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公开(公告)号：US20200256253A1
公开(公告)日：2020-08-13
申请号：US16271213
申请日：2019-02-08
IPC分类号： F02C7/24
摘要： A gas turbine engine system includes a gas turbine engine, a temperature-sensitive component, and a thermal protection structure. The gas turbine engine has an engine core that generates heat while operational and for a period after operation. The temperature-sensitive component is disposed at a component location proximate the engine core. The thermal protection structure is interposed between the temperature-sensitive component and the gas turbine-engine, and includes a phase change material (PCM) layer disposed to absorb a transient heat spike from the engine core.
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公开(公告)号：US20180065754A1
公开(公告)日：2018-03-08
申请号：US15258927
申请日：2016-09-07
CPC分类号： B64D29/06 , B64D27/16 , F01D25/24 , F02K1/56 , F02K1/72 , F02K1/763 , F05D2220/323 , F05D2230/60 , F05D2260/50 , F16C11/045 , F16C2360/23 , Y02T50/672
摘要： A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a base member, and a retaining member at least partially defining a first aperture and a cavity. The pivot is configured to extend at least partially into the first aperture. The cavity is configured to accommodate a portion of the link arm.
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公开(公告)号：US20180051715A1
公开(公告)日：2018-02-22
申请号：US15239869
申请日：2016-08-18
摘要： A fan duct seal for a gas turbine engine has at least one seal body with a hollow center. A first opening is formed in the seal body that is in fluid communication with the hollow center. The first opening is configured to receive fan air flow. A second opening is formed in the seal body that is in fluid communication with the hollow center such that cooling flow enters the first opening, moves through the seal body and exits from the second opening. A fan duct for a gas turbine engine and a method of cooling a fan duct seal assembly are also disclosed.
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公开(公告)号：US20150369078A1
公开(公告)日：2015-12-24
申请号：US14765037
申请日：2014-02-27
CPC分类号： F01D17/14 , F01D9/04 , F01D25/24 , F02K1/09 , F02K1/1261 , F02K1/15 , F02K1/70 , F02K1/72 , F02K1/763 , F02K3/075 , F05D2220/32 , F05D2270/62 , F05D2270/64 , F05D2270/65
摘要： A gas turbine engine includes a nacelle assembly having a core nacelle defined about an engine axis and a fan nacelle assembly mounted at least partially around the core nacelle to define a fan bypass flow path. The fan nacelle assembly includes a fan duct nacelle section and a fan nozzle nacelle section moveable relative to the fan duct nacelle section. A thrust reverser system includes a plurality of pivot doors movable relative to the fan nacelle assembly between stowed and deployed positions. A variable area fan nozzle is in communication with the fan bypass flow path. A first actuator is mounted to the fan duct nacelle section to actuate the pivot door thrust reverser system, and a second actuator is mounted to the fan duct nacelle section to move the fan nozzle nacelle section relative to the fan duct nacelle section to vary a fan nozzle exit area.
摘要翻译： 燃气涡轮发动机包括具有围绕发动机轴线限定的核心机舱的机舱组件和至少部分地安装在核心机舱周围的风扇机舱组件，以限定风扇旁路流动路径。 风扇机舱组件包括风扇管道机舱部分和相对于风扇管道机舱部分可移动的风扇喷嘴机舱部分。 推力反向器系统包括在收起和展开位置之间可相对于风扇机舱组件移动的多个枢轴门。 可变区域风扇喷嘴与风扇旁路流路连通。 第一致动器安装到风扇管道机舱部分以致动枢转门推力反向器系统，并且第二致动器安装到风扇管道机舱部分以相对于风扇管道机舱部分移动风扇喷嘴机舱部分以改变风扇 喷嘴出口区域。
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公开(公告)号：US10570852B2
公开(公告)日：2020-02-25
申请号：US15711229
申请日：2017-09-21
摘要： An exhaust section of a gas turbine engine includes an exhaust plug defining a plurality of exhaust plug apertures circumferentially spaced from each other. Also included is an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. Further included is an exhaust plug liner having a non-uniform outer surface axially aligned with the exhaust plug apertures. The exhaust plug liner is rotatable relative to the exhaust plug between a first position and a second position to selectively change a cross-sectional area of the exhaust pathway during thrust reversal operation to reduce an amount of reverse thrust necessary.
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公开(公告)号：US10371051B2
公开(公告)日：2019-08-06
申请号：US14766825
申请日：2014-02-13
摘要： A fan section for a gas turbine engine includes a fan hub and a nose cone section operatively mounted to the fan hub. The nose cone section includes a noise attenuation feature.
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公开(公告)号：US10066510B2
公开(公告)日：2018-09-04
申请号：US14769915
申请日：2014-03-13
摘要： A nacelle for a gas turbine engine includes a upper and lower bifurcations, an inner diameter cowl and a first latch system. The inner diameter cowl extends between the upper and lower bifurcations and the first latch system is mounted on the inner diameter cowl. The first latch system is spaced along the inner diameter cowl between the upper and lower bifurcations.
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公开(公告)号：US20170175766A1
公开(公告)日：2017-06-22
申请号：US14974195
申请日：2015-12-18
摘要： A gas turbine engine comprises a nacelle that encloses a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle is rotatable such that a circumferential location of the one portion and the other portion may be varied dependent on flight conditions. A method of operating a gas turbine engine is also disclosed.
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公开(公告)号：US09670877B2
公开(公告)日：2017-06-06
申请号：US14320829
申请日：2014-07-01
CPC分类号： F02K1/763 , F02K1/72 , Y02T50/672
摘要： A flowpath channel has a blade pivotally connected along a longitudinal axis thereof, at opposing top and bottom ends thereof, to respective top and bottom portions of the flowpath channel. The chord axis of the blade, between leading and trailing edges thereof, is capable of pivoting parallel to and skewed from the flowpath. The top end of the blade and an attachment structure secured to the flowpath channel each include a race. A bearing is disposed therebetween, and the blade is rotatable about the longitudinal axis.
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公开(公告)号：US20160169157A1
公开(公告)日：2016-06-16
申请号：US14970214
申请日：2015-12-15
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , F02K1/763 , F05D2260/56 , Y02T50/672
摘要： The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct by means of a camming surface, thereby diverting air in the fan duct through the cascade. In the stowed position, both the cascade and the blocker door are disposed radially outward of a radially inner wall of the nacelle and/or the translating cowl.
摘要翻译： 本公开总体上涉及一种用于燃气涡轮发动机的推力反向器。 当平移的整流罩从燃气涡轮发动机的机舱翻转后方时，在后方向上也平移了级联，并且通过凸轮表面将联接到级联的阻挡门转动到风扇管道中，从而将空气 风扇管通过级联。 在收起位置中，级联和阻塞门均位于机舱的径向内壁和/或平移罩的径向外侧。
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