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    • 1. 发明公开
    • AFTERBURNER AND AIRCRAFT ENGINE
    • NACHBRENNER UND FLUGZEUGTRIEBWERK
    • EP3101259A4
    • 2017-10-04
    • EP15785388
    • 2015-04-27
    • IHI CORP
    • TANAKA SHINJITAKAHASHI KATSUYOSHIHOSOI JUN
    • F02K3/10F23R3/20
    • F23R3/18F01D25/24F01D25/305F02K1/822F02K3/10F05D2220/323F05D2240/35F23R3/20F23R3/28F23R3/286Y02T50/675
    • The present embodiment sufficiently ensures the ignition stability and the flame-holding property of an afterburner 25 while suppressing a reduction in the engine efficiency of an aircraft engine 1. A flame holder 45 is disposed directly downstream of an injection hole 41 of a fuel injector 39 in a liner 31. The flame holder 45 comprises: a ring-shaped annulus flame-holding member 49 which is provided on the inner circumferential surface of the liner 31 and is capable of propagating a flame in the circumferential direction; and a plurality of radial flame-holding members 51 which are radially disposed inwards of the annulus flame-holding member 49 and are capable of propagating the flame in the radial direction. A guide ring 53 is provided inwards of the radial flame-holding members 51, and a ring-shaped guide channel 57 that guides a fuel-containing mixed gas in the downstream direction is formed between the outer peripheral surface of the guide ring 53 and the inner peripheral surface of the annulus flame-holding member 49.
    • 在抑制飞机发动机1的发动机效率降低的同时,本实施例充分确保了后燃器25的点火稳定性和火焰稳定性。火焰稳定器45直接布置在燃料喷射器39的喷射孔41的下游 火焰保持器45包括:环形的环形火焰保持构件49,其设置在衬套31的内周表面上并且能够在周向方向上传播火焰; 以及多个径向框架构件51,其径向地设置在环形框架构件49的内部并且能够沿着径向传播火焰。 导向环53设置在径向火焰保持部件51的内部,在导向环53的外周面与导向环53的外周面之间形成有向下游方向引导含燃料混合气体的环状的导向通道57。 环形火焰保持部件49的内周面。