专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

91. 发明授权

US08337148B2 Gas turbine engine compressor arrangement 有权
标题翻译：燃气涡轮发动机压缩机布置
公开(公告)号：US08337148B2
公开(公告)日：2012-12-25
申请号：US13483426
申请日：2012-05-30
申请人： Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
发明人： Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC分类号： F01D25/28
CPC分类号： F02C3/107 , F02K3/06
摘要： A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.
摘要翻译：燃气涡轮发动机包括低压压缩机部分和高压压缩机部分。低压涡轮机驱动低压压缩机部分。齿轮装置由低压涡轮机驱动，从而驱动风扇部分。低压压缩机部分的压力比在大约4-8之间，并且高压压缩机部分的压力比在大约8-15之间。在单独的特征中，压缩机壳体包括前压缩机壳体部分和后压缩机壳体部分，后压缩机壳体部分比从前压缩机壳体部分的入口壳体更远离轴向。支撑构件在风扇部分和前压缩机壳体部分之间延伸。

92. 发明授权

US08337147B2 Gas turbine engine compressor arrangement 有权
公开(公告)号：US08337147B2
公开(公告)日：2012-12-25
申请号：US13337354
申请日：2011-12-27
申请人： Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
发明人： Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC分类号： F01D5/06
CPC分类号： F02C3/107 , F02K3/06
摘要： A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.

93. 发明申请

US20120171018A1 GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT 有权
标题翻译：燃气涡轮发动机压缩机装置
公开(公告)号：US20120171018A1
公开(公告)日：2012-07-05
申请号：US13418457
申请日：2012-03-13
申请人： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
发明人： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC分类号： F01D1/04 , F01D15/12
CPC分类号： F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
摘要： 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. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.
摘要翻译：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。由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约而高压压缩机部分的压力比为约7至约15。

94. 发明申请

US20120099963A1 ENGINE MOUNT SYSTEM FOR A TURBOFAN GAS TURBINE ENGINE 有权
标题翻译：发动机涡轮发动机发动机系统
公开(公告)号：US20120099963A1
公开(公告)日：2012-04-26
申请号：US13336140
申请日：2011-12-23
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson
IPC分类号： F01D15/12
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A gas turbine engine according to an exemplary aspect of the present invention includes a gear train defined along an engine centerline axis, and a spool along the engine centerline axis which drives the gear train, the spool includes a low stage count low pressure turbine.
摘要翻译：根据本发明的示例性方面的燃气涡轮发动机包括沿着发动机中心线轴线限定的齿轮系和沿着发动机中心线轴线驱动齿轮系的线轴，所述线轴包括低阶数低压涡轮机。

95. 发明授权

US08128021B2 Engine mount system for a turbofan gas turbine engine 有权
标题翻译：用于涡轮风扇燃气涡轮发动机的发动机支架系统
公开(公告)号：US08128021B2
公开(公告)日：2012-03-06
申请号：US12131876
申请日：2008-06-02
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A mount system for a gas turbine engine includes an aft mount which reacts at least a portion of a thrust load at an engine case generally parallel to an engine axis.
摘要翻译：用于燃气涡轮发动机的安装系统包括尾座，其在大致平行于发动机轴线的发动机壳体上反作用于推力载荷的至少一部分。

96. 发明申请

US20090314881A1 ENGINE MOUNT SYSTEM FOR A TURBOFAN GAS TURBINE ENGINE 有权
标题翻译：发动机涡轮发动机发动机系统
公开(公告)号：US20090314881A1
公开(公告)日：2009-12-24
申请号：US12131876
申请日：2008-06-02
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson
IPC分类号： B64D27/10
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A mount system for a gas turbine engine includes an aft mount which reacts at least a portion of a thrust load at an engine case generally parallel to an engine axis.
摘要翻译：用于燃气涡轮发动机的安装系统包括尾座，其在大致平行于发动机轴线的发动机壳体上反作用于推力载荷的至少一部分。

97. 发明申请

US20090056343A1 ENGINE MOUNTING CONFIGURATION FOR A TURBOFAN GAS TURBINE ENGINE 有权
标题翻译：发动机安装涡轮发动机涡轮发动机的配置
公开(公告)号：US20090056343A1
公开(公告)日：2009-03-05
申请号：US11832107
申请日：2007-08-01
申请人： Gabriel L. Suciu , Jon A. Marx , Brian D. Merry , Craig A. Nordeen , Christopher M. Dye
发明人： Gabriel L. Suciu , Jon A. Marx , Brian D. Merry , Craig A. Nordeen , Christopher M. Dye
IPC分类号： F02C7/20 , B23P11/00
CPC分类号： F02C7/20 , B64D27/18 , B64D27/26 , B64D2027/268 , Y02T50/44 , Y10T29/49826
摘要： An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle.
摘要翻译：发动机安装配置可使发动机推力在后方安装。发动机安装配置减少了发动机的主干弯曲，中间壳失真和内部机舱内的释放空间。

98. 发明申请

US20130219919A1 GAS TURBINE ENGINE BUFFER COOLING SYSTEM 有权
标题翻译：气体涡轮发动机缓冲器冷却系统
公开(公告)号：US20130219919A1
公开(公告)日：2013-08-29
申请号：US13405514
申请日：2012-02-27
申请人： Gabriel L. Suciu , loannis Alvanos
发明人： Gabriel L. Suciu , loannis Alvanos
IPC分类号： F02C6/08
CPC分类号： F02C6/08 , F01D5/081 , F01D9/065 , F02C7/18 , F02C7/185 , F05B2260/205 , Y02T50/676
摘要： A gas turbine engine includes a heat exchanger, a mid-turbine frame, a passageway that extends through at least a portion of the mid-turbine frame and a first nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The mid-turbine frame is in fluid communication with the heat exchanger. The conditioned airflow is communicated through the passageway and is received by the first nozzle assembly to condition gas turbine engine hardware.
摘要翻译：燃气涡轮发动机包括热交换器，中涡轮机架，延伸穿过中涡轮机框架的至少一部分的通道和第一喷嘴组件。热交换器与放气气流交换热量以提供调节气流。中涡轮机架与热交换器流体连通。调节气流通过通道连通并被第一喷嘴组件接收以调节燃气涡轮发动机硬件。

99. 发明申请

US20130219917A1 GAS TURBINE ENGINE BUFFER COOLING SYSTEM 有权
标题翻译：气体涡轮发动机缓冲器冷却系统
公开(公告)号：US20130219917A1
公开(公告)日：2013-08-29
申请号：US13405466
申请日：2012-02-27
申请人： Gabriel L. Suciu , loannis Alvanos
发明人： Gabriel L. Suciu , loannis Alvanos
IPC分类号： F02C6/08
CPC分类号： F02C7/185 , F01D5/081 , F01D25/125 , F02C6/08 , F02C7/06 , F05D2220/32 , F05D2260/232
摘要： A gas turbine engine includes a heat exchanger, a bearing compartment, and a nozzle assembly in fluid communication with the bearing compartment. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The bearing compartment is in fluid communication with the heat exchanger. A first passageway communicates the conditioned airflow from the heat exchanger to the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment to the nozzle assembly.
摘要翻译：燃气涡轮发动机包括热交换器，轴承室和与轴承室流体连通的喷嘴组件。热交换器与放气气流交换热量以提供调节气流。轴承室与热交换器流体连通。第一通道将经调节的气流从热交换器传递到轴承室。第二通道将经调节的气流从轴承室传送到喷嘴组件。

100. 发明申请

US20130223993A1 COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE 有权
标题翻译：带齿轮系统的逆转低压涡轮机安装在涡轮机排气箱
公开(公告)号：US20130223993A1
公开(公告)日：2013-08-29
申请号：US13408301
申请日：2012-02-29
申请人： Brian D. Merry , Gabriel L. Suciu
发明人： Brian D. Merry , Gabriel L. Suciu
IPC分类号： F01D25/00 , F01D25/24
CPC分类号： F01D15/12 , F01D1/24 , F01D25/162 , F01D25/30 , F02C3/107 , F02C7/32 , F02K3/072 , Y02T50/671
摘要： A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.
摘要翻译：燃气涡轮发动机包括限定旋转轴线的轴。外转子直接驱动轴并且包括一组外部叶片。内转子具有与外组叶片交替散布的内组叶片。内转子构造成围绕与外转子的旋转轴线相反的方向旋转。齿轮系统将内转子连接到轴，并且构造成以比外部组叶片更快的速度旋转内组叶片。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式