共查询到20条相似文献,搜索用时 0 毫秒
1.
讨论弹用涡喷发动机启动加速过程的试验研究,并分析了某弹用涡喷发动机启动加速过程的有关问题,通过地面模拟试验建立了该发动机启动加速的数值模型。 相似文献
2.
在分析S形进气道的总压损失以及进气道,喷管/后体外部阻力计算方法的基础上,建立了针对某型号导弹涡喷发动机的安装性能的计算程序,并结合实际飞行条件,对用户附加引气,功率输出,进气道,喷管安装和环境温度对该发动机性能的影响进行了计算,结果表明,引气和提取功率影响不大,而进气道总压损失和进、排气系统的外部阻力有重要影响,环境温度有一定影响;而且由于弹用涡喷发动机的推力比较小,必须考虑安装性能计算,以便准确判断每一种安装因素所造成的性能损失,为设计和使用方提供理论指导依据。 相似文献
3.
利用辐射光谱法开展发动机燃烧火焰参数在线测量 总被引:4,自引:0,他引:4
针对发动机高温燃烧火焰参数非接触式在线原位测量难题,提出了基于火焰辐射光谱(radiation spectroscopy, RS)的火焰参数在线测量方法,采用光纤光谱仪搭建了发动机燃烧火焰参数在线测量系统,并利用黑体炉对光谱仪电荷耦合元件(charge-coupled device, CCD)波长响应特性进行了标定.之后,应用该系统获得了火箭基组合循环(rocket based combined cycle, RBCC)发动机地面试验高温燃烧火焰200~1100nm波段辐射光谱,结合普朗克定律与最小二乘法,实现了火焰温度与辐射率参数的在线测量,为发动机燃烧诊断与优化提供了直接数据支撑. 相似文献
4.
5.
针对无人机用涡喷发动机转速不跟随油门问题,建立了发动机转速不跟随油门故障树并进行了故障机理分析。基于地面故障复现试验和试飞故障数据,对起动自动器活门及薄膜压力的变化关系进行了分析,确定了故障原因:在高空副油路单独供油情况下,起动自动器活门打开,大量放油,造成局部低压腔压力升高,液压延迟器作动失效,导致故障发生。根据故障原因提出了取消放气窗的解决措施,并通过试飞验证了措施的可行性和有效性。研究成果为发动机燃油系统排故积累了经验,也为发动机燃油系统设计和生产优化提供了参考。 相似文献
6.
M. D. Garipov R. Yu. Sakulin K. N. Garipov R. F. Zinnatullin 《Russian Aeronautics (Iz VUZ)》2012,55(1):36-40
The results of an experimental research, conducted to study a possibility of reducing nitrogen oxide emission in the reciprocating internal combustion engine (ICE) at the combustion mode close to stoichiometric one by increasing the water content in the aqueous ethanol solution are presented. It has been established that as the water quantity in aqueous ethanol grows, a 30-fold reduction in the nitrogen oxides emission level is achieved without a drop in the engine power-to-weight ratio. 相似文献
7.
8.
9.
V. A. Kuz’min E. I. Maratkanova I. A. Zagrai R. V. Rukavishnikova 《Russian Aeronautics (Iz VUZ)》2016,59(1):100-106
The paper presents technology and results of the computational experiment on investigation of thermal radiation in the combustion chamber of a model rocket engine. Dependence of optical properties, radiation characteristics and emission characteristics on the main determining factors and parameters is analyzed. 相似文献
10.
双模态超燃冲压发动机准一维流场数值模拟 总被引:2,自引:0,他引:2
使用一维模型和定比热假设,对超燃发动机在超声速状态下的几何截面的设计及在固定几何截面如何调节气动热力(燃烧速率,喷射位置等)优化工作状态进行了数值研究。采用加热规律经验公式,分析加热规律变化对燃烧室和隔离段内流动参数的影响。采用四阶龙格-库塔法对一维控制方程求解,表明几何形状及加热规律对燃烧室工作的优劣有很大的影响。通过研究发现完全可以单独通过调节加热规律达到优化燃烧工况的目的。 相似文献
11.
为研究等离子体对火箭发动机高频燃烧不稳定性的影响,提出了一种基于脉冲激励准直流放电等离子体的控制方案,采用数值仿真方法研究了脉冲放电等离子体对燃烧室流场平均参数及动态特征的影响规律。结果表明:脉冲激励下燃烧室平均温度和压力都较定常激励下有所降低,对整个燃烧室的影响可以忽略。与定常激励相似,等离子体可以在一段时间内抑制高频压力振荡,而且在特定控制参数下其对不稳定燃烧的抑制效果优于定常激励方式;从功率谱密度分析可知脉冲激励下燃烧室压力振荡特征频率由燃烧室固有声学频率和脉冲激励频率两者共同决定,提高激励频率则特征频率幅值有所降低。脉冲激励方式与定常激励一样不改变燃烧室压力-释热耦合特征,但是通过降低释热率能够改变压力振荡幅值,进而实现对高频不稳定燃烧的抑制。在所研究工况中,激励频率为50 kHz、占空比为20%的脉冲控制参数下等离子体的抑制效果最佳。 相似文献
12.
V. A. Afanas’ev 《Russian Aeronautics (Iz VUZ)》2008,51(3):251-258
A mathematical model of the atmospheric flight of a flight vehicle being controlled by small propulsive engines is presented. The analytical solutions of differential equations are obtained for the approximate calculation of kinematic parameters in the steady-state motions. The flight dynamics and control are studied under conditions of nose lift and diving. The results are suitable for the choice of design FV parameters and synthesis of onboard algorithms of control and parametric identification. 相似文献
13.
《Aerospace Science and Technology》2007,11(6):459-463
The prediction of nitrogen oxides emissions in turbojet engines exhausts remains a field of immense importance given the increasing coercive environmental requirements in relation to the emissions from turbojet engines. Emissions of nitrogen oxides (NOx) are subjected to limits fixed by legislators in a lot of countries because of their toxic character beyond specific concentrations in the air and their effects on climate change. However, analytical methods used to evaluate the quantities of the emissions are not efficiently established because of a lack of complete understanding of the phenomena governing the formation of the NOx in turbojet engines. It is a combination of chemical, thermal, and fluid dynamic processes. In this paper, a more accurate empirical correlation is determined for the prediction of nitrogen oxides emission index (EINOx) in turbojet engines exhausts using the main combustion operational parameters. The relationship between EINOx and the following parameters: fuel flow rate, output power, pressure ratio, efficiency, flame temperature and combustor inlet temperature is analysed with 227 ICAO certification data measured on turbojets engines from manufacturers such as Pratt and Whitney, General Electric, CFM International and Rolls-Royce. A set of 556 test point data used to show flame and combustor inlet temperature relationship with NOx emission index is from the work of G.F. Pearce et al. on twelve gas turbine engines. From this analysis it can be noticed that the relationship between EINOx and flame temperature is strong but not as the relationship between EINOx and the combustor inlet temperature. Since the combustor inlet temperature is easier to measure, EINOx value can be deduce from it. By predicting NOx emissions from combustor inlet temperature we can avoid exhausts gas measurements and analysis, saving on time and money. 相似文献
14.
V. R. Rubinskii S. P. Khrisanfov V. Yu. Klimov A. V. Kretinin 《Russian Aeronautics (Iz VUZ)》2010,53(1):81-86
The numerical results are presented for the case of coaxial-jet supply at the different ratio of mass component velocities at the combustion chamber inlet with the constant and variable relationship of oxygen-methane components. The experimental investigations of coaxial-jet mixing elements as part of the model setup chamber operating on corrosive producer gas and gaseous methane were carried out. A qualitative pattern of the $
overline {rho u}
$
overline {rho u}
parameter influence on the chamber economic feasibility was obtained: as $
overline {rho u}
$
overline {rho u}
decreases, the combustion efficiency coefficient grows. 相似文献
15.
16.
17.
18.
ESO 3.6m Caspec spectra of the LMC luminous blue variable (LBV) taken at minimum have been analysed using NLTE model atmospheres and line formation calculations to derive atmospheric parameters and chemical composition. Using the silicon ionization balance and the hydrogen Balmer lines we deriveT
eff
=17250, log g=1.80 and a microturbulent velocity of 15–20 km/s. The analysis yields abundance ratios by number of approximately 0.43 for He/H, 0.03 for C/N and 0.14 for O/N, implying that enrichment of the atmosphere by processed material has taken place. We have re-evaluated the reddening of R71 using IUE low resolution data and published UBVRIJHKL photometry and derive a value for A
V
of 0.63. We also construct an extinction curve using archive IUE data for mid-B LMC supergiants and show that the extinction is anomalous; the 2175A bump being almost absent and the far UV rise very pronounced. A comparison of our model flux in theV-band with the observed (dereddened)V magnitude and the D.M. of the LMC (18.45), implies that the bolometric magnitude or R71 is –9.9. This is significantly higher than the value of –9.0 usually adopted for R71 and suggests that this object may not in fact be a subluminous LBV. 相似文献
19.
20.
激光吸收光谱技术测量非均匀燃烧流场研究进展 总被引:1,自引:0,他引:1
可调谐半导体激光吸收光谱技术(TDLAS)具有非侵入性、灵敏度高和时间响应快等优点,将激光吸收光谱技术与最小二乘法、计算机断层扫描重建技术(CT)相结合,可以实现对非均匀燃烧流场的分布测量。首先简要介绍了激光吸收光谱技术的发展历程及测量基本原理,然后分别对激光吸收光谱技术测量非均匀流场一维分布、二维分布的国内外研究现状及关键技术进行了综述,比较分析了二维非均匀流场诊断实验中旋转和固定两种安装模式的优缺点及相对应的光线布局,总结了用于流场二维重建的相关重建算法,最后讨论了激光吸收光谱技术测量非均匀流场研究工作的发展趋势和有待解决的相关问题。 相似文献