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公开(公告)号：EP3147489A1
公开(公告)日：2017-03-29
申请号：EP15795518.8
申请日：2015-05-22
申请人： IHI Corporation
摘要： A thrust increasing device (10) includes: a fuel injector (10b) that ejects fuel toward a jet flow; an ignition device (10c) that is disposed downstream from the fuel injector; a cylindrical duct (10a) that surrounds a combustion region; a flame holder (10d) that is disposed in the duct; and a swirling flow generating part (10d) that maintains an axial (L) flow of the jet flow in an axial direction of the duct in an outer region of the duct in a radial direction inside the duct and that converts the jet flow to a swirling flow centered on an axis of the duct in an inner region of the duct in the radial direction inside the duct.
摘要翻译： 推力增加装置（10）包括：燃料喷射器（10b），其向喷射流喷射燃料; 点燃装置（10c），其设置在燃料喷射器的下游; 围绕燃烧区域的圆柱形管道（10a）; 设置在所述管道中的火焰保持器（10d） 以及旋流产生部（10d），其在所述管道的径向方向内在所述管道的外侧区域内沿着所述管道的轴向在所述管道的轴向保持轴向（L）流动，并将所述射流转换为 在管道的内部区域中沿着管道的轴线在管道内沿径向方向居中的旋流。
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公开(公告)号：EP3101260A1
公开(公告)日：2016-12-07
申请号：EP15786393.7
申请日：2015-04-27
申请人： IHI Corporation
CPC分类号： F02K3/10 , F02K1/822 , F23R3/20 , F23R2900/03041 , Y02T50/675
摘要： The present embodiment improves the durability of an afterburner 25 and yet suppresses a reduction in the engine efficiency of an aircraft engine 1. A ring-shaped cooling channel 35 through which cooling air CA flows is formed between the outer peripheral surface of a liner 31 and the inner peripheral surface of a rear duct 29. A plurality of cooling holes 37 for blowing the cooling air CA along the inner peripheral surface of the liner 31 are formed penetrating the liner 31. A ring-shaped annulus flame-holding member 51 on the inner peripheral surface of the liner 31 is provided concentrically with respect to a plurality of radial flame-holding members 47. The inner diameter of the annulus flame-holding member 51 decreases in the downstream direction. The annulus flame-holding member 51 functions as a throttle ring which throttles the flowing of a main flow of a mixed gas inside the liner 31.
摘要翻译： 本实施例提高了加力燃烧器25的耐久性，并且抑制了飞机发动机1的发动机效率的降低。冷却空气CA流过的环形冷却通道35形成在衬套31的外周面与 后管道29的内周面。沿着衬套31的内周面吹送冷却空气CA的多个冷却孔37形成为穿过衬套31.一个环形环形火焰保持构件51 衬套31的内周面相对于多个径向火焰保持构件47同心地设置。环形火焰保持构件51的内径沿下游方向减小。 环形火焰保持构件51用作节流阀，其节流衬套31内部的混合气体的主流的流动。
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公开(公告)号：EP3101259A1
公开(公告)日：2016-12-07
申请号：EP15785388.8
申请日：2015-04-27
申请人： IHI Corporation
CPC分类号： F23R3/18 , F01D25/24 , F01D25/305 , F02K1/822 , F02K3/10 , F05D2220/323 , F05D2240/35 , F23R3/20 , F23R3/28 , F23R3/286 , F23R3/34 , Y02T50/675
摘要： 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.
摘要翻译： 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。
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公开(公告)号：EP3244054A1
公开(公告)日：2017-11-15
申请号：EP15895561.7
申请日：2015-06-16
申请人： IHI Corporation
CPC分类号： F02K3/10 , F02K1/78 , F05D2220/323 , F23R3/18
摘要： An aft section structure of a jet engine has an axis and the aft section structure is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; one or more guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; one or more spray bars, each of the spray bars extending radially within the duct and comprising one or more trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and one or more flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.
摘要翻译： 喷气发动机的后段结构具有轴线，并且后段结构由限定围绕轴线的管道并且前后轴向打开的壳体组成; 与所述轴线成第一角度向后渐缩的锥体，并具有尖端; 一个或多个导向叶片，所述叶片中的每一个从所述锥体径向延伸到所述壳体并且包括与包含所述轴线的平面成第二角度的压力侧; 一个或多个喷射杆，每个喷射杆在管道内径向延伸并且包括一个或多个后侧，每个后侧以与包含轴的平面成第三角度向后定向; 以及一个或多个火焰保持器，所述火焰保持器中的每一个在所述管道内径向延伸并且包括一个或多个内侧，所述内侧中的每一个与包含所述轴线的平面成第四角度向后定向。
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公开(公告)号：EP2821627A1
公开(公告)日：2015-01-07
申请号：EP13754480.5
申请日：2013-03-01
申请人： IHI Corporation
摘要： An aircraft engine (1) includes an afterburner (23) which has a flame stabilizer (37). The flame stabilizer (37) maintains a flame generated from a mixed gas of a combustion gas and air. The flame stabilizer (37) includes multiple gutters (39) each configured to generate a flame stabilization area (FA) for the flame on its downstream side. Each gutter (39) is formed from: a curved apex section (39a) having a stagnation point (P); and flat plate-shaped side surface sections (39b) integrally formed on the respective two sides of the apex section (39a). Each gutter (39) has a V-shaped cross-sectional shape which is opened to the downstream side. At least one through-hole (41) is formed only in each side surface section (39b) of each gutter (39).
摘要翻译： 飞机发动机（1）包括具有火焰稳定器（37）的加力燃烧器（23）。 火焰稳定器（37）保持由燃烧气体和空气的混合气体产生的火焰。 火焰稳定器（37）包括多个槽口（39），每个槽口被配置成在其下游侧产生火焰的火焰稳定区域（FA）。 每个沟槽（39）由具有停滞点（P）的弯曲顶部（39a）形成; 以及一体地形成在顶点部（39a）的两侧的平板状的侧面部（39b）。 每个沟槽（39）具有向下游侧开口的V形横截面形状。 至少一个通孔（41）仅形成在每个沟槽（39）的每个侧表面部分（39b）中。
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