-
公开(公告)号：US10252790B2
公开(公告)日：2019-04-09
申请号：US15234055
申请日：2016-08-11
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan
IPC: B64C21/06 , B64D29/00 , F02K3/062 , F04D19/00 , F04D29/52 , F04D29/54 , F02K5/00 , F02C7/042 , B64D33/02
Abstract: The present disclosure is directed to a low-distortion inlet assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet assembly includes a plurality of structural members, such as struts or strakes, mounted at predetermined locations around a circumference of the fan shaft of the fan at the inlet. The predetermined location(s) may be determined as a function of swirl distortion entering the inlet. As such, the structural member(s) are configured to reduce swirl distortion of the airflow entering the fan. In some embodiments, the inlet assembly may also include inlet guide vanes. In alternative embodiments, the inlet assembly may be absent of inlet guide vanes.
-
公开(公告)号：US12258923B2
公开(公告)日：2025-03-25
申请号：US18182613
申请日：2023-03-13
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor Howard Wood , Kishore Ramakrishnan
Abstract: A propulsor is provided having a power source; a fan section coupled to the power source and configured to provide thrust opposite a downstream direction; and a cowl assembly at least partially enclosing the power source and the fan section, the cowl assembly including: a forward cowl component; a first aft cowl component disposed in the downstream direction relative to the forward cowl component and movable to vary a first aft cowl displacement from the forward cowl component in the downstream direction; and a second aft cowl component disposed in the downstream direction relative to the first aft cowl component and movable to vary a second aft cowl intermediate displacement from the first aft cowl component.
-
公开(公告)号：US12258875B2
公开(公告)日：2025-03-25
申请号：US18618081
申请日：2024-03-27
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
-
公开(公告)号：US12215596B2
公开(公告)日：2025-02-04
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.
-
公开(公告)号：US20250012216A1
公开(公告)日：2025-01-09
申请号：US18891458
申请日：2024-09-20
Applicant: General Electric Company
Inventor： Nikolai Pastouchenko , Kishore Ramakrishnan , Trevor H. Wood , Timothy Richard Depuy
Abstract: An inlet duct for a nacelle of a ducted fan engine includes an inlet portion having an inlet lip and a hardwall portion, a highlight plane defined at an upstream end of the inlet portion, and an acoustic liner downstream of the inlet portion, a hardwall-acoustic liner interface defined at an interface of the hardwall portion and the acoustic liner. The inlet portion and the acoustic liner are coupled at an inlet-acoustic liner interface extending circumferentially about an inner circumferential surface of the inlet duct. The inlet lip varies circumferentially and axially with respect to the highlight plane and the inlet centerline axis, and includes a plurality of inlet lip crests arranged along the highlight plane, and a plurality of inlet lip troughs arranged downstream of the highlight plane. The hardwall-acoustic liner interface extends circumferentially about the inner circumferential surface and is arranged axially parallel to the highlight plane.
-
Patent Agency Ranking
公开(公告)号：US20240418182A1
公开(公告)日：2024-12-19
申请号：US18813586
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.
-
公开(公告)号：US20240418181A1
公开(公告)日：2024-12-19
申请号：US18813578
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.
-
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：US20240263565A1
公开(公告)日：2024-08-08
申请号：US18618081
申请日：2024-03-27
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
CPC classification number: F01D25/04 , F01D5/141 , F01D5/145 , F01D5/18 , F01D9/041 , F02K1/827 , G10K11/16 , B64D2033/0226 , F05D2240/121 , F05D2250/184 , F05D2260/96 , F05D2260/961
Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
-
公开(公告)号：US20240254883A1
公开(公告)日：2024-08-01
申请号：US18161122
申请日：2023-01-30
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Nikolai N. Pastouchenko , Trevor Howard Wood , Thomas William Vandeputte
IPC: F01D5/14
CPC classification number: F01D5/142 , F05D2240/121 , F05D2240/122 , F05D2250/713 , F05D2260/96
Abstract: A turbine airfoil is provided. The turbine airfoil defines a chord line, a spanwise direction, a span along the spanwise direction, and a midpoint along the spanwise direction. The turbine airfoil includes a pressure side and a suction side. The pressure side and the suction side intersecting at a leading edge and a trailing edge. The turbine airfoil further includes a root and a tip at opposing ends along the spanwise direction. In addition, the turbine airfoil defines a leading edge reference line extending from where the leading edge meets the root to where the leading edge meets the tip and a trailing edge reference line extending from where the trailing edge meets the root to where the trailing edge meets the tip. The turbine airfoil includes a lobe positioned at the leading edge or the trailing edge and defines a maximum axially height relative to the leading edge reference line or the trailing edge reference line. The maximum axial height being equal to at least five percent of the chord line of the turbine airfoil.
-
-
-
-
-
-
-
-
-
Search Results
124
records
(took 0.029 seconds)
