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公开(公告)号：US09797311B2
公开(公告)日：2017-10-24
申请号：US14729800
申请日：2015-06-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Allan R. Penda , Brian D. Merry , Christopher M. Dye , Nathan Snape
CPC classification number: F02C7/185 , F02C7/08 , F02C7/14 , F02C7/18 , Y02T50/671
Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.
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公开(公告)号：US20160032828A1
公开(公告)日：2016-02-04
申请号：US14796209
申请日：2015-07-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
CPC classification number: F02K3/06 , B64D27/26 , B64D2027/266 , B64D2027/268 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F05D2220/32 , F05D2220/36 , F05D2260/4031 , F05D2260/40311 , F05D2270/42
Abstract: A gas turbine engine including a core nacelle defined about an engine axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A gear train is defined along an engine axis. The gear train defines a gear reduction ratio of greater than or equal to about 2.3. A spool along the engine axis drives the gear train. The spool includes a downstream turbine having six or fewer stages. A fan is driven through the gear train by the downstream turbine. A pressure ratio across the fan is less than about 1.45. A fan variable area nozzle is axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
Abstract translation: 一种燃气涡轮发动机，包括围绕发动机轴线限定的核心机舱。 风扇机舱至少部分地安装在核心机舱周围，以限定用于风扇旁路气流的风扇旁路气流路径。 齿轮系沿发动机轴线定义。 齿轮系确定齿轮减速比大于或等于约2.3。 沿着发动机轴的线轴驱动齿轮系。 阀芯包括具有六个或更少级的下游涡轮机。 风扇由下游涡轮驱动通过齿轮系。 风扇的压力比小于约1.45。 风扇可变区喷嘴可相对于风扇机舱轴向移动，以改变风扇喷嘴出口区域，并调节发动机运行期间风扇旁路气流的压力比。
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公开(公告)号：US20150300207A1
公开(公告)日：2015-10-22
申请号：US14755221
申请日：2015-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
CPC classification number: F02K3/06 , B64D27/26 , B64D2027/266 , B64D2027/268 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F05D2220/32 , F05D2220/36 , F05D2260/4031 , F05D2260/40311 , F05D2270/42
Abstract: A gas turbine engine comprises a gear train defined along an engine axis. A spool along the engine axis drives the gear train, and includes a low stage count downstream turbine. A fan rotates at a fan speed about the engine axis and drives the downstream turbine through the gear train. The fan speed is less than a speed of the downstream turbine. A core is surrounded by a core housing defined about the engine axis. A fan nacelle is mounted around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10).
Abstract translation: 燃气涡轮发动机包括沿发动机轴线限定的齿轮系。 沿着发动机轴线的线轴驱动齿轮系，并且包括低阶计数的下游涡轮机。 风扇以发动机轴线的风扇速度旋转，并通过齿轮系驱动下游涡轮机。 风扇速度小于下游涡轮机的速度。 一个铁芯围绕发动机轴线定义的铁芯壳体围绕。 风扇机舱安装在核心机舱周围，以确定风扇旁路气流的风扇旁路气流。 由风扇旁路通道气流除以通过芯的气流所限定的旁路比大于约十（10）。
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公开(公告)号：US10830152B2
公开(公告)日：2020-11-10
申请号：US15184253
申请日：2016-06-16
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
Abstract: A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to about 8 at cruise power. A gear arrangement is configured to drive the fan section. A compressor section includes both a first compressor section and a second compressor section. A turbine section is configured to drive the gear arrangement, and may have a low pressure turbine with four stages and a low pressure turbine pressure ratio greater than about 5:1, and a high pressure turbine with two stages. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than about 40, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor section is greater than about 7.
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公开(公告)号：US20150300252A1
公开(公告)日：2015-10-22
申请号：US14753474
申请日：2015-06-29
Applicant: United Technologies Corporation
Inventor： Hung Duong , Gabriel L. Suciu , Christopher M. Dye
IPC: F02C7/00
CPC classification number: F02C7/00 , F02C7/32 , F02C7/36 , F05D2230/70 , F05D2250/312 , F16H1/20 , Y10T29/49464
Abstract: An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis and includes first and second sides. A first geartrain includes one or more shafts rotatable about axes perpendicular to the first side of the accessory gearbox and a second geartrain includes one or more shafts rotatable about axes perpendicular to the second side of the accessory gearbox. A driven gear set defines an input axis and drives first geartrain and the second geartrain about corresponding first and second drive axes parallel to the input axis.
Abstract translation: 用于燃气涡轮发动机的附件系统包括限定附件齿轮箱轴线并包括第一和第二侧面的附件齿轮箱。 第一齿轮箱包括可围绕垂直于附件齿轮箱的第一侧的轴线旋转的一个或多个轴，并且第二齿轮箱包括可围绕垂直于附件齿轮箱的第二侧的轴线旋转的一个或多个轴。 从动齿轮组限定输入轴并且驱动第一齿轮和第二齿轮组，绕相应于输入轴平行的第一和第二驱动轴。
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Patent Agency Ranking
公开(公告)号：US20140174056A1
公开(公告)日：2014-06-26
申请号：US14190429
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven M. Johnson , Frederick M. Schwarz
IPC: F02K3/06
CPC classification number: F02K3/06 , B64D27/26 , B64D2027/266 , B64D2027/268 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F05D2220/32 , F05D2220/36 , F05D2260/4031 , F05D2260/40311 , F05D2270/42
Abstract: A gas turbine engine comprises a gear train defined along an axis. A spool along the axis drives the gear train and includes a low stage count low pressure turbine. A fan i s rotatable at a fan speed about the axis and driven by the low pressure turbine through the gear train. The fan speed is less than a speed of the low pressure turbine. A core is surrounded by a core nacelle defined about the axis. A fan nacelle i s mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10).
Abstract translation: 燃气涡轮发动机包括沿轴线限定的齿轮系。 沿着轴的线轴驱动齿轮系并且包括低阶数低压涡轮机。 风扇可以围绕轴线以风扇转速旋转，并由低压涡轮机通过齿轮系驱动。 风扇转速小于低压汽轮机的转速。 一个核心围绕着围绕轴定义的核心机舱。 一个风扇机舱至少部分安装在核心机舱周围，以便为风扇旁路气流定义一个风扇旁路气流路径。 由风扇旁路通道气流除以通过芯的气流所限定的旁路比大于约十（10）。
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公开(公告)号：US20140165534A1
公开(公告)日：2014-06-19
申请号：US14179714
申请日：2014-02-13
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/06
CPC classification number: F02K3/06 , F02C3/107 , F05D2260/4031
Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than or equal to about 8.
Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供，总压力比大于或等于约35.风扇构造成将一部分空气输送到压缩机部分中，并且一部分 的空气进入旁路管道。 旁路比被定义为与通过压缩机部分的空气体积相比通过旁通管道的空气体积大于或等于约8。
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公开(公告)号：US20140157757A1
公开(公告)日：2014-06-12
申请号：US14179799
申请日：2014-02-13
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/06
CPC classification number: F02K3/06 , F02C3/107 , F05D2260/4031
Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. The turbine section includes a fan drive turbine configured to drive the fan section, a pressure ratio across the fan drive turbine being greater than or equal to about 5. An overall pressure ratio is provided by the combination of the first compressor and the second compressor.
Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 涡轮部分包括风扇驱动涡轮机，其构造成驱动风扇部分，风扇驱动涡轮机的压力比大于或等于约5.总压力比由第一压缩机和第二压缩机的组合提供。
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公开(公告)号：US20130239587A1
公开(公告)日：2013-09-19
申请号：US13869057
申请日：2013-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Hasel Karl , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02C7/00
CPC classification number: F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
Abstract: A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.
Abstract translation: 燃气涡轮发动机具有风扇部，构造成驱动风扇部的齿轮装置，包括低压压缩部和高压压缩部两者的压缩部。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过低压压缩机部分的压力比和高压压缩机部分的压力比的组合提供的总压力比大于约35。第一低压压缩机部分和高压压缩机部分之间的压力比在 约3和约8之间。跨过第二个低压和高压压缩机段的压力比在约7至约15之间。风扇构造成将一部分空气输送到压缩机部分中，并且一部分空气进入 旁路管道。
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公开(公告)号：US20180313266A1
公开(公告)日：2018-11-01
申请号：US16027496
申请日：2018-07-05
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Nathan Snape , Christopher M. Dye
CPC classification number: F02C3/04 , F01D25/12 , F01D25/18 , F02C7/06 , F02C7/12 , F02C7/14 , F02C7/32
Abstract: A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.
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