专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明专利

JP2006132533A Flade type gas turbine engine and aircraft 有权
标题翻译：流体式涡轮发动机和飞机
公开(公告)号：JP2006132533A
公开(公告)日：2006-05-25
申请号：JP2005312090
申请日：2005-10-27
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： BAUGHMAN JOHN LEWIS , JOHNSON JAMES E
IPC分类号： F02K3/06 , B64D27/20 , F02K1/78 , F02K3/075
CPC分类号： F02K3/062 , F01D5/022 , F02C3/13 , F02K3/075 , F02K3/077
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine engine for a FLADE type aircraft being not complicated, not heavy, not bulky or not expensive and being very effective for thrust deflection.
SOLUTION: This aft FLADE type gas turbine engine 1 includes a fan section 115 in which an aft FLADE turbine 160 having at least one row of aft FLADE fan blades 5 connected with a low pressure turbine section 150 in a driven manner and extending in the radial direction by crossing a FLADE duct 3 surrounding the aft FLADE turbine 160 follows it and at least one thrust deflection nozzle 123 communicating with the FLADE duct 3 to receive a stream of pressurized fluid.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于FLADE型飞机的燃气涡轮发动机，其不复杂，不重，不笨重或不昂贵，并且对于推力偏转非常有效。解决方案：这种FLADE型燃气涡轮发动机1包括风扇部分115，其中具有至少一排后FLADE风扇叶片5的后FLADE涡轮机160以驱动方式与低压涡轮部分150连接并延伸通过使围绕后方FLADE涡轮机160的FLADE管道3与径向方向相交，并且与至少一个与FLADE管道3连通以接收加压流体流的推力偏转喷嘴123。版权所有（C）2006，JPO＆NCIPI

2. 发明专利

JP2008151134A Duct burning mixed flow turbofan 有权
标题翻译： DUCT BURNING混合流量涡轮膨胀
公开(公告)号：JP2008151134A
公开(公告)日：2008-07-03
申请号：JP2007324194
申请日：2007-12-17
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： JOHNSON JAMES E , STEINMETZ RONALD B
IPC分类号： F02K3/105 , F02C7/00 , F02K1/06 , F02K3/075 , F02K3/115
CPC分类号： F02K1/82 , F02K3/06 , F02K3/077 , F02K3/11 , F02K3/115
摘要： PROBLEM TO BE SOLVED: To provide a duct burning mixed flow turbofan, and its operation method. SOLUTION: A gas turbine engine 10 includes a turbomachinery core 28 having an exit plane E, and operable to generate a first flow of pressurized combustion gases; a fan 14 disposed upstream of the core 28, and adapted to extract energy from the core 28 and generate a first flow of pressurized air; a bypass duct 30 surrounding the core 28, and receiving a portion of the flow of pressurized air from the fan 14; a duct burner 32 disposed in the bypass duct, upstream of the exit plane E, for receiving the first flow of pressurized air and generating a second flow of pressurized combustion gases; and an exhaust duct 38 disposed downstream of the core 28 and operable to receive the first and second flows of pressurized combustion gases and to discharge the combined flows in the downstream direction. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供管道燃烧混流涡轮风扇及其操作方法。解决方案：燃气涡轮发动机10包括具有出口平面E的涡轮机械芯28，并可操作以产生第一流的加压燃烧气体; 风扇14，设置在芯28的上游，并且适于从芯28提取能量并产生第一压缩空气流; 围绕芯28的旁路管道30，并且接收来自风扇14的加压空气流的一部分; 设置在旁路管道中的管道燃烧器32，在出口平面E的上游，用于接收第一流量的加压空气并产生第二加压燃烧气体流; 以及设置在芯28的下游并且可操作以接收第一和第二加压燃烧气体流并沿下游方向排出组合流的排气管道38。版权所有（C）2008，JPO＆INPIT

3. 发明专利

JP2006105138A Method and apparatus for assembling gas turbine engine 有权
标题翻译：用于组装气体涡轮发动机的方法和装置
公开(公告)号：JP2006105138A
公开(公告)日：2006-04-20
申请号：JP2005283188
申请日：2005-09-29
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： JOHNSON JAMES E
IPC分类号： F02K3/06 , F02K1/78
CPC分类号： F02K3/077 , F02C7/042 , F02K3/075 , F02K7/16
摘要： PROBLEM TO BE SOLVED: To provide a flade system for a gas turbine engine.
SOLUTION: The gas turbine engine (12) includes a core engine provided with an inner fan duct (28) for channeling an air flow through a portion of the core engine and with an inner fan section (34) including at least one row of inner fan blades (40) positioned inside the inner fan duct (28). This flade system includes a flade duct (26) surrounding the inner fan duct (28) and forming a flade stream (74); a flade type fan (88) including a row of flade type fan blades (90) positioned radially outward of the inner fan section (34) and coupled to the inner fan section (34) so as to be driven by the inner fan section (34), positioned inside the flade duct (26) and producing a flade stream air flow (74); and a flade stream augmentor (110) arranged inside the flade duct (26).
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于燃气涡轮发动机的叶片系统。燃气涡轮发动机（12）包括具有内部风扇管道（28）的核心发动机，内部风扇管道（28）用于将空气流引导通过核心发动机的一部分，并且内部风扇部分（34）包括至少一个位于内部风扇管道（28）内部的一列内部风扇叶片（40）。该落叶系统包括围绕内部风扇管道（28）并形成叶轮（74）的叶轮（26）; 一种排风扇（88），包括位于内风扇部分（34）的径向外侧的一排排列式风扇叶片（90），并连接到内风扇部分（34），以便被内风扇部分 34），其位于所述叶片管道（26）内并产生落叶气流（74）; 以及布置在所述花式管道（26）内的落叶加注器（110）。版权所有（C）2006，JPO＆NCIPI

4. 发明专利

JP2008163945A Convertible gas turbine engine 有权
标题翻译：可燃气体涡轮发动机
公开(公告)号：JP2008163945A
公开(公告)日：2008-07-17
申请号：JP2007335456
申请日：2007-12-27
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： JOHNSON JAMES E
IPC分类号： F02K3/075 , F02K1/38
CPC分类号： F02K3/075 , F02K3/06
摘要： PROBLEM TO BE SOLVED: To provide a convertible gas turbine engine.
SOLUTION: This gas turbine engine 10 includes: a turbomachinery core 14A operable to generate a flow of pressurized combustion gases at a variable flow rate, while maintaining a substantially constant core pressure ratio; a rotating fan 12 disposed upstream of the core 14A, which is adapted to extract energy from the core 14A and generate a first flow of air which is compressed at a first pressure ratio; and at least a first bypass duct 38 surrounding the core downstream of the fan, adapted to selectively receive at least a first selected portion of the first flow which is compressed at a second pressure ratio lower than the first pressure ratio, and to bypass the first selected portion around the core 14A, thereby varying a bypass ratio of the engine 10. The fan 12 is adapted to maintain a flow rate of the first flow substantially constant independent of the bypass ratio.
COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供一种可转换燃气轮机。解决方案：该燃气涡轮发动机10包括：涡轮机械芯14A，其可操作以在可变流量下产生加压燃烧气体流，同时保持基本上恒定的芯压比; 设置在芯部14A上游的旋转风扇12，其适于从芯部14A提取能量并产生以第一压力比压缩的第一空气流; 以及至少第一旁路管道38，其围绕所述风扇下游的核心，适于选择性地接收以低于所述第一压力比的第二压力比压缩的所述第一流动的至少第一选定部分，并绕过所述第一流量选择部分，从而改变发动机10的旁路比。风扇12适于保持第一流量的流量基本上恒定，而与旁路比无关。版权所有（C）2008，JPO＆INPIT

5. 发明专利

JP2008151135A Turbine engine with flow control fan, and its operation method 有权
标题翻译：具有流量控制风扇的涡轮发动机及其运行方法
公开(公告)号：JP2008151135A
公开(公告)日：2008-07-03
申请号：JP2007324196
申请日：2007-12-17
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： JOHNSON JAMES E
IPC分类号： F02K1/78 , F02C6/08 , F02C7/00 , F02K3/075 , F04D29/32
CPC分类号： F02K3/075
摘要： PROBLEM TO BE SOLVED: To provide a turbine engine with a flow control fan, and its operation method. SOLUTION: This gas turbine engine 10 includes a turbomachinery core 28 operable to generate a flow of pressurized combustion gases; a rotating fan 14 adapted to extract energy from the core 28 and generate a first flow of pressurized air; a fan stator assembly 32, 36 connected in fluid communication with the fan 14 and operable to vary the first flow of pressurized air while the fan 14 operates at a substantially constant speed; a fan outer duct 48 surrounding the core 28; and a flade stage 44 comprising a supplementary fan disposed in the fan outer duct 48 and driven by the fan 14 for generating a pressurized bleed air flow. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：为涡轮发动机提供流量控制风扇及其运行方法。解决方案：该燃气涡轮发动机10包括可操作以产生加压燃烧气体流的涡轮机械芯28; 适于从芯28提取能量并产生第一压缩空气流的旋转风扇14; 风扇定子组件32,36与风扇14流体连通并且可操作以在风扇14以基本恒定的速度运行时改变第一加压空气流; 围绕芯28的风扇外管48; 以及落叶台44，其包括设置在风扇外部管道48中并由风扇14驱动的辅助风扇，用于产生加压的排气流。版权所有（C）2008，JPO＆INPIT

6. 发明专利

JP2007247645A High pressure ratio aft fan assembly and gas turbine engine 有权
标题翻译：高压比AFT风扇组件和气体涡轮发动机
公开(公告)号：JP2007247645A
公开(公告)日：2007-09-27
申请号：JP2007062894
申请日：2007-03-13
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： GIFFIN ROLLIN GEORGE , JOHNSON JAMES E
IPC分类号： F02K3/062 , F04D29/32
CPC分类号： F02K3/062 , F02C3/073 , F02C7/042 , F05D2240/80 , Y02T50/672
摘要： PROBLEM TO BE SOLVED: To provide a structure of fans arranged on a turbine for realizing a high pressure ratio. SOLUTION: The fan assembly (30) of a gas turbine engine (10) consists of a turbine rotor (36) arranged in the aft of the core (20) of the gas turbine engine (10); a row of turbine blades (42) carried by the rotor (36) and extending from it toward its leading end (52) respectively, each turbine moving blade (42) includes a row of turbine moving blades (42) extracting energy from the steam of pressurized combustion gas generated by the core (20); and at least two radially extending and axially separated rows of fan moving blades (62, 72) carried by and rotating together with the row of turbine blades (42). COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：提供一种布置在涡轮机上以实现高压比的风扇的结构。燃气涡轮发动机（10）的风扇组件（30）由布置在燃气涡轮发动机（10）的核心（20）的后部的涡轮机转子（36）组成。一列涡轮机叶片（42）由转子（36）承载并分别从其延伸到其前端（52），每个涡轮机动叶片（42）包括一排涡轮机动叶片（42），从蒸汽中提取能量由所述芯（20）产生的加压燃烧气体; 以及至少两个径向延伸且轴向分离的扇形叶片（62,72）的行，与所述一列涡轮机叶片（42）一起承载并与之一起旋转。版权所有（C）2007，JPO＆INPIT

7. 发明专利

JP2013199936A Turbine engine with modulated flow fan and method of operation therefor 有权
标题翻译：具有调节流量风扇的涡轮发动机及其运行方法
公开(公告)号：JP2013199936A
公开(公告)日：2013-10-03
申请号：JP2013132195
申请日：2013-06-25
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： JOHNSON JAMES E
IPC分类号： F02K3/075 , F02C7/00 , F02C7/042
CPC分类号： F02K3/075
摘要： PROBLEM TO BE SOLVED: To provide a turbine engine with a modulated flow fan and a method of operation therefor.SOLUTION: A gas turbine engine (10) includes: a turbomachinery core (28) operable to generate a flow of pressurized combustion gases; a rotating fan (14) adapted to extract energy from the core (28) and generate a first flow of pressurized air; a fan stator assembly (32, 36) connected in flow communication with the fan (14) and operable to vary the first flow of pressurized air while the fan (14) operates at a substantially constant speed; a fan outer duct (48) surrounding the core (28); and a flade stage (44) comprising a supplementary fan disposed in the fan outer duct (48) and driven by the fan (14) for generating a pressurized bleed air flow.
摘要翻译：要解决的问题：提供一种具有调制流动风扇的涡轮发动机及其操作方法。解决方案：燃气涡轮发动机（10）包括：涡轮机械芯（28），其可操作以产生加压燃烧气体流; 旋转风扇（14），其适于从所述芯（28）提取能量并产生第一压缩空气流; 风扇定子组件（32,36），其与所述风扇（14）流体连通地连接并且可操作以在所述风扇（14）以基本恒定的速度运行时改变所述第一加压空气流; 围绕所述芯（28）的风扇外管（48）; 以及包括设置在所述风扇外部管道（48）中并由所述风扇（14）驱动以用于产生加压的排出气流的补充风扇的落叶台（44）。

8. 发明专利

JP2003286857A Double-inverted aircraft gas turbine engine provided with compressor with high total pressure ratio 审中-公开
标题翻译：具有高压总压比的压缩机提供的双重反转的飞机燃气涡轮发动机
公开(公告)号：JP2003286857A
公开(公告)日：2003-10-10
申请号：JP2003055273
申请日：2003-03-03
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： SEDA JORGE F , DUNBAR LAWRENCE W , SZUCS PETER N , BRAUER JOHN C , JOHNSON JAMES E
IPC分类号： F02C3/067 , F01D5/03 , F02K3/06 , F02K3/072 , F04D19/02 , F04D29/38
CPC分类号： F04D19/024 , F01D5/03 , F02K3/072 , F05D2240/12 , F05D2250/52 , Y02T50/672 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide a double-inverted aircraft gas turbine engine having the high by-pass ratio, high overall pressure ratio of a compressor and the small ratio of inner and outer diameters.
SOLUTION: Shafts 130, 140 on a low pressure side and on a high pressure side are connected to blade trains 13, 15 of first and second fans and first and second boosters 16, 17 in a drive relation, respectively. A by-pass duct 21 radially demarcated by a fan casing 11 and an annular by-pass duct wall 9 on radially inward side surrounds the booster disposed in the axial position between the blade train 13 of the first fan and the blade train 15 of the second fan. The engine 10 includes a high pressure compressor 18 such that the overall pressure ratio ranges between 40 and 65, the ratio of the inner and outer diameters in an inlet (RH/RT) of the fan ranging from 0.20 to 0.35, the by-pass ratio ranging from 5 to 15, the pressure ratio of the fan ranging between 1.4 and 2.5, and the total of the tip velocity of the fan operating in a region between 1,000 and 2,500 ft/s.
COPYRIGHT: (C)2004,JPO
摘要翻译：要解决的问题：提供具有高旁路比，压缩机总压比高，内外径小的双反型飞机燃气轮机。解决方案：低压侧和高压侧的轴130,140分别以驱动关系连接到第一和第二风扇和第一和第二增压器16,17的叶片列车13,15。由风扇壳体11径向划分的旁通管道21和位于径向内侧的环形旁通管道壁9围绕设置在第一风扇的叶片系列13与第一风扇叶片系列15之间的轴向位置的增压器第二扇发动机10包括高压压缩机18，使得总体压力比范围在40和65之间，风扇的入口内径和外径之比（RH / RT）在0.20至0.35之间，旁路比例范围为5至15，风扇的压力比范围在1.4和2.5之间，风扇的尖端速度的总和在1000和2,500英尺/秒之间的区域中运行。版权所有（C）2004，JPO

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