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公开(公告)号：US11293375B2
公开(公告)日：2022-04-05
申请号：US16788384
申请日：2020-02-12
Applicant: General Electric Company
Inventor： Arvind Namadevan , Hari Shanker Thakur , Jeffrey Douglas Rambo , Arnab Sen , Siddhartha Pal
Abstract: An ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, a secondary nozzle in fluid communication with a secondary fluid inlet, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area. A gas turbine engine includes a source of high pressure air, a region of low pressure air, and an ejector assembly, the ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, the primary fluid inlet in fluid communication with the source of high pressure air, a secondary nozzle in fluid communication with a secondary fluid inlet, the secondary fluid inlet in fluid communication with the region of low pressure air, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area.
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公开(公告)号：US20210285332A1
公开(公告)日：2021-09-16
申请号：US16817742
申请日：2020-03-13
Applicant: General Electric Company
Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.
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公开(公告)号：US10781709B2
公开(公告)日：2020-09-22
申请号：US15865359
申请日：2018-01-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Nathan Evan McCurdy Gibson , Robert Proctor , Bhaskar Nanda Mondal , Steven Douglas Johnson
Abstract: A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component.
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公开(公告)号：US20190218913A1
公开(公告)日：2019-07-18
申请号：US15870313
申请日：2018-01-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.
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公开(公告)号：US20190203644A1
公开(公告)日：2019-07-04
申请号：US15861802
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Raymond Floyd Martell , Jeffrey Douglas Rambo , Ryan James Matthys , Joel Francis Kirk
CPC classification number: F02C7/143 , F01D5/085 , F01D9/065 , F01D25/12 , F02C3/06 , F02C7/12 , F02C7/185 , F02C7/22 , F05D2220/3216 , F05D2240/12 , F05D2260/201 , F05D2260/213 , F23R3/283
Abstract: A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.
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Patent Agency Ranking
公开(公告)号：US20190128189A1
公开(公告)日：2019-05-02
申请号：US15796991
申请日：2017-10-30
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo
CPC classification number: F02C7/185 , F01D17/16 , F01D17/162 , F02C7/14 , F02C7/18 , F02K3/06 , F02K3/075 , F02K3/077 , F02K3/115 , F05D2220/323 , F05D2240/12 , F05D2260/213
Abstract: A gas turbine engine includes an outer nacelle; a fan at least partially surrounded by the outer nacelle; and a turbomachine drivingly coupled to the fan and at least partially surrounded by the outer nacelle. The outer nacelle defines a bypass airflow passage with the turbomachine. The turbomachine includes a compressor section defining in part a core air flowpath. The turbomachine also includes a heat sink heat exchanger; and a thermal management duct assembly defining a thermal management duct flowpath extending between an inlet and an outlet and positioned between the core air flowpath and the bypass airflow passage along the radial direction, the outlet selectively in airflow communication with a core compartment of the turbomachine, and the heat sink heat exchanger positioned in thermal communication with the thermal management duct flowpath for transferring heat to an airflow through the thermal management duct flowpath during operation.
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公开(公告)号：US20180038243A1
公开(公告)日：2018-02-08
申请号：US15229466
申请日：2016-08-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jeffrey Douglas Rambo , Andrew Martin , Curtis Walton Stover , Jared Matthew Wolfe , Mohammed El Hacin Sennoun
CPC classification number: F01D25/14 , F01D17/105 , F01D17/145 , F01D17/162 , F01D25/12 , F02C6/08 , F02C7/14 , F02C7/18 , F02K3/06 , F02K3/115 , F04D19/002 , F04D29/542 , F05D2220/32 , F05D2260/213 , F05D2260/601 , F05D2260/98 , Y02T50/676
Abstract: A heat exchanger assembly for a gas turbine engine that includes an outer engine case. The heat exchanger assembly includes at least one cooling channel, the at least one cooling channel is configured to receive a flow of fluid to be cooled. At least one first coolant flow duct that is configured to receive a flow of a first coolant, wherein the at least one cooling channel is disposed between a first inlet and a first outlet. The heat exchanger assembly further include at least one second coolant flow duct that is configured to receive a flow of a second coolant, wherein the at least one cooling channel is disposed between a second inlet and a second outlet.
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公开(公告)号：US20250075674A1
公开(公告)日：2025-03-06
申请号：US18432315
申请日：2024-02-05
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Timothy Richard DePuy , Steven B. Morris , Arthur William Sibbach
Abstract: A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.
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公开(公告)号：US12215588B2
公开(公告)日：2025-02-04
申请号：US18190403
申请日：2023-03-27
Applicant: General Electric Company
Inventor： Tajinder Singh , Rajesh Kumar , David Raju Yamarthi , Bryan Jung Woo Hong , Narendra Anand Hardikar , Ravindra Shankar Ganiger , Jeffrey Douglas Rambo
IPC: F01D11/10
Abstract: A turbine engine includes a rotor, a stator, and a seal assembly disposed between the rotor and the stator. The seal assembly includes seal segment. The seal segment includes a seal face that is configured to form a fluid bearing with the rotor. A lift channel extends within the seal segment from an opening on the seal face. The turbine engine further includes a spring assembly disposed within the lift channel. The spring assembly including a biasing element and a piston element coupled to the biasing element. The lift channel includes a lift volume portion extending is between the opening and the piston element. The piston element is movable within the lift channel based on a pressure within the fluid bearing to adjust a size of the lift volume portion.
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公开(公告)号：US12172758B2
公开(公告)日：2024-12-24
申请号：US17069034
申请日：2020-10-13
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo
Abstract: A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a water separator configured to receive the compressed air from the compressor and remove moisture from the compressed air to dry the compressed air. Furthermore, the system includes a turbine configured to receive the dried air from the heat exchanger, with the dried air expanding as the dried air flows through the turbine. Moreover, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, the moisture removed from the compressed air by the water separator is routed to the defroster to melt the captured frozen particulate matter.
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