RESEARCH ON COMBINED CYCLE ENGINES FOR SUPER AND HYPERSONIC AEROSPACE PROPULSION

超音速和高超音速航空航天推进联合循环发动机研究

• 批准号: 06302061
• 负责人: NAMBA Masanobu
• 金额: $ 13.95万
• 依托单位: KYUSHU UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Co-operative Research (A)
• 财政年份: 1994
• 资助国家: 日本
• 起止时间: 1994 至 1995
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-06302061/
• 关键词: Aerospace Propulsion; Hypersonic Propulsion; Supersonic Propulsion; Supersonic Through-Flow Fan; Supersonic Combustion; Supersonic Mixing; Turbulent Diffusion Combustion; Rupture; 超高速通過流ファン; 乱流拡散火炎

Supersonic Through-Flow Fan (STFF) Aerodvnamics : Parametric studies of the cascade flutter boundaries have been conducted by using the newly developed CFD and Double Linearization Theory codes. The usefulness of the latter code has been confirmed. The start and unstart conditions of STFF cascade flows have been investigated by N-S code numerical simulation. The flow field has been studied by means of the flow visualization.Chemically Reacting Flows : A plasma torch system has been constructed. The effect of active chemical species on initiating the hydrogen combustion in supersonic air flows has been theoretically and experimentally verified. the conditions of generating and controlling the precombustion shock for holding flames in a supersonic air flow mixed with a low-reacting fuel gas have been experimentally investigated by using Mie-scattering and OH emission measurement techniques. A new computational model to predict NOx concentrations in turbulent diffusion combustion has been developedMixing : Three-dimensional structures of concentration, velocity and vorticity fields generated by a lobed plate mixer have been experimentally studied. The behavior and role of vortices in mixing phenomena have been theoretically investigated.Shock Wave : The mechanism of unstable shock motion in cascade has been numerically studied.Material : A residual stress reduction technique by modifying the surface geometry has been proposed to prevent cracks from developing in the coated layr due to thermal stress and its usefulness has been theoretically verified.

超音速横流风扇（STFF）Aerodvemics：通过使用新开发的CFD和双重线性化理论代码进行了级联反式边界的参数研究。后一种代码的有用性已得到证实。通过N-S代码数值模拟研究了STFF级联流的开始和解开条件。通过流动可视化研究了流场。化学反应流：已经构建了等离子火炬系统。在理论上和实验验证了活性化学物种对超音速空气流中氢燃烧的影响。通过使用MIE散射和OH排放测量技术，已经研究了实验研究和控制在超音速空气流中固定火焰与低反应燃料气体混合的火焰的预防燃烧冲击的条件。已经开发了一种新的计算模型来预测湍流扩散燃烧中的NOX浓度：已经研究了由裂片板混合器产生的浓度，速度和涡度场的三维结构。理论上已经研究了涡流在混合现象中的行为和作用。摇摆：级联反应中不稳定的冲击运动的机制已经进行了数值研究。材料：通过修改表面几何形状的残留压力减小技术，以防止由于热应力和其有用性而导致的涂层裂纹，以防止在涂层外行中发生裂纹，并且其有用性均已验证。

项目成果

Y.Sugiyama: "Pressure Distributions Growing on and around an Exit Plane of a Jet Normal to a Cross Flow" Proceedings of 1995 Yokohama International Gas Turbine Congress. 2. 375-382 (1995)

Y.Sugiyama：“压力分布在射流垂直于横流的出口平面上及其周围增长”，1995 年横滨国际燃气轮机大会论文集。

T.Hanada and M.Namba: "Mean Loading Effect on the Flutter of Supersonic Through-Flow Fan Blade" Unsteady Aerodynamics and Aeroelasticity of Turbomachines,Y.Tanida and M.Namba (Eds.),Elsevier Science B.V.547-564 (1995)

T.Hanada 和 M.Namba：“超音速通流风扇叶片颤振的平均载荷效应”涡轮机的非定常空气动力学和空气弹性，Y.Tanida 和 M.Namba（编辑），Elsevier Science B.V.547-564 (1995)

N.Yamasaki, et al.: "Flow Field Analysis for the Supersonic Through-Flow Fan" Trans.JSME. Series B. 62 (1996)

N.Yamasaki 等人：“超音速通流风扇的流场分析”Trans.JSME。

H.Yamashita,et al.: "Prediction of Nox Emission Index of Turbulent Diffusion Flame" Modeling in Combustion Science,J.Buckmaster and T.Takeno (Eds.),Lecture Notes in Physics 449,Springer-Verlag. 59-67 (1995)

H.Yamashita 等人：燃烧科学中的“湍流扩散火焰的氮氧化物排放指数预测”模型，J.Buckmaster 和 T.Takeno（编辑），物理学讲义 449，Springer-Verlag。

T.Shioya and K.Uenishi: "A Method of Thermal Stress Reduction in Oxidation-Protective Layrs by Surface Geometry Modification" Proceedings of 1995 Yokohama International Gas Turbine Congress. 3. 93-100 (1995)

T.Shioya 和 K.Uenishi：“通过表面几何修改减少氧化保护层热应力的方法”1995 年横滨国际燃气轮机大会论文集。