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公开(公告)号：US20160061045A1
公开(公告)日：2016-03-03
申请号：US14842404
申请日：2015-09-01
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Stephen K. Kramer , Jesse M. Chandler
CPC classification number: F01D9/02 , F01D5/04 , F01D5/06 , F01D13/003 , F02C3/04 , F02C3/05 , F02C3/085 , F02C3/10 , F02C3/103 , F02C3/14 , F02C7/04 , F05D2220/32 , F05D2240/24 , F05D2240/35 , F05D2250/312 , F05D2250/314
Abstract: A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor.
Abstract translation: 解耦燃气涡轮发动机包括一个高阀芯组件和一个低阀芯组件，每个都具有一个彼此间隔开的旋转轴线。 发动机还包括可具有与每个线轴组件的旋转轴线间隔开的中心线的燃烧器。 发动机的转向管道被配置为将气流从一个线轴组件重新引导到下一个和/或一个线轴组件和燃烧器之间。
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公开(公告)号：US20160040626A1
公开(公告)日：2016-02-11
申请号：US14773958
申请日：2014-03-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02K1/70 , F02K1/06 , F02K1/52 , F02K1/60 , F02K1/62 , F05D2220/323 , F05D2240/40
Abstract: A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.
Abstract translation: 一种用于双燃气涡轮发动机推进系统的喷嘴组件，包括靠近第一燃气涡轮发动机的第一旁通通道安装的壳体和第二燃气涡轮发动机的第二旁通通道，第一和第二上部门，以及第一和第二下部 门。 第一和第二上部门以及第一和第二下部门中的每一个都枢转地安装到壳体上，以在收起位置和展开位置之间移动，在该位置中，穿过第一和第二旁路通道的气流相对于相应的中心线 第一和第二燃气涡轮发动机。
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公开(公告)号：US20160024957A1
公开(公告)日：2016-01-28
申请号：US14872405
申请日：2015-10-01
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson
CPC classification number: F01D25/28 , B64D27/26 , B64D2027/264 , B64D2027/266 , F01D1/02 , F01D5/02 , F01D5/06 , F01D9/02 , F01D15/12 , F01D17/105 , F01D17/14 , F01D17/16 , F01D25/162 , F01D25/24 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2230/60 , F05D2240/128 , F05D2240/24 , F05D2240/50 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a first compressor section including three (3) or more stages, a second compressor section including between eight (8) and thirteen (13) stages, and a first turbine section operable for driving the first compressor section, the first turbine section including between three (3) and six (6) stages, a second turbine section operable for driving the second compressor section, and a gear train defined along an engine centerline axis. One of the first turbine section and the second turbine section is operable to drive the fan section through the gear train.
Abstract translation: 根据本公开的示例的燃气涡轮发动机包括除了别的以外的风扇部分，包括三（3）或更多级的第一压缩机部分，包括八（8）至十三（13） 以及可操作以驱动第一压缩机部分的第一涡轮机部分，第一涡轮部分包括三（3）和六（6）级，第二涡轮部分可操作以驱动第二压缩机部分，以及沿着 发动机中心轴。 第一涡轮部分和第二涡轮部分中的一个可操作以通过齿轮系驱动风扇部分。
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公开(公告)号：US20160024944A1
公开(公告)日：2016-01-28
申请号：US14775730
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Grant O. Cook, III , Mark F. Zelesky , Dilip M. Shah
CPC classification number: F01D5/30 , B23K20/16 , B23K2101/001 , F01D5/18 , F01D5/3061 , F02C3/04 , Y02T50/672
Abstract: A rotor assembly for a turbine engine includes a rotor disk constructed of a first material. Multiple rotor blades constructed of a second material are connected to the rotor disk via a diffusion material.
Abstract translation: 用于涡轮发动机的转子组件包括由第一材料构成的转子盘。 由第二材料构成的多个转子叶片通过扩散材料连接到转子盘。
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公开(公告)号：US20150377142A1
公开(公告)日：2015-12-31
申请号：US14767477
申请日：2014-02-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Gabriel L. Suciu , Brian D. Merry
CPC classification number: F02C7/275 , F01D19/00 , F02C3/107 , F02C7/36 , F05D2260/40 , F05D2260/403 , F05D2260/85
Abstract: A gas turbine engine comprises a first compressor, a second compressor, a starter generator and a clutch. The starter generator is coupled to the first compressor. The clutch selectively couples the second compressor and the first compressor. The clutch is disposed between a first shaft and a second shaft to engage the first shaft with the second shaft at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft relative to the second shaft when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine comprises engaging a low pressure compressor with a high pressure compressor utilizing a clutch, rotating the low pressure compressor and the high pressure compressor utilizing a starter generator coupled to the low pressure compressor, igniting the gas turbine engine, and disengaging the clutch at an operational speed of the gas turbine engine.
Abstract translation: 燃气涡轮发动机包括第一压缩机，第二压缩机，起动发电机和离合器。 起动发电机联接到第一压缩机。 离合器选择性地联接第二压缩机和第一压缩机。 离合器设置在第一轴和第二轴之间，以使第一轴与静止的第二轴接合。 飞行重量系统与离合器机构接合以允许当经受超过阈值速度的旋转运动时第一轴相对于第二轴的续流。 一种用于启动燃气涡轮发动机的方法包括使用离合器将低压压缩机与高压压缩机接合，利用联接到低压压缩机的启动发电机旋转低压压缩机和高压压缩机，点燃燃气涡轮发动机， 以及在所述燃气涡轮发动机的操作速度下离合所述离合器。
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Patent Agency Ranking
公开(公告)号：US20150377124A1
公开(公告)日：2015-12-31
申请号：US14793795
申请日：2015-07-08
Applicant: United Technologies Corporation
Inventor： Paul R. Adams , Shankar S. Magge , Joseph Brent Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
Abstract: A turbofan engine includes an engine case, a gaspath through the engine case, a fan having a circumferential array of fan blades, a compressor in fluid communication with the fan, a combustor in fluid communication with the compressor, and a turbine in fluid communication with the combustor. The turbine has a fan drive turbine section having 3 to 6 blade stages. A speed reduction mechanism couples the fan drive turbine section to the fan. A bypass area ratio is between about 8.0 and about 20.0. A ratio of maximum gaspath radius along the fan drive turbine section to maximum radius of the fan is less than about 0.50. A ratio of a turbine section airfoil count to the bypass area ratio is between about 10 and about 170. The fan drive turbine section airfoil count being the total number of blade airfoils and vane airfoils of the fan drive turbine section.
Abstract translation: 涡轮风扇发动机包括发动机壳体，通过发动机壳体的气路，具有圆周阵列的风扇叶片的风扇，与风扇流体连通的压缩机，与压缩机流体连通的燃烧器，以及与压缩机流体连通的涡轮机 燃烧器。 涡轮机具有风扇驱动涡轮机部分，具有3到6个叶片级。 减速机构将风扇驱动涡轮部分连接到风扇。 旁路面积比在约8.0和约20.0之间。 风扇驱动涡轮机部分的最大气路径半径与风扇的最大半径的比值小于约0.50。 涡轮机翼型计数与旁路面积比的比率在约10和约170之间。风扇驱动涡轮机翼型计数是风扇驱动涡轮机部分的叶片翼型和叶片翼型的总数。
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公开(公告)号：US20150361890A1
公开(公告)日：2015-12-17
申请号：US14740312
申请日：2015-06-16
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
CPC classification number: F02C9/18 , F01D9/065 , F02C7/185 , Y02T50/671 , Y02T50/675
Abstract: A gas turbine engine includes a compressor section having a plurality of compressor stages, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, the turbine section having at least one stage, a compressor bleed structure disposed in one of the plurality of compressor stages and operable to remove air from the compressor stage, a heat exchanger having an input connected to the compressor bleed, and an output connected to an active cooling system of at least one turbine stage, and wherein the compressor stage in which the compressor bleed structure is disposed includes airflow at a pressure above a minimum pressure threshold, and wherein the airflow has a temperature above a maximum temperature threshold.
Abstract translation: 燃气涡轮发动机包括具有多个压缩机级的压缩机部分，与压缩机部分流体连接的燃烧器，与燃烧器部分流体连接的涡轮机部分，具有至少一个级的涡轮机部分， 的多个压缩机级，并且可操作以从压缩机级移除空气，具有连接到压缩机排气口的输入端的热交换器和连接到至少一个涡轮级的主动冷却系统的输出，并且其中压缩机级 压缩机排气结构被布置成包括处于最高压力阈值以上的压力的气流，并且其中气流具有高于最大温度阈值的温度。
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公开(公告)号：US20150361880A1
公开(公告)日：2015-12-17
申请号：US14600487
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler , Michael Winter , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括多个风扇转子。 气体发生器包括至少一个压缩机转子，至少一个气体发生器涡轮机转子，燃烧部分和在至少一个气体发生器涡轮机转子下游的风扇驱动涡轮机。 轴构造成由风扇驱动涡轮机驱动。 轴接合齿轮以驱动多个风扇转子。 系统控制提供给多个风扇转子的功率量。 还公开了一种操作燃气涡轮发动机的方法。
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公开(公告)号：US20150354465A1
公开(公告)日：2015-12-10
申请号：US14729002
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Mark F. Zelesky
CPC classification number: F02C3/13 , F01D5/081 , F01D25/12 , F02C3/04 , F02C7/18 , F02C7/185 , F02C9/18 , F05D2260/213 , F05D2270/112 , F05D2270/20 , F05D2270/3032 , F05D2270/3062 , Y02T50/673 , Y02T50/676
Abstract: A turbine cooling air generation system for a gas turbine engine includes a first fluid pathway connecting a compressor bleed outlet and a mixing valve, a second fluid pathway connecting the compressor bleed outlet and an input of a heat exchanger, and a third fluid pathway connecting an output of the heat exchanger and the mixing valve. The mixing valve is further connected to an input of a turbine stage active cooling system.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机冷却空气产生系统包括连接压缩机排气口和混合阀的第一流体路径，连接压缩机排气口和热交换器的输入口的第二流体路径，以及连接 输出热交换器和混合阀。 混合阀进一步连接到涡轮级主动冷却系统的输入端。
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公开(公告)号：US20150354456A1
公开(公告)日：2015-12-10
申请号：US14732319
申请日：2015-06-05
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
Abstract: A cooling system for gas turbine engines includes a turbine rotor compartment defining a cooling air plenum. A plurality of turbine discs are rotatably housed within the rotor compartment. A cooling air inlet is in fluid communication with the plenum. Each turbine disc includes a cooling outlet in fluid communication with the plenum for cooling the rotor compartment.
Abstract translation: 用于燃气涡轮发动机的冷却系统包括限定冷却空气室的涡轮转子隔室。 多个涡轮盘可旋转地容纳在转子室内。 冷却空气入口与气室流体连通。 每个涡轮盘包括一个冷却出口，该冷却出口与用于冷却转子室的增压室流体连通。
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