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1. 发明专利

JP2001050110A VARIABLE BYPASS NOZZLE DEVICE FOR TURBO-FAN ENGINE 失效
公开(公告)号：JP2001050110A
公开(公告)日：2001-02-23
申请号：JP22543199
申请日：1999-08-09
申请人： ISHIKAWAJIMA HARIMA HEAVY IND
发明人： KODAMA KOJI
IPC分类号： F02K3/04 , F02K1/30
摘要： PROBLEM TO BE SOLVED: To hold a passage configuration and a nozzle area which are optimum for an engine operating condition. SOLUTION: A recess is formed in the outer wall surface part of an inner cowl 4 in the outlet part of a bypass passage 7. A plurality of flexible tubes 14 are arranged being wound in the recess 12 in the vertical direction of the bypass passage, at required interval. The recess 12 is fitted thereto with an elastic material fairing 15 so as to cover the flexible tubes 14. A fluid pressure control device 16 is provided for applying fluid pressure to the respective flexible tubes 14. Expansion and contraction of the tubes are transmitted to the fairing 15 so as to adjust the nozzle area.

2. 发明专利

JP6129580B2 ガスタービン有权
公开(公告)号：JP6129580B2
公开(公告)日：2017-05-17
申请号：JP2013033620
申请日：2013-02-22
申请人：三菱重工業株式会社
发明人：秋元健太郎 , 岡部能幸 , 石坂浩一
IPC分类号： F02C7/00 , F02K1/30 , F02K1/36 , F02K1/38 , F01D25/30

3. 发明专利

JP2013019330A Variable exhaust nozzle of jet engine 有权
标题翻译：喷气发动机可变排气喷嘴
公开(公告)号：JP2013019330A
公开(公告)日：2013-01-31
申请号：JP2011153582
申请日：2011-07-12
申请人： Ihi Corp , 株式会社Ihi
发明人： OBA YOSHINORI , OISHI TSUTOMU , TANAKA NOZOMI , MATSUMOTO YUTA
IPC分类号： F02K1/12 , F02K1/10 , F02K1/30
摘要： PROBLEM TO BE SOLVED: To provide a variable exhaust nozzle of a jet engine that has a simple configuration and reliably decreases an infrared radiation intensity level.SOLUTION: This variable exhaust nozzle includes a plurality of seals 10 that are annularly arranged to constitute an exhaust port 2, a plurality of flaps 20 that are annularly arranged outside the seals 10 in the radial direction of the exhaust port 2 and positioned between adjacent seals 10, a plurality of fairing members 31 that are annularly arranged outside the plurality of flaps 20 in the radial direction of the exhaust port 2 to cover the outer surfaces of the plurality of flaps 20 and seals 10. Notches 25 are disposed at the tips of the flaps 20. At the tips of the fairing members 31, cutouts 34 for exposing the notches 25 to the outside in the radial direction of the exhaust port 2 are disposed at positions facing the notches 25.
摘要翻译：要解决的问题：提供一种具有简单构造并可靠地降低红外辐射强度水平的喷气发动机的可变排气喷嘴。解决方案：该可变排气喷嘴包括多个密封件10，它们环形地设置成构成排气口2;多个翼片20，其在排气口2的径向方向上环形地设置在密封件10的外部，在相邻的密封件10之间，在排气口2的径向上环形地设置在多个翼片20的外侧的多个整流罩31，以覆盖多个翼片20和密封件10的外表面。槽口25设置在翼片20的顶端。在整流罩构件31的顶端处，将切口34在排气口2的径向方向上露出到外侧的切口34设置在与切口25相对的位置。 C）2013，JPO＆INPIT

4. 发明专利

JPS6441651A EXTENSION SECTION HAVING DISCONTINUOUS CURVATURE FOR ROCKET ENGINE 失效
公开(公告)号：JPS6441651A
公开(公告)日：1989-02-13
申请号：JP18145288
申请日：1988-07-20
申请人： EUROP PROPULSION
发明人： ERITSUKU HERUMANTO
IPC分类号： F02K9/44 , F02K1/30 , F02K9/82 , F02K9/97
摘要： PURPOSE: To make it possible to inject gas at little loss by constructing a diverging portion which consists of a fixing portion starting from the nozzle throat part and a down-stream portion to be connected in the join zone and providing the join zone with a controlled injection device which injects an additional jet of gas into the diverging portion. CONSTITUTION: The diverging portion 10 for a rocket engine shown in a solid line (the conventional diverging portion 20 is shown in a broken line) starts from a nozzle throat part 13 and has a first length part (fixing portion) 11 having a curvature in the axial profile section to be constructed from the first circumferential surface. The diverging portion 10 further has a second length (down-stream portion) 12 having a curvature in the axial profile section to be constructed from the second circumferential surface on the nozzle axis. Each of these lengths 11, 12 forms a discontinuous curvature connected at the joint zone 16. Outside the diverging portion 10 in the vicinity of the join zone 16, a controlled injection device 100 is disposed such that an additional jet of gas can be injected in the direction of the main flow of the gas 31 ejected by the nozzle.

5. 发明专利

JP2009002329A Turbine engine and method for regulating bearing load in turbine engine 有权
标题翻译：涡轮发动机及其在涡轮发动机中调节轴承负荷的方法
公开(公告)号：JP2009002329A
公开(公告)日：2009-01-08
申请号：JP2008129001
申请日：2008-05-16
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： GRABOWSKI ZBIGNIEW M , WINTER MICHAEL
IPC分类号： F02K1/30 , F01D3/00 , F01D25/16 , F02K3/06
CPC分类号： F02K1/12 , F01D21/04 , F01D25/16 , F02K1/70 , F05D2270/114 , F05D2270/30 , F05D2270/304
摘要： PROBLEM TO BE SOLVED: To provide a method and device for controlling actively the bearing load of a turbine engine.
SOLUTION: The engine 10 has a flow control device 41 for use in changing the nozzle outlet area effectively. The flow control device 41 changes the fan nozzle outlet area 40 which discharges to axial direction the bypass flow B compressed by an upstream fan 20 of the engine 10. Owing to a high bypass ratio, a considerably large thrust force is given by the bypass flow B. In one example, the flow control device 41 generates a change of approximately 20% in the fan nozzle outlet area 40. A fan nacelle 34 includes members such as a plurality of hinge type flaps 42 arranged in the circumferential direction around the back part of the fan nacelle 34.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种主动控制涡轮发动机的轴承负荷的方法和装置。解决方案：发动机10具有用于有效地改变喷嘴出口区域的流量控制装置41。流量控制装置41将通过发动机10的上游风扇20压缩的旁通流B向轴向喷射的风扇喷嘴出口区域40变化。由于旁通比高，旁路流量给出相当大的推力在一个示例中，流量控制装置41在风扇喷嘴出口区域40中产生大约20％的变化。风扇机舱34包括沿周向布置的多个铰链式翼片42的构件，围绕后部的风扇机舱34.版权所有（C）2009，JPO＆INPIT

6. 发明专利

JPH10281003A PASSAGE CLOSING GEAR AND ITS SEALING STRUCTURE 失效
公开(公告)号：JPH10281003A
公开(公告)日：1998-10-20
申请号：JP8782197
申请日：1997-04-07
申请人： ISHIKAWAJIMA HARIMA HEAVY IND
发明人： UDO TOMOICHIRO
IPC分类号： F02K1/30 , F02K1/38 , F02K7/16
摘要： PROBLEM TO BE SOLVED: To provide a passage closing gear and its sealing structure which can be used in a high temperature part and are capable of adapting to large heat distortion. SOLUTION: The gear is equipped with a flap 12 which opens or closes an opening 5 provided on a passage, and the flap 12 consists of a sealing plate 14 which contacts the opening 5 and seals a seal area 5a, and a support plate 16 which is driven by an opening/closing gear 20. The sealing plate 14 is mounted with a space left away from and approximately in parallel to the support plate 16 while allowing the free movement of the sealing plate 14. Further, leaf springs 18 are sandwiched between the sealing plate 14 and the support plate 16 so that the sealing plate 14 is always pushed in direction to move away from the support plate 16. The force of the leaf springs 18 is preset to a value which is larger than the operating force required to seal the opening 5 when closing the passage, so even if the clearance between the flap 12 and the opening 5 varies, the elastic force of the leaf springs 18 causes the clearance between the sealing plate 14 and the support plate 16 to change, and the sealing plate 14 and the opening 5 are always kept in firmly joined condition and the sealable property is maintained.

7. 发明专利

JP2767186B2 失效
公开(公告)号：JP2767186B2
公开(公告)日：1998-06-18
申请号：JP17033993
申请日：1993-07-09
申请人： DAIMURAA BENTSU AEROSUPEESU AG
发明人： YOAHIMU KURECHUMAARU
IPC分类号： F02K1/08 , F02K1/09 , F02K1/30 , F02K1/52 , F02K7/16

8. 发明专利

JPH06159136A JET ENGINE 失效
公开(公告)号：JPH06159136A
公开(公告)日：1994-06-07
申请号：JP17033993
申请日：1993-07-09
申请人： DEUTSCHE AEROSPACE
发明人： YOAHIMU KURECHIYUMAARU
IPC分类号： F02K1/08 , F02K1/09 , F02K1/30 , F02K1/52 , F02K7/16
摘要： PURPOSE: To be adapted to the very different operation conditions and obtain a simple structure and high propelling efficiency of a hypersonic compound engine by arranging a particular propelling nozzle divergent lengthening part at an outlet end of a nozzle outer wall. CONSTITUTION: A propelling nozzle 16 contains a propelling nozzle divergent lengthening part 48 which is axially movable for the outlet-side expansion of a hot gas flow duct 56. In the moved-out position, the lengthening part 48 connects to a divergent outlet end 54 of a nozzle outer wall 42 fixed to an engine, and in the moved-in condition, forms together with the nozzle outer wall 42 an air outlet duct 58 which encloses the fixed nozzle wall end. Thus, in the low flying speed range, a secondary air injection that is uniform along the whole outer circumference of the fixed nozzle takes place through the air outlet duct 58. A mushroom-shaped central body 44 which can be adjusted axially is arranged in the propelling nozzle 16.

9. 发明专利

JPH05133274A THRUST DEFLECTING NOZZLE 失效
公开(公告)号：JPH05133274A
公开(公告)日：1993-05-28
申请号：JP31838491
申请日：1991-11-06
申请人： ISHIKAWAJIMA HARIMA HEAVY IND
发明人： FUJIMURA TETSUJI , YAMAMOTO MASAHIKO , UDAGAWA YUTAKA , WATANABE TADAAKI
IPC分类号： F02K1/30
摘要： PURPOSE:To simplify the structure in a thrust deflecting nozzle for use in aircraft by controlling the opening and closing of plural air intake valves provided on the front end part of a nozzle cover in the circumferential direction, thereby regulating the direction of a gas flow jetted from the rear side end part of the thrust deflecting nozzle. CONSTITUTION:A large diameter nozzle cover 6 is coaxially installed to a nearly cylindrical nozzle body l, the cross-section of the passage of which is gradually reduced from the longitudinal intermediate part to the rear side end part, and plural air intake valves 9a-9d are provided on the outer peripheral surface near the front side end part of the nozzle cover 6 up and down, and right and left at nearly equal intervals in the circumferential direction. For example, when only the air intake valve 9b is opened when the respective air intake valves 9a-9d are closed during usual flight to al-low a subsonic gas flow to flow from the front side in the nozzle body 1 toward the rear side, the peripheral air E flows from the air intake valve 9b into a space 8 to throttle the gas flow by the ejector effect to allow the gas flow S to jet so that the gas flow is deflected from the rear side end part of the nozzle cover 6 downward.

10. 发明专利

JP2012127349A Method and apparatus for variable exhaust nozzle exit area 审中-公开
标题翻译：可变排气喷嘴出口区域的方法和装置
公开(公告)号：JP2012127349A
公开(公告)日：2012-07-05
申请号：JP2011271964
申请日：2011-12-13
申请人： Boeing Co:The , ザ・ボーイング・カンパニーThe Boeing Company
发明人： WINKLER CHAD M , DORGAN ANDREW J , WERNER ERIC L
IPC分类号： F02K1/30 , F02K1/06
CPC分类号： F02K1/30
摘要： PROBLEM TO BE SOLVED: To optimize thrust through adjusting engine performance by controlling an exit area of an exhaust nozzle for jet engine.SOLUTION: A nozzle effective exit area control system is created with a convergent-divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12° from a freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator to a throat of the nozzle and pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit.
摘要翻译：要解决的问题：通过控制喷气发动机的排气喷嘴的出口面积来调节发动机性能来优化推力。解决方案：喷嘴有效的出口区域控制系统产生具有会聚扩散喷嘴，喷嘴的发散部分具有与自由流方向成至少12°的预定角度的壁。干扰发生器基本上对称地位于壁上以引起与壁的流动分离，其中预定的壁角度引起流动分离，以从每个扰动发生器的上游延伸到喷嘴的喉部并且加压壁并减小射流的有效面积在喷嘴出口流动。版权所有（C）2012，JPO＆INPIT

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