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2. 发明专利

JP2012067738A Low noise supersonic propeller 审中-公开
标题翻译：低噪声超音速螺旋桨
公开(公告)号：JP2012067738A
公开(公告)日：2012-04-05
申请号：JP2010230042
申请日：2010-09-24
申请人： Isamu Nemoto , 勇根本
发明人： NEMOTO ISAMU
IPC分类号： F02K3/075 , F02C9/22 , F02K1/08 , F02K1/36 , F02K3/06
摘要： PROBLEM TO BE SOLVED: To compensate a thrust loss occurring owing to mixing, by enhancing a thrust without speeding up exhaust in such a way to increase an engine flow rate, in a mixer ejector nozzle reducing an exhaust jetting speed by taking in the outer air and mixing it with engine exhaust so that the jetting noise of a supersonic propeller is reduced.SOLUTION: The low pressure turbine stator vane of a low bypass ratio turbo fan is made variable; a tail cone movable forward and back is equipped in a core duct outlet in the downstream of the low pressure turbine; and the low pressure turbine variable stator vane is narrowed down in the takeoff so as to choke the low pressure turbine. At the same time, the tail cone is moved so as to expand a core duct outlet area, and to increase the expansion ratio of the low pressure turbine. By the combination of the two variable mechanisms, a fan air flow rate is increased by enhancing the number of fan revolutions, so that the thrust is increased without increasing a fuel flow rate.
摘要翻译：要解决的问题：为了补偿由于混合而产生的推力损失，通过增加推力而不加速排气以增加发动机流量，在混合器喷射器喷嘴中，通过吸入减少排气喷射速度外部空气并与发动机排气混合，从而减少了超音速螺旋桨的喷射噪音。
解决方案：低旁路比涡轮风扇的低压涡轮机定子叶片可变; 在低压涡轮机的下游的核心管道出口处装有可前后移动的尾锥; 并且低压涡轮机可变定子叶片在起飞时变窄，以便扼流低压涡轮机。同时，尾锥移动以扩大芯管出口面积，并增加低压涡轮机的膨胀比。通过两个可变机构的组合，通过增加风扇转数来增加风扇空气流量，从而在不增加燃料流量的情况下增加推力。版权所有（C）2012，JPO＆INPIT

3. 发明专利

JP4875854B2 Split shroud-type exhaust nozzle 有权
公开(公告)号：JP4875854B2
公开(公告)日：2012-02-15
申请号：JP2005147696
申请日：2005-05-20
申请人：ゼネラル・エレクトリック・カンパニイ
发明人：バーナード・ジェームズ・レングリ
IPC分类号： F02K1/09 , B64G99/00 , F02K1/08
CPC分类号： F02K1/09 , F02K1/386 , F05D2250/11 , F05D2250/311 , Y02T50/671

4. 发明专利

JP2006037949A Divided shroud type exhaust nozzle 有权
标题翻译： DIVIDED SHROUD型排气喷嘴
公开(公告)号：JP2006037949A
公开(公告)日：2006-02-09
申请号：JP2005147696
申请日：2005-05-20
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： RENGGLI BERNARD J
IPC分类号： F02K1/09 , B64G99/00 , F02K1/08
CPC分类号： F02K1/09 , F02K1/386 , F05D2250/11 , F05D2250/311 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a variable convergent-divergent type nozzle for a gas turbine engine.
SOLUTION: This nozzle 30 comprises a center body 32 having a large diameter throat section and extending rearward along the longitudinal direction of the engine. An inner shroud 34 surrounds the center body 32, and forms the throat of the nozzle 3 in association of the center body 32. An outer shroud 36 surrounds the inner shroud 34 and forms the outlet area of the nozzle 30 in association with the center body 32. Both shrouds are movable parallel with each other so as to independently control a nozzle throat area and a nozzle expansion ratio.
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可变会聚发散型喷嘴。解决方案：该喷嘴30包括具有大直径喉部并沿着发动机的纵向方向向后延伸的中心体32。内护罩34围绕中心体32，并且与中心体32相关联地形成喷嘴3的喉部。外护罩36围绕内护罩34并与中心体相关联地形成喷嘴30的出口区域两个护罩可彼此平行地移动，以独立地控制喷嘴喉部区域和喷嘴膨胀比。版权所有（C）2006，JPO＆NCIPI

5. 发明专利

JP3219177B2 失效
公开(公告)号：JP3219177B2
公开(公告)日：2001-10-15
申请号：JP9038494
申请日：1994-04-28
IPC分类号： F02K1/08 , F02K3/06 , F02K3/075 , F02K7/16

6. 发明专利

JP2643551B2 失效
公开(公告)号：JP2643551B2
公开(公告)日：1997-08-20
申请号：JP17925890
申请日：1990-07-06
申请人： NITSUSAN JIDOSHA KK
发明人： FUNAKI KATSUMI
IPC分类号： F02C7/042 , F02C7/057 , F02K1/08 , F02K7/10

7. 发明专利

JPH09195853A VARIABLE AREA FAN EXHAUST NOZZLE 失效
公开(公告)号：JPH09195853A
公开(公告)日：1997-07-29
申请号：JP33260596
申请日：1996-12-13
申请人： UNITED TECHNOLOGIES CORP
发明人： POORU DABURIYUU DOUESURAA , KONSUTANTEIINO BUI ROFUREDO , HARORUDO TEII PUROTSUSAA JIYUN , KURISUTOFUAA DABURIYUU JIYOONZ
IPC分类号： F02K1/08 , F02K1/09 , F02K1/72 , F02K3/06
摘要： PROBLEM TO BE SOLVED: To provide a high power gas turbine engine of which weight is minimized, noise is lowered and the energy consumption is lessened. SOLUTION: A gas turbine engine has a displaceable sleeve 38 and the displaceable sleeve 38 is positioned in the downstream side of an outside nacelle 20. A variable area fan exhaust nozzle 30 is installed between the rear edge 32 of the displaceable sleeve 38 and a core cowl 26 having a conical shape and the core cowl 26 is installed in the inside in the radius direction of the outside nacelle 20 while being parted from the nacelle. The displaceable sleeve 38 can be displaced to the downstream side and together with the core cowl 26 whose diameter is decreased, the sleeve increases the area of the fan exhaust nozzle 30.

8. 发明专利

JPH07247905A LINER STRUCTURE OF EXHAUST NOZZLE FOR SUPERSONIC AIRCRAFT 失效
公开(公告)号：JPH07247905A
公开(公告)日：1995-09-26
申请号：JP4067794
申请日：1994-03-11
申请人： ISHIKAWAJIMA HARIMA HEAVY IND
发明人： OISHI TSUTOMU , NAKAMURA YOSHINARI
IPC分类号： F02K1/08 , F02K1/82
摘要： PURPOSE:To efficiently reduce the noise of a target frequency by making the liner structure of an exhaust nozzle to form the flowing passage for a high speed gas flow from a core engine in such a way that a cold/hot air is supplied in the exhaust nozzle through air introduction holes, a noise eliminating chamber and noise eliminating holes. CONSTITUTION:This liner structure is provided with a honeycomb structural material 14 having a plurality of independent noise eliminating chambers 13 which form the inner surface of an exhaust nozzle and support from inner sides, inner wall plates 12 having a plurality of noise eliminating through holes 11, and the honeycomb structural materials 14 are supported by reflectors 16 having plurality of air introduction through holes 15. An air chamber 18 into which cold/hot air is supplied from a core engine is on the inner side of the reflectors 16. The inner wall plates 12 to be directly exposed to a high- temperature jet stream after mixing is formed by materials having high heat resistance, and the honeycomb structural material 14 is formed form a material whose inside is partitioned in a hexagonal shape or rectangular shape by thin metallic plates.

9. 发明专利

JP2009057955A Inter-turbine-bypass variable-cycle engine for supersonic aircraft 审中-公开
标题翻译：用于超级飞机的涡轮机 - 旁通可变循环发动机
公开(公告)号：JP2009057955A
公开(公告)日：2009-03-19
申请号：JP2007250151
申请日：2007-08-29
申请人： Isamu Nemoto , 勇根本
发明人： NEMOTO ISAMU
IPC分类号： F02K3/075 , F02C9/18 , F02K1/08 , F02K1/48 , F02K3/06
摘要： PROBLEM TO BE SOLVED: To provide, without provision of an after-burner, an inter-turbine bypass variable-cycle engine as an environmentally friendly supersonic engine wherein, as practicable technology, mixing of three flows is accomplished by overcoming difficulties in obtaining a bypass ratio higher than that is previously possible, and bleeding is effected from between the high/low pressure turbines, and the bleed is reintroduced in an exhaust duct by bypassing the low pressure turbine (LPT), and such a problem is resolved that the total pressure of the bleed gas is higher than LPT-outlet gas or the fan bypass-flow to incur serious loss.
SOLUTION: In a first mixing system, a tail cone is moved to and fro to make variable the outlet area of the core to mix thereby the three flows at equal static pressures. In a second system, a double-lobe mixer is employed to allow LPT bleed to flow in a state of spokes between the double lobes to achieve a big-scale mixing by enlarging the contact surfaces of the flows.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：为了提供一种作为环境友好的超音速发动机的涡轮机旁路可变循环发动机，不需要后燃烧器，其中在实际可行的技术中，三个流的混合是通过克服困难而实现的获得高于先前可能的旁路比，并且从高压/低压涡轮机之间进行渗流，并且通过旁路低压涡轮机（LPT）将排放物重新引入排气管道，并且这样的问题被解决为排放气体的总压力高于LPT出口气体或风扇旁路流量，造成严重损失。解决方案：在第一混合系统中，尾锥来回移动，使芯的出口面积变化，从而混合三相流等静压力。在第二系统中，使用双叶混合器以允许LPT渗流在双瓣之间的轮辐状态下流动，以通过扩大流动的接触表面来实现大规模的混合。版权所有（C）2009，JPO＆INPIT

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