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《中国航空学报》2021,34(11):79-93
In the current state-of-the-art, high-loss flow in the endwall significantly influences compressor performance. Therefore, the control of endwall corner separation in compressor blade rows is important to consider. Based on the previous research of the Blended Blade and EndWall (BBEW) technique, which can significantly reduce corner separation, in combination with a non-axisymmetric endwall, the full-BBEW technique is proposed in this study to further reduce the separation in endwall region. The principle of the unchanged axial passage area is considered to derive the geometric method for this technique. Three models are further classified based on different geometric characteristics of this technique: the BBEW model, Inclining-Only EndWall (IOEW) model, and full-BBEW model. The most effective design of each model is then found by performing several optimizations at the design point and related numerical investigations over the entire operational conditions. Compared with the prototype, the total pressure loss coefficient decreases by 7%–9% in the optimized full-BBEW at the design point. Moreover, the aerodynamic blockage coefficient over the entire operational range decreases more than the other models, which shows its positive effect for diffusion. This approach has a larger decrease at negative incidence angles where the intersection of the boundary layer plays an important role in corner separation. The analysis shows that the blended blade profile enlarges the dihedral angle and creates a span-wise pressure gradient to move low momentum fluid towards the mainstream. Furthermore, the inclining hub geometry accelerates the accumulated flow in the corner downstream by increasing the pressure gradient. Overall, though losses in the mainstream grow, especially for large incidences, the full-BBEW technique effectively reduces the separation in corners. 相似文献
43.
针对叶冠腔内有冷却气流的转子叶片叶冠,通过改变主流雷诺数、前后孔岀流比、叶尖间隙等参数得到静止状态下叶冠间隙流动的总压损失系数.实验结果表明:增大主流雷诺数与前孔岀流比,叶冠总压损失系数增大;减小叶尖间隙,总压损失系数也增大,小叶尖间隙下,总压损失系数随主流雷诺数与前孔岀流比增长更快,而后孔岀流比对叶冠总压损失系数影响不大. 相似文献
44.
无导叶对转涡轮气动设计技术 总被引:2,自引:0,他引:2
采用先进的无导叶对转涡轮气动布局是提升航空发动机性能最为有效的措施之一。结合无导叶对转涡轮高压涡轮动叶进出口轴向速度变化较大等特点,采用理论分析等研究了对转涡轮基元速度三角形参数的优化选取方法,并给出了高压涡轮导叶、动叶出口气流角等变化对效率影响的详细变化关系。流量系数小、高压动叶出口气流角大以及高压动叶进出口轴向速度比大是设计满足出功比高效率对转涡轮的关键。而采用Bezier曲线造型的收敛-扩散叶型叶背曲率的控制、尾缘半径的选择、叶型出口面积与几何喉道面积之比等则是设计适合出口马赫数1.5~1.6高性能叶型的关键。 相似文献
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导风轮轮罩引气对离心式压气机性能影响的数值研究 总被引:4,自引:2,他引:2
为了研究扩大离心压气机喘振裕度的实用技术 ,以解决某工程设计中的问题 ,用三维粘性计算流体力学 ( CFD)计算软件对离心压气机导风轮轮罩引气措施进行了数值模拟。该项技术在应用中所涉及的设计参数经过了初步的数值试验。从数值模拟的结果中 ,可以看到该项技术对离心压气机性能改进的明显效果 相似文献
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为强化航空发动机涡轮叶片内冷通道传热性能,针对带有微小V肋-凹陷涡高效复合冷却结构矩形通道,采用Abe Kondoh Nagano (AKN) k-ε湍流模型数值模拟研究了肋高与凹陷深度组合对流动传热特性的影响机理。结果表明,当凹陷深度一定,复合结构的强化换热效果随肋高增加而增加,3mm肋高复合结构的传热相比纯凹陷提高了87.1%;当肋高一定,传热随凹陷深度增加先增强后基本保持不变,6mm深凹陷复合结构相比纯V肋提高了52.8%。通过在凹陷上游布置V肋,增强了越过V肋冲入凹陷内流体的湍动能,从而使凹陷前部回流区减小;同时来自微小V肋的涡流与凹陷内部的涡流相互作用,增强了整个流场的动量和热量输运,使通道换热均匀,并相较纯凹陷或纯V肋结构均有显著提升。 相似文献
49.
Parametric study of turbine NGV blade lean and vortex design 总被引:1,自引:1,他引:0
《中国航空学报》2016,(1):104-116
The effects of blade lean and vortex design on the aerodynamics of a turbine entry nozzle guide vane (NGV) are considered using computational fluid dynamics. The aim of the work is to address some of the uncertainties which have arisen from previous studies where conflicting results have been reported for the effect on the NGV. The configuration was initially based on the energy efficient engine turbine which also served as the validation case for the computational method. A total of 17 NGV configurations were evaluated to study the effects of lean and vortex design on row efficiency and secondary kinetic energy. The distribution of mass flow ratio is introduced as an additional factor in the assessment of blade lean effects. The results show that in the turbine entry NGV, the secondary flow strength is not a dominant factor that determines NGV losses and therefore the changes of loading distribution due to blade lean and the associated loss mecha-nisms should be regarded as a key factor. Radial mass flow redistribution under different NGV lean and twist is demonstrated as an addition key factor influencing row efficiency. 相似文献
50.
To comprehensively consider the effects of strength degeneration and failure correlation, an improved stress-strength interference (SSI) model is proposed to analyze the reliability of aeroengine blades with the fatigue failure mode. Two types of TC4 alloy experiments are conducted for the study on the damage accumulation law. All the parameters in the nonlinear damage model are obtained by the tension-compression fatigue tests, and the accuracy of the nonlinear damage model is verified by the damage tests. The strength degeneration model is put forward on the basis of the Chaboche nonlinear damage theory and the Griffith fracture criterion, and determined by measuring the fatigue toughness during the tests. From the comparison of two kinds of degeneration models based on the Miner’s linear law and the nonlinear damage model respectively, the nonlinear model has a significant advantage on prediction accuracy especially in the later period of life. A time-dependent SSI reliability model is established. By computing the stress distribution using the finite element (FE) technique, the reliability of a single blade during the whole service life is obtained. Considering the failure correlation of components, a modified reliability model of aero-engine blades with common cause failure (CCF) is presented. It shows a closer and more reasonable process with the actual working condition. The improved reliability model is illustrated to be applied to aero-engine blades well, and the approach purposed in this paper is suitable for any actual machinery component of aero-engine rotor systems. 相似文献