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公开(公告)号：US20160097304A1
公开(公告)日：2016-04-07
申请号：US14966538
申请日：2015-12-11
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
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, and a low spool including a low pressure compressor section and a low pressure turbine. A high spool includes a high pressure compressor section. A gear arrangement is defined along an engine axis. The low spool is operable to drive the fan section through the gear arrangement. A mount system includes an aft mount configured to react at least a portion of a thrust load at an engine case generally parallel to an engine axis.
Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括风扇部分和包括低压压缩机部分和低压涡轮机的低线轴。 高阀芯包括高压压缩机部分。 齿轮装置沿发动机轴线定义。 低阀芯可操作以通过齿轮装置驱动风扇部分。 安装系统包括后部安装件，其构造成使大致平行于发动机轴线的发动机壳体上的推力负载的至少一部分反作用。
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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：US10451004B2
公开(公告)日：2019-10-22
申请号：US15173288
申请日：2016-06-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
IPC: F01D5/06 , F02C7/20 , F02C7/36 , F02K3/06 , B64D27/26 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C9/20 , F02C9/18 , F01D9/02 , F02K1/15
Abstract: A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a first nacelle which at least partially surrounds a second nacelle and the fan rotor, the fan section configured to communicate airflow into the first nacelle and the second nacelle, a first turbine, and a second turbine followed by the first turbine. The first turbine is configured to drive the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.
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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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Patent Agency Ranking
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：US20170058830A1
公开(公告)日：2017-03-02
申请号：US15173288
申请日：2016-06-03
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 includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a first nacelle which at least partially surrounds a second nacelle and the fan rotor, the fan section configured to communicate airflow into the first nacelle and the second nacelle, a first turbine, and a second turbine followed by the first turbine. The first turbine is configured to drive the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.
Abstract translation: 燃气涡轮发动机尤其包括风扇部分，其包括风扇转子，围绕发动机旋转轴线限定的齿轮系，至少部分地围绕第二机舱的第一机舱和风扇转子，风扇部分配置为 将气流传送到第一机舱和第二机舱，第一涡轮机和第二涡轮机，随后是第一涡轮机。 第一涡轮机构造成通过齿轮系驱动风扇转子。 静态结构包括第一发动机安装位置和第二发动机安装位置。
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公开(公告)号：US20160047268A1
公开(公告)日：2016-02-18
申请号：US14801925
申请日：2015-07-17
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
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 exemplary aspect of the present disclosure includes, among other things, a spool along an engine axis which drives a gear train, the spool including a low stage count low pressure turbine.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机尤其包括沿着发动机轴线驱动齿轮系的线轴，所述线轴包括低段计数低压涡轮机。
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公开(公告)号：US20160024958A1
公开(公告)日：2016-01-28
申请号：US14872508
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 low spool that includes a low pressure compressor section, the low pressure compressor section including three (3) or more stages, and a high spool including a high pressure compressor section. The high pressure compressor section includes between eight to thirteen (8-13) stages. A gear train is defined along an engine axis. The low spool 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，包括低压压缩机部分的低阀芯，包括三级或更多级的低压压缩机部分和高 阀芯包括高压压缩机部分。 高压压缩机部分包括八到十三（8-13）级。 齿轮系沿发动机轴线定义。 低阀芯可操作以通过齿轮系驱动风扇部分。
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公开(公告)号：US20150315977A1
公开(公告)日：2015-11-05
申请号：US14755366
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 includes 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 fan drive turbine along the engine axis which drives the gear train. The fan drive turbine includes three to six (3-6) stages. A fan is configured for rotation within the fan nacelle for operation at a fan pressure ratio less than about 1.45. A fan variable area nozzle is axially movable relative to said fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. A high bypass gas turbine engine is also disclosed.
Abstract translation: 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。 沿着发动机轴线的驱动齿轮系的风扇驱动涡轮机。 风扇驱动轮机包括三到六（3-6）个阶段。 风扇被配置为在风扇机舱内旋转，以便在小于约1.45的风扇压力比下操作。 风扇可变区域喷嘴可相对于所述风扇机舱轴向移动，以改变风扇喷嘴出口区域，并且在发动机运行期间调节风扇旁路气流的压力比。 还公开了一种高旁路燃气涡轮发动机。
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