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公开(公告)号：US10100736B2
公开(公告)日：2018-10-16
申请号：US14927536
申请日：2015-10-30
Applicant: General Electric Company
Abstract: A gas turbine engine includes a compressor section in series flow with a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines, the compressor section and turbine section together defining a core air flowpath. A sump is positioned inward of the core air flowpath for containing and collecting lubrication oil. Additionally, a heat exchanger is positioned in direct thermal communication with the sump for removing heat from lubrication oil contained therein to reduce a size and/or amount of heat exchangers located radially outward of the core air flowpath.
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公开(公告)号：US10093428B2
公开(公告)日：2018-10-09
申请号：US15242844
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Randy M. Vondrell
Abstract: A propulsion system includes an electric propulsor and a gas turbine engine. The propulsion system also includes an electric machine coupled to a rotary component of the gas turbine engine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine. An electric communication bus is provided electrically connecting the electric machine to the electric propulsor. The propulsion system additionally includes a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.
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公开(公告)号：US10072510B2
公开(公告)日：2018-09-11
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.
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公开(公告)号：US20180238186A1
公开(公告)日：2018-08-23
申请号：US15439122
申请日：2017-02-22
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Thomas Ory Moniz , Monty Lee Shelton , Joel Francis Kirk , Jeffrey Donald Clements
CPC classification number: B64D27/10 , B64D27/18 , F02C7/20 , F02K3/06 , F05D2250/323 , F05D2250/52 , F05D2250/712 , Y02T50/672
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a low pressure (LP) turbine defining an outer flowpath. The outer flowpath defines a first outer flowpath radius at an upstream-most end of the LP turbine, a last outer flowpath radius disposed at a downstream-most end of the LP turbine, a middle outer flowpath radius disposed therebetween along the longitudinal direction. The middle outer flowpath radius is greater than the last outer flowpath radius.
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公开(公告)号：US20180230805A1
公开(公告)日：2018-08-16
申请号：US15434658
申请日：2017-02-16
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Jeffrey Donald Clements , Daniel Waslo , Joel Francis Kirk
CPC classification number: F01D5/08 , F01D1/26 , F01D5/03 , F01D5/06 , F01D5/186 , F01D5/187 , F01D11/08 , F02C3/04 , F05D2220/32 , F05D2240/14 , F05D2240/24 , F05D2240/55 , F05D2250/185 , F05D2260/202
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine defines a core flowpath extended generally along the longitudinal direction. The gas turbine engine includes a first turbine rotor. The first turbine rotor includes an annular outer band disposed outward of the core flowpath along the radial direction. The first turbine rotor further includes a plurality of airfoils coupled to an inner diameter of the outer band in which the plurality of airfoils are extended generally inward along the radial direction. The outer band defines a plurality of airfoil cooling passages in which the plurality of airfoil cooling passages are extended at least partially in the radial direction in fluid communication with the plurality of airfoils.
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Patent Agency Ranking
公开(公告)号：US20180216575A1
公开(公告)日：2018-08-02
申请号：US15417745
申请日：2017-01-27
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Matthew Ryan Polakowski , Patrick Michael Marrinan , Joel Francis Kirk , Randy M. Vondrell , Jeffrey Donald Clements
CPC classification number: F02K3/06 , F01D25/26 , F02C3/04 , F02C7/18 , F02C7/36 , F05D2220/36 , F05D2300/20 , Y02T50/672
Abstract: A turbofan engine is provided including a fan having a plurality of rotatable fan blades and defining a fan pressure ratio during operation of the turbofan engine. The turbofan engine also includes a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath. The turbofan also includes an outer nacelle at least partially surrounding the fan and the turbomachine, the outer nacelle defining a bypass passage with the turbomachine. A bypass ratio of an amount of airflow through the bypass passage to an amount of airflow through the core air flowpath during operation of the turbofan is less than or equal to about 11 and wherein the fan pressure ratio is less than or equal to about 1.5.
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公开(公告)号：US10017270B2
公开(公告)日：2018-07-10
申请号：US14879217
申请日：2015-10-09
Applicant: General Electric Company
IPC: B64D33/02 , B64D27/18 , B64D27/24 , B64D27/26 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/32 , F04D29/36 , F04D29/52 , F04D29/54 , B64C1/16 , B64C21/06 , B64D27/20 , B64D29/04 , B64D27/02
CPC classification number: B64D33/02 , B64C1/16 , B64C21/06 , B64D27/18 , B64D27/20 , B64D27/24 , B64D27/26 , B64D29/04 , B64D2027/026 , B64D2033/0226 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/325 , F04D29/36 , F04D29/522 , F04D29/542 , F05D2220/323 , Y02T50/166
Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades attached to a fan shaft. The aft engine also includes a nacelle encircling the plurality of fan blades and a structural support system for mounting the aft engine to the aircraft. The structural support system extends from the fuselage of the aircraft, through the fan shaft, and to the nacelle when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
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公开(公告)号：US20180138761A1
公开(公告)日：2018-05-17
申请号：US15354323
申请日：2016-11-17
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Paul Robert Gemin
CPC classification number: H02K1/187 , H02K1/2786 , H02K16/00 , H02K21/22 , H02K2201/03 , H02K2213/09
Abstract: An electric machine is provided which includes a rotor disk extending along a radial direction and having a rotor flange attached to or formed integrally with the rotor disk and extending substantially along the axial direction. A plurality of rotor magnets are mounted on the rotor disk and positioned against the rotor flange. The electric machine includes a stator assembly including a tracking tooth in magnetic flux communication with the rotor magnets across an air gap. The stator assembly further includes an actuator operable with the tracking tooth to move the tracking tooth along the radial direction to adjust a height of the air gap.
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公开(公告)号：US09932858B2
公开(公告)日：2018-04-03
申请号：US14809560
申请日：2015-07-27
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Richard Schmidt , Daniel Alan Niergarth
CPC classification number: F01D25/164 , F01D9/065 , F01D25/162 , F01D25/18 , F01D25/20 , F02C7/32 , F05D2260/98 , Y02T50/671
Abstract: A gas turbine engine is provided including a shaft coupling a compressor of a compressor section to a turbine of a turbine section. An aft bearing assembly, including at least two bearings, is positioned at least partially in an aft sump and supports the shaft within the turbine section. The aft sump is configured to receive lubrication oil from a lubrication oil supply extending through at least a portion of a turbine center frame of the turbine section, and provide such lubrication to the at least two bearings of the aft bearing assembly.
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公开(公告)号：US20180050810A1
公开(公告)日：2018-02-22
申请号：US15241157
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
IPC: B64D33/08 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/32 , F04D29/056 , F04D29/063 , F04D29/58
Abstract: A propulsion system for an aircraft includes an electric propulsion engine. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis of the electric propulsion engine by the electric motor. The electric propulsion engine also includes a bearing supporting rotation of the fan and a thermal management system. The thermal management system includes a lubrication oil circulation assembly and a heat exchanger thermally connected to the lubrication oil circulation assembly. The lubrication oil circulation assembly is configured for providing the bearing with lubrication oil. Such an electric propulsion engine may be a relatively self-sufficient engine.
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