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公开(公告)号：US20170152020A1
公开(公告)日：2017-06-01
申请号：US15378614
申请日：2016-12-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
IPC: B64C11/18
CPC classification number: B64C11/18 , B64D2027/005 , Y02T50/66
Abstract: In some embodiments, an airfoil comprises a proximal end; a distal end opposite said proximal end; a distal portion extending adjacent said distal end; an edge extending between said proximal end and said distal end; and a surface extending between said proximal end and said distal end, said edge and said surface defining a sweep and a cahedral through said distal portion, wherein the distal portion extends over an acoustically active portion of the airfoil.
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公开(公告)号：US12276199B2
公开(公告)日：2025-04-15
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
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.
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公开(公告)号：US20250003340A1
公开(公告)日：2025-01-02
申请号：US18345018
申请日：2023-06-30
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Daniel Lawrence Tweedt
IPC: F01D5/14
Abstract: An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.
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公开(公告)号：US20240426247A1
公开(公告)日：2024-12-26
申请号：US18824999
申请日：2024-09-05
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Ramakrishna Venkata Mallina , Giridhar Jothiprasad , Kishore Ramakrishnan , Thomas Malkus
Abstract: A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
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公开(公告)号：US20240418180A1
公开(公告)日：2024-12-19
申请号：US18813567
申请日：2024-08-23
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor H. Wood , Kishore Ramakrishnan , William J. Solomon , Giridhar Jothiprasad , Aaron J. King
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.
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Patent Agency Ranking
公开(公告)号：US12117019B2
公开(公告)日：2024-10-15
申请号：US18301692
申请日：2023-04-17
Applicant: General Electric Company
Inventor： Trevor Wood , Kishore Ramakrishnan
CPC classification number: F04D29/544 , F01D9/042 , F04D29/667 , F02C3/04 , F05D2220/323 , F05D2230/80 , F05D2240/121 , F05D2240/122 , F05D2260/96
Abstract: Disclosed examples include an airfoil comprising: a pressure side and a suction side that are coupled together at a substantially radial trailing edge of the airfoil, wherein the substantially radial trailing edge is downstream from a leading edge, the leading edge including a sweep feature of a variable chord length, the variable chord length to include: a first increase in chord length and a decrease in chord length along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and a second increase in chord length along the radial length from the hub end to the opposite tip end, the second increase different than the first increase.
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公开(公告)号：US20240318660A1
公开(公告)日：2024-09-26
申请号：US18678303
申请日：2024-05-30
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 first side and a second side coupled together at a leading edge and a trailing edge, a plurality of first chord sections defining at least one first chord length, and a plurality of second chord sections defining at least one second chord length. The plurality of first chord sections and second chord sections define a waveform along a leading edge of the airfoil. 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.
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公开(公告)号：US12084166B2
公开(公告)日：2024-09-10
申请号：US17108431
申请日：2020-12-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Davide Giacché , Angela Knepper , Nicholas Bown , Rathakrishnan Bhaskaran
CPC classification number: B64C11/18 , B64C11/14 , B64D33/02 , B64D2033/0293 , F02C7/04 , F05D2220/323
Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.
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公开(公告)号：US20240288003A1
公开(公告)日：2024-08-29
申请号：US18656078
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
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 blades include a first fan blade having a fan blade airfoil body and a metal edge. The fan blade airfoil body has a leading edge. The metal edge is located at the leading edge and has a plurality of fail-fuse elements. 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.
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公开(公告)号：US12049306B2
公开(公告)日：2024-07-30
申请号：US18169757
申请日：2023-02-15
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Valeria Andreoli , Daniel L. Tweedt
IPC: B64C27/467 , B64C27/473
CPC classification number: B64C27/473 , B64C27/467
Abstract: A blade for an open rotor includes a pressure side and a suction side, the pressure side and the suction side intersecting at a leading edge and a trailing edge, wherein for at least 30% of a span of the blade, the meanline of the airfoil section is shaped such that a relative curvature parameter is greater than 1.2 in a first region, less than 0.75 in a second region, and greater than 0.9 in a third region, wherein the relative curvature parameter of a region is defined by Δζn/Δζtot/Δ(x/c)n wherein ζ corresponds to the inverse tangent of the slope of a meanline curve, subscript n indicates the region, and x/c is a chordwise location normalized by the chord and wherein the first region comprises at least x/c=0.0 to 0.15 and the third region comprises at least x/c=0.80 to 1.0.
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