-
公开(公告)号：US20190218973A1
公开(公告)日：2019-07-18
申请号：US16360329
申请日：2019-03-21
IPC分类号： F02C7/18 , F02K3/105 , F02C7/32 , F02C7/12 , F02K3/115 , F02K3/077 , B64D33/10 , F01D25/14 , F02C7/14 , F01D25/08 , B64D33/08 , B64D33/12
CPC分类号： F02C7/185 , B64D33/08 , B64D33/10 , B64D33/12 , B64D2033/024 , F01D25/08 , F01D25/14 , F02C7/12 , F02C7/14 , F02C7/32 , F02K3/077 , F02K3/105 , F02K3/115 , F05D2260/20 , F05D2260/213 , F28D2021/0021 , F28D2021/0026 , Y02T50/675
摘要： A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.
-
2.发明授权公开(公告)号：US10082040B2
公开(公告)日：2018-09-25
申请号：US15745704
申请日：2016-07-21
IPC分类号： F01D17/14 , B64D27/20 , F02K3/072 , F02K3/12 , F01D17/16 , B64D27/14 , F01D1/02 , B64C11/48 , F01D1/24 , F02K3/075 , F02K3/077 , F01D17/10
CPC分类号： F01D17/141 , B64C11/48 , B64D27/14 , B64D27/20 , F01D1/023 , F01D1/24 , F01D17/105 , F01D17/14 , F01D17/145 , F01D17/148 , F01D17/16 , F01D17/162 , F01D17/167 , F02C3/10 , F02K1/52 , F02K3/072 , F02K3/075 , F02K3/077 , F02K3/12 , F05D2220/323 , F05D2240/128 , F05D2260/606 , F05D2270/093 , F05D2270/102
摘要： The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).
-
公开(公告)号：US10072584B2
公开(公告)日：2018-09-11
申请号：US14534318
申请日：2014-11-06
发明人： Michael R. Thomas , Nathan Snape
IPC分类号： F02K3/077 , F02C9/18 , F02K3/00 , F02C7/141 , F02C7/32 , F02K3/02 , F02C7/14 , F02K3/04 , F02C7/18
CPC分类号： F02C9/18 , F02C7/14 , F02C7/141 , F02C7/185 , F02C7/32 , F02K3/00 , F02K3/02 , F02K3/025 , F02K3/04 , F02K3/077
摘要： A gas turbine engine comprises a first bypass flow path housing configured within the engine, radially exterior to an engine core housing, and a second bypass flow path housing configured within the engine, radially exterior to the first bypass flow path housing. An axially downstream portion of the first bypass flow path housing includes a stepwise increase in area compared with an axially adjacent upstream portion of the first bypass flow path housing, thereby defining a component placement cavity in the axially downstream portion.
-
公开(公告)号：US10001084B2
公开(公告)日：2018-06-19
申请号：US13523315
申请日：2012-06-14
CPC分类号： F02K3/077 , F02C7/18 , F02K3/115 , Y02T50/675
摘要： A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat area for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.
-
公开(公告)号：US09957823B2
公开(公告)日：2018-05-01
申请号：US14604228
申请日：2015-01-23
发明人： Alan H. Epstein
IPC分类号： F01D1/02 , F01D5/22 , F01D9/04 , F01D17/16 , F02C9/20 , F02K3/075 , F02K3/077 , F04D29/56 , F01D5/14
CPC分类号： F01D9/041 , F01D1/023 , F01D5/148 , F01D5/225 , F01D17/162 , F02C9/20 , F02K3/075 , F02K3/077 , F04D29/563 , Y02T50/673
摘要： A gas turbine engine is provided that includes a core flow path to direct a core stream flow. A common flow path is outboard of the core flow path, where the common flow path directs both a second stream flow and a third stream flow. Another gas turbine engine is provided that includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is inboard of the outer case structure, where the intermediate case structure and the outer case structure direct both a third stream flow and a second stream flow. An inner case structure is inboard of the intermediate case structure, where the inner case structure and the intermediate case structure direct a core stream flow.
-
公开(公告)号：US09909506B2
公开(公告)日：2018-03-06
申请号：US14759979
申请日：2013-01-28
IPC分类号： F02C9/18 , F02K3/10 , F02K3/077 , F01D1/04 , F02K1/78 , F02K3/075 , F02C3/04 , F02C3/14 , F02C7/08 , F02K3/02
CPC分类号： F02C9/18 , F01D1/04 , F02C3/04 , F02C3/145 , F02C7/08 , F02K1/78 , F02K3/025 , F02K3/075 , F02K3/077 , F02K3/10 , F05D2220/32 , F05D2250/31
摘要： A gas turbine engine has a fan rotor for delivering air axially downstream into a core engine duct, which sequentially passes a turbine, a combustor, and a compressor. The core engine duct extends to a turning supply duct configured to turn the core air flow axially upstream so that the core air sequentially passes through the compressor, combustor and turbine, and into an exhaust conduit which turns the core airflow radially outwardly and axially downstream into an exhaust duct. A door is selectively opened to communicate a portion of the core airflow in the core engine duct to an augmentor with the exhaust duct isolated from the augmentor. The door is at a location prior to the core airflow reaching the compressor. A method is also disclosed.
-
公开(公告)号：US09878796B2
公开(公告)日：2018-01-30
申请号：US14620259
申请日：2015-02-12
发明人： William G. Sheridan
CPC分类号： B64D27/24 , B64D35/02 , B64D35/04 , B64D2027/026 , F01D15/12 , F02C7/36 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312 , F05D2260/4023 , F05D2260/4031 , Y02T50/62 , Y10S903/903
摘要： A gas turbine engine has a fan drive turbine for selectively driving a fan rotor. A drive shaft between the fan drive turbine and the fan rotor includes a clutch, and an electric motor. The electric motor is positioned such that it is not downstream of a flow path relative to the fan drive turbine. A method of operating a gas turbine engine is also disclosed.
-
公开(公告)号：US20170314509A1
公开(公告)日：2017-11-02
申请号：US15140079
申请日：2016-04-27
CPC分类号： F02K3/062 , F01D5/022 , F02C3/04 , F02C3/13 , F02K1/386 , F02K3/065 , F02K3/075 , F02K3/077 , F05D2220/32 , F05D2230/60 , Y02T50/673
摘要： A turbofan assembly that includes a primary turbine section and an aft fan section positioned downstream from the primary turbine section. The primary turbine section includes a bypass duct configured to channel a stream of bypass air therethrough, and a main flow duct configured to discharge a stream of exhaust gas therefrom. The bypass duct and the main flow duct each include a discharge end positioned such that a mixed stream of bypass air and exhaust gas is discharged from the primary turbine section. The aft fan section includes at least one turbine and fan stage including a turbine portion and a fan portion coupled to the turbine portion. The turbine portion is positioned to receive the mixed stream of bypass air and exhaust gas, and the fan portion is positioned radially outward from the turbine portion.
-
公开(公告)号：US20170306842A1
公开(公告)日：2017-10-26
申请号：US15443113
申请日：2017-02-27
发明人： Gabriel L. Suciu , Michael E. McCune , Jesse M. Chandler , Alan H. Epstein , Steven M. O'Flarity , Christopher J. Hanlon , William F. Schneider , Joseph B. Staubach , James A. Kenyon
IPC分类号： F02C3/107 , B64D35/04 , F01D13/00 , F02C3/067 , F02K3/077 , B64D27/18 , F02C7/36 , F02C9/18 , F02C3/06
CPC分类号： F02C3/107 , B64D27/18 , B64D35/04 , F01D13/003 , F02C3/06 , F02C3/067 , F02C7/36 , F02C9/18 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312
摘要： A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.
-
公开(公告)号：US09777631B2
公开(公告)日：2017-10-03
申请号：US13251139
申请日：2011-09-30
IPC分类号： F02C7/04
CPC分类号： F02C7/04 , F02K3/075 , F02K3/077 , Y02T50/671 , Y10T137/0536
摘要： An inlet apparatus for a gas turbine engine includes: a fan duct adapted to surround at least one row of rotating fan blades, the fan duct having a circular frontal area, and defining a first inlet plane; and an outer duct surrounding the fan duct, the outer duct including: a first frontal area shape at the first inlet plane which defines, cooperatively with an exterior of the fan duct, at least one lobe through which air can pass; and a second frontal area shape at a second inlet plane located axially downstream from the forward end which is circular, and which defines, cooperatively with an exterior of the fan duct, an annulus through which air can pass.
-
-
-
-
-
-
-
-
-
搜索结果
284 条记录 (耗时 0.02 秒)