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公开(公告)号：US20250012236A1
公开(公告)日：2025-01-09
申请号：US18430907
申请日：2024-02-02
Applicant: General Electric Company
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：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：US12012898B2
公开(公告)日：2024-06-18
申请号：US17979992
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Egbert Geertsema , Arthur W. Sibbach , Andrew Hudecki , Timothy Richard DePuy , John C. Schilling , Frank Worthoff , Tsuguji Nakano
CPC classification number: F02C7/24 , F02C7/36 , F05D2260/96
Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.
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公开(公告)号：US20230322382A1
公开(公告)日：2023-10-12
申请号：US17658909
申请日：2022-04-12
Applicant: General Electric Company
Inventor： Mustafa Dindar , Timothy Richard DePuy
CPC classification number: B64C39/10 , B64D33/02 , B64C2039/105 , B64D2033/0206
Abstract: A blended wing body aircraft includes a body section having an aerodynamic lifting surface. The body section includes an upper body and a lower body. The blended wing body aircraft also includes a plurality of blended wing sections further defining the body section. The blended wing body aircraft includes one or more grooves in the body section. The one or more grooves extend from the upper body towards the lower body. The blended wing body aircraft further includes one or more open-fan engines mounted at least partially within the one or more grooves. The one or more open-fan engines ingest a portion of a boundary layer of the blended wing body aircraft.
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公开(公告)号：US20220259985A1
公开(公告)日：2022-08-18
申请号：US17176106
申请日：2021-02-15
Applicant: General Electric Company
Inventor： Timothy Richard DePuy , Trevor Goerig , Jeffrey D. Clements , Syed Arif Khalid
Abstract: A turbomachinery engine includes an unducted rotor assembly, a low-pressure turbine, a low-pressure shaft, a gearbox, and an engine correlation parameter. The unducted rotor assembly includes a plurality of rotor blades arranged in a single row and defining a blade diameter. The gearbox includes an input, an output, and a gear ratio. The input of the gearbox is coupled to the low-pressure shaft (which is coupled to the LPT), and the output of the gearbox is coupled to the unducted rotor assembly. The engine correlation parameter is greater than 0.17 and less than 0.83. The engine correlation parameter equals D/N/GR, where D is the blade tip diameter measured in feet, N is the stage count of the low-pressure turbine, and GR is the gear ratio of the gearbox. The unducted propulsor assembly optionally includes a disk loading within a range of 60-180 HP/ft2 at a takeoff flight condition.
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Patent Agency Ranking
公开(公告)号：US20250043720A1
公开(公告)日：2025-02-06
申请号：US18434047
申请日：2024-02-06
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Timothy Richard DePuy , Steven B. Morris , Eric Barre , Brandon Wayne Miller , Leonardo Aguilar Willys , Victor Moreno Patan
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：US20250035038A1
公开(公告)日：2025-01-30
申请号：US18434128
申请日：2024-02-06
Applicant: General Electric Company
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：US20250027448A1
公开(公告)日：2025-01-23
申请号：US18436275
申请日：2024-02-08
Applicant: General Electric Company
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：US20240003543A1
公开(公告)日：2024-01-04
申请号：US17853200
申请日：2022-06-29
Applicant: General Electric Company
Inventor： Ravikanth Avancha , Ravish Karve , Jeffrey Donald Clements , Hiranya Kumar Nath , Timothy Richard DePuy
CPC classification number: F02C7/24 , F23R3/002 , F23R2900/00014
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order and together defining a working gas flowpath, the turbomachine including an acoustic liner, the acoustic liner having: a flowpath wall exposed to the working gas flowpath, the flowpath wall defining an opening; and a duct wall extending from the flowpath wall defining at least in part an acoustic passage defining a volume, the acoustic passage operable to attenuate noise through the working gas flowpath during an operating condition of the gas turbine engine.
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公开(公告)号：US20230043809A1
公开(公告)日：2023-02-09
申请号：US17388618
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Daniel Alan Niergarth , Daniel Lawrence Tweedt , Michael Simonetti , Michael Julian Castillo , Timothy Richard DePuy , Steven Benjamin Morris
Abstract: A gas turbine engine is provided including a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a rotor assembly driven by the turbomachine, the rotor assembly, the turbomachine, or both comprising a substantially annular duct relative to the centerline of the gas turbine engine, the annular duct defining a flowpath; a heat exchanger positioned within the annular duct and extending substantially continuously along the circumferential direction, the heat exchanger comprising a first material defining a heat exchange surface exposed to the flowpath, wherein the first material defines a heat exchange coefficient and wherein the heat exchange surface defines a surface area (A), and wherein the heat exchanger has an effective transmission loss (ETL) of between 5 decibels and 1 decibel for an operating condition.
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