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公开(公告)号：US10808608B2
公开(公告)日：2020-10-20
申请号：US16027496
申请日：2018-07-05
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Nathan Snape , Christopher M. Dye
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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公开(公告)号：US10760423B2
公开(公告)日：2020-09-01
申请号：US15947119
申请日：2018-04-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve, Jr. , James W. Norris
Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.
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公开(公告)号：US10072569B2
公开(公告)日：2018-09-11
申请号：US14806809
申请日：2015-07-23
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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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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Patent Agency Ranking
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：US20150322854A1
公开(公告)日：2015-11-12
申请号：US14806809
申请日：2015-07-23
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.
Abstract translation: 燃气涡轮发动机包括包括压缩机部分和涡轮机部分的发动机静态结构壳体。 燃烧器部分轴向布置在压缩机部分和涡轮部分之间。 一个核心机舱包围发动机静态结构以提供一个核心隔间。 油箱布置在芯部隔室中并与压缩机部分轴向对准。 热交换器被固定到油箱并且布置在核心隔间中。
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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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公开(公告)号：US20140157752A1
公开(公告)日：2014-06-12
申请号：US14179827
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 method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. The pressure ratio across the first compressor is greater than or equal to about 7.
Abstract translation: 一种设计燃气涡轮发动机的方法包括：提供包括风扇的风扇部分; 通过齿轮装置驱动风扇部分; 提供包括第一压缩机和第二压缩机的压缩机部分; 并且经由涡轮机部分驱动压缩机部分和齿轮装置。 跨越第一压缩机的压力比大于或等于约7。
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公开(公告)号：US20180230944A1
公开(公告)日：2018-08-16
申请号：US15943100
申请日：2018-04-02
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian Merry , Christopher M. Dye
Abstract: A turbine engine is disclosed that includes a fan case surrounding a fan rotatable about an axis. A core is supported relative to the fan case by support structure arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage having a rotor blade with a blade trailing edge. The support structure includes a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge. The support structure trailing edge is arranged axially forward of the blade trailing edge. In one example, a forward attachment extends from the support structure to the inlet case.
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