公开(公告)号：US20240401491A1

公开(公告)日：2024-12-05

申请号：US18678000

申请日：2024-05-30

Applicant: General Electric Company

Inventor： Syed Khalid ,  David Marion Ostdiek ,  Jeffrey S. Spruill ,  Daniel Lawrence Tweedt ,  William Joseph Solomon ,  Brandon Wayne Miller ,  Randy M. Vondrell ,  Kevin Edward Hinderliter

IPC: F01D9/04 ,  F01D5/14

Abstract: A gas turbine engine is provided, comprising: a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; and a fan section having a fan drivingly coupled to the turbomachine and an airflow surface rotatable with the fan and exposed to a fan airflow provided to and through the fan during operation of the gas turbine engine, the airflow surface defining a plurality of boundary layer openings configured to ingest a boundary layer of the fan airflow over the airflow surface during operation of the gas turbine engine.

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：US20190002086A1

公开(公告)日：2019-01-03

申请号：US15636017

申请日：2017-06-28

Applicant: General Electric Company

Inventor： Daniel Lawrence Tweedt

IPC: B64C11/18

Abstract: An open rotor airfoil apparatus includes: an airfoil body having pressure and suction sides extending in span from a root to a tip, and in chord between leading and trailing edges. A majority of the leading edge in an outer portion of the airfoil body has a sweep equal to or greater than a predetermined sweep profile, selected to produce a blade-relative velocity component perpendicular to the leading edge, at a tip radius, of Mach 0.75 or less, and to produce a blade-relative velocity component perpendicular to the leading edge, at 65% of tip radius, of Mach 0.87 or less, with the blade-relative velocity component perpendicular to the leading edge varying linearly between the two limits, in the presence of transonic or supersonic relative velocity conditions. Each of the blades has a leading edge thickness greater than 0.45% of the chord, measured at a 0.5% chordwise location.

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.

公开(公告)号：US20210108653A1

公开(公告)日：2021-04-15

申请号：US16599459

申请日：2019-10-11

Applicant: General Electric Company

Inventor： Daniel Lawrence Tweedt ,  Syed Arif Khalid

IPC: F04D29/54 ,  F04D19/00

Abstract: A ducted fan is provided including a fan casing surrounding a plurality of fan blades mounted to a rotating drive shaft. The plurality of blades define a tip stagger angle of greater than 68 degrees and the fan casing defines an annular recess defined by an inner wall of the fan casing, the annular recess extending about the circumferential direction proximate a blade tip of each of the plurality of blades. The annular recess may define an average recess depth greater than 10 percent of the tip chord length. The annular recess may also define a length ratio equal to a recess length over the tip axial chord length that is greater than 1.5.

公开(公告)号：US20200023959A1

公开(公告)日：2020-01-23

申请号：US16042141

申请日：2018-07-23

Applicant: General Electric Company

Inventor： Andrew Breeze-Stringfellow ,  Daniel Lawrence Tweedt ,  Syed Arif Khalid ,  Kurt David Murrow

IPC: B64C29/00

Abstract: A lift fan apparatus includes: a rotor having at least one rotatable hub carrying at least one row of blades; a duct surrounding the rotor, the duct including spaced-apart peripheral walls extending between an inlet and an exit, the peripheral walls collectively defining a flow channel which includes a diffuser disposed downstream of the rotor, in which a flow area at the exit is greater than a flow area at the rotor; and a plurality of spaced-apart splitters disposed in the diffuser, each of the splitters having opposed side walls extending between an upstream leading edge and a downstream trailing edge, wherein the splitters divide the diffuser into a plurality of side-by-side flow passages.

公开(公告)号：US10399664B2

公开(公告)日：2019-09-03

申请号：US15145894

申请日：2016-05-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： William Joseph Bowden ,  Andrew Breeze-Stringfellow ,  Richard David Cedar ,  Syed Arif Khalid ,  Patrick John Lonneman ,  Aleksander Piotr Pasieczny ,  Daniel Lawrence Tweedt

IPC: B64C11/14 ,  B64D33/02 ,  F02C6/20 ,  F02C7/05 ,  F01D5/02 ,  F01D9/04 ,  F01D25/04 ,  F01D25/24 ,  F04D29/32 ,  F04D29/38 ,  B64D27/00

Abstract: An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.

公开(公告)号：US20190204010A1

公开(公告)日：2019-07-04

申请号：US15858453

申请日：2017-12-29

Applicant: General Electric Company

Inventor： Andrew Breeze-Stringfellow ,  Daniel Lawrence Tweedt ,  Tsuguji Nakano ,  Syed Arif Khalid

IPC: F28D7/00 ,  F28F1/22 ,  F28F13/08 ,  F28D7/10 ,  F02C7/14

CPC classification number: F28D7/005 ,  F02C3/04 ,  F02C7/14 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/22141 ,  F28D7/10 ,  F28D2021/0026 ,  F28F1/22 ,  F28F13/08

Abstract: A heat exchanger apparatus includes: spaced-apart peripheral walls extending between an inlet and an outlet, the peripheral walls collectively defining a flow channel which includes a diverging portion downstream of the inlet, in which a flow area is greater than a flow area at the inlet; a plurality of spaced-apart fins disposed in the flow channel, each of the fins having opposed side walls extending between an upstream leading edge and a downstream trailing edge, wherein the fins divide at least the diverging portion of the flow channel into a plurality of side-by-side flow passages; and a heat transfer structure disposed within at least one of the fins.