自维持合成双射流对超声速燃烧室凹腔质量交换特性影响研究
|
摘要
为了改善燃烧室凹腔与主流的掺混性能,提出了一种利用凹腔内压力差形成自维持合成射流的流场控制方法,在超声速冷流条件下,采用动网格技术对激励器的膜片振动过程进行模拟,详细分析了自维持合成双射流与凹腔相互作用的过程,研究了激励器出口位置、参数、凹腔构型以及来流Ma数等参数的影响。结果表明:加入自维持合成双射流激励器可以大幅提升凹腔的质量交换特性,减小气体在凹腔内的驻留时间;且激励器出口位置分布对控制效果影响较大,当激励器出口位于凹腔底部中间位置时,质量交换率最大能够提升49%。此外,凹腔构型以及来流条件都会影响自维持合成双射流对凹腔掺混的控制效果,在相同来流条件下,凹腔长深比越大,控制效果越显著,自维持合成双射流能使长深比L/D=7.76的凹腔质量交换率提升115%;对于同一凹腔,随着来流马赫数增加,激励器对凹腔质量交换特性控制效果提升更为明显,但改变振动膜片的振幅和频率对控制效果的改善不明显。
In order to enhance the mixing characteristic of cavity with mainstream in the scramjet engine,a flow field control method using self-sustaining dual synthetic jet is proposed by utilizing the pressure difference in the cavity.Adapting dynamic mesh technology,periodical vibration of the membrane are numerically studied under supersonic cold flow,and the interactions between self-sustaining dual synthetic and cavity are analyzed in detail.The impacts of outlet positions,driving parameters,cavity configurations and Mach numbers on control effects are mainly researched.The results show that self-sustaining dual synthetic jet actuator can improve the mass exchange characteristics of cavity and reduce the residence time of gas in the cavity.The position of the actuator'outlet has a great influence on the control effect.The mass exchange rate can be improved by 49.2% when the position of outlet is located in the middle of cavity floor.Besides,cavity configurations and Mach numbers can also make a difference to the mixing characteristic.The results suggest that the cavity with a longer ratio of length and diameter(L/D)can obtain a better control effect when using self-sustaining dual synthetic jet actuator,and the mass exchange rate of cavity with L/D=7.76 can increase by 115%.For the same cavity,the mass exchange rate is improved when increasing the fluid velocity,but when changing amplitudes and frequencies of the membrane,the control effects are not obvious.
In order to enhance the mixing characteristic of cavity with mainstream in the scramjet engine,a flow field control method using self-sustaining dual synthetic jet is proposed by utilizing the pressure difference in the cavity.Adapting dynamic mesh technology,periodical vibration of the membrane are numerically studied under supersonic cold flow,and the interactions between self-sustaining dual synthetic and cavity are analyzed in detail.The impacts of outlet positions,driving parameters,cavity configurations and Mach numbers on control effects are mainly researched.The results show that self-sustaining dual synthetic jet actuator can improve the mass exchange characteristics of cavity and reduce the residence time of gas in the cavity.The position of the actuator'outlet has a great influence on the control effect.The mass exchange rate can be improved by 49.2% when the position of outlet is located in the middle of cavity floor.Besides,cavity configurations and Mach numbers can also make a difference to the mixing characteristic.The results suggest that the cavity with a longer ratio of length and diameter(L/D)can obtain a better control effect when using self-sustaining dual synthetic jet actuator,and the mass exchange rate of cavity with L/D=7.76 can increase by 115%.For the same cavity,the mass exchange rate is improved when increasing the fluid velocity,but when changing amplitudes and frequencies of the membrane,the control effects are not obvious.
引文
[1]Cockrell J C E,Engelund W C,Bittner R D,et al.Integrated Aero-Propulsive CFD Methodology for the HyperX Flight Experiment[J].AIAA Journal,2000,38(6):161-170.
[2]Serre L,Falempin F.Promethee-The French Military Hypersonic Propulsion Program[C].UK:AIAA International Space Planes and Hypersonic Systems and Technologies,2003.
[3]Mathur T,Gruber M,Jackson K,et al.Supersonic Combustion Experiments with a Cavity-Based Fuel Injector[J].Journal of Propulsion and Power,2001,17(6):1305-1312.
[4]潘余.超燃冲压发动机多凹腔燃烧室燃烧与流动过程研究[D].长沙:国防科学技术大学,2007.
[5]Baurle R,Gruber M.A Study of Recessed Cavity Flowfields for Supersonic Combustion Applications[C].USA:AIAA Aerospace Sciences Meeting and Exhibit,1998.
[6]Zhang X,Edwards J K,Smith R A,et al.Experimental Investigation of Supersonic Flow over Two Cavities in Tandem[J].AIAA Journal,1992,30(5):1182-1190.
[7]耿辉.超声速燃烧室中凹腔上游横向喷注燃料的流动、混合与燃烧特性研究[D].长沙:国防科学技术大学,2007.
[8]Quick A,King P,Gruber M,et al.Upstream Mixing Cavity Coupled with a Downstream Flame Holding Cavity Behavior in Supersonic Flow[C].USA:41st AIAA/ASEM/SAE/ASEE Joint Propulsion Conference and Exhibit,2005.
[9]Jeyakumar S,Balachandran P,Indira S.Experimental Investigations on Supersonic Stream Past Axisymmetric Cavities[J].Journal of Propulsion and Power,2006,22(5):1142-1145.
[10]Yu G,Li J,Zhang X,et al.Investigation of Kerosene Combustion Characteristics with Pilot Hydrogen in Model Supersonic Combustors[J].Journal of Biomedical Optics,2001,17(6):1263-1272.
[11]范周琴,刘卫东,孙明波,等.超燃冲压发动机多凹腔燃烧室混合与燃烧性能定量分析[J].推进技术,2012,33(02):185-192.(FAN Zhou-qin,LIU Weidong,SUN Ming-bo,et al.Quantitative Analysis of Mixing and Combustion in the Scramjet Multi-Cavity Combustor[J].Journal of Propulsion Technology,2012,33(2):185-192.
[12]周思引,车学科,聂万胜,等.等离子体对超燃燃烧室凹腔性能影响的数值研究[J].推进技术,2013,34(7):950-955.(ZHOU Si-yin,CHE Xue-ke,NIE Wan-sheng,et al.Numerical Study of Effects of Plasma on Performance of Scramjet Combustor Cavity[J].Journal of Propulsion Technology,2013,34(7):950-955.)
[13]周思引,车学科,聂万胜.纳秒脉冲介质阻挡放电等离子体对超声速燃烧室中凹腔性能的影响[J].高电压技术,2014,40(10):3032-3037.
[14]Smith B,Glezer A.Vectoring of Adjacent Synthetic Jets[J].AIAA Journal,2005,43(10):2117-2124.
[15]Lou Z B,Deng X,Xis Z X,et al.Flow Field and Heat Transfer Characteristics of Impingement Baesd on a Vec-toring Dual Synthetic Jet Actuator[J].International Journal of Heat and Mass Transfer,2016,10(2):18-25.
[16]Guo D,Cary A W,Agarwal R K.Numerical Simulation of Vectoring Control of a Primary Jet with a Synthetic Jet[J].AIAA Journal,2003,41(12):2364-2370.
[17]张攀峰,王晋军.孔口倾斜角对合成射流控制翼型流动分离的影响[J].兵工学报,2009,30(12).
[18]Luo Z B,Xia Z X,Liu B.New Generation of Synthetic Jet Actuator[J].AIAA Journal,2006,44(10):2418-2419.
[19]罗振兵,夏智勋,邓雄,等.合成双射流及其流动控制技术研究进展[J].空气动力学报,2017,35(2):253-264.
[20]Baurle R A,Tam C J,Edwards J R,et al.Hybrid Simulation Approach for Cavity Flow:Blending,Algorithm,and Boundary Treatment Issues[J].AIAA Journal,2003,41(8):1463-1480.
[21]Gruber M R.Fundamental Investigations of an Integrated Fuel Injector Flameholder Concept for Supersonic Combustion[J].ADA,2001,17(1).
[22]罗振兵.合成射流/合成双射流机理及其在射流矢量控制和微泵中的应用研究[D].长沙:国防科学技术大学,2006.
[23]Luo Zhen-bing,Xia Zhi-xun.A Novel Valve-Less Synthetic-Jet-Based Micro-Pump[J].Sensors and Actuators A,2005,122(1):131-140.
[24]Luo Z B,Xia Z X.Numerical Simulation of Synthetic Jet Flow Field and Parameter Analysis of Actuator[J].Journal of Propulsion Technology,2004,25(3):199-205.
[25]Gruber M R,Donber J M,Carter C D.Mixing and Combustion Studies Using Cavity-Based Flameholders in a Supersonic Flow[J].Journal of Propulsion and Power,2004,20(5):769-778.
[26]汪洪波,孙明波,吴海燕,等.超声速燃烧凹腔质量交换特性的混合RAN/LES模拟[J].航空动力学报,2010,25(1):41-46.
[27]孙明波.超声速来流稳焰凹腔的流动及火焰稳定机制研究[D].长沙:国防科学技术大学,2008.
[2]Serre L,Falempin F.Promethee-The French Military Hypersonic Propulsion Program[C].UK:AIAA International Space Planes and Hypersonic Systems and Technologies,2003.
[3]Mathur T,Gruber M,Jackson K,et al.Supersonic Combustion Experiments with a Cavity-Based Fuel Injector[J].Journal of Propulsion and Power,2001,17(6):1305-1312.
[4]潘余.超燃冲压发动机多凹腔燃烧室燃烧与流动过程研究[D].长沙:国防科学技术大学,2007.
[5]Baurle R,Gruber M.A Study of Recessed Cavity Flowfields for Supersonic Combustion Applications[C].USA:AIAA Aerospace Sciences Meeting and Exhibit,1998.
[6]Zhang X,Edwards J K,Smith R A,et al.Experimental Investigation of Supersonic Flow over Two Cavities in Tandem[J].AIAA Journal,1992,30(5):1182-1190.
[7]耿辉.超声速燃烧室中凹腔上游横向喷注燃料的流动、混合与燃烧特性研究[D].长沙:国防科学技术大学,2007.
[8]Quick A,King P,Gruber M,et al.Upstream Mixing Cavity Coupled with a Downstream Flame Holding Cavity Behavior in Supersonic Flow[C].USA:41st AIAA/ASEM/SAE/ASEE Joint Propulsion Conference and Exhibit,2005.
[9]Jeyakumar S,Balachandran P,Indira S.Experimental Investigations on Supersonic Stream Past Axisymmetric Cavities[J].Journal of Propulsion and Power,2006,22(5):1142-1145.
[10]Yu G,Li J,Zhang X,et al.Investigation of Kerosene Combustion Characteristics with Pilot Hydrogen in Model Supersonic Combustors[J].Journal of Biomedical Optics,2001,17(6):1263-1272.
[11]范周琴,刘卫东,孙明波,等.超燃冲压发动机多凹腔燃烧室混合与燃烧性能定量分析[J].推进技术,2012,33(02):185-192.(FAN Zhou-qin,LIU Weidong,SUN Ming-bo,et al.Quantitative Analysis of Mixing and Combustion in the Scramjet Multi-Cavity Combustor[J].Journal of Propulsion Technology,2012,33(2):185-192.
[12]周思引,车学科,聂万胜,等.等离子体对超燃燃烧室凹腔性能影响的数值研究[J].推进技术,2013,34(7):950-955.(ZHOU Si-yin,CHE Xue-ke,NIE Wan-sheng,et al.Numerical Study of Effects of Plasma on Performance of Scramjet Combustor Cavity[J].Journal of Propulsion Technology,2013,34(7):950-955.)
[13]周思引,车学科,聂万胜.纳秒脉冲介质阻挡放电等离子体对超声速燃烧室中凹腔性能的影响[J].高电压技术,2014,40(10):3032-3037.
[14]Smith B,Glezer A.Vectoring of Adjacent Synthetic Jets[J].AIAA Journal,2005,43(10):2117-2124.
[15]Lou Z B,Deng X,Xis Z X,et al.Flow Field and Heat Transfer Characteristics of Impingement Baesd on a Vec-toring Dual Synthetic Jet Actuator[J].International Journal of Heat and Mass Transfer,2016,10(2):18-25.
[16]Guo D,Cary A W,Agarwal R K.Numerical Simulation of Vectoring Control of a Primary Jet with a Synthetic Jet[J].AIAA Journal,2003,41(12):2364-2370.
[17]张攀峰,王晋军.孔口倾斜角对合成射流控制翼型流动分离的影响[J].兵工学报,2009,30(12).
[18]Luo Z B,Xia Z X,Liu B.New Generation of Synthetic Jet Actuator[J].AIAA Journal,2006,44(10):2418-2419.
[19]罗振兵,夏智勋,邓雄,等.合成双射流及其流动控制技术研究进展[J].空气动力学报,2017,35(2):253-264.
[20]Baurle R A,Tam C J,Edwards J R,et al.Hybrid Simulation Approach for Cavity Flow:Blending,Algorithm,and Boundary Treatment Issues[J].AIAA Journal,2003,41(8):1463-1480.
[21]Gruber M R.Fundamental Investigations of an Integrated Fuel Injector Flameholder Concept for Supersonic Combustion[J].ADA,2001,17(1).
[22]罗振兵.合成射流/合成双射流机理及其在射流矢量控制和微泵中的应用研究[D].长沙:国防科学技术大学,2006.
[23]Luo Zhen-bing,Xia Zhi-xun.A Novel Valve-Less Synthetic-Jet-Based Micro-Pump[J].Sensors and Actuators A,2005,122(1):131-140.
[24]Luo Z B,Xia Z X.Numerical Simulation of Synthetic Jet Flow Field and Parameter Analysis of Actuator[J].Journal of Propulsion Technology,2004,25(3):199-205.
[25]Gruber M R,Donber J M,Carter C D.Mixing and Combustion Studies Using Cavity-Based Flameholders in a Supersonic Flow[J].Journal of Propulsion and Power,2004,20(5):769-778.
[26]汪洪波,孙明波,吴海燕,等.超声速燃烧凹腔质量交换特性的混合RAN/LES模拟[J].航空动力学报,2010,25(1):41-46.
[27]孙明波.超声速来流稳焰凹腔的流动及火焰稳定机制研究[D].长沙:国防科学技术大学,2008.