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公开(公告)号：US11236639B2
公开(公告)日：2022-02-01
申请号：US14618572
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Christopher J. Hanlon , Daniel B. Kupratis , Walter A. Ledwith , William F. Schneider , Sean Danby , Robert H. Bush , Benjamin Bellows
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.
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公开(公告)号：US11415044B2
公开(公告)日：2022-08-16
申请号：US16431271
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil Terwilliger , Christopher J. Hanlon
Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.
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公开(公告)号：US11168616B2
公开(公告)日：2021-11-09
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：US11125168B2
公开(公告)日：2021-09-21
申请号：US16168934
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 dirt mitigation system for a gas turbine engine. The dirt mitigation system includes a plurality of bleeds of the gas turbine engine and a control system configured to determine a particulate ingestion estimate indicative of dirt ingested in the gas turbine engine. The control system is further configured to determine one or more operating parameters of the gas turbine engine and alter a bleed control schedule of the gas turbine engine to purge at least a portion of the dirt ingested in the gas turbine engine through one or more of the bleeds of the gas turbine engine based on the particulate ingestion estimate and the one or more operating parameters.
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公开(公告)号：US20160298550A1
公开(公告)日：2016-10-13
申请号：US14685166
申请日：2015-04-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , Christopher J. Hanlon , Walter A. Ledwith, JR.
CPC classification number: F02C9/18 , F02C3/13 , F02K3/075 , F02K3/077 , F05D2220/323 , F05D2260/213 , Y02T50/675
Abstract: Aspects of the disclosure are directed to an engine of an aircraft. The engine may include a first fan configured to output a first air flow, a second fan configured to receive a first portion of the first air flow and output a second air flow, a core configured to receive a first portion of the second air flow and generate a first stream, and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream based on at least one of the first air flow and the second air flow.
Abstract translation: 本公开的方面涉及飞机的发动机。 发动机可以包括构造成输出第一空气流的第一风扇，被配置为接收第一气流的第一部分并输出第二空气流的第二风扇，被配置为接收第二气流的第一部分的芯和 产生第一流，以及至少一个阀，其配置为基于第一气流和第二空气流中的至少一个，与第二流和第三流的产生相关联地呈现至少三个状态中的一个。
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Patent Agency Ranking
公开(公告)号：US11111809B2
公开(公告)日：2021-09-07
申请号：US15979085
申请日：2018-05-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Neil Terwilliger , Christopher J. Hanlon , Patrick D Couture , Coy Bruce Wood
Abstract: A clearance control system for a gas turbine engine may comprise a rotor blade, an outer structure disposed radially outward from the rotor blade, and a heating element configured to cause the outer structure to be heated in response to electric current being supplied to the heating element, wherein a gap between the rotor blade and the outer structure is at least one of increased, decreased, and maintained in response to the outer structure being heated.
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公开(公告)号：US11015523B2
公开(公告)日：2021-05-25
申请号：US16431259
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , Daniel Bernard Kupratis , Christopher J. Hanlon
Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines connected by an inter-engine gas path. The first gas turbine engine has a first spool with a first compressor section, and a second spool with a second compressor section downstream of and rotationally independent from the first compressor section. The second gas turbine engine is configured to provide power to at least one of the first and second spools of the first gas turbine engine. The inter-engine gas path is disposed to receive gas flow bled from a bleed location in the first gas turbine engine downstream of the first compressor section, and to supply this gas flow to an inlet of the second gas turbine engine.
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公开(公告)号：US20200032702A1
公开(公告)日：2020-01-30
申请号：US16431271
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil Terwilliger , Christopher J. Hanlon
Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.
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公开(公告)号：US10161316B2
公开(公告)日：2018-12-25
申请号：US14685166
申请日：2015-04-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , Christopher J. Hanlon , Walter A. Ledwith, Jr.
Abstract: Aspects of the disclosure are directed to an engine of an aircraft. The engine may include a first fan configured to output a first air flow, a second fan configured to receive a first portion of the first air flow and output a second air flow, a core configured to receive a first portion of the second air flow and generate a first stream, and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream based on at least one of the first air flow and the second air flow.
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公开(公告)号：US20160208692A1
公开(公告)日：2016-07-21
申请号：US14600978
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Christopher J. Hanlon , Daniel B. Kupratis , Walter A. Ledwith
CPC classification number: F02C9/18 , F02K3/075 , F02K3/077 , Y02T50/671
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.
Abstract translation: 燃气涡轮发动机包括构造和布置成围绕发动机轴线旋转的低和高线轴。 低阀芯驱动风扇部分的至少一个引导级，高阀芯驱动风扇部分的后级。 后段通常可以包括用于将旁路流直接从引导级可控地流动并且可选地和/或选择性地流入辅助流动路径的旁路管道和/或从核心流路径向向外定位的第二流路。
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