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公开(公告)号：US20150367949A1
公开(公告)日：2015-12-24
申请号：US14764375
申请日：2013-01-29
Applicant: United Technologies Corporation
Inventor： Matthew J. Forcier
Abstract: A gas turbine engine includes an engine core, a core cowl extending circumferentially around the engine core, and a pressure actuated latch assembly. The core cowl includes a first cowl section on a first side of the engine core and a second cowl section on a second side of the engine core. The pressure actuated latch assembly connects the first cowl section to a support structure and is actuatable between an unlatched position when pressure within the core cowl is relatively low and a latched position when pressure within the core cowl is relatively high.
Abstract translation: 燃气涡轮发动机包括发动机芯，围绕发动机芯周向延伸的芯套，以及压力驱动的闩锁组件。 核心罩包括在发动机芯的第一侧上的第一整流罩部分和在发动机芯的第二侧上的第二整流罩部分。 压力致动的闩锁组件将第一整流罩部分连接到支撑结构，并且可以在内芯前罩内的压力相对较低时的解锁位置和当芯外罩内的压力相对较高时的锁定位置之间致动。
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公开(公告)号：US10697323B2
公开(公告)日：2020-06-30
申请号：US15216180
申请日：2016-07-21
Applicant: United Technologies Corporation
Inventor： Matthew J. Forcier
IPC: F01D25/16 , F16C19/16 , F16C33/66 , F16C35/04 , F04D29/059 , F16C35/077 , F01D25/18 , F02C3/04 , F02C7/06
Abstract: Aspects of the disclosure are directed to an engine oil damper comprising: a bearing support, and a housing radially outward from the bearing support and co-axial with the bearing support, where at least one oil flow restrictor is formed with respect to at least one of the bearing support and the housing, where the at least one oil flow restrictor is configured to at least partially interrupt a flow of oil in an annulus radially defined between the bearing support and the housing.
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公开(公告)号：US20150308292A1
公开(公告)日：2015-10-29
申请号：US14647838
申请日：2013-01-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew J. Forcier
CPC classification number: F01D25/28 , B64D29/06 , F01D25/24 , F05D2220/32
Abstract: A core cowl for use with an engine core of a gas turbine engine includes a first cowl section for covering a first side of an engine core and a second cowl section for covering a second side of the engine core. A locking retractor connects the first cowl section to a support structure.
Abstract translation: 用于燃气涡轮发动机的发动机核心的核心罩包括用于覆盖发动机芯的第一侧的第一整流罩部分和用于覆盖发动机芯的第二侧的第二整流罩部分。 锁定牵开器将第一整流罩部分连接到支撑结构。
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Patent Agency Ranking
公开(公告)号：US20180023418A1
公开(公告)日：2018-01-25
申请号：US15216180
申请日：2016-07-21
Applicant: United Technologies Corporation
Inventor： Matthew J. Forcier
Abstract: Aspects of the disclosure are directed to an engine oil damper comprising: a bearing support, and a housing radially outward from the bearing support and co-axial with the bearing support, where at least one oil flow restrictor is formed with respect to at least one of the bearing support and the housing, where the at least one oil flow restrictor is configured to at least partially interrupt a flow of oil in an annulus radially defined between the bearing support and the housing.
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公开(公告)号：US09845708B2
公开(公告)日：2017-12-19
申请号：US14647838
申请日：2013-01-29
Applicant: United Technologies Corporation
Inventor： Matthew J. Forcier
CPC classification number: F01D25/28 , B64D29/06 , F01D25/24 , F05D2220/32
Abstract: A core cowl for use with an engine core of a gas turbine engine includes a first cowl section for covering a first side of an engine core and a second cowl section for covering a second side of the engine core. A locking retractor connects the first cowl section to a support structure.
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公开(公告)号：US10094286B2
公开(公告)日：2018-10-09
申请号：US14647844
申请日：2013-01-29
Applicant: United Technologies Corporation
Inventor： Matthew J. Forcier
Abstract: A gas turbine engine includes a nacelle, a lower bifurcation structure, and a heat exchanger. The nacelle extends circumferentially around an engine core and defines a fan bypass duct that is substantially annular between an inner wall and an outer wall. The lower bifurcation structure extends between the inner wall and the outer wall, bifurcating the fan bypass duct. The lower bifurcation structure defines a bifurcation duct extending along a central axis of the lower bifurcation structure. A heat exchanger is positioned in the bifurcation duct.
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公开(公告)号：US09376215B2
公开(公告)日：2016-06-28
申请号：US14764375
申请日：2013-01-29
Applicant: United Technologies Corporation
Inventor： Matthew J. Forcier
Abstract: A gas turbine engine includes an engine core, a core cowl extending circumferentially around the engine core, and a pressure actuated latch assembly. The core cowl includes a first cowl section on a first side of the engine core and a second cowl section on a second side of the engine core. The pressure actuated latch assembly connects the first cowl section to a support structure and is actuatable between an unlatched position when pressure within the core cowl is relatively low and a latched position when pressure within the core cowl is relatively high.
Abstract translation: 燃气涡轮发动机包括发动机芯，围绕发动机芯周向延伸的芯套，以及压力驱动的闩锁组件。 核心罩包括在发动机芯的第一侧上的第一整流罩部分和在发动机芯的第二侧上的第二整流罩部分。 压力致动的闩锁组件将第一整流罩部分连接到支撑结构，并且可以在内芯前罩内的压力相对较低时的解锁位置和当芯外罩内的压力相对较高时的锁定位置之间致动。
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公开(公告)号：US20150308339A1
公开(公告)日：2015-10-29
申请号：US14647844
申请日：2013-01-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew J. Forcier
IPC: F02C7/141
CPC classification number: F02C7/141 , F01D25/24 , F02C7/14 , F02C7/32 , F02K3/115 , F05D2230/72 , F05D2260/213 , Y02T50/675
Abstract: A gas turbine engine includes a nacelle, a lower bifurcation structure, and a heat exchanger. The nacelle extends circumferentially around an engine core and defines a fan bypass duct that is substantially annular between an inner wall and an outer wall. The lower bifurcation structure extends between the inner wall and the outer wall, bifurcating the fan bypass duct. The lower bifurcation structure defines a bifurcation duct extending along a central axis of the lower bifurcation structure. A heat exchanger is positioned in the bifurcation duct.
Abstract translation: 燃气涡轮发动机包括机舱，下分叉结构和热交换器。 机舱围绕发动机核心周向延伸并且限定了在内壁和外壁之间基本上环形的风扇旁路管道。 下分叉结构在内壁和外壁之间延伸，将风扇旁路管道分叉。 下分叉结构定义了沿着下分叉结构的中心轴延伸的分叉管。 热交换器位于分叉管中。
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