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1. 发明公开

US20240344487A1 PROPULSION SYSTEM ARCHITECTURE 审中-公开
公开(公告)号：US20240344487A1
公开(公告)日：2024-10-17
申请号：US18675233
申请日：2024-05-28
申请人： General Electric Company
发明人： David Marion Ostdiek , Alan Roy Stuart , David Alan Niergarth , Gert Johannes van der Merwe , Brandon Wayne Miller , Stephen William Freund
IPC分类号： F02K3/072 , B64D27/10 , F02C3/073 , F02K1/34 , F02K3/02 , F02K3/075 , F02K3/077
CPC分类号： F02K3/072 , B64D27/10 , F02C3/073 , F02K1/34 , F02K3/025 , F02K3/075 , F02K3/077
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.

2. 发明授权

US11753939B2 Turbomachine with alternatingly spaced rotor blades 有权
公开(公告)号：US11753939B2
公开(公告)日：2023-09-12
申请号：US16280531
申请日：2019-02-20
申请人： General Electric Company
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.

3. 发明授权

US10830136B2 Fan case for use in a turbofan engine, and method of assembling a turbofan engine 有权
公开(公告)号：US10830136B2
公开(公告)日：2020-11-10
申请号：US14946404
申请日：2015-11-19
申请人： General Electric Company
发明人： Alan Roy Stuart
IPC分类号： F02C7/042 , F02C7/045 , F02K3/068 , B64D33/02 , B64D29/00 , F02K3/06
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.

4. 发明授权

US10815881B2 Counter rotating turbine with reversing speed reduction assembly 有权
公开(公告)号：US10815881B2
公开(公告)日：2020-10-27
申请号：US15709651
申请日：2017-09-20
申请人： General Electric Company
发明人： Jeffrey Donald Clements , Darek Tomasz Zatorski , Alan Roy Stuart
IPC分类号： F02C3/067 , F02K3/072 , F01D5/14 , F01D5/03 , F01D1/26 , F02K3/068 , F02C3/107 , F02C7/36
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.

5. 发明授权

US10669893B2 Air bearing and thermal management nozzle arrangement for interdigitated turbine engine 审中-公开
公开(公告)号：US10669893B2
公开(公告)日：2020-06-02
申请号：US15605351
申请日：2017-05-25
申请人： General Electric Company
发明人： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
IPC分类号： F01D25/22 , F01D5/08 , F02C7/06
摘要： The present disclosure is directed to a gas turbine engine defining a longitudinal direction, an axial centerline extended along the longitudinal direction, an upstream end and a downstream end opposite of the upstream end along the longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes a high speed turbine rotor coupled to a high pressure (HP) shaft and HP compressor, a low speed turbine rotor comprising an axially extended hub, and a first turbine bearing disposed radially between the low speed turbine rotor and the high speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit through the high speed turbine rotor. The low speed turbine rotor includes a rotating nozzle adjacent to the turbine cooling conduit. The first turbine bearing defines an outer air bearing and an inner air bearing. The first turbine bearing defines a stationary nozzle adjacent to the rotating nozzle of the first turbine rotor.

6. 发明申请

US20180362170A1 METHOD AND SYSTEM FOR MOUNTING AN AIRCRAFT ENGINE 审中-公开
公开(公告)号：US20180362170A1
公开(公告)日：2018-12-20
申请号：US15622290
申请日：2017-06-14
申请人： General Electric Company
发明人： Alan Roy Stuart , Thomas Ory Moniz , Jeffrey Donald Clements , Joseph George Rose
IPC分类号： B64D27/26 , B64D27/12 , B64D29/02
CPC分类号： B64D27/26 , B64D27/12 , B64D29/02 , B64D2027/266 , B64D2027/268
摘要： A system for mounting an engine to an aircraft includes an engine forward mount angled toward the forward end of the engine at a first angle. At least two thrust links extend between an engine aft mount to a link support connection at a second angle. The engine aft mount is angled toward the forward end of the engine at a third angle. A projection of a load vector of the engine forward mount onto a vertical plane extending through the axis of rotation of the engine and a projection of a load vector of each of the at least two thrust links onto the vertical plane intersect the axis of rotation of the engine within a first vertical plane segment extending between a forward end of a nose of a fan assembly and forward of a forward mount interface.

7. 发明申请

US20180340446A1 INTERDIGITATED TURBINE ENGINE AIR BEARING COOLING STRUCTURE AND METHOD OF THERMAL MANAGEMENT 审中-公开
公开(公告)号：US20180340446A1
公开(公告)日：2018-11-29
申请号：US15605225
申请日：2017-05-25
申请人： General Electric Company
发明人： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
IPC分类号： F01D25/12 , F02C3/04 , F01D25/16 , F01D5/06 , F01D9/04
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.

8. 发明申请

US20180209336A1 THREE SPOOL GAS TURBINE ENGINE WITH INTERDIGITATED TURBINE SECTION 审中-公开
公开(公告)号：US20180209336A1
公开(公告)日：2018-07-26
申请号：US15412175
申请日：2017-01-23
申请人： General Electric Company
发明人： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
IPC分类号： F02C3/06 , F02K3/06 , F02C7/06
摘要： 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 long the longitudinal direction. The gas turbine engine includes a turbine section including a low speed turbine rotor, a high speed turbine rotor, and an intermediate speed turbine rotor. The low speed turbine rotor 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 low speed turbine rotor further includes at least one connecting airfoil coupling the inner shroud to the outer shroud. The high speed turbine rotor is disposed upstream of the one or more connecting airfoils of the low speed turbine rotor along the longitudinal direction. The high speed turbine rotor includes a plurality of high speed turbine airfoils extended outward in the radial direction. The intermediate speed turbine rotor is disposed upstream of the one or more connecting airfoils of the low speed turbine rotor along the longitudinal direction. The intermediate speed turbine rotor includes a plurality of intermediate speed turbine airfoils extended outward in the radial direction. The intermediate speed turbine rotor is disposed among the plurality of outer shroud airfoils of the low speed turbine rotor along the longitudinal direction.

9. 发明申请

US20170145916A1 FAN CASE FOR USE IN A TURBOFAN ENGINE, AND METHOD OF ASSEMBLING A TURBOFAN ENGINE 审中-公开
公开(公告)号：US20170145916A1
公开(公告)日：2017-05-25
申请号：US14946404
申请日：2015-11-19
申请人： General Electric Company
发明人： Alan Roy Stuart
IPC分类号： F02C7/042 , F02C7/045 , F02K3/06
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.

10. 发明申请

US20140119885A1 TURBINE ENGINE ASSEMBLY AND METHODS OF ASSEMBLING SAME 有权
标题翻译：涡轮发动机总成及组装方法
公开(公告)号：US20140119885A1
公开(公告)日：2014-05-01
申请号：US14149511
申请日：2014-01-07
申请人： General Electric Company
发明人： Robert Joseph Orlando , Thomas Ory Moniz , Alan Roy Stuart
IPC分类号： F02K3/072
CPC分类号： F02K3/072 , F02C7/36 , F05D2220/323 , F05D2220/327 , Y10T29/49229
摘要： A turbine engine assembly is provided. The turbine engine assembly includes a core gas turbine engine including a first rotatable drive shaft, a first low-pressure turbine section in serial flow communication with the gas turbine engine, a gear assembly coupled to the first low-pressure turbine section through a second rotatable drive shaft, and a second low-pressure turbine section in serial flow communication with the core gas turbine engine. The first low-pressure turbine section is configured to rotate in a first rotational direction, and the second low-pressure turbine section is configured to rotate in a second rotational direction opposite the first rotational direction. The first and second low-pressure turbine sections are spaced axially apart from each other. The turbine engine assembly also includes a fan assembly coupled to the first low-pressure turbine section through the gear assembly, and coupled to the second low-pressure turbine section through a third rotatable drive shaft.
摘要翻译：提供涡轮发动机组件。涡轮发动机组件包括核心燃气涡轮发动机，其包括第一可旋转驱动轴，与燃气涡轮发动机串联流动连接的第一低压涡轮机部分，通过第二可旋转的驱动轴和与核心燃气涡轮发动机串联流动连通的第二低压涡轮部分。第一低压涡轮部分构造成沿第一旋转方向旋转，并且第二低压涡轮部分构造成沿与第一旋转方向相反的第二旋转方向旋转。第一和第二低压涡轮机部分彼此轴向间隔开。涡轮发动机组件还包括通过齿轮组件联接到第一低压涡轮机部分并通过第三可旋转驱动轴联接到第二低压涡轮机部分的风扇组件。

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