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1. 发明专利

JP2013137021A Airfoil including compliant tip 审中-公开
标题翻译：航空包括合规提示
公开(公告)号：JP2013137021A
公开(公告)日：2013-07-11
申请号：JP2012272909
申请日：2012-12-14
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： SHAH PRANAV DHOJ , FINN SCOTT ROGER , KRAY NICHOLAS JOSEPH , PRENTICE IAN FRANCIS , SHIM DONG JIN , WANG BO
IPC分类号： F04D29/32 , F01D5/14 , F01D5/28 , F02K3/06 , F02K3/065 , F02K3/072
CPC分类号： F01D5/20 , F01D21/045 , F05D2300/43 , F05D2300/431 , F05D2300/432 , Y02T50/672 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide a fan blade that is resistant to airfoil surface strains produced during foreign object impacts.SOLUTION: The body portion 105 is configured extending radially outward from the root portion 106 and the tip portion 118 is configured extending radially outward from the root portion 106 and the body portion 105. The airfoil 102 includes a compliant tip 120 at the tip portion 118. The compliant tip 120 extends along at least a portion of the tip portion 118 in a chord-wise direction and a span-wise direction. The compliant tip 120 is configured to provide wave propagation along the tip portion 118 such that critical strain proximate the tip portion 118 and the trailing edge 116 is reduced during the foreign object impact.
摘要翻译：要解决的问题：提供一种能够抵抗在异物冲击期间产生的翼面表面应变的风扇叶片。解决方案：主体部分105构造成从根部106径向向外延伸，并且顶端部分118构造成从根部106和主体部分105.翼型件102在尖端部分118处包括柔性尖端120.柔性尖端120沿着顶端部分118的至少一部分沿弦向方向和跨度方向延伸方向。柔性尖端120被配置为沿着尖端部分118提供波传播，使得在外来物体撞击期间，靠近尖端部分118和后缘116的临界应变减小。

2. 发明专利

JPS5440912A METHOD OF OPERATING VARIABLE CYCLE ENGINE AND ITS DEVICE 失效
公开(公告)号：JPS5440912A
公开(公告)日：1979-03-31
申请号：JP9003578
申请日：1978-07-25
申请人： GEN ELECTRIC
发明人： AASAA POORU ADAMUSON , ERUMOA BUAAN SUPURANGAA
IPC分类号： F02K3/04 , F02C6/00 , F02K3/065 , F02K3/075 , F02K3/08 , F02K3/10

3. 发明专利

JP2007182873A Thrust augmenting device and its method, and exhaust nozzle 审中-公开
标题翻译： THRUST AUGMENTING DEVICE及其方法和排气喷嘴
公开(公告)号：JP2007182873A
公开(公告)日：2007-07-19
申请号：JP2006327808
申请日：2006-12-05
申请人： United Technol Corp , ユナイテッドテクノロジーズコーポレイションUnited Technologies Corporation
发明人： SMITH JESSE W
IPC分类号： F02K1/00 , F02K3/065 , F02K3/10 , F23R3/18 , F23R3/28
CPC分类号： F02K3/10 , F02K3/11 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a thrust augmenting device for a turbofan engine with simplified structure at low cost.
SOLUTION: The thrust augmenting device 12 for a mixed exhaust turbofan engine 10 comprises an augmentation duct 34, a combustion system and a fixed area exhaust nozzle 26. The augmentation duct 34 receives primary and secondary air of the turbofan engine 10 and is positioned co-axially with an exhaust case of the turbofan engine 10. The combustion system increases the thrust produced by the mixed exhaust flow of the turbofan engine 10. The fixed area exhaust nozzle 26 has a throat area larger than that which would maximize the non-augmented thrust. Therefore, the thrust augmentation system 12 efficiently increases the thrust.
COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：以低成本提供具有简化结构的涡轮风扇发动机的推力增大装置。解决方案：用于混合排气涡扇风扇发动机10的推力增大装置12包括增压管道34，燃烧系统和固定区域排气喷嘴26.增压管道34接收涡轮风扇发动机10的初级和次级空气，并且是与涡轮风扇发动机10的排气箱同轴地定位。燃烧系统增加了涡轮风扇发动机10的混合排气流产生的推力。固定区域排气喷嘴26的喉部面积大于最大化非涡轮风扇被推挤的推力。因此，推力增加系统12有效地增加推力。版权所有（C）2007，JPO＆INPIT

4. 发明专利

JPH065038B2 失效
公开(公告)号：JPH065038B2
公开(公告)日：1994-01-19
申请号：JP10277090
申请日：1990-04-18
申请人： NASHIONARU DECHUUDO E DO KONSUTORYUKUSHION DE MOTOORU DABIASHION SOC
发明人： ARAN MARII JOZEFU RARUDORIE
IPC分类号： F02C3/067 , F02C3/073 , F02K3/065 , F02K3/072 , F02K3/077

5. 发明专利

JPS5439718A TURBOOFAN ENGINE 失效
公开(公告)号：JPS5439718A
公开(公告)日：1979-03-27
申请号：JP9003478
申请日：1978-07-25
申请人： GEN ELECTRIC
发明人： AASAA POORU ADAMUSON
IPC分类号： B62K19/16 , B64C29/00 , F02K1/00 , F02K1/78 , F02K3/02 , F02K3/065

6. 发明专利

JP2009215895A High bypass-ratio turbofan jet engine 有权
标题翻译：高比例涡轮喷气式发动机
公开(公告)号：JP2009215895A
公开(公告)日：2009-09-24
申请号：JP2008057474
申请日：2008-03-07
申请人： Japan Aerospace Exploration Agency , 独立行政法人宇宙航空研究開発機構
发明人： YANAGI RYOJI , FUJIWARA HITOSHI
IPC分类号： F02K3/065 , F02C7/04 , F02C7/042
CPC分类号： F02K3/065 , B64C7/02 , B64D29/02 , F02C7/04 , F05D2250/14 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a turbofan jet engine which is capable of increasing a bypass ratio without increasing a fan diameter and of reducing air resistance acting on the engine.
SOLUTION: In a high-bypass ratio turbofan jet engine, front-fan flow ducts 20a, 20b for discharging compressed air compressed by a front fan 10 to the open air, and aft-fan flow ducts 50a, 50b for introducing air to an aft-fan 40 are disposed so as to change cross-sectional shapes thereof by rorating around a core engine 30 in a counterclockwise direction, so that the geometrical relationship between the front-fan flow ducts 20a, 20b and the aft-fan flow ducts 50a, 50b is inverted, in a section 1 immediately posterior to the front-fan 10 and a section 11 immediately anterior to the aft-fan 40.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够增加旁路比而不增加风扇直径并降低作用在发动机上的空气阻力的涡轮风扇喷气发动机。解决方案：在高旁通比涡轮风扇喷气发动机中，用于将由前风扇10压缩的压缩空气排放到开放空气的前风扇流道20a，20b，以及用于引入空气的后风扇流动管道50a，50b 后风扇40被设置成通过围绕芯发动机30沿逆时针方向旋转来改变其横截面形状，使得前风扇流动管20a，20b与后风扇流之间的几何关系管道50a，50b在紧邻前风扇10的正后方的部分1中和在后风扇40正前方的部分11处倒置。（C）2009，JPO＆INPIT

7. 发明专利

JP2005155621A Rear flade type engine 有权
标题翻译：后缘型发动机
公开(公告)号：JP2005155621A
公开(公告)日：2005-06-16
申请号：JP2004336213
申请日：2004-11-19
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 EDWARD
IPC分类号： F02K3/077 , F02K3/062 , F02K3/065
CPC分类号： F02K3/077 , F02K1/386 , F02K3/065 , F05D2220/327 , F05D2250/611
摘要： PROBLEM TO BE SOLVED: To provide a rear FLADE type engine for an aircraft.
SOLUTION: The rear FLADE type gas turbine engine 1 comprises a fan section 115 drivenly connected to a low pressure turbine section 150, a core engine 18 installed between the fan section 115 and the low pressure turbine section 150, a fan bypass duct 40 encircling the core engine 18 in fluid communication with the fan section, a mixer 49 installed on the downstream side of the low pressure turbine section in fluid communication with the fan bypass duct, and a rear FLADE turbine 160 installed on the downstream side of the mixer. At least one train of rear FLADE fan blades 5 are installed on the radial outside of the rear FLADE turbine and joined to the rear FLADE turbine, and they radially extend across a FLADE duct 3 encircling the fan bypass duct.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：为飞机提供后FLADE型发动机。解决方案：后部FLADE型燃气涡轮发动机1包括驱动地连接到低压涡轮机部分150的风扇部分115，安装在风扇部分115和低压涡轮机部分150之间的核心发动机18，风扇旁通管围绕与风扇部分流体连通的核心发动机18;安装在低压涡轮机部分与风扇旁通管道流体连通的下游侧的混合器49以及安装在风扇旁路管道的下游侧的后部FLADE涡轮机160 混合器。至少一列后面的FLADE风扇叶片5安装在后FLADE涡轮机的径向外侧并且连接到后FLADE涡轮机，并且它们径向延伸穿过环绕风扇旁路管道的FLADE管道3。版权所有（C）2005，JPO＆NCIPI

8. 发明专利

JP2001207911A DUCT DEVICE FOR GAS TURBINE ENGINE 失效
公开(公告)号：JP2001207911A
公开(公告)日：2001-08-03
申请号：JP2000396998
申请日：2000-12-27
申请人： UNITED TECHNOLOGIES CORP
发明人： GUINAN DANIEL P , HUBER DAVID J , PERKINS GARY M
IPC分类号： F02C7/00 , F02C7/04 , F02K3/065 , F02K3/077 , F04D25/16 , F04D29/54
摘要： PROBLEM TO BE SOLVED: To provide a duct device capable of increasing an air flow rate passing a fan part of a gas turbine engine without increasing a diameter of a fan. SOLUTION: This duct device 10 used in the gas turbine engine 100 having two fans 102, 104 connected to a common shaft includes one primary inlet duct 12 integrated with four primary discharge ducts 14, 16, 18, 20 and two secondary inlet ducts 32, 34 integrated with one secondary discharge duct 36. Each of the ducts includes a port, the ports 38, 40 of the secondary inlet ducts 32, 34 are arranged outside in the radial direction of a port 22 of the primary inlet duct 12 and the ports 24, 26, 28, 30 of the primary discharge ducts 14, 16, 18, 20 are arranged outside in the radial direction of a port 42 of the secondary discharge duct 36.

9. 发明专利

JPH0361621A HIGH BYPASS RATIO TURBOJET ENGINE WITH REVERSAL UPSTREAM AND DOWNSTREAM FAN 失效
公开(公告)号：JPH0361621A
公开(公告)日：1991-03-18
申请号：JP10277090
申请日：1990-04-18
申请人： SNECMA
发明人： ARAN MARII JIYOZEFU RARUDORIE
IPC分类号： F02C3/067 , F02C3/073 , F02K3/065 , F02K3/072 , F02K3/077
摘要： PURPOSE: To reduce a cross-sectional area as well as overall dimensions while obtaining a high by-pass ratio by providing two separate overlapped channels for cold air. CONSTITUTION: An engine is furnished with two separate overlapped channels for cold air. A first cold air channel has an air intake port E1 common with a first air current through an upstream fan 1 and to a gas generator and two crescent/outlets S1 set on the outside sideward of an outlet S2 from a downstream fan 12. Additionally, a second cold air channel has two crescent air intake ports E2 set on the outside sideward of the air intake port E1, a ring passage 27 starting from the air intake port E2 and in which the downstream fan 12 is set and an outlet S2 from the downstream fan 12. The upstream fan 1 and the downstream fan 12 have a high by-pass ratio by the two channels. Additionally, as a part of the two channels is formed in a nacelle structural body, it is possible to reduce overall dimensions and a cross-sectional area of the engine.

10. 发明专利

JP5092143B2 High-bypass ratio turbofan jet engine 有权
公开(公告)号：JP5092143B2
公开(公告)日：2012-12-05
申请号：JP2008057474
申请日：2008-03-07
申请人：独立行政法人宇宙航空研究開発機構
发明人：良二柳 , 仁志藤原
IPC分类号： F02K3/065 , F02C7/04
CPC分类号： F02K3/065 , B64C7/02 , B64D29/02 , F02C7/04 , F05D2250/14 , Y02T50/671

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