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公开(公告)号：US20230043809A1
公开(公告)日：2023-02-09
申请号：US17388618
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Daniel Alan Niergarth , Daniel Lawrence Tweedt , Michael Simonetti , Michael Julian Castillo , Timothy Richard DePuy , Steven Benjamin Morris
Abstract: A gas turbine engine is provided including a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a rotor assembly driven by the turbomachine, the rotor assembly, the turbomachine, or both comprising a substantially annular duct relative to the centerline of the gas turbine engine, the annular duct defining a flowpath; a heat exchanger positioned within the annular duct and extending substantially continuously along the circumferential direction, the heat exchanger comprising a first material defining a heat exchange surface exposed to the flowpath, wherein the first material defines a heat exchange coefficient and wherein the heat exchange surface defines a surface area (A), and wherein the heat exchanger has an effective transmission loss (ETL) of between 5 decibels and 1 decibel for an operating condition.
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公开(公告)号：US20190048724A1
公开(公告)日：2019-02-14
申请号：US15675239
申请日：2017-08-11
Applicant: General Electric Company
Inventor： Daniel Lawrence Tweedt
CPC classification number: F01D5/141 , B64C11/18 , B64C21/00 , F01D5/142 , F01D5/16 , F05D2220/36 , F05D2240/301 , F05D2240/302 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2250/70 , F05D2260/96
Abstract: An airfoil section of 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 a chord of the airfoil section is defined as a straight-line distance between the leading edge and the trailing edge; the airfoil section has a meanline defined midway between the pressure side and the suction side; and the meanline is shaped such that, in the presence of predetermined transonic or supersonic relative velocity conditions, maximum and minimum ideal Mach numbers on the suction side will lie within a 0.08 band, between 25% and 80% percent of the chord.
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公开(公告)号：US20240318613A1
公开(公告)日：2024-09-26
申请号：US18680469
申请日：2024-05-31
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberley Simpson , Syed Arif Khalid , Jeffrey S. Spruill , Daniel Lawrence Tweedt , William Joseph Solomon , Kevin Edward Hinderliter
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
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公开(公告)号：US11262144B2
公开(公告)日：2022-03-01
申请号：US15858453
申请日：2017-12-29
Applicant: General Electric Company
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.
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公开(公告)号：US10358926B2
公开(公告)日：2019-07-23
申请号：US15675239
申请日：2017-08-11
Applicant: General Electric Company
Inventor： Daniel Lawrence Tweedt
Abstract: An airfoil section of 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 a chord of the airfoil section is defined as a straight-line distance between the leading edge and the trailing edge; the airfoil section has a meanline defined midway between the pressure side and the suction side; and the meanline is shaped such that, in the presence of predetermined transonic or supersonic relative velocity conditions, maximum and minimum ideal Mach numbers on the suction side will lie within a 0.08 band, between 25% and 80% percent of the chord.
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Patent Agency Ranking
公开(公告)号：US11352132B2
公开(公告)日：2022-06-07
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
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.
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公开(公告)号：US11286955B2
公开(公告)日：2022-03-29
申请号：US16599459
申请日：2019-10-11
Applicant: General Electric Company
Inventor： Daniel Lawrence Tweedt , Syed Arif Khalid
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.
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公开(公告)号：US10710705B2
公开(公告)日：2020-07-14
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.
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公开(公告)号：US20180362155A1
公开(公告)日：2018-12-20
申请号：US15626825
申请日：2017-06-19
Applicant: General Electric Company
Inventor： Daniel Lawrence Tweedt , Andrew Breeze-Stringfellow
Abstract: A variable-solidity propeller apparatus, comprising a propeller having at least one rotatable hub carrying at least one row of propeller blades, wherein the propeller has a first configuration in which the propeller has a first average solidity, and a second configuration in which the propeller has a second average solidity which is greater than the first average solidity.
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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.
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