公开(公告)号：US20230235680A1

公开(公告)日：2023-07-27

申请号：US17649030

申请日：2022-01-26

Applicant: General Electric Company

Inventor： Valeria Andreoli ,  Thomas W. Vandeputte ,  Neelesh N. Sarawate

IPC: F01D11/20 ,  F01D7/00 ,  F01D25/00

CPC classification number: F01D11/20 ,  F01D7/00 ,  F01D25/005

Abstract: A rotor blade system includes a rotor, a casing radially spaced apart from the rotor, and a plurality of blades coupled to the rotor and positioned between the rotor and the casing. The one or more of the plurality of blades have a radial length different from a remaining one or more of the plurality of blades so as to vary a tip gap between a tip of the one or more of the plurality of blades and the casing to break up a frequency content of a leakage vortex at the tip to modify natural frequencies of the plurality of blades and mode shapes to reduce or substantially eliminate flutter.

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.

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：US20250067193A1

公开(公告)日：2025-02-27

申请号：US18938401

申请日：2024-11-06

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Valeria Andreoli ,  Shashwat Swami Jaiswal ,  Thomas William Vandeputte

IPC: F01D11/08 ,  F01D11/02

Abstract: A blade assembly for a gas turbine engine having an engine casing, with the blade assembly being configured to rotate about a rotational axis. The blade assembly having a blade, and at least one fin. The blade extending between a root and a tip, with the tip being spaced radially from the engine casing to define a space therebetween. The at least one fin extending radially with respect to the tip and into the space.

公开(公告)号：US20240328320A1

公开(公告)日：2024-10-03

申请号：US18192859

申请日：2023-03-30

Applicant: General Electric Company

Inventor： Kishore Ramakrishnan ,  Daniel Lawrence Tweedt ,  Valeria Andreoli

IPC: F01D5/14

CPC classification number: F01D5/14 ,  F05D2220/323

Abstract: An unducted airfoil assembly includes an airfoil defining a leading edge, a trailing edge, a root, and a tip. A forward-most axial point of the leading edge is radially located at or greater than sixty percent of a tip radius of the airfoil when the airfoil is oriented at a design orientation for subsonic cruise operation.

公开(公告)号：US12196087B2

公开(公告)日：2025-01-14

申请号：US17859456

申请日：2022-07-07

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Valeria Andreoli ,  Shashwat Swami Jaiswal ,  Thomas William Vandeputte

IPC: F01D11/08 ,  F01D11/02

Abstract: A blade assembly for a gas turbine engine having an engine casing, with the blade assembly being configured to rotate about a rotational axis. The blade assembly having a blade, and at least one fin. The blade extending between a root and a tip, with the tip being spaced radially from the engine casing to define a space therebetween. The at least one fin extending radially with respect to the tip and into the space.

公开(公告)号：US20240011407A1

公开(公告)日：2024-01-11

申请号：US17859456

申请日：2022-07-07

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Valeria Andreoli ,  Shashwat Swami Jaiswal ,  Thomas William Vandeputte

IPC: F01D11/02

CPC classification number: F01D11/02 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/55

Abstract: A blade assembly for a gas turbine engine having an engine casing, with the blade assembly being configured to rotate about a rotational axis. The blade assembly having a blade, and at least one fin. The blade extending between a root and a tip, with the tip being spaced radially from the engine casing to define a space therebetween. The at least one fin extending radially with respect to the tip and into the space.

公开(公告)号：US20230249810A1

公开(公告)日：2023-08-10

申请号：US18169757

申请日：2023-02-15

Applicant: General Electric Company

Inventor： Kishore Ramakrishnan ,  Valeria Andreoli ,  Daniel L. Tweedt

IPC: B64C27/473 ,  B64C27/467

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.