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公开(公告)号：US20190353104A1
公开(公告)日：2019-11-21
申请号：US15980870
申请日：2018-05-16
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Christopher J. Hanlon , William G. Sheridan
Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.
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公开(公告)号：US10119477B2
公开(公告)日：2018-11-06
申请号：US14600978
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Christopher J. Hanlon , Daniel B. Kupratis , Walter A. Ledwith
Abstract: A gas turbine engine includes low and high spools constructed and arranged to rotate about an engine axis. The low spool drives at least one leading stage of a fan section and the high spool drives an aft stage of the fan section. The aft stage may generally include a bypass duct for controllably flowing a bypass stream directly from the leading stage and controllably and/or selectively into an auxiliary flowpath and/or into a second flowpath both located radially outward from a core flowpath.
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公开(公告)号：US09650954B2
公开(公告)日：2017-05-16
申请号：US14597510
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： 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: F02C3/107 , B64D35/04 , F01D13/00 , F02K3/077 , F02C7/36 , F02C3/06 , F02C3/067 , F02C9/18 , B64D27/18
CPC classification number: 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
Abstract: 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.
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公开(公告)号：US20160230658A1
公开(公告)日：2016-08-11
申请号：US14618572
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Christopher J. Hanlon , Daniel B. Kupratis , Water A. Ledwith , William F. Schneider , Sean Danby , Robert H. Bush , Benjamin Bellows
CPC classification number: F01D25/30 , F01D1/023 , F02C7/185 , F02K3/075 , F02K3/077 , F02K3/10 , F05D2260/213 , Y02T50/671 , Y02T50/675
Abstract: A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.
Abstract translation: 燃气涡轮发动机包括用于流动核心流的核心流动路径，从用于流动第二流的核心流径径向向外定位的第二流动路径，以及从第二流动路径径向向外设置用于流动辅助流的辅助流动路径。 热交换装置被构造和布置成将第二流的一部分转入辅助流路。 涡轮排气箱被构造和布置成将辅助流流动到芯流道中以与核心流混合。
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公开(公告)号：US20150226117A1
公开(公告)日：2015-08-13
申请号：US14597510
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： 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
CPC classification number: 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
Abstract: 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.
Abstract translation: 气体发生器具有至少一个压缩机转子，至少一个气体发生器涡轮机转子和燃烧部分。 风扇驱动涡轮机位于已经通过至少一个气体发生器涡轮机转子的燃烧产物的路径的下游。 风扇驱动涡轮机驱动轴并且轴接合齿轮以驱动至少三个风扇转子。
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Patent Agency Ranking
公开(公告)号：US11261800B2
公开(公告)日：2022-03-01
申请号：US16168943
申请日：2018-10-24
Applicant: United Technologies Corporation
Inventor： Christopher J. Hanlon , James F. Krenzer , Becky E. Rose , Mark F. Zelesky
Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.
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17.发明申请公开(公告)号：US20190048796A1
公开(公告)日：2019-02-14
申请号：US16048738
申请日：2018-07-30
Applicant: United Technologies Corporation
Inventor： Walter A. Ledwith, Jr. , Scott A. Carr , Christopher J. Hanlon , Peter A. White , Theodore W. Hall , John R. Farris , Andrew S. Miller , Christopher W. Robak , David C. Pimenta , David Richard Griffin
Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.
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公开(公告)号：US20180003071A1
公开(公告)日：2018-01-04
申请号：US15200128
申请日：2016-07-01
Applicant: United Technologies Corporation
Inventor： Charles E. Lents , Christopher J. Hanlon , Larry W. Hardin , Jonathan Rheaume
CPC classification number: F01D15/10 , B64D27/10 , B64D27/24 , B64D41/00 , F02C6/14 , F02C7/36 , F05D2220/76 , F05D2240/60
Abstract: A gas turbine engine includes a compressor section having a first compressor and a second compressor, the second compressor having a higher pressure than the first compressor, and a turbine section having a first turbine and a second turbine, the second turbine having a higher pressure than the first turbine. The first compressor is connected to the first turbine via a first shaft. The second compressor is connected to the second turbine via a second shaft. An electric motor is connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft. A fan is connected to the first shaft via a gear system. The gas turbine engine includes at least a takeoff mode of operations, a top of climb mode of operations and a maximum cruise mode of operations. The gas turbine engine is sized to operate at peak efficiency in the maximum cruise mode of operations.
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19.发明申请公开(公告)号：US20170328231A1
公开(公告)日：2017-11-16
申请号：US14640060
申请日：2015-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Walter A. Ledwith, JR. , Scott A. Carr , Christopher J. Hanlon , Peter A. White , Theodore W. Hall , John R. Farris , Andrew S. Miller , Christopher W. Robak , David C. Pimenta , David Richard Griffin
CPC classification number: F02C3/055 , F01D11/24 , F02C7/185 , F05D2260/213 , F05D2270/20 , F05D2270/44 , Y02T50/676
Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.
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公开(公告)号：US20170306842A1
公开(公告)日：2017-10-26
申请号：US15443113
申请日：2017-02-27
Applicant: United Technologies Corporation
Inventor： 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: F02C3/107 , B64D35/04 , F01D13/00 , F02C3/067 , F02K3/077 , B64D27/18 , F02C7/36 , F02C9/18 , F02C3/06
CPC classification number: 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
Abstract: 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.
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