-
公开(公告)号：US20240301891A1
公开(公告)日：2024-09-12
申请号：US18667564
申请日：2024-05-17
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor H. Wood , Kishore Ramakrishnan , William J. Solomon , Giridhar Jothiprasad , Aaron J. King
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
-
公开(公告)号：US20240301890A1
公开(公告)日：2024-09-12
申请号：US18667556
申请日：2024-05-17
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor H. Wood , Kishore Ramakrishnan , William J. Solomon , Giridhar Jothiprasad , Aaron J. King
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
-
公开(公告)号：US20240301889A1
公开(公告)日：2024-09-12
申请号：US18667278
申请日：2024-05-17
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Aaron J. King
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, and an airfoil. The fan includes fan blades that extend radially outwardly toward the annular casing. The airfoil includes a composite core having a pressure sidewall and a suction sidewall extending between a core leading edge and a core trailing edge and a leading edge protective wrap. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
-
公开(公告)号：US20240288001A1
公开(公告)日：2024-08-29
申请号：US18654444
申请日：2024-05-03
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor H. Wood , Kishore Ramakrishnan , William J. Solomon , Giridhar Jothiprasad , Aaron J. King
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
-
公开(公告)号：US20240209748A1
公开(公告)日：2024-06-27
申请号：US18086039
申请日：2022-12-21
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Ravish Karve , Sara Elizabeth Carle , Trevor Howard Wood
CPC classification number: F01D17/162 , B64D27/12 , F05D2220/325 , F05D2220/36 , F05D2240/12
Abstract: A turbofan engine defining a circumferential direction is provided. The turbofan engine includes a turbomachine; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes each defining a span, the spans of the plurality of outlet guide vanes being nonuniform along the circumferential direction.
-
Patent Agency Ranking
公开(公告)号：US20240175362A1
公开(公告)日：2024-05-30
申请号：US17994549
申请日：2022-11-28
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Valeria Andreoli , Trevor Howard Wood
IPC: F01D5/14
CPC classification number: F01D5/142 , F05D2240/301 , F05D2240/303 , F05D2240/304 , F05D2250/70 , F05D2260/961
Abstract: An airfoil assembly for a gas turbine engine includes a first blade having a first leading edge and a first trailing edge, and a second blade circumferentially spaced from the first blade where the second blade has a second leading edge and a second trailing edge. The first blade includes a feature formed on the first leading edge where the first blade includes a chord extending from the first leading edge to the first trailing edge. The chord is located radially where a projection of a line normal to an intersection of the chord with the first trailing edge intersects the second leading edge. At least a portion of the feature is radially located at or inboard of the chord.
-
公开(公告)号：US11938539B2
公开(公告)日：2024-03-26
申请号：US17232516
申请日：2021-04-16
Applicant: General Electric Company , Concept Laser GmbH
Inventor： Eric Edward Halla , Ramakrishna Venkata Mallina , Kishore Ramakrishnan , Shashwat Swami Jaiswal , Mohammed Mounir Shalaby , Peter Pontiller-Schymura
CPC classification number: B22F10/77 , B22F10/28 , B22F12/33 , B22F12/70 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B22F2201/10
Abstract: A build unit for additively manufacturing three-dimensional objects may include an energy beam system having one or more irradiation devices respectively configured to direct one or more energy beams onto a region of a powder bed, and an inertization system including an irradiation chamber defining an irradiation plenum, one or more supply manifolds, and a return manifold. The one or more supply manifolds may include a downflow manifold configured to provide a downward flow of a process gas through at least a portion of the irradiation plenum defined by the irradiation chamber, and/or a crossflow manifold configured to provide a lateral flow of the process gas through at least a portion of the irradiation plenum defined by the irradiation chamber. The return manifold may evacuate or otherwise remove process gas from the irradiation plenum defined by the irradiation chamber.
-
公开(公告)号：US11920539B1
公开(公告)日：2024-03-05
申请号：US17964097
申请日：2022-10-12
Applicant: General Electric Company
CPC classification number: F02K1/48 , F01D25/30 , F05D2220/323 , F05D2240/128 , F05D2260/96
Abstract: An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.
-
公开(公告)号：US20230408091A1
公开(公告)日：2023-12-21
申请号：US17845472
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Trevor Howard Wood
CPC classification number: F23R3/04 , F02C7/04 , B64D29/06 , F05D2220/36 , B64D33/06
Abstract: An aerodynamic device defining a thickness direction is provided. The aerodynamic device configured to produce lift or thrust or configured to be a part of an aerodynamic system that produces lift or thrust. The aerodynamic device includes a cowl assembly that defines at least in part an airflow stream. The cowl assembly includes a first cowl and a second cowl moveable relative to the first cowl. The first cowl includes a plurality of first cowl indentations at an end of the first cowl. The second cowl defines an outer surface along the thickness direction and an inner surface along the radial direction. The second cowl includes a plurality of second cowl indentations complementary in shape to the plurality of first cowl indentations. The plurality of second cowl indentations are positioned locally on the outer surface of the second cowl or locally on the inner surface of the second cowl.
-
公开(公告)号：US11834964B2
公开(公告)日：2023-12-05
申请号：US17535291
申请日：2021-11-24
Applicant: General Electric Company
Inventor： Li Zheng , Scott Roger Finn , Nicholas J. Kray , Trevor H. Wood , Kishore Ramakrishnan
CPC classification number: F01D5/3007 , F01D5/282 , F05D2220/32 , F05D2230/60 , F05D2240/30
Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement a low radius ratio fan blade for a gas turbine engine. A fan blade for a gas turbine engine includes an airfoil including a leading edge and a trailing edge extending between a root and a tip of the airfoil, a distance between the leading edge and the trailing edge defining a flow path length, a leading edge hub point defined by a radially innermost point of the leading edge, and an axial dovetail including a pair of opposed pressure faces, an axial length of the axial dovetail less than the flow path length, a top edge of the axial dovetail separating the pressure faces from the airfoil, the top edge of the axial dovetail radially outward of the leading edge hub point.
-
-
-
-
-
-
-
-
-
Search Results
124
records
(took 0.026 seconds)
