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公开(公告)号：US11066989B2
公开(公告)日：2021-07-20
申请号：US16386670
申请日：2019-04-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel B. Kupratis , Howard K. Gregory
IPC: F01D17/16 , F02C3/14 , F02C9/22 , F02C9/54 , F23R3/42 , F01D9/02 , F02C5/02 , F01D17/18 , F23R3/46 , F02K3/11
Abstract: A gas turbine engine includes an inner annular combustor radially inboard of an outer annular combustor. An outer variable turbine vane array is downstream of the outer annular combustor and an inner variable turbine vane array downstream of the inner annular combustor.
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公开(公告)号：US10125722B2
公开(公告)日：2018-11-13
申请号：US14622485
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , William G. Sheridan
IPC: F02K1/60 , F02K1/68 , F01D5/02 , F01D25/24 , F02C3/04 , F02C7/36 , F04D19/00 , F04D29/32 , F04D29/38 , F04D29/52
Abstract: A turbine engine is provided that include a turbo-compressor, a combustor section and a nacelle which houses the turbo-compressor and the combustor section. The turbo-compressor includes a compressor section and a turbine section. The combustor section is fluidly coupled between the compressor section and the turbine section. The nacelle includes a thrust reverser.
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公开(公告)号：US10100731B2
公开(公告)日：2018-10-16
申请号：US14622383
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , William G. Sheridan
IPC: F02C3/10 , F02C6/12 , F01D1/12 , F02C3/045 , F02C3/073 , F02C3/14 , F01D5/12 , F01D9/04 , F02C3/04 , F02C7/36 , F04D29/32 , F04D29/54
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.
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公开(公告)号：US20160237895A1
公开(公告)日：2016-08-18
申请号：US14622438
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , William G. Sheridan
CPC classification number: F02C6/12 , F01D5/02 , F01D5/146 , F01D5/147 , F01D5/225 , F01D13/006 , F02C3/045 , F02C3/06 , F02C3/073 , F02C3/107 , F02C7/36 , F02K1/60 , F02K1/68 , F02K3/00 , F02K3/06 , F04D29/321 , F05D2220/3216 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2250/36 , F05D2260/4031
Abstract: A turbine engine is provided that includes a turbo-compressor and a combustor section. The turbo-compressor includes a compressor section and a turbine section. The combustor section is fluidly coupled between the compressor section and the turbine section. The compressor section includes a first number of stages. The turbine section includes a second number of stages that is different than the first number.
Abstract translation: 提供涡轮发动机，其包括涡轮压缩机和燃烧器部分。 涡轮压缩机包括压缩机部分和涡轮部分。 燃烧器部分流体耦合在压缩机部分和涡轮部分之间。 压缩机部分包括第一级数。 涡轮部分包括与第一数目不同的第二数量级。
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公开(公告)号：US20130121824A1
公开(公告)日：2013-05-16
申请号：US13735345
申请日：2013-01-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel B. Kupratis
IPC: F01D25/24
CPC classification number: F01D25/24 , F02K1/085 , F02K1/1207 , F02K1/1261 , F02K1/386
Abstract: A gas turbine engine system according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly defined about an axis and a core engine positioned radially inward of the nacelle assembly and having a core passage and at least one core auxiliary duct passage. The at least one core auxiliary duct passage includes an inlet for receiving a portion of a core airflow from the core engine and an outlet for discharging the portion of the core airflow. At least one of the inlet and the outlet are selectively translatable to divert the portion of the core airflow into the at least one core auxiliary duct passage and a mixer disposed between the nacelle assembly and the core engine.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机系统包括围绕轴线定义的机舱组件和位于机舱组件的径向内侧的核心发动机，并且具有芯通道和至少一个芯辅助导管 通道。 至少一个核心辅助管道通道包括用于接收来自核心发动机的核心气流的一部分的入口和用于排出核心气流的该部分的出口。 入口和出口中的至少一个可选择性地平移以将核心气流的一部分转移到至少一个核心辅助管道通道中，以及设置在机舱组件和核心发动机之间的混合器。
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Patent Agency Ranking
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：US20200182113A1
公开(公告)日：2020-06-11
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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8.发明申请公开(公告)号：US20200109685A1
公开(公告)日：2020-04-09
申请号：US16152488
申请日：2018-10-05
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , Coy Bruce Wood
Abstract: A hybrid gas turbine engine comprises a turbine, a compressor, and a gear system that is driven by the turbine where the gear system includes a sun gear, a ring gear and a plurality of planet gears, where the ring gear has a ring gear radius of RRing gear and the sun gear has a sun gear radius of RSun gear such that the gear system provides a reduction ratio of RRing gear/RSun gear. A fan is driven by the ring gear, and a generator is driven by the ring gear and provides a generator output signal. A power circuit receives the generator output signal and provides a gain RRing gear/RSun gear to the generator output signal and provides a gain signal indicative thereof to an electrical load.
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9.发明申请公开(公告)号：US20170009703A1
公开(公告)日：2017-01-12
申请号：US15271541
申请日：2016-09-21
Applicant: United Technologies Corporation
Inventor： Francis R. Moon , Daniel B. Kupratis
CPC classification number: F02K1/12 , F02K1/06 , F02K1/36 , F02K1/38 , F02K1/386 , F02K1/46 , F02K3/06 , F02K3/077 , F05D2220/323
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.
Abstract translation: 燃气涡轮发动机包括围绕中心纵向发动机轴线的外壳结构。 中间壳体结构包括在外壳结构内。 内壳结构包括在中间壳结构的内侧。 包括可变面积排气混合器，其可在与中间壳体结构相邻的关闭位置和与内壳结构相邻的打开位置之间移动。
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公开(公告)号：US20160356244A1
公开(公告)日：2016-12-08
申请号：US14622485
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： Daniel B. Kupratis , William G. Sheridan
IPC: F02K1/60 , F04D19/00 , F04D29/52 , F02C7/36 , F04D29/38 , F01D5/02 , F01D25/24 , F02C3/04 , F04D29/32
CPC classification number: F02K1/60 , F01D5/02 , F01D25/24 , F02C3/04 , F02C7/36 , F02K1/68 , F04D19/002 , F04D29/321 , F04D29/38 , F04D29/522 , F05D2220/32 , F05D2240/20 , F05D2260/40311
Abstract: A turbine engine is provided that include a turbo-compressor, a combustor section and a nacelle which houses the turbo-compressor and the combustor section. The turbo-compressor includes a compressor section and a turbine section. The combustor section is fluidly coupled between the compressor section and the turbine section. The nacelle includes a thrust reverser.
Abstract translation: 提供涡轮发动机，其包括涡轮压缩机，燃烧器部分和容纳涡轮压缩机和燃烧器部分的机舱。 涡轮压缩机包括压缩机部分和涡轮部分。 燃烧器部分流体耦合在压缩机部分和涡轮部分之间。 机舱包括推力反向器。
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