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公开(公告)号：US11105269B2
公开(公告)日：2021-08-31
申请号：US15593748
申请日：2017-05-12
发明人： Thomas Ory Moniz , Alan Roy Stuart , James William Simunek , Jeffrey Donald Clements , Brandon Wayne Miller , Sridhar Adibhatla
IPC分类号： F02C9/48 , F02C9/20 , F02C7/36 , F02C7/22 , F04D29/56 , F01D5/03 , F04D27/00 , F02C9/28 , F02C3/067
摘要： The present disclosure is directed to a method of control of a gas turbine engine comprising a fan section coupled to a low turbine together defining a low spool, an intermediate compressor coupled to an intermediate turbine together defining an intermediate spool, and a high compressor coupled to a high turbine together defining a high spool. The method includes providing an intermediate spool speed to low spool speed characteristic curve to a controller; providing a commanded power output to the controller; providing one or more of an environmental condition to the controller; determining, via the controller, a commanded fuel flow rate; determining, via the controller, a commanded intermediate compressor loading; and generating an actual power output of the engine, wherein the actual power output is one or more of an actual low spool speed, an actual intermediate spool speed, an actual high spool speed, and an actual engine pressure ratio.
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公开(公告)号：US20200263547A1
公开(公告)日：2020-08-20
申请号：US16280531
申请日：2019-02-20
发明人： Alan Roy Stuart , Tsuguji Nakano , Thomas Ory Moniz , Andrew Breeze-Stringfellow , Richard Schmidt
IPC分类号： F01D5/06
摘要： A gas turbine engine is provided including a turbine section including a turbine having a plurality of first speed turbine rotor blades; a compressor section including a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades; a gearbox; and a first spool rotatable by the plurality of first speed turbine rotor blades, the first spool coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades in a first direction and to the plurality of second speed compressor rotor blades across the gearbox for driving the plurality of second speed compressor rotor blades in a second direction, opposite the first direction.
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3.发明授权公开(公告)号：US10605168B2
公开(公告)日：2020-03-31
申请号：US15605225
申请日：2017-05-25
IPC分类号： F02C7/06 , F01D25/22 , F01D5/08 , F02C7/18 , F16C32/06 , F01D25/16 , F02C3/067 , F01D1/26 , F01D25/12
摘要： The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor including a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor including a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; and a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit extended within the high speed turbine rotor. The first turbine bearing defines an outer air bearing along an outer diameter of the first turbine bearing and adjacent to the hub of the low speed turbine rotor. The first turbine bearing defines an inner air bearing along an inner diameter of the first turbine bearing and adjacent to the HP shaft. The first turbine bearing further defines a cooling orifice adjacent along the longitudinal direction to the turbine cooling conduit of the high speed turbine rotor. The cooling orifice and the turbine cooling conduit are in fluid communication.
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公开(公告)号：US10539020B2
公开(公告)日：2020-01-21
申请号：US15412157
申请日：2017-01-23
摘要： The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section that includes a first rotating component and a second rotating component. The first rotating component includes an inner shroud and an outer shroud outward of the inner shroud in the radial direction. The outer shroud defines a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction. The first rotating component further includes at least one connecting airfoil coupling the inner shroud and the outer shroud. The second rotating component is upstream of the one or more connecting airfoils of the first rotating component along the longitudinal direction. The second rotating component includes a plurality of second airfoils extended outward in the radial direction. The first rotating component defines at least one stage of the plurality of outer shroud airfoils upstream of the second rotating component.
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公开(公告)号：US10465606B2
公开(公告)日：2019-11-05
申请号：US15427324
申请日：2017-02-08
摘要： The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section, a gearbox proximate to the turbine section, and a driveshaft. The turbine section includes a first rotating component interdigitated with a second rotating component along the longitudinal direction. The first rotating component includes an outer shroud defining a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction and one or more connecting airfoils coupling the outer shroud to a radially extended rotor. The second rotating component includes an inner shroud defining a plurality of inner shroud airfoils extended outward of the inner shroud along the radial direction. The second rotating component is coupled to an input shaft connected to an input gear of the gearbox. The driveshaft is extended in the longitudinal direction and is connected to an output gear of the gearbox. The first rotating component is coupled to the driveshaft.
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公开(公告)号：US10247137B2
公开(公告)日：2019-04-02
申请号：US14908557
申请日：2014-07-30
发明人： Alan Roy Stuart
IPC分类号： F02K1/72
摘要： A thrust reverser system suitable for a high-bypass turbofan engine of a type having a nacelle. The thrust reverser system includes a transcowl having a stowed, deployed and open positions. A hinge assembly translationally and rotationally couples the transcowl to a fixed structure that does not translate when the transcowl is translated in the aft direction. The hinge assembly includes a first member connected to the transcowl for translation therewith, and a fixed second member that defines a channel in which a portion of the first member is slidably received. The first and second members are configured to enable the portion of the first member to translate within the slider channel in an aft direction corresponding to a translational movement of the transcowl, and to enable the portion of the first member to rotate within the channel corresponding to a pivotal movement of the transcowl.
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公开(公告)号：US20190085766A1
公开(公告)日：2019-03-21
申请号：US15709651
申请日：2017-09-20
CPC分类号： F02C3/067 , F01D1/26 , F01D5/03 , F01D5/142 , F02C3/107 , F02C7/36 , F02K3/068 , F02K3/072 , F05D2250/44 , F05D2250/80 , F05D2260/40311 , F05D2270/051
摘要： The present disclosure is directed to a gas turbine engine including a turbine section including a first rotating component interdigitated along a longitudinal direction with a second rotating component. The first rotating component and the second rotating component are each coupled to a speed reduction assembly in counter-rotating arrangement. The first rotating component comprising an outer shroud and a plurality of outer shroud airfoils extended inward along a radial direction from the outer shroud. A connecting member couples the outer shroud to a radially extended first rotor. The second rotating component comprising an inner shroud and a plurality of inner shroud airfoils extended outward along the radial direction from the inner shroud, the plurality of inner shroud airfoils in alternating arrangement along the longitudinal direction with the plurality of outer shroud airfoils. The gas turbine engine defines a radius per unit thrust defined by a maximum radius at the turbine section over a maximum thrust output between approximately 0.0004 to approximately 0.0010 inches per pound thrust.
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公开(公告)号：US20240344487A1
公开(公告)日：2024-10-17
申请号：US18675233
申请日：2024-05-28
发明人： David Marion Ostdiek , Alan Roy Stuart , David Alan Niergarth , Gert Johannes van der Merwe , Brandon Wayne Miller , Stephen William Freund
摘要： A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.
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公开(公告)号：US11753939B2
公开(公告)日：2023-09-12
申请号：US16280531
申请日：2019-02-20
发明人： Alan Roy Stuart , Tsuguji Nakano , Thomas Ory Moniz , Andrew Breeze-Stringfellow , Richard Schmidt
IPC分类号： F01D5/06
CPC分类号： F01D5/06 , F05D2220/32
摘要： A gas turbine engine is provided including a turbine section including a turbine having a plurality of first speed turbine rotor blades; a compressor section including a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades; a gearbox; and a first spool rotatable by the plurality of first speed turbine rotor blades, the first spool coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades in a first direction and to the plurality of second speed compressor rotor blades across the gearbox for driving the plurality of second speed compressor rotor blades in a second direction, opposite the first direction.
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公开(公告)号：US10830136B2
公开(公告)日：2020-11-10
申请号：US14946404
申请日：2015-11-19
发明人： Alan Roy Stuart
摘要： A fan case for use in a turbofan engine is provided. The fan case includes an aft portion having a substantially cylindrical cross-sectional shape, and a forward portion extending from the aft portion. A cross-sectional shape of the forward portion progressively decreases in radial size as the forward portion extends from the aft portion.
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