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公开(公告)号：US4546606A
公开(公告)日：1985-10-15
申请号：US491372
申请日：1983-05-04
申请人： Jean G. Bouiller , Marc F. B. Buisson , Gerard E. A. Jourdain , Denis J. M. Sandelis , Yves R. A. Urruty
发明人： Jean G. Bouiller , Marc F. B. Buisson , Gerard E. A. Jourdain , Denis J. M. Sandelis , Yves R. A. Urruty
CPC分类号： F02K3/075 , F01D17/162 , Y10T137/87442
摘要： The control device comprises at least one control ring to which one end ofn elbow lever is articulated. The vane pivot of alternating vanes is fixed at the intersection of the arms of the elbow levers. The other end of each elbow lever is connected by a rod to the end of a straight lever, the other end of which is fixed to the pivot of an adjacent vane. The circumferential movement of the ring causes the pivots of the adjacent vanes to pivot in opposite directions. Two other embodiments have two rings.
摘要翻译： 控制装置包括至少一个控制环，肘杆的一端被铰接到该控制环上。 交替叶片的叶片枢轴固定在肘杆臂的交叉处。 每个肘杆的另一端通过杆连接到直杆的端部，另一端固定在相邻叶片的枢轴上。 环的圆周运动导致相邻叶片的枢轴在相反的方向枢转。 另外两个实施例具有两个环。
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2.发明授权Variable section nozzle for a turbo-jet engine and an aircraft comprising such equipment 失效用于涡轮喷气发动机的可变截面喷嘴和包括这种设备的飞机
公开(公告)号：US4577814A
公开(公告)日：1986-03-25
申请号：US554301
申请日：1983-11-22
CPC分类号： F02K1/10 , F02K1/006 , Y02T50/671
摘要： The invention relates to a variable area nozzle for a turbo-jet engine. This nozzle comprises a convergent portion, formed by a fixed semi-shell (2) and a semi-shell (3) pivotal about a diametral axis (4a-4b); the fluid-tightness of the convergent portion is ensured by a substantially semi-circular seal (6) and by two longitudinal seals (7a, 7b). The nozzle can be used for example with an engine comprising a partial re-heat system of moderate output.
摘要翻译： 本发明涉及一种用于涡轮喷气发动机的可变区域喷嘴。 该喷嘴包括由固定的半壳体（2）和围绕径向轴线（4a-4b）枢转的半壳体（3）形成的会聚部分; 收敛部分的流体密封性通过基本上为半圆形的密封件（6）和两个纵向密封件（7a，7b）来确保。 喷嘴可以例如用于包括中等输出的局部再热系统的发动机。
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公开(公告)号：US4280324A
公开(公告)日：1981-07-28
申请号：US944616
申请日：1978-09-21
摘要： The invention concerns a fuel distribution device in a high velocity gase flow. The device consists of two coaxial, toric injection manifolds placed in close proximity with respect to each other, pierced by small diameter uniformly distributed orifices and arranged to introduce fuel into the flow. The orifices in the manifold located downstream with respect to the direction of the flow of gases, are arranged on the face turned upstream of the manifold, in a circular row coaxial with it.It is the object of the invention to reduce the drag induced in the flow by the devices presently in use, while improving the distribution of the fuel; it finds particularly advantageous applications in the afterburner ducts of gas turbine engines.
摘要翻译： 本发明涉及一种高速气流中的燃料分配装置。 该装置由两个同轴的复曲面注入歧管组成，彼此相邻靠近，被小直径均匀分布的孔刺穿并被布置成将燃料引入流中。 相对于气体流动方向位于下游的歧管中的孔布置在与歧管上游相通的面上，与其同轴的圆形排列。 本发明的目的是在改善燃料分配的同时，减少目前使用的装置在流动中引起的阻力; 它在燃气涡轮发动机的后燃器管中发现特别有利的应用。
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4.发明授权
公开(公告)号：US4125998A
公开(公告)日：1978-11-21
申请号：US794242
申请日：1977-05-05
申请人： Ernest J. Barou , Roland Beyler , Marc F. B. Buisson , Jacques E. J. Caruel , Roger A. J. Vandenbroucke
发明人： Ernest J. Barou , Roland Beyler , Marc F. B. Buisson , Jacques E. J. Caruel , Roger A. J. Vandenbroucke
摘要： An auxiliary chamber or ignition "prechamber" for afterburners of aeronautical turbine engines draws in, through a perforated plate, a carbureted mixture produced by fuel projected against an anvil by an injection manifold, and the injection manifold also issues a jet of fuel into a tube which discharges into the chamber downstream of a spark plug. The produced flame is guided into a flame stabilizer.
摘要翻译： 用于航空涡轮发动机的后燃烧器的辅助室或点燃“预燃室”通过多孔板吸入由通过喷射歧管向砧投射的燃料产生的化油混合物，并且喷射歧管还将一喷射燃料喷射到管 其排放到火花塞下游的室中。 产生的火焰被引导到火焰稳定器中。
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