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公开(公告)号：US10539156B2
公开(公告)日：2020-01-21
申请号：US15452641
申请日：2017-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj , Glenn Levasseur
Abstract: Disclosed is a flutter damper, including a chamber having an internal space, a movable diaphragm disposed at least partially within the chamber, the diaphragm separating the chamber into a first chamber and a second chamber, the second chamber forming an acoustic volume, wherein a size of the acoustic volume configures the chamber for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and a biasing member that moves the diaphragm responsive to a signal from an aircraft or engine electronic control (EEC) unit, wherein movement of the diaphragm increases or reduces the size of the acoustic volume of the second chamber.
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公开(公告)号：US20140076998A1
公开(公告)日：2014-03-20
申请号：US13622526
申请日：2012-09-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj
IPC: F02K1/76
Abstract: A nacelle assembly includes a thrust reverser moveable between a stowed position and a deployed position, a variable area fan nozzle, a motor to move the variable area fan nozzle, a drive shaft including a first portion coupled to the motor and a second portion coupled to the variable area fan nozzle, and a clutch mechanism that couples the first portion of the drive shaft and the second portion of the drive shaft The first portion of the drive shaft decouples from the second portion of the drive shaft when the thrust reverser moves from the stowed position to the deployed position.
Abstract translation: 机舱组件包括可在收起位置和展开位置之间移动的推力反向器，可变区域风扇喷嘴，移动可变区域风扇喷嘴的电动机，包括联接到电动机的第一部分的驱动轴和耦合到 可变区域风扇喷嘴以及耦合驱动轴的第一部分和驱动轴的第二部分的离合器机构当推力反向器从驱动轴移动时驱动轴的第一部分与驱动轴的第二部分分离 收起位置到部署位置。
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公开(公告)号：US10519859B2
公开(公告)日：2019-12-31
申请号：US15452604
申请日：2017-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj , Bruce L. Morin , Mani Sadeghi , Daniel L. Gysling
Abstract: Disclosed is a flutter damper, including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner being configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber being in fluid communication with the acoustic liner, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and at least one stiffening structure connected to a top surface of the chamber that tunes the top surface out of the frequency range associated with one or more fan flutter modes.
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公开(公告)号：US20180149083A1
公开(公告)日：2018-05-31
申请号：US15365466
申请日：2016-11-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj
CPC classification number: F02C7/045 , F02K3/06 , F05D2220/32 , F05D2220/323 , F05D2260/96 , F05D2270/333 , G10K11/172 , Y02T50/671
Abstract: A gas turbine engine may include at least one of a fan inlet case and a bypass duct case. Additionally, the gas turbine engine may include a variable volume acoustic damper coupled to the at least one of the fan inlet case and the bypass duct case, wherein the variable volume acoustic damper is configured to damp acoustic energy. The variable volume acoustic damper may include a case and a diaphragm movably coupled within the case. An acoustic volume may be defined by a position of the diaphragm relative to the case and the acoustic volume may correspond to and may be configured to damp acoustic energy of a gas turbine engine.
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公开(公告)号：US20180258853A1
公开(公告)日：2018-09-13
申请号：US15452604
申请日：2017-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj , Bruce L. Morin , Mani Sadeghi , Daniel L. Gysling
CPC classification number: F02C7/045 , B64D2033/0206 , F01D25/04 , F01D25/24 , F02K1/827 , F02K3/06 , F05D2220/323 , F05D2260/96 , F05D2260/963 , G10K11/172 , Y02T50/672
Abstract: Disclosed is a flutter damper, including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner being configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber being in fluid communication with the acoustic liner, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and at least one stiffening structure connected to a top surface of the chamber that tunes the top surface out of the frequency range associated with one or more fan flutter modes.
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Patent Agency Ranking
公开(公告)号：US20160160758A1
公开(公告)日：2016-06-09
申请号：US14947174
申请日：2015-11-20
Applicant: United Technologies Corporation
Inventor： Ian T. Marchaj
IPC: F02C7/047
CPC classification number: F02C7/047 , B64D33/02 , B64D2033/0233 , B64D2033/0286 , F01D25/02 , F02C7/14 , F02K3/06 , F05D2260/207 , Y02T50/675
Abstract: A gas turbine engine de-icing system includes a heat exchanger. A coolant loop is in fluid communication with the heat exchanger and is configured to circulate a coolant. An engine oil loop is in fluid communication with the heat exchanger and is configured to transfer heat to the coolant. A gas turbine engine inlet structure includes a cavity. A manifold is arranged in the cavity and is in fluid communication with the coolant loop. The manifold is configured to spray the coolant onto the gas turbine engine inlet structure to de-ice the gas turbine engine inlet structure.
Abstract translation: 燃气涡轮发动机除冰系统包括热交换器。 冷却剂回路与热交换器流体连通并且构造成使冷却剂循环。 发动机油回路与热交换器流体连通，并被配置为将热量传递给冷却剂。 燃气涡轮发动机入口结构包括空腔。 歧管布置在空腔中并与冷却剂回路流体连通。 歧管被配置为将冷却剂喷射到燃气涡轮发动机入口结构上以使燃气涡轮发动机入口结构脱冰。
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公开(公告)号：US11365647B2
公开(公告)日：2022-06-21
申请号：US16804905
申请日：2020-02-28
Applicant: United Technologies Corporation
Inventor： Ian T. Marchaj
Abstract: A gas turbine engine de-icing system includes a heat exchanger. A coolant loop is in fluid communication with the heat exchanger and is configured to circulate a heat transfer fluid. An engine oil loop is in fluid communication with the heat exchanger and is configured to transfer heat to the heat transfer fluid. A gas turbine engine inlet structure has at least one fan inlet guide vane. A spray bar is disposed at least partially in at least one fan inlet guide vane. The spray bar is in fluid communication with the coolant loop. The spray bar is configured to spray the heat transfer fluid onto an inner surface of the at least one fan inlet guide vane to de-ice the fan inlet guide vane.
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公开(公告)号：US20210270148A1
公开(公告)日：2021-09-02
申请号：US16804905
申请日：2020-02-28
Applicant: United Technologies Corporation
Inventor： Ian T. Marchaj
IPC: F01D25/02
Abstract: A gas turbine engine de-icing system includes a heat exchanger. A coolant loop is in fluid communication with the heat exchanger and is configured to circulate a heat transfer fluid. An engine oil loop is in fluid communication with the heat exchanger and is configured to transfer heat to the heat transfer fluid. A gas turbine engine inlet structure has at least one fan inlet guide vane. A spray bar is disposed at least partially in at least one fan inlet guide vane. The spray bar is in fluid communication with the coolant loop. The spray bar is configured to spray the heat transfer fluid onto an inner surface of the at least one fan inlet guide vane to de-ice the fan inlet guide vane.
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公开(公告)号：US10415471B2
公开(公告)日：2019-09-17
申请号：US15365466
申请日：2016-11-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj
IPC: F02C7/045 , G10K11/172 , F02K3/06
Abstract: A gas turbine engine may include at least one of a fan inlet case and a bypass duct case. Additionally, the gas turbine engine may include a variable volume acoustic damper coupled to the at least one of the fan inlet case and the bypass duct case, wherein the variable volume acoustic damper is configured to damp acoustic energy. The variable volume acoustic damper may include a case and a diaphragm movably coupled within the case. An acoustic volume may be defined by a position of the diaphragm relative to the case and the acoustic volume may correspond to and may be configured to damp acoustic energy of a gas turbine engine.
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公开(公告)号：US20180258956A1
公开(公告)日：2018-09-13
申请号：US15452641
申请日：2017-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj , Glenn Levasseur
Abstract: Disclosed is a flutter damper, including a chamber having an internal space, a movable diaphragm disposed at least partially within the chamber, the diaphragm separating the chamber into a first chamber and a second chamber, the second chamber forming an acoustic volume, wherein a size of the acoustic volume configures the chamber for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and a biasing member that moves the diaphragm responsive to a signal from an aircraft or engine electronic control (EEC) unit, wherein movement of the diaphragm increases or reduces the size of the acoustic volume of the second chamber.
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