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1. 发明专利

JP2006125387A Double reverse turbine engine, and method for assembling the same 有权
标题翻译：双向涡轮发动机及其装配方法
公开(公告)号：JP2006125387A
公开(公告)日：2006-05-18
申请号：JP2005245340
申请日：2005-08-26
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： SEDA JORGE F , MONIZ THOMAS ORY , BUTLER LAWRENCE
IPC分类号： F02C3/067 , F01D1/24 , F01D25/16 , F02C7/06 , F04D25/16 , F04D29/056
CPC分类号： F16C17/024 , F01D1/24 , F01D25/16 , F02C3/067 , F02K3/072 , F05D2240/53 , F16C17/18 , F16C2360/23
摘要： PROBLEM TO BE SOLVED: To provide a method for assembling a gas turbine engine 10. SOLUTION: This method includes a step of preparing a low pressure turbine inner rotor 42 composed to rotate in a first rotation direction, a step of preparing a low pressure turbine outer rotor 38 composed to rotate in a second rotation direction that is opposite to the first rotation direction, and a step of coupling at least one foil bearing 100 to at least one of the inner and the outer rotors for improving gap control between a first rotational component part or a second rotational component part and at least one non-rotational component part. COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：解决方案：提供一种用于组装燃气涡轮发动机10的方法。解决方案：该方法包括制备组成沿第一旋转方向旋转的低压涡轮内转子42的步骤，步骤制备构成为沿与第一旋转方向相反的第二旋转方向旋转的低压涡轮机外转子38以及将至少一个箔轴承100连接到内转子和外转子中的至少一个的步骤，以改善第一旋转分量部分或第二旋转分量部分与至少一个非旋转分量部分之间的间隙控制。版权所有（C）2006，JPO＆NCIPI

2. 发明专利

JP2006125386A Counter-rotating turbine engine, and method for assembling the same 有权
标题翻译：逆向涡轮发动机及其装配方法
公开(公告)号：JP2006125386A
公开(公告)日：2006-05-18
申请号：JP2005245339
申请日：2005-08-26
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： MONIZ THOMAS O , SEDA JORGE F
IPC分类号： F01D25/18 , F01D25/16 , F01D25/20 , F02C7/06 , F02K3/072 , F16C33/66 , F16N7/38
CPC分类号： F04D29/063 , F01D25/18 , F01D25/20 , F02K3/072 , F05D2250/232
摘要： PROBLEM TO BE SOLVED: To provide a method for assembling a gas turbine engine 10.
SOLUTION: This method comprises a step of providing a first fan assembly 12 composed to rotate in a first rotation direction, a step of coupling a second fan assembly 14 composed to rotate in a second rotation direction that is opposite to the first rotation direction to the first fan assembly in a rotatable state, and a step of coupling a lubrication system 150 to the gas turbine engine in such a way that lubricating fluid is sent through at least part of the second fan assembly.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于组装燃气涡轮发动机10的方法。解决方案：该方法包括提供第一风扇组件12的步骤，第一风扇组件12构成为沿第一旋转方向旋转，第二风扇组件14，其被构造成在可旋转状态下沿与第一旋转方向相反的第二旋转方向旋转到第一风扇组件;以及将润滑系统150连接到燃气涡轮发动机的步骤，润滑流体通过第二风扇组件的至少一部分被送出。版权所有（C）2006，JPO＆NCIPI

3. 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

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