某型航空发动机燃烧室等离子体助燃的数值研究

为开展等离子体助燃技术在航空发动机燃烧室中的应用研究,利用Fluent软件对某型航空发动机环形燃烧室进行了等离子体助燃的数值计算,设计了等离子体助燃的数值计算方案,对比分析了正常燃烧状态条件和等离子体助燃条件下的数值计算结果.结果表明:从主燃孔实施助燃后火焰筒内的高温区向主燃区移动,煤油在主燃区燃烧得更充分,燃烧室出口截面的平均温升增高约57.97 K,燃烧效率提高约2.42%;出口处温度分布均匀性有所改善,燃烧室出口处截面温度的分布不均匀系数下降达21.82%;提高了燃料燃烧完全程度,燃烧尾气中CO的体积分数下降约13.58%,极大改善了燃烧室的性能.     

交流放电等离子体助燃乙烯/空气的数值模拟

通过耦合零维等离子动力学求解器和燃烧动力学求解器,建立了交流放电等离子体助燃模型,研究了交流放电非平衡等离子体对C2H4/空气的助燃路径,并与自燃过程进行了对比.该模型使用电子能量分布函数计算电子碰撞反应速率,并得到贫燃条件下连续放电过程中温度、组分浓度、放热速率、关键组分的生成/消耗速率随时间的变化.研究表明,等离子...     

煤矿通风瓦斯在燃气轮机中的催化燃烧特性

在不同进口温度、工作压力和当量比条件下,研究了煤矿通风瓦斯气在燃气轮机催化燃烧室内部的燃烧特性,对数值模拟结果与试验结果进行了对比,并分析了催化燃烧对超低浓度瓦斯气性能的影响.结果表明:增加甲烷浓度(或当量比)可促进超低浓度甲烷的催化燃烧;提高催化燃烧室进口温度或工作压力可相应提高煤矿通风瓦斯燃气轮机系统的效率.     

压力对等离子氮化工艺的温度均匀性影响

等离子氮化不用辅助加热，阴极工件各区域的温度取决于工件能量的热平衡，取决于离子和中性粒子的轰击，同时温度通过热传导、对流和辐射而损失。本文着重分析压力和阴阳极距离对流密度和温度均匀性的影响，叙述大型曲轴的等离子氮化，具有应用推广价值。     

辅助动力装置全环形燃烧室燃烧性能试验研究

针对某型辅助动力装置全环形燃烧室开展了整机燃烧性能试验研究。采用温度耙测量全环形燃烧室出口温度分布,研究不同进口温度和油气比条件下辅助动力装置燃烧室整机燃烧性能。试验结果表明:随着进口温度和油气比的增加,燃烧室出口温度相应增加,但温度分布规律基本保持不变,出口温度分布系数(OTDF)小于0.2,径向温度分布系数(RTDF)基本小于0.1,而燃烧效率和燃烧室进出口压力损失系数增加;随着进口总温的增加,燃烧室贫油熄火油气比逐渐减少(余气系数增加),但燃烧室的贫油熄火余气系数均大于13。     

超临界压力下航空煤油在竖直管内的传热研究

对竖直上升管内超临界压力下航空煤油的传热特性进行了实验研究。分析了不同质量流量、热流密度、压力和进口温度对超临界压力下航空煤油传热特性的影响。实验结果表明,提高质量流量或进口温度均使煤油传热效果变好。而热流密度对流体传热的影响主要在于改变了流体和壁面温度,热流密度越大,传热系数越高。压力对煤油传热影响不大,一般情况下,提高压力会恶化传热。超临界状态下,煤油物性变化很大,因此对煤油的传输和热力学性质的准确计算是研究超临界压力下传热现象的关键。利用拓展的对比态法来计算煤油的密度和传输特性,如黏度、热导率等。给出了煤油在超临界压力下的传热关联式,其计算值和实验值吻合良好。     

提高助燃风温度对熔铝炉燃烧特性影响的研究

回收熔铝炉排烟热量加热助燃风可以提高熔铝炉热效率。为了深入研究提高助燃风温度对熔铝炉燃烧的影响,首先通过对天然气理论燃烧温度、火焰长度、烧嘴燃烧能力等方面进行理论计算分析,得到不同助燃风温度对熔铝炉燃烧特性的影响变化趋势。然后根据助燃风压力对烧嘴燃烧能力的影响,分析并得到不同助燃风下满足烧嘴燃烧能力的最优助燃风压力。最后通过具体实例分析证明:在不改变烧嘴的前提下,回收熔铝炉烟气余热可以提高助燃风温度,还可以提高熔铝炉热效率及熔铝速度。     

配风比对微型燃气轮机燃烧室燃烧性能影响的数值模拟

以采用燃料和空气预混燃烧方式的微型燃气轮机燃烧室为研究对象,根据设计参数对燃烧室进行建模和模拟计算,模拟不同工况下预混燃料在燃烧室内经过湍流流动并发生燃烧化学反应的过程,进而得到燃烧室内的热态流场、温度分布以及出口烟气中污染物的排放量.结果 表明:在总过量空气系数为3.01的情况下,随着旋流器进口当量比的增大以及助燃风质量流量比例的升高,预混火焰的锋面温度有所升高,出口NOx质量浓度与出口温度分布因子呈正相关.     

煤焦油燃烧特性数值模拟

利用数值模拟方法,选用标准k-ε湍流模型,化学反应采用涡-耗散模型,辐射模型应用P-1辐射模型,研究进油口尺寸、进气口尺寸一定,煤焦油蒸气速度和助燃气体速度不变,富氧条件下不同含氧助燃气体对燃烧室火焰空间温度场和气流场压力场的影响。结果表明,助燃气体含氧量越高,火焰温度越高,燃烧速率越快,尾气排放所带走热量越小,火焰空间温度场分布梯度变大。数值模拟结果对于煤焦油用于工业燃烧条件的设计和操作具有一定的理论指导和实践意义。     

初始条件对燃气轮机DLE燃烧室性能影响研究

以单头部中心分级旋流干式低排放(Dry Low Emission, DLE)燃烧室为研究对象,以天然气为燃料,针对不同的全局当量比、进口温度、进口压力条件开展试验测试和数值模拟,研究燃烧室的燃烧性能以及污染物排放的变化规律。研究发现：随全局当量比增大,中心回流区长度略有增大、宽度变窄、回流速度增大,燃料量的增加使得高温区面积明显扩大,燃烧室出口温升明显增大,出口温度分布系数变化不大,燃烧室出口CO和NO_x排放摩尔分数明显增大;随进口温度的增大,中心回流区长度先明显增大再减小、宽度变窄、回流速度先增大再减小,进口空气温度的升高使得反应速率加快从而导致燃烧室出口温度升高,但温升、出口温度分布系数变化不大,CO和NO_x排放摩尔分数增大;随进口压力的增大,中心回流区长度、宽度略有增大,回流速度增大,燃烧室内部和燃烧室出口温度无明显变化,出口温度分布系数减小,CO和NO_x排放摩尔分数受影响较小。     

The combustion tuning methodology of an industrial gas turbine using a sensitivity analysis

This paper presents the results of combustion performance testing of a 5.25 MWe industrial gas turbine which features a conical counter-flow double-swirl stabilized, premixed combustor and the Combustion Tuning methodology using a Sensitivity Analysis (abbreviated to CTSA). The combustion performance test was conducted in an atmospheric pressure, optically accessible, real engine scale combustor. The atmospheric rig and real engine correlation was verified by comparing real engine data which were gathered from high pressure tests. NOx and CO emissions, combustor temperature at the fuel nozzle, dump plane and exhaust, dynamic pressure and flame structure, using planer laser induced fluorescence, were investigated with respect to power load and ambient temperature. To enhance the NOx and CO emission performances with stable combustion, the relative sensitivities of five control parameters were analyzed, and on the basis of sensitivity analysis data, combustion tuning testing was conducted. By using the CTSA, NOx emission in exhaust gas was reduced from 18 to 2.2 ppm at base load, with high combustion efficiency (>99.9%), and very little pressure fluctuation (P_rms < 0.1 kPa).     

Plasma assisted combustion: Dynamics and chemistry

Plasma assisted combustion is a promising technology to improve engine performance, increase lean burn flame stability, reduce emissions, and enhance low temperature fuel oxidation and processing. Over the last decade, significant progress has been made towards the applications of plasma in engines and the understanding of the fundamental chemistry and dynamic processes in plasma assisted combustion via the synergetic efforts in advanced diagnostics, combustion chemistry, flame theory, and kinetic modeling. New observations of plasma assisted ignition enhancement, ultra-lean combustion, cool flames, flameless combustion, and controllability of plasma discharge have been reported. Advances are made in the understanding of non-thermal and thermal enhancement effects, kinetic pathways of atomic O production, diagnostics of electronically and vibrationally excited species, plasma assisted combustion kinetics of sub-explosion limit ignition, plasma assisted low temperature combustion, flame regime transition of the classical ignition S-curve, dynamics of the minimum ignition energy, and the transport effect by non-equilibrium plasma discharge. These findings and advances have provided new opportunities in the development of efficient plasma discharges for practical applications and predictive, validated kinetic models and modeling tools for plasma assisted combustion at low temperature and high pressure conditions. This article is to provide a comprehensive overview of the progress and the gap in the knowledge of plasma assisted combustion in applications, chemistry, ignition and flame dynamics, experimental methods, diagnostics, kinetic modeling, and discharge control.     

回收垃圾填埋气发电的热气机燃烧系统研究

针对热气机连续燃烧的特点,采用稀薄燃烧和燃气再循环技术,开发了一套新型旋流扩散燃烧系统和燃烧控制逻辑,建立了利用热气机回收填埋气发电的试验系统,在垃圾填埋场进行了现场系统性能试验.结果表明,改装了燃烧垃圾填埋气燃烧器的热气机系统启动容易,对甲烷浓度适应范围广,燃烧完善,燃烧室内温度分布均匀合理,污染物排放低,并且实现了热气机发电系统无人值守运行.     

空气分级比对同轴分级燃烧室性能参数的影响

为掌握同轴分级燃烧室性能参数随空气分级比(主燃级空气流量的比值)的变化规律,以某同轴分级燃烧室为研究对象,数值分析了空气分级比对燃烧室的燃烧效率、总压损失、出口温度分布、污染物排放和绝热壁面最高温度的影响。结果表明：空气分级比主要会改变角涡位置的燃烧温度和高温烟气的停留时间;随着空气分级比的升高,燃烧室总压损失、出口温度分布系数、NO_x排放、绝热壁面最高温度逐渐升高,但燃烧效率、CO污染物排放、径向温度分布系数对空气分级比不敏感;在同轴分级燃烧室设计中,在保证燃烧稳定的前提下可采用较小的空气分级比以实现燃烧室高效、低阻、低污染燃烧。     

Combustion modes of hydrogen jet combustion in a cavity-based supersonic combustor

Optical diagnosis-based combustion experiments were conducted to investigate the characteristics of cavity assisted hydrogen jet combustion in a supersonic flow with a total pressure of 1.6 MPa, a total temperature of 1486 K, and a Mach number of 2.52, simulating flight Mach 6 conditions. A supersonic combustor with a constant cross-sectional area was employed with several cavity configurations, fueling schemes and equivalence ratios. It was found that stable combustion could not be obtained without a cavity, indicating that pure jet-wake stabilized combustion could not be achieved and the cavity acted as a flameholder. Three combustion modes were observed for the cavity assisted hydrogen jet combustion: cavity assisted jet-wake stabilized combustion, cavity shear-layer stabilized combustion, and combined cavity shear-layer/recirculation stabilized combustion. The cavity assisted jet-wake stabilized combustion was observed to be the most unstable mode, accompanied by intermittent blowoff under the present conditions, while the combined cavity shear-layer/recirculation stabilized combustion mode seemed to be the most robust one.     

降低冒烟数燃烧室火焰筒头部改进设计研究

为了解决某型航空发动机燃烧室冒烟数较大的问题,通过分析航空煤油的燃烧化学反应过程和燃烧室内油气掺混燃烧过程,确认了炭烟的产生主要发生在初级反应阶段火焰筒的头部区域。因此提出改进措施,将火焰筒头部的单级旋流器更换为旋流杯,并对旋流杯的结构参数进行调整。采用数值模拟及扇形试验对改进前后的火焰筒性能进行对比分析。研究表明：相对于单级旋流器,旋流杯使燃烧室头部流场由单涡结构变为双涡结构,燃油分布更加均匀,在头部高温的环境中降低了局部富油程度,从而减少了头部炭烟的生成;改进后,燃烧室冒烟数大幅降低,总压恢复系数变化不大,贫油熄火油气比达到了0.004 6,能够满足发动机使用要求。     

Influence of jet-to-crossflow pressure ratio on nonreacting and reacting processes in a scramjet combustor with backward-facing steps

The jet-to-crossflow pressure ratio has a large impact on the combustion mode transition in the scramjet engine, and this information needs to be explored comprehensively. The effect of the jet-to-crossflow pressure ratio on the mixing and combustion processes in a backward-facing step combustor has been investigated numerically, and two similar cases have been utilized to validate the numerical approaches employed. The obtained results show that the wall pressure distribution for the nonreacting flow field has been predicted well, and the peak pressures are all a bit underestimated. However, the predicted wall pressure distribution for the reacting flow field does not match well with the experimental data, and it is overestimated. When the hydrogen is injected only from the bottom wall of the combustor, the mixing efficiency decreases with the increase of the jet-to-crossflow pressure ratio irrespective of the nonreacting or reacting flow field. When the hydrogen is injected simultaneously from the top and bottom walls, the separation shock wave is pushed forward to the entrance of the combustor, and it varies from an oblique one to a normal one. This means that the jet-to-crossflow pressure ratio has a great impact on the combustion mode transition for the scramjet engine, and the stable ramjet/scramjet mode transition can be obtained by controlling the fuel injection scheme.     

Energy consideration for designing supercharged ram jet engines

The present work investigates the energy considerations and performance characteristics of a newly proposed supercharged ram jet engine. Thermodynamics and fluid mechanics analyses were developed to predict specific thrust, thrust‐specific fuel consumption (TSFC), overall efficiency, and thrust‐to‐weight ratio of the engine. Compressor pressure ratio and efficiency, combustor temperature, and pressure losses in the burner and nozzle are considered as primary variables in the engine performance analysis. Performance characteristics are calculated to illustrate the effect of each parameter independently at different flight speeds. This is done while maintaining other parameters at given typical operating values. A computer program was developed to perform the iterative calculations. Results indicate that the compressor pressure ratio and the combustion product temperature are the most critical parameters in determining the performance of the engine. At compressor pressure ratio of 1.15–1.2, the typical static thrust‐to‐weight ratio is at maximum. Increasing combustion product temperature increases the thrust‐to‐weight ratio as well as TSFC. Finally, newly developed high power‐to‐weight ratio IC engine makes it possible for the supercharged ram jet engine to achieve high performance, in terms of thrust‐to‐weight ratio and TSFC. Copyright © 2007 John Wiley & Sons, Ltd.     

主燃孔对某小型发动机燃烧室流动及燃烧特性影响

以头部涡流片加主燃孔形式的小型发动机环形回流燃烧室为研究对象,采用Fluent软件进行了数值研究,对比分析了有无主燃孔、主燃孔相对位置以及主燃孔轴向位置对该类型燃烧室主燃区流场、温度场以及出口温度分布的影响。结果表明：该类型燃烧室主要通过火焰筒头部圆形结构、涡流片形成回流区,而内外环主燃孔的射流主要起到截断主流、促进回流区形成以及改变回流区形态的作用;主燃孔相互交错,有利于促进内外环主燃孔的射流相互对冲剪切,形成较为饱满的回流区;主燃孔轴向位置向燃烧室出口方向移动,主燃孔射流截断主流和挤压主流的效果减弱,出口温度分布系数急剧变大。     

Stabilization performances and mechanisms of a diffusion-like vortex-tube combustor for oxygen-enriched combustion

The stabilization performance and mechanisms in a diffusion-like vortex-tube combustor is investigated for oxygen-enriched combustion. The stability limit, flame configuration, and pressure fluctuation are investigated under various conditions. Results show that a diffusion-like flame structure is established in the combustor and the nonpremixed peculiarity becomes more prominent with the increase of oxygen mole fraction. The steady combustion can be achieved in the range of global equivalence ratio 0.01 to 1.0 with a low-pressure fluctuation amplitude always less than 1300 Pa, indicating a good combustion stability of this combustor. Additionally, the stabilization mechanism is discussed from the time matching and velocity matching. Based on the axial fuel entry method, the Damköhler number (Da) is always less than 1.0 as a whole, which is the principal reason for the tubular flame shape and the steady combustion procedure in this vortex-tube combustor. The intensified combustion under oxygen-enriched combustion can increase the flame speed, and subsequently reduce the mixing quality and make the yellow flame more visible. Besides, the temperature distribution and the flow field structure can explain the corrugation and deformation of the flame front under oxygen-enriched conditions.