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公开(公告)号：US20190218971A1
公开(公告)日：2019-07-18
申请号：US15873605
申请日：2018-01-17
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Jeffrey Douglas Rambo , Matthew Robert Cerny
CPC classification number: F02C7/14 , F02C7/185 , F02C9/18 , F05D2260/213 , F05D2270/301 , F05D2270/303
Abstract: A heat engine comprising a compressor providing a flow of compressed air from a core flowpath of the heat engine; a cooled cooling air (CCA) heat exchanger system to which the flow of compressed air is provided from the compressor; a coolant supply system providing a flow of coolant to the CCA heat exchanger in thermal communication with the flow of compressed air at the CCA heat exchanger, in which the coolant supply system and CCA heat exchanger together define a CCA circuit through which the compressed air flows in thermal communication with the coolant; and a hot section disposed downstream of the compressor section along the core flowpath through which combustion gases flow, in which the hot section defines a secondary flowpath through which the flow of compressed air from the CCA heat exchanger is provided.
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公开(公告)号：US10094283B2
公开(公告)日：2018-10-09
申请号：US14924888
申请日：2015-10-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bugra Han Ertas , Daniel Alan Niergarth , Brandon Wayne Miller
Abstract: Embodiments of a gas bearing for aircraft engines are provided herein. In some embodiments, a gas bearing may include a first shaft; a second shaft disposed concentrically about the first shaft; and a protrusion extending from at least one of an inner surface of the first shaft or the outer surface of the second shaft to form a gap between the first shaft and the second shaft.
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公开(公告)号：US20180050811A1
公开(公告)日：2018-02-22
申请号：US15241168
申请日：2016-08-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan , Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko
Abstract: A propulsion system for an aircraft includes a gas turbine engine and an electric propulsion engine defining a central axis. The electric propulsion engine includes an electric motor and a fan rotatable about the central axis of the electric propulsion engine by the electric motor. The electric propulsion engine additionally includes a bearing supporting rotation of the fan and a thermal management system including a thermal fluid circulation assembly. The thermal fluid circulation assembly is in thermal communication with at least one of the electric motor or the bearing and is further in thermal communication with a heat exchanger of a thermal management system of the gas turbine engine.
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公开(公告)号：US20180050806A1
公开(公告)日：2018-02-22
申请号：US15242789
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Daniel Alan Niergarth , Randy M. Vondrell
CPC classification number: B64D27/24 , B64D27/12 , B64D2027/026 , F01D15/10 , F01D25/183 , F02C7/24 , F02C7/32 , F02K3/06 , F02K5/00 , F04D19/02 , F04D25/06 , F05D2220/323 , F05D2220/768 , F05D2260/98 , H02K1/27 , H02K7/1823
Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
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公开(公告)号：US20170292523A1
公开(公告)日：2017-10-12
申请号：US15095249
申请日：2016-04-11
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
CPC classification number: B64D27/24 , B64C21/06 , B64C2230/04 , B64D33/02 , B64D2027/026 , B64D2033/0226 , F02K5/00 , F04D19/002 , F04D25/06 , F04D29/668 , Y02T50/166 , Y02T50/62
Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a power gearbox mechanically coupled to an electric motor. The electric propulsion engine further includes a fan rotatable about a central axis of the electric propulsion engine by the electric motor through the power gearbox. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor or the power gearbox. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor or the power gearbox.
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Patent Agency Ranking
公开(公告)号：US09677659B1
公开(公告)日：2017-06-13
申请号：US15008986
申请日：2016-01-28
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Bugra Han Ertas , Donald Albert Bradley , Joseph Robert Dickman
CPC classification number: F16H57/0006 , F01D25/164 , F02C7/36 , F02K3/06 , F05D2260/40311 , F05D2260/96 , F16C19/28 , F16C27/045 , F16F15/0237 , F16H1/28 , F16H57/028 , F16H57/08 , F16H57/082 , F16H2057/0012 , F16H2057/085
Abstract: An epicyclic gearing arrangement includes a planet gear rotatable on a planet bearing that is mounted via a support pin to a carrier of the epicyclic gearing arrangement. An attenuation spring is disposed between the outer surface of the bearing's outer ring and the opposing inner surface of the planet gear and includes an annular gap. A spring film damper is disposed between the cylindrical outer surface of the support pin and the opposing inner surface of the inner ring of the planet bearing and includes an annular gap. The support pin (96) and/or outer ring include oil feed holes that open into the respective annular gap(s). A gas turbine engine includes an epicyclic gearing arrangement having such a planet bearing.
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公开(公告)号：US20170138307A1
公开(公告)日：2017-05-18
申请号：US14943058
申请日：2015-11-17
Applicant: General Electric Company
Abstract: A gas turbine engine includes a core and a tie shaft. The tie shaft is rotatable about an axial direction of the gas turbine engine by the core of the gas turbine engine. The gas turbine engine additionally includes a modular fan having a plurality of fan blades and a frame. The plurality fan blades are attached to the frame and the frame is slidably received on the tie shaft of the gas turbine engine. The modular fan additionally includes an attachment member removably attaching the frame to the tie shaft of the gas turbine engine to removably install the modular fan in the gas turbine engine.
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公开(公告)号：US20170122119A1
公开(公告)日：2017-05-04
申请号：US14932661
申请日：2015-11-04
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Darek Tomasz Zatorski
Abstract: A method and system for controlling a pitch of blades of a fan assembly having a centerline axis of rotation is provided. The system includes a pitch change mechanism (PCM) including a hydraulic actuator positioned axisymmetric with respect to the fan assembly and configured to angularly displace the blades of the fan assembly between a first position and a second position. The PCM further includes a plurality of hydraulic fluid supply lines coupled in flow communication between the hydraulic actuator and a hydraulic fluid transfer sleeve, the hydraulic fluid transfer sleeve configured to transfer a flow of pressurized hydraulic fluid across a gap between a stationary member of the hydraulic fluid transfer sleeve and a rotatable member of the hydraulic fluid transfer sleeve.
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99.发明申请VARIABLE PITCH FAN FOR GAS TURBINE ENGINE AND METHOD OF ASSEMBLING THE SAME 审中-公开用于气体涡轮发动机的可变风口风扇及其组装方法公开(公告)号：US20160146025A1
公开(公告)日：2016-05-26
申请号：US14873382
申请日：2015-10-02
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice , Daniel Alan Niergarth
CPC classification number: F01D7/00 , F01D5/02 , F01D7/02 , F01D9/041 , F01D17/105 , F01D25/24 , F02C3/04 , F04D29/323 , F05D2220/32 , F05D2220/36 , F05D2240/35 , F05D2260/71 , F05D2260/74
Abstract: A gas turbine engine is provided. The gas turbine engine includes a core and a variable pitch fan arranged in flow communication with the core. The variable pitch fan has a disk and at least nine fan blades coupled to the disk for rotation together with the disk. The gas turbine engine further includes a rotatable nacelle covering the disk such that the engine has a fan hub radius ratio of between about 0.1 and about 0.4.
Abstract translation: 提供燃气涡轮发动机。 燃气涡轮发动机包括与芯部流动连通的芯部和可变节距风扇。 可变间距风扇具有盘，并且至少有九个风扇叶片联接到盘上以与盘一起旋转。 燃气涡轮发动机还包括覆盖盘的可旋转机舱，使得发动机的风扇轮毂半径比在约0.1和约0.4之间。
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公开(公告)号：US20250163853A1
公开(公告)日：2025-05-22
申请号：US19032996
申请日：2025-01-21
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Jeffrey Donald Clements , Jeffrey S. Spruill , Erich Alois Krammer , Matthew Kenneth MacDonald , Scott Alan Schimmels , Nicholas Joseph Kray , Arthur William Sibbach
IPC: F02K3/06
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).
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