volume of the system; optimization circuitry to iteratively determine a mass loss of the gas based on the mass of the gas using a system of equations; and component control circuitry to adjust use of the system of the gas based on the mass loss of the gas.
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公开(公告)号：US20180283203A1
公开(公告)日：2018-10-04
申请号：US15478321
申请日：2017-04-04
Applicant: General Electric Company
CPC classification number: F01D21/02 , F01D5/02 , F01D5/12 , F01D9/042 , F01D21/045 , F01D25/24 , F01D25/246 , F05D2220/323 , F05D2260/311 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.
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4.发明授权公开(公告)号：US12247516B2
公开(公告)日：2025-03-11
申请号：US17955713
申请日：2022-09-29
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ranganayakulu Alapati , Peeyush Pankaj , Sanjeev Sai Kumar Manepalli , Bhaskar Nanda Mondal , Thomas Moniz , N V Sai Krishna Emani , Shishir Paresh Shah , Anil Soni , Praveen Sharma , Randy T. Antelo , Antonio Giuseppe D'Ettole
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.
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Patent Agency Ranking
公开(公告)号：US11193720B2
公开(公告)日：2021-12-07
申请号：US16828186
申请日：2020-03-24
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Atanu Saha , Bhaskar Nanda Mondal , Sanjeev Sai Kumar Manepalli
Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path. The heat absorption device is configured to exchange heat between the phase change material and the input bleed flow to generate an output bleed flow of a different temperature than the input bleed flow and discharge the output bleed flow to a second predefined location different from the first predefined location.
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6.发明公开公开(公告)号：US20240110504A1
公开(公告)日：2024-04-04
申请号：US17955713
申请日：2022-09-29
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Ranganayakulu Alapati , Peeyush Pankaj , Sanjeev Sai Kumar Manepalli , Bhaskar Nanda Mondal , Thomas Moniz , N V Sai Krishna Emani , Shishir Paresh Shah , Anil Soni , Praveen Sharma , Randy T. Antelo , Antonio Giuseppe D'Ettole
CPC classification number: F02C3/067 , F02C3/10 , F05D2220/323 , F05D2240/24
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.
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公开(公告)号：US20200240720A1
公开(公告)日：2020-07-30
申请号：US16828186
申请日：2020-03-24
Applicant: General Electric Company
Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path. The heat absorption device is configured to exchange heat between the phase change material and the input bleed flow to generate an output bleed flow of a different temperature than the input bleed flow and discharge the output bleed flow to a second predefined location different from the first predefined location.
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公开(公告)号：US20240263671A1
公开(公告)日：2024-08-08
申请号：US18191631
申请日：2023-03-28
Applicant: General Electric Company
Inventor： Mohan Kannaiah Raju , David Raju Yamarthi , Santosh Kumar Pattnaik , Adam Joseph Wangler , Ravindra Shankar Ganiger , Sanjeev Sai Kumar Manepalli
CPC classification number: F16C17/04 , F16C17/26 , F16C2360/00
Abstract: Example thrust bearing apparatus disclosed herein include: a thrust disk extending radially from the shaft, the thrust disk having a first side and a second side opposite the first side; a bearing housing surrounding the thrust disk and the shaft, the bearing housing having a first wall facing the first side of the thrust disk and a second wall facing the second side of the thrust disk; a first thrust pad coupled to the first wall of the bearing housing, the first thrust pad including a first plurality of serrations circumferentially arranged in a first pattern along the first thrust pad; and a second thrust pad coupled to the first side of the thrust disk, the second thrust pad including a second plurality of serrations circumferentially arranged in a second pattern along the second thrust pad.
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公开(公告)号：US20190078516A1
公开(公告)日：2019-03-14
申请号：US15702730
申请日：2017-09-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Karthikeyan Sampath , Atanu Saha , Bhaskar Nanda Mondal , Sanjeev Sai Kumar Manepalli
Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor, a combustor, a turbine, a bleed fluid cavity, and the heat absorption device. The combustor is coupled to the compressor. The turbine is coupled to the compressor and the combustor. The bleed fluid cavity is formed at a first predefined location in the compressor. The heat absorption device is disposed in the bleed fluid cavity and includes a casing, a flow path, and a phase change material. The casing includes an inlet and an outlet. The flow path is within the casing, extends between the inlet and the outlet, and directs an input bleed fluid separated from a fluid stream discharged from the compressor. The phase change material is filled in the casing, separated from the flow path.
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