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）气动：采用新开发的计算流体动力学和双线性化理论代码对叶栅颤振边界进行了参数研究。后一个守则的效用已得到证实。采用N-S程序对STFF叶栅流场进行了数值模拟，研究了STFF叶栅流场的起动和非起动条件。利用流动显示技术研究了等离子体炬的流场。化学反应流：建立了等离子体炬系统。本文从理论和实验两方面验证了活性组分对超音速气流中氢气燃烧的影响。采用Mie散射和OH排放测量技术，对低反应性燃气与超音速空气混合流中预燃激波的产生和控制条件进行了实验研究。本文建立了一个新的湍流扩散燃烧NOx浓度计算模型。混合：实验研究了波瓣板混合器产生的浓度场、速度场和涡量场的三维结构。从理论上研究了涡在混合现象中的行为和作用;激波：数值研究了叶栅中不稳定激波运动的机理;材料：提出了一种通过改变表面几何形状来降低残余应力的技术，以防止由于热应力引起的涂层裂纹的发展，并从理论上验证了这种技术的有效性。

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。