-
公开(公告)号：US20250163850A1
公开(公告)日：2025-05-22
申请号：US18515871
申请日：2023-11-21
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , James R. Reepmeyer , Erich Alois Krammer , Koji Asari , Jeffrey D. Clements
Abstract: A turbine engine for an aircraft includes a turbo-engine with a core air flow path, a fan having a fan shaft coupled to the turbo-engine to rotate the fan shaft, and a steam system. The core air flow path includes a plurality of core air flow path zones. A combustor is positioned in the core air flow path to combust fuel and to generate combustion gases. The steam system extracts water from combustion gases and vaporizes the water to generate steam. The steam system is fluidly coupled to a core air flow path to inject the steam into the core air flow path at a plurality of steam injection zones to add mass flow to the core air. Each steam injection zone of the plurality of steam injection zones corresponds to a core air flow path zone of the plurality of core air flow path zones.
-
公开(公告)号：US12158113B2
公开(公告)日：2024-12-03
申请号：US18430283
申请日：2024-02-01
Applicant: General Electric Company
Inventor： Pranav R. Kamat , Bhaskar Nanda Mondal , Jeffrey D. Clements
Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
-
公开(公告)号：US20240287940A1
公开(公告)日：2024-08-29
申请号：US18651425
申请日：2024-04-30
Applicant: General Electric Company
Inventor： Pranav R. Kamat , Bhaskar Nanda Mondal , Jeffrey D. Clements
Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
-
公开(公告)号：US20240254925A1
公开(公告)日：2024-08-01
申请号：US18604985
申请日：2024-03-14
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Andrea Piazza , Jeffrey D. Clements
CPC classification number: F02C7/36 , F02C3/067 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2200/221 , F05D2260/40311 , F05D2260/98
Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0.
-
公开(公告)号：US11959393B2
公开(公告)日：2024-04-16
申请号：US17523505
申请日：2021-11-10
Applicant: GE Avio S.r.l. , General Electric Company
Inventor： Saurya Ranjan Ray , Francesco Bertini , Lyle Douglas Dailey , Jeffrey D. Clements , Jaikumar Loganathan , Simone Rosa Taddei
IPC: F01D5/14
CPC classification number: F01D5/141 , F05D2240/301 , F05D2240/305 , F05D2240/306 , F05D2250/181 , F05D2250/711 , F05D2250/712
Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.
-
Patent Agency Ranking
公开(公告)号：US20230243309A1
公开(公告)日：2023-08-03
申请号：US17929542
申请日：2022-09-02
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Andrea Piazza , Jeffrey D. Clements
CPC classification number: F02C7/36 , F02K3/06 , F02C3/067 , F05D2200/14 , F05D2260/98 , F05D2200/221 , F05D2260/40311 , F05D2200/13
Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.
-
公开(公告)号：US20250084797A1
公开(公告)日：2025-03-13
申请号：US18463800
申请日：2023-09-08
Applicant: General Electric Company
Inventor： Brandon W. Miller , Geoffrey Whitener , Jeffrey D. Clements , Patrick Marrinan , Andrew J. Hank
IPC: F02C9/18
Abstract: A method of operating a turbine engine. The turbine engine includes a high-pressure compressor including a high-pressure compressor flowpath and a plurality of stages, and a bleed system. The bleed system includes a plurality of bleed flowpaths including a first bleed flowpath from one stage of the plurality of stages and a second bleed flowpath from another stage of the plurality of stages. The method includes directing compressed air through the high-pressure compressor flowpath, directing a first portion of the compressed air through the first bleed flowpath, the first portion of the compressed air having a first mass flow, directing a second portion of the compressed air through the second bleed flowpath, determining an altitude of the turbine engine, and changing the first mass flow of the first portion of the compressed air through the first bleed flowpath based on the altitude of the turbine engine.
-
公开(公告)号：US20250084788A1
公开(公告)日：2025-03-13
申请号：US18463793
申请日：2023-09-08
Applicant: General Electric Company
Inventor： Brandon W. Miller , Andrew J. Hank , Scott D. Hunter , Geoffrey Whitener , Paul Pezzi , Jeffrey D. Clements
Abstract: A turbine engine includes a high-pressure (HP) compressor and a bleed system. The HP compressor includes an HP compressor flowpath and a plurality of stages of HP compressor rotor blades and HP compressor stator vanes. The bleed system includes a plurality of bleed flowpaths including at least three bleed flowpaths in fluid communication with the HP compressor flowpath. The plurality of bleed flowpaths direct compressed air from the HP compressor flowpath. At least two of the bleed flowpaths are at successive stages of the plurality of stages.
-
公开(公告)号：US12123358B2
公开(公告)日：2024-10-22
申请号：US18651425
申请日：2024-04-30
Applicant: General Electric Company
Inventor： Pranav R. Kamat , Bhaskar Nanda Mondal , Jeffrey D. Clements
Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
-
公开(公告)号：US12085026B2
公开(公告)日：2024-09-10
申请号：US18604985
申请日：2024-03-14
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Andrea Piazza , Jeffrey D. Clements
CPC classification number: F02C7/36 , F02C3/067 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2200/221 , F05D2260/40311 , F05D2260/98
Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0.
-
-
-
-
-
-
-
-
-
Search Results
31
records
(took 0.024 seconds)
