-
公开(公告)号：US20180363678A1
公开(公告)日：2018-12-20
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
CPC classification number: F04D29/563 , F01D9/041 , F02C3/04 , F02C7/04 , F02K3/06 , F04D29/542 , F04D29/545 , F04D29/684 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2250/182 , F05D2250/184 , F05D2260/14
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.
-
公开(公告)号：US10113633B2
公开(公告)日：2018-10-30
申请号：US15008907
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
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. 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.
-
公开(公告)号：US10107200B2
公开(公告)日：2018-10-23
申请号：US14700172
申请日：2015-04-30
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Jeffrey Glover
Abstract: A gas turbine engine including core engine is provided. Air may enter the core engine through an inlet and travel through and engine air flowpath extending through the core engine, e.g., generally along an axial direction of the gas turbine engine. The gas turbine engine additionally includes a cooling air flowpath extending outwardly generally along the radial direction of the gas turbine engine. The cooling air flowpath extends between an inlet in flow communication with engine air flowpath and an outlet defined by an opening in an outer casing of the core engine. Moreover, the gas turbine engine includes a heat exchanger positioned at least partially within the outer casing the core engine with the cooling air flowpath extending over or through the heat exchanger.
-
公开(公告)号：US20180258858A1
公开(公告)日：2018-09-13
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
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.
-
公开(公告)号：US10071811B2
公开(公告)日：2018-09-11
申请号：US15242811
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Randy M. Vondrell , Paul Robert Gemin
CPC classification number: B64D27/12 , B64C21/06 , B64D27/18 , B64D27/24 , B64D29/04 , B64D33/00 , B64D2027/026 , B64D2033/0226 , B64D2221/00 , F01D9/065 , F01D15/10 , F01D25/162 , F02C3/04 , F02C7/16 , F02C7/32 , F02K5/00 , F04D25/06 , F05D2220/32 , F05D2220/76 , F05D2260/20 , F05D2260/98 , Y02T50/676
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. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.
-
Patent Agency Ranking
公开(公告)号：US20180138766A1
公开(公告)日：2018-05-17
申请号：US15354370
申请日：2016-11-17
Applicant: General Electric Company
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 supported by the rotor flange such that the rotor flange absorbs centrifugal loads exerted on the magnets and enables high speeds of operation.
-
公开(公告)号：US20180051702A1
公开(公告)日：2018-02-22
申请号：US15242811
申请日：2016-08-22
Applicant: General Electric Company
Inventor： Thomas Kupiszewski , Brandon Wayne Miller , Randy M. Vondrell , Paul Robert Gemin
CPC classification number: B64D27/12 , B64D27/18 , B64D27/24 , F01D9/065 , F01D15/10 , F01D25/162 , F02C3/04 , F02C7/16 , F02C7/32 , F02K5/00 , F04D25/06 , F05D2220/32 , F05D2220/76 , F05D2260/20 , F05D2260/98
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. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.
-
公开(公告)号：US20170342839A1
公开(公告)日：2017-11-30
申请号：US15164648
申请日：2016-05-25
Applicant: General Electric Company
CPC classification number: F01D1/10 , F01D5/06 , F01D5/141 , F01D9/041 , F01D25/24 , F02C3/107 , F02K3/06 , F05D2220/3215 , F05D2220/323 , F05D2240/35 , F05D2240/60 , Y02T50/671 , Y02T50/673
Abstract: The low pressure turbine includes a rotor, an outer casing, a plurality of stages of rotor blades, and a plurality of stages of stator vanes. The rotor includes a longitudinal centerline. The outer casing circumscribes the rotor. The plurality of stages of rotor blades is disposed on a radially outer surface of the rotor in a serial flow arrangement. The plurality of stages of stator vanes is disposed on a radially inner surface of the outer casing in a serial flow arrangement. Each stage of the plurality of stages of stator vanes precedes a stage of rotor blades. The last stage of rotor blades of the plurality of stages of rotor blades includes a low swirl outlet rotor blade stage.
-
公开(公告)号：US20170297727A1
公开(公告)日：2017-10-19
申请号：US15132298
申请日：2016-04-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
CPC classification number: B64D27/24 , B64D27/02 , B64D27/18 , B64D2027/026 , F02C3/04 , F02C7/20 , F02C7/36 , F02K3/04 , F05D2220/76 , Y10S903/905 , Y10S903/906 , Y10S903/907
Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.68×RFP−0.518, such that the propulsion engine may operate at a desired efficiency.
-
公开(公告)号：US20170284303A1
公开(公告)日：2017-10-05
申请号：US15083392
申请日：2016-03-29
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Brandon Wayne Miller , Craig Alan Gonyou
CPC classification number: F02C9/18 , B64D13/08 , F01D17/105 , F01D25/14 , F02C3/04 , F02C7/18 , F02K3/06 , F02K3/075 , F05D2220/323 , F05D2250/411 , F05D2260/213 , F05D2270/101 , F05D2270/112
Abstract: Axially adjacent annular booster bleed aft and forward plenums with annular common wall therebetween extend radially outwardly from transition duct. Variable bleed valve includes bleed valve door in bleed inlet in transition duct, attached to rotatable valve body rotatable about axis of rotation, operable to open and close bleed inlet to aft plenum. Rotatable plenum door clocked or circumferentially spaced apart from variable bleed valve door and attached to rotatable valve body, operable to close and open up and control flow through an inter plenum aperture in common wall. Aft and forward bleed exhaust ducts extend from booster bleed aft and forward plenums to bypass flow path. One or more heat exchanger, such as from thermal management system, may be disposed in the bleed exhaust ducts. Heat exchangers may be used for cooling oil for power gear box and/or engine bearings, air conditioning, or variable frequency generator.
-
-
-
-
-
-
-
-
-
Search Results
357
records
(took 0.041 seconds)
