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公开(公告)号：US20150089959A1
公开(公告)日：2015-04-02
申请号：US14570091
申请日：2014-12-15
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu
IPC: F02C7/06
CPC classification number: F02C7/06 , F01D25/162 , F01D25/18 , F02C7/36 , F02K3/04 , F05D2260/40311
Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supporting the shaft relative to the inlet case. The second bearing is arranged radially outward from the shaft.
Abstract translation: 燃气涡轮发动机包括具有入口壳体和中间壳体的芯壳体，其分别提供入口壳体流动路径和中间壳体流动路径。 轴支撑轴向设置在入口壳体流动路径和中间壳体流动路径之间的压缩机部分。 齿轮架构耦合到轴，并且风扇耦合到由齿轮架构旋转地驱动。 齿轮架构包括在第二端支撑的太阳齿轮。 第一轴承相对于中间壳体支撑轴和相对于入口壳体支撑轴的第二轴承。 第二轴承从轴径向向外设置。
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公开(公告)号：US20140165588A1
公开(公告)日：2014-06-19
申请号：US13715202
申请日：2012-12-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nathan Snape , Brian D. Merry , Allan R. Penda , Gabriel L. Suciu
IPC: F02C9/18
Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.
Abstract translation: 公开的泄放空气系统利用来自高压压缩机的高压空气来驱动涡轮压缩机以增加从低压压缩机抽出的排出空气的压力。 从低压压缩机抽出的空气的压力低于高压压缩机所遇到的温度和压力。 涡轮压缩机增加了气流的压力，并且使得流入主排气通道的气流被传送到利用排放空气的系统。
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公开(公告)号：US20140157755A1
公开(公告)日：2014-06-12
申请号：US14179743
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. 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。 风扇被配置为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通管道。 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的旁路比大于或等于约8。
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公开(公告)号：US20130202415A1
公开(公告)日：2013-08-08
申请号：US13836799
申请日：2013-03-15
Applicant: United Technologies Corporation
Inventor： Hasel Karl , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02K3/02
CPC classification number: F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. The engine includes a combination of quantities providing beneficial operation.
Abstract translation: 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 发动机包括提供有益操作的量的组合。
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公开(公告)号：US11073087B2
公开(公告)日：2021-07-27
申请号：US14187612
申请日：2014-02-24
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.
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Patent Agency Ranking
公开(公告)号：US10718233B2
公开(公告)日：2020-07-21
申请号：US16012152
申请日：2018-06-19
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Glenn Levasseur , Brian D. Merry
Abstract: A gas turbine engine includes a plurality of rotatable components housed within a main compressor section and a turbine section. A cooling system is connected to tap air from said main compressor section. A first tap is connected to a first heat exchanger. The first heat exchanger is connected to a cooling compressor for raising a pressure of the tapped air downstream of the first heat exchanger. A second heat exchanger is downstream of the cooling compressor, and a connection is downstream of the second heat exchanger for delivering air to a bearing compartment. A connection intermediate the cooling compressor and the second heat exchanger delivers cooling air to at least one of the rotatable components.
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公开(公告)号：US10563592B2
公开(公告)日：2020-02-18
申请号：US13715202
申请日：2012-12-14
Applicant: United Technologies Corporation
Inventor： Nathan Snape , Brian D. Merry , Allan R. Penda , Gabriel L. Suciu
Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.
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公开(公告)号：US20200025030A1
公开(公告)日：2020-01-23
申请号：US16286970
申请日：2019-02-27
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Todd A. Davis , Gregory E. Reinhardt , Enzo DiBenedetto
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 first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.
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公开(公告)号：US10526915B2
公开(公告)日：2020-01-07
申请号：US15062442
申请日：2016-03-07
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry
IPC: F01D25/08 , F02C7/25 , F02C7/36 , F02C7/32 , F01D25/20 , F02C7/22 , F04D19/02 , F04D27/00 , F04D29/56
Abstract: A gas turbine engine comprises an engine having a compressor section, and a turbine section. A firewall and accessory pumps are mounted on a downstream side of the firewall. The accessory pumps are driven by electric motors mounted on the firewall on an upstream side of the firewall.
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公开(公告)号：US20190383167A1
公开(公告)日：2019-12-19
申请号：US16012152
申请日：2018-06-19
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Glenn Levasseur , Brian D. Merry
Abstract: A gas turbine engine includes a plurality of rotatable components housed within a main compressor section and a turbine section. A cooling system is connected to tap air from said main compressor section. A first tap is connected to a first heat exchanger. The first heat exchanger is connected to a cooling compressor for raising a pressure of the tapped air downstream of the first heat exchanger. A second heat exchanger is downstream of the cooling compressor, and a connection is downstream of the second heat exchanger for delivering air to a bearing compartment. A connection intermediate the cooling compressor and the second heat exchanger delivers cooling air to at least one of the rotatable components.
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