正十二烷高温机理简化及验证

由于详细化学反应机理在模拟燃烧室燃烧时,计算量极大,很难被广泛运用。为了满足工程设计要求,采用替代燃料的简化机理进行计算不失为一种行之有效的方法。本文基于误差传播的直接关系图法和敏感性分析法对正十二烷180组分1962步高温机理(温度大于1100 K)进行简化,获得40组分234步化学反应机理。在温度为1100–1650 K,压力为0.1–4 MPa条件下,采用简化机理及详细机理对不同当量比、压力下着火延迟时间进行模拟,模拟结果与实验数据吻合得较好。通过对不同压力及温度下火焰传播速度进行模拟,验证了简化机理能够正确地反映正十二烷的燃烧特性。利用C_(12)H_(26)/OH/H_2O/CO_2等重要组分随时间变化的数据,验证了简化机理能够准确描述燃烧过程反应物消耗、基团变化、生成物产生的过程,并表明该机理具有较高的模拟精度。利用该简化机理对本生灯进行数值分析,结果表明该机理能够准确地反映火焰区温度和组分浓度的变化。紧凑的正十二烷高温简化机理不仅能够正确体现其物理化学特性,而且能够用于三维数值模拟,具有较高的工程运用价值和应用前景。

航空发动机燃烧室光学可视模型试验件及其流场测量研究进展

航空发动机燃烧室内的燃烧组织是高温高压受限空间内多级旋流复杂流场结构的气动、燃油雾化、蒸发、油气混合和燃烧化学反应多场耦合过程,而其流场特性影响雾化和燃烧过程,从而对燃烧室的燃烧性能具有决定性影响。对燃烧室内复杂强旋流流场组织机理的认识和高精度测试一直是发动机燃烧室研制过程中的难点之一。本文针对光学可视模型燃烧室试验件设计方法及典型发动机燃烧室的流场组织机理和特性进行总结,希望给发动机燃烧室研制过程中光学模型燃烧室试验件的设计提供一定的借鉴,深刻认识目前两类典型的传统旋流杯模型燃烧室和基于分区分级耦合燃烧技术的新型燃烧室的流场特性,促进航空发动机燃烧室的研制。

Experimental Investigations of the Flow Field Structure and Interactions between Sectors of a Double-Swirl Low-Emission Combustor:Effects of Main Stage Swirl Intensity and Venturi Angle

Effect of venturi angle and main stage swirl intensity on flow field and interactions were investigated using PIV.The results showed the difference between the side sector and the middle sector was caused by interactions.The interactions were stronger with the rise of the main stage swirl intensity.When the swirl intensity was 0.7 and 0.9,there was little difference of the width of the recirculation zone.But the flow field had a great difference when the swirl intensity was 0.5 and 0.7,which means that when the swirl intensity was small,the swirl intensity had a great influence on the flow field.Venturi angle had a great influence on the flow field structure and interactions when the venturi angle was big,such as 90°.The venturi angle just had a small influence on the width of the recirculation zone when the venturi angle was relatively small,such as 28°and 52°.The velocity of the center plane between two sectors(plane 3)was small.There was a recirculation zone at upstream of the center plane between two sectors(plane 3)when the swirl intensity was 0.7 and 0.9,whereas not one when the swirl intensity was 0.5.The above was induced by interactions.In addition,the velocity of plane 1,plane 3,and plane 5 when the venturi angle was 52°was smaller than that of 28°and 90°.

Experimental Investigations of the Flow Field Structure and Interactions between Sectors of a Double-Swirl Low-Emission Combustor

In this paper,the flow field characteristics of a double-swirl low-emission combustor were analyzed by using Particle Imaging Velocimetry(PIV)technology in an optical three-sector combustor test rig.The interactions between sectors and the flow field structure were explained.The results illustrated that there was a big difference between the flow field structures of the middle sector and the side sector under the same pressure drop,which was mainly induced by the interactions between sectors.The interactions made the swirl intensity of the middle sector weaker than that of the side sector,which made the recirculation zone of the middle sector be smaller than that of the side sector.With the increase of swirler pressure drop,the jet velocity at the exit of the swirler,the jet expansion angle,the width of the recirculation zone and the recirculating speed of the central axis became larger,enhancing the interactions between air streams from middle sector and side sector.The flow velocity in the central plane between sectors was small,especially the radial velocity,mainly because of the loss of the swirl intensity by the interactions between flow field of adjacent sectors.The expansion angle determined the position of the vortex in the primary recirculation zone;the axial and radial position of the vortex move downstream and radial outward with the increase of the jet expansion angle.The results of the mechanism of flow field organization in this study can be used to support the design of new low-emission combustor.

Premixed Gas Mixing Performance of Lobe-Forced Mixer at Different Configurations

The mixing process of pre-evaporated afterburner fuel at different positions upstream of the mixers and airflow was numerically simulated in a straight channel,with semicircular mixer,rectangular mixer,triangular mixer and chevron mixer respectively.The effects of vortices generated by mixers on fuel distribution and mixing characteristics were studied.The results show that:(1)The scale,strength and breaking speed of the streamwise vortex and the development speed of normal vortex are different downstream of the four mixers,which accelerate the mixing process of fuel and airflow.(2)The fuel distribution at the outlet of mixers,downstream of straight section and downstream of the crest and trough is mainly affected by secondary flow,the streamwise vortex and the normal vortex respectively.(3)The fuel mixing uniformity downstream of the four mixers is increased by about 80%compared with no mixer.In the limited distance,the mixing performance of chevron mixer is the best,while the triangular mixer is the worst Rectangular mixer has the fastest mixing speed and superior comprehensive performance.In addition,the effect of the channel wall on the mixing process downstream of mixers cannot be ignored.

Experimental Studies on Fuel Spray Characteristics of Pressure-Swirl Atomizer and Air-Blast Atomizer

In this work,the effects of fuel temperatures and pressure drops on the flow field and spray characteristics of a pressure-swirl atomizer were discussed using the Particle Imaging Velocimetry(PIV),Planar Laser Induced Fluorescence(PLIF)and Laser Particle Size Analyzer(LPSA)methods.Then the air-blast atomizer was selected to study the interaction of initial atomization and flow field.The effect of fuel-air ratio on the air-blast atomizer were also considered,where the fuel-air ratio was varied by adjusting mass flow rate of the air and fuel respectively.The results show that the spray angle of the pressure-swirl atomizer increases first and changes a little after the pressure drop higher than 0.5 MPa.However,more fuel concentrate on the central region,which is mainly caused by the increase of the proportion of small droplets with lower centrifugal force.The fuel temperature can improve the spray angle only in lower pressure drop,and it has a little effect under higher pressure drops.In addition,the fuel pressure drop has an obvious influence on the fuel distribution and flow field near the nozzle exit compared with the downstream.For the air-blast atomizer,the spray angle increases compared with the pressure-swirl atomizer for the introduction of swirl air.Furthermore,the spray angle decreases with the air mass rate increasing,and it increases with the fuel mass rate increasing.The distribution of velocity and droplet near the nozzle exit is influenced by the air mass rate,and the fuel mass rate mainly affects the distribution in the downstream.The fuel accumulates in the annular area below the nozzle,and the distribution of it changes little with the development along the axial direction.

The Effect of Different Reaction Mechanisms on Combustion Simulation of a Reverse-Flow Combustor

Three different reaction mechanisms of kerosene and flamelet models were used to simulate combustion in a reverse-flow combustor.By comparing the effects of different mechanisms on the flow field characteristics,components and temperature distribution of the combustion chamber,the results showed that:Under different reaction mechanisms,there was a strong similarity between flow filed and temperature field,but the penetration depth and temperature distribution of local jets were affected by the mechanism.Due to the different reaction paths and reaction rates,the distribution of major components had a great degree of similarity,but the concentration of intermediate components varied greatly.Comprehensive analysis,the 16 species and 17 species reaction mechanisms can simulate the flow field and outlet temperature distribution of the combustor well.