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公开(公告)号：US10975717B2
公开(公告)日：2021-04-13
申请号：US15382817
申请日：2016-12-19
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Joseph George Rose , Robert Harold Weisgerber , Jeffrey Donald Clements , Brandon Wayne Miller
Abstract: A gas turbine engine includes a fan section having a fan rotatable with a fan shaft and a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine. A power gearbox is also provided mechanically coupled to both the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox. A torque monitoring system includes a gearbox sensor operable with a gear of the power gearbox and a shaft sensor operable with at least one of the turbomachine shaft or the fan shaft. The torque monitoring system determines an angular position of the gear of the gearbox relative to at least one of the fan shaft or the turbomachine shaft using the gearbox sensor and the shaft sensor to determine a torque within the gas turbine engine.
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公开(公告)号：US10762726B2
公开(公告)日：2020-09-01
申请号：US15621279
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Michael Thomas Gansler , Sridhar Adibhatla , Brandon Wayne Miller
Abstract: A computer-implemented method of assessing a health of a gas turbine engine of a hybrid-electric propulsion system for an aircraft includes receiving, by one or more computing devices, data indicative of an amount of electrical power provided to, or extracted from, an electric machine. The method also includes receiving, by the one or more computing devices, data indicative of an operating parameter of the hybrid-electric propulsion system. The method also includes assessing, by the one or more computing devices, a health of the gas turbine engine based at least in part on the received data indicative of the amount of electrical power provided to, or extracted from, the electric machine and the received data indicative of the operating parameter of the hybrid electric propulsion system. The method also includes providing, by the one or more computing devices, information to a user indicative of the health of the gas turbine engine.
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公开(公告)号：US10724435B2
公开(公告)日：2020-07-28
申请号：US15625186
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades. The gas turbine engine also includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide vanes cantilevered from the outer nacelle at a location forward of the plurality of fan blades along the axial direction. Each of the plurality of inlet guide vanes defines an inner end along the radial direction and it is unconnected with an adjacent part-span inlet guide vane at the inner end.
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公开(公告)号：US10711797B2
公开(公告)日：2020-07-14
申请号：US15625212
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades, each of the plurality of fan blades defining a fan blade span along a radial direction. The gas turbine engine further includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide varies attached to the outer nacelle at a location forward of the plurality of fan blades along an axial direction. Each of the plurality of inlet guide vanes defines an IGV span along the radial direction, the IGV span being at least about five percent of the fan blade span and up to about fifty-five percent of the fan blade span.
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公开(公告)号：US20200040821A1
公开(公告)日：2020-02-06
申请号：US16051877
申请日：2018-08-01
Applicant: General Electric Company
Inventor： Donald Scott Yeager , Brandon Wayne Miller
Abstract: A structure for damping at a fluid manifold assembly for an engine is generally provided. The fluid manifold assembly includes a first walled conduit defining a first fluid passage therewithin. A flow of fluid defining a first frequency is permitted through the first fluid passage. A second walled conduit includes a pair of first portions each coupled to the first walled conduit. A second portion is coupled to the pair of first portions. A second fluid passage is defined through the first portion and the second portion in fluid communication with the first fluid passage. The flow of fluid is permitted through the second fluid passage at a second frequency approximately 180 degrees out of phase from the first frequency.
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Patent Agency Ranking
公开(公告)号：US10519860B2
公开(公告)日：2019-12-31
申请号：US15451498
申请日：2017-03-07
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Alan Roy Stuart , Jeffrey Donald Clements , Brandon Wayne Miller , Darek Tomasz Zatorski
IPC: F01D25/16 , F02C7/06 , F02C3/067 , F01D5/06 , F01D1/24 , F01D11/00 , F02C7/28 , F02K3/072 , F01D25/18
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. The gas turbine engine defines an upstream end and a downstream end along the longitudinal direction and includes a turbine frame defined around the axial centerline. The turbine frame includes a first bearing surface, a second bearing surface, and a third bearing surface. The first bearing surface corresponds to a first turbine rotor, the second bearing surface corresponds to a second turbine rotor, and the third bearing surface corresponds to a third turbine rotor, and each turbine rotor is independently rotatable.
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公开(公告)号：US10443412B2
公开(公告)日：2019-10-15
申请号：US14838405
申请日：2015-08-28
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller
Abstract: A variable pitch fan for gas turbine engine is provided. The variable pitch fan includes a plurality of fan blades rotatably coupled to a disk and an actuation assembly for changing a pitch of each of the plurality of fan blades. The actuation assembly generally includes an actuation member operably connected to at least one of the plurality of fan blades and a pin. The pin is movable between a first position in which the pin is positioned at least partially in a channel defined in the actuation member, and a second position. The pin blocks movement of the actuation member relative to the pin past a range defined by the channel when in the first position. The actuation assembly further includes a retraction system for selectively engaging the pin in moving the pin from the first position to the second position.
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公开(公告)号：US10442541B2
公开(公告)日：2019-10-15
申请号：US14923062
申请日：2015-10-26
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice
Abstract: A propulsion system for an aircraft includes at least two propulsion engines. Each propulsion engine rotates about a longitudinal rotational axis, and a propulsive fan associated with each propulsion engine rotates in a plane perpendicular to the longitudinal rotational axis. Each plane is at least one of spaced axially along a fuselage of the aircraft and canted such that each plane does not intersect any other plane associated with another propulsion engine and propulsive fan.
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公开(公告)号：US20190203644A1
公开(公告)日：2019-07-04
申请号：US15861802
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Raymond Floyd Martell , Jeffrey Douglas Rambo , Ryan James Matthys , Joel Francis Kirk
CPC classification number: F02C7/143 , F01D5/085 , F01D9/065 , F01D25/12 , F02C3/06 , F02C7/12 , F02C7/185 , F02C7/22 , F05D2220/3216 , F05D2240/12 , F05D2260/201 , F05D2260/213 , F23R3/283
Abstract: A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.
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公开(公告)号：US20180298784A1
公开(公告)日：2018-10-18
申请号：US15485515
申请日：2017-04-12
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Alan Roy Stuart , Jeffrey Donald Clements , Brandon Wayne Miller , Darek Tomasz Zatorski , Gert Johannes van der Merwe , Joel Francis Kirk , Richard Wesling
CPC classification number: F01D25/183 , F01D25/162
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 wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction, and wherein the gas turbine engine defines a core flowpath extended generally along the longitudinal direction. The gas turbine engine includes a turbine frame defined around the axial centerline, the turbine frame comprising a first bearing surface disposed inward along the radial direction. The gas turbine engine further includes a turbine rotor assembly including a bearing assembly coupled to the first bearing surface of the turbine frame and the turbine rotor assembly. The turbine rotor assembly further includes a first turbine rotor disposed upstream of the turbine frame and a second turbine rotor disposed downstream of the turbine frame. The first turbine rotor and the second turbine rotor are rotatable together about the axial centerline.
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