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公开(公告)号：US20150345427A1
公开(公告)日：2015-12-03
申请号：US14663727
申请日：2015-03-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Karl L. Hasel
CPC classification number: F02C3/13 , F02C3/06 , F02C3/10 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/24 , F05D2240/30 , F05D2240/35 , F05D2240/55 , F05D2250/283 , F05D2260/40311 , Y02T50/671
Abstract: A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000° F. and about 1500° F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.
Abstract translation: 燃气涡轮发动机包括具有可围绕轴线旋转的多个风扇叶片的风扇和至少包括第一和第二压缩机部分的压缩机部分。 压缩机部分的平均出口温度在约1000°F和约1500°F之间。发动机还包括与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮机部分。 齿轮架构由涡轮部分驱动，用于围绕轴线旋转风扇。
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公开(公告)号：US09194329B2
公开(公告)日：2015-11-24
申请号：US14219112
申请日：2014-03-19
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Karl L. Hasel
CPC classification number: F02C7/06 , F01D25/162 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/00 , F02K3/04 , Y02T50/671 , Y10T29/4932
Abstract: A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.
Abstract translation: 燃气涡轮发动机包括壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 入口箱内设有齿轮架构。 齿轮架构包括行星齿轮系。 风扇由齿轮架构旋转驱动。 轴提供旋转轴。 轮毂由轴可操作地支撑。 第一和第二轴承分别相对于中间壳体和进气口支撑轴。
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公开(公告)号：US20150267610A1
公开(公告)日：2015-09-24
申请号：US14571737
申请日：2014-12-16
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Karl L. Hasel
CPC classification number: F02C3/107 , F02K3/06 , F02K3/075 , F05D2220/3213 , F05D2220/3218
Abstract: A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor section second portion stages is less than or equal to 1.
Abstract translation: 涡轮发动机至少包括压缩机部分和涡轮机部分，每个部分至少具有第一和第二部分。 涡轮部分第二部分级与压缩机部分第二部分级的比例小于或等于1。
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公开(公告)号：US20150013301A1
公开(公告)日：2015-01-15
申请号：US14143342
申请日：2013-12-30
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Karl L. Hasel
IPC: F02K3/06
CPC classification number: F02K3/06 , F02K3/075 , F05D2220/3213 , F05D2220/3218 , F05D2260/83
Abstract: A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor section second portion stages is less than or equal to 1.
Abstract translation: 涡轮发动机至少包括压缩机部分和涡轮机部分，每个部分至少具有第一和第二部分。 涡轮部分第二部分级与压缩机部分第二部分级的比例小于或等于1。
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公开(公告)号：US20140290211A1
公开(公告)日：2014-10-02
申请号：US13799475
申请日：2013-03-13
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Karl L. Hasel
IPC: F02K3/075
CPC classification number: F02K3/075 , F05D2220/3213 , F05D2220/3218
Abstract: A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor section second portion stages is less than or equal to 1.
Abstract translation: 涡轮发动机至少包括压缩机部分和涡轮机部分，每个部分至少具有第一和第二部分。 涡轮部分第二部分级与压缩机部分第二部分级的比例小于或等于1。
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Patent Agency Ranking
36.发明授权Method for setting a gear ratio of a fan drive gear system of a gas turbine engine 有权用于设定燃气轮机的风扇驱动齿轮系的齿轮比的方法公开(公告)号：US08807916B2
公开(公告)日：2014-08-19
申请号：US14204125
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Karl L. Hasel
CPC classification number: F02C7/36 , F02C3/04 , F02C3/06 , F02C3/107 , F02C3/113 , F02C7/00 , F02C7/32 , F05D2210/12 , F05D2220/32 , F05D2220/36 , F05D2240/40 , F05D2260/40311 , F16H1/28 , F16H1/36
Abstract: A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.
Abstract translation: 燃气涡轮发动机包括风扇部分，风扇部分包括可围绕轴线旋转的风扇。 减速装置连接到风扇。 减速装置包括具有至少1.5的星形齿轮比的星形驱动齿轮系。 旁路比大于约11.0。
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公开(公告)号：US20140186158A1
公开(公告)日：2014-07-03
申请号：US14012773
申请日：2013-08-28
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Karl L. Hasel
CPC classification number: F02C7/06 , F01D25/162 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/00 , F02K3/04 , Y02T50/671 , Y10T29/4932
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 入口箱内设有齿轮架构。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分轴向地布置在入口壳体流动路径和中间壳体流动路径之间。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。
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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：US20190040793A1
公开(公告)日：2019-02-07
申请号：US16157224
申请日：2018-10-11
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Karl L. Hasel
CPC classification number: F02C3/13 , F02C3/06 , F02C3/10 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/24 , F05D2240/30 , F05D2240/35 , F05D2240/55 , F05D2250/283 , F05D2260/40311 , Y02T50/671
Abstract: A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.
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