-
公开(公告)号：US09038367B2
公开(公告)日：2015-05-26
申请号：US13234213
申请日：2011-09-16
CPC分类号： F02K1/70 , F01D17/162 , F02K1/12 , F02K1/1207 , F02K1/72 , F05D2220/36 , F05D2250/25
摘要： A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section.
摘要翻译： 燃气涡轮发动机的风扇壳体包括围绕发动机轴线限定的风扇叶片容纳部分，叶片容纳部分下游的推力反向器级联部分和推力反向器级联部分下游的风扇出口引导叶片部分。
-
公开(公告)号：US08695920B2
公开(公告)日：2014-04-15
申请号：US13340834
申请日：2011-12-30
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
IPC分类号： B64D29/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266 , F01D25/162 , F02C3/107 , F02C7/20 , F02K3/06 , F02K3/075 , F05D2260/4031 , F05D2260/40311
摘要： A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.
摘要翻译： 燃气涡轮发动机包括沿着发动机中心线轴线驱动齿轮系的线轴，所述线轴包括低段数低压涡轮机。
-
公开(公告)号：US08672260B2
公开(公告)日：2014-03-18
申请号：US12629317
申请日：2009-12-02
IPC分类号： B64D27/00
CPC分类号： B64D27/20 , B64D27/26 , B64D2027/268 , Y02T50/44
摘要： A mounting system for a gas turbine engine assembly includes a plurality of mounting links attached the gas turbine engine along a single plane transverse to the engine centerline for separating the loads from the core engine.
摘要翻译： 用于燃气涡轮发动机组件的安装系统包括沿着与发动机中心线横向的单个平面连接燃气涡轮发动机的多个安装链路，用于将负载与核心发动机分离。
-
公开(公告)号：US08596965B2
公开(公告)日：2013-12-03
申请号：US13294492
申请日：2011-11-11
IPC分类号： F01D1/00
CPC分类号： F01D25/24 , F01D9/041 , F01D9/065 , F05D2240/12 , F05D2240/55
摘要： A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area.
摘要翻译： 用于燃气涡轮发动机的压缩机壳体支撑装置包括具有中心轴线的风扇部分和用于容纳压缩机的压缩机壳体。 入口箱将空气引导到压缩机。 压缩机壳体比入口箱更远离风扇部分。 支撑构件在风扇部分和压缩机壳体之间延伸。 支撑构件限制压缩机壳体相对于入口壳体的移动。 支撑构件比管道通路区域更远离风扇部分。
-
公开(公告)号：US08511604B2
公开(公告)日：2013-08-20
申请号：US13484400
申请日：2012-05-31
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
IPC分类号： B64D29/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
摘要翻译： 燃气涡轮发动机包括沿发动机中心线轴线驱动齿轮系的线轴。
-
公开(公告)号：US08448895B2
公开(公告)日：2013-05-28
申请号：US13484361
申请日：2012-05-31
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
IPC分类号： B64D29/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
摘要翻译： 燃气涡轮发动机包括风扇部分和包括低压压缩机部分的低阀芯。 低压压缩机部分包括八（8）个或更少的阶段。 高阀芯包括高压压缩机部分，其具有8至15（8-15）级。 整体压缩机压力比由低压压缩机部分和高压压缩机的组合提供。 齿轮系沿发动机中心线定义。 低阀芯可操作以通过齿轮系驱动风扇部分。
-
公开(公告)号：US20130108466A1
公开(公告)日：2013-05-02
申请号：US13283710
申请日：2011-10-28
CPC分类号： F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
摘要： A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
摘要翻译： 用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环，转子环限定限定第一厚度的前周向凸缘和限定第二厚度的后周向凸缘，第一厚度不同于第二厚度 。 多个核心气体路径密封件，其从转子环延伸，与斜坡界面相对。
-
公开(公告)号：US20130108445A1
公开(公告)日：2013-05-02
申请号：US13283689
申请日：2011-10-28
申请人： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
发明人： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.
摘要翻译： 用于燃气涡轮发动机的转子包括从转子盘延伸的多个叶片，所述多个叶片中的每一个叶片在接合处从转子盘延伸，所述界面沿辐条限定。
-
公开(公告)号：US20120234017A1
公开(公告)日：2012-09-20
申请号：US13483426
申请日：2012-05-30
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。
-
公开(公告)号：US08267349B2
公开(公告)日：2012-09-18
申请号：US13336140
申请日：2011-12-23
IPC分类号： B64D27/00
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。
-
-
-
-
-
-
-
-
-
搜索结果
138 条记录 (耗时 0.039 秒)
