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21.发明授权Gas turbine engine with intercooling turbine section and intercooling turbine section bypass 有权具有中间冷却涡轮部分和中间冷却涡轮部分旁路的燃气涡轮发动机公开(公告)号：US09341121B2
公开(公告)日：2016-05-17
申请号：US14569282
申请日：2014-12-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel B. Kupratis
Abstract: A gas turbine engine includes an intercooling turbine section to selectively cool the core flow. An intercooling turbine section bypass is also included to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling turbine section.
Abstract translation: 燃气涡轮发动机包括中间冷却涡轮机部分，以选择性地冷却核心流。 还包括中间冷却涡轮机旁路以选择性地绕过中间冷却涡轮机部分周围的中间冷却涡轮部分旁路的核心流的至少一部分。
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公开(公告)号：US10337401B2
公开(公告)日：2019-07-02
申请号：US14622523
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , William G. Sheridan
Abstract: A turbine engine is provided that includes a turbo-compressor, a combustor section, a flow path and a recuperator. The turbo-compressor includes a compressor section and a turbine section. The combustor section includes a combustor and a plenum adjacent the combustor. The flow path extends through the compressor section, the combustor section and the turbine section. The recuperator is configured with the flowpath between the combustor section and the turbine section. An inlet duct to the recuperator is fluidly coupled with the flow path upstream of the plenum. An outlet duct from the recuperator is fluidly coupled with the plenum.
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公开(公告)号：US10030606B2
公开(公告)日：2018-07-24
申请号：US14553284
申请日：2014-11-25
Applicant: United Technologies Corporation
Inventor： Francis R. Moon , Daniel B. Kupratis
Abstract: A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.
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公开(公告)号：US20160356218A1
公开(公告)日：2016-12-08
申请号：US14622383
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , William G. Sheridan
CPC classification number: F02C6/12 , F01D1/12 , F01D5/12 , F01D9/041 , F02C3/04 , F02C3/045 , F02C3/073 , F02C3/14 , F02C7/36 , F04D29/324 , F04D29/542 , F05D2220/32 , F05D2240/35
Abstract: A turbine engine is provided that includes a first rotor, a second rotor and a combustor section. The first rotor includes a first set of compressor blades. The second rotor is adjacent the first rotor. The second rotor includes a second set of compressor blades and a set of turbine blades respectively connected to the second set of compressor blades. The combustor section is configured to receive air compressed by the first and the second sets of compressor blades. The combustor section is also configured to provide combustion products to the set of turbine blades.
Abstract translation: 提供一种涡轮发动机，其包括第一转子，第二转子和燃烧器部分。 第一转子包括第一组压缩机叶片。 第二转子与第一转子相邻。 第二转子包括分别连接到第二组压缩机叶片的第二组压缩机叶片和一组涡轮叶片。 燃烧器部分构造成接收由第一组和第二组压缩机叶片压缩的空气。 燃烧器部分还构造成向燃气轮机组提供燃烧产物。
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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
26.发明申请GAS TURBINE ENGINE ARCHITECTURE WITH INTERCOOLED TWIN CENTRIFUGAL COMPRESSOR 有权带有双组分离心压缩机的气体涡轮发动机结构公开(公告)号：US20140271121A1
公开(公告)日：2014-09-18
申请号：US14209326
申请日：2014-03-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis
IPC: F04D17/12
CPC classification number: F04D17/12 , F01D9/02 , F02C3/08 , F02C3/107 , F02C7/143 , F02K3/075 , F04D29/5833 , F05D2220/324 , F05D2250/311 , F05D2260/40311 , Y02T50/675
Abstract: A gas turbine engine includes an intercooled twin centrifugal compressor. A pipe diffuser extends from the intercooled twin centrifugal compressor into an airflow path.
Abstract translation: 燃气涡轮发动机包括中间冷却的双离心压缩机。 管道扩散器从中间冷却的双离心压缩机延伸到气流路径中。
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公开(公告)号：US11530635B2
公开(公告)日：2022-12-20
申请号：US16586348
申请日：2019-09-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel B. Kupratis , Neil Terwilliger , Gary Roberge
IPC: F01N3/04
Abstract: A fluid injection system for a gas turbine engine may comprise a fluid injector configured to inject a fluid into an exhaust flow exiting a turbine section of the gas turbine engine. The fluid injector may be coupled to a turbine exit guide vane located at a forward end of an exhaust system of the gas turbine engine. The fluid may decrease a temperature of the exhaust flow exiting the turbine section and/or increase a thrust of the gas turbine engine.
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公开(公告)号：US10514002B2
公开(公告)日：2019-12-24
申请号：US15271541
申请日：2016-09-21
Applicant: United Technologies Corporation
Inventor： Francis R. Moon , Daniel B. Kupratis
Abstract: A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.
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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：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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