Experimental study of rotating gliding arc discharge plasma-assisted combustion in an aero-engine combustion chamber
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摘要
The combustion chamber is the core component of an aero-engine, and affects its reliability and security operation, even the performance of the aircraft. In this work, a Plasma-Assisted Combustion(PAC) test platform was developed to validate the feasibility of using PAC actuators to enhance annular combustor performance. Two plans of PAC(rotating gliding arc discharge plasma) were designed, Assisted Combustion from Primary Holes(ACPH) and Assisted Combustion from Dilution Holes(ACDH). Comparative experiments and analysis between conventional combustion and PAC were conducted to study the effects of ACPH and ACDH on the performances including average outlet temperature, combustion efficiency, pattern factor under four different excessive air coefficients(0.8, 1, 2, and 4), and lean blowout performance at different inlet airflow velocities. Experimental results show that the combustion efficiency is improved after PAC compared with that in normal conditions, and the combustion efficiency of ACPH increases2.45%, 1.49%, 1.04%, and 0.47%, while it increases 2.75%, 1.67%, 1.36%, and 0.36% under ACDH conditions. The uniformity of the outlet temperature field and the lean blowout performance are improved after PAC. Especially for ACPH, the widening of the lean blowout limit is8.3%, 12.4%, 12.8%, and 25% respectively when the inlet velocity ranges from 60 m/s to120 m/s. These results offer new perspectives for using PAC devices to enhance aero-engine combustors' performances.
The combustion chamber is the core component of an aero-engine, and affects its reliability and security operation, even the performance of the aircraft. In this work, a Plasma-Assisted Combustion(PAC) test platform was developed to validate the feasibility of using PAC actuators to enhance annular combustor performance. Two plans of PAC(rotating gliding arc discharge plasma) were designed, Assisted Combustion from Primary Holes(ACPH) and Assisted Combustion from Dilution Holes(ACDH). Comparative experiments and analysis between conventional combustion and PAC were conducted to study the effects of ACPH and ACDH on the performances including average outlet temperature, combustion efficiency, pattern factor under four different excessive air coefficients(0.8, 1, 2, and 4), and lean blowout performance at different inlet airflow velocities. Experimental results show that the combustion efficiency is improved after PAC compared with that in normal conditions, and the combustion efficiency of ACPH increases2.45%, 1.49%, 1.04%, and 0.47%, while it increases 2.75%, 1.67%, 1.36%, and 0.36% under ACDH conditions. The uniformity of the outlet temperature field and the lean blowout performance are improved after PAC. Especially for ACPH, the widening of the lean blowout limit is8.3%, 12.4%, 12.8%, and 25% respectively when the inlet velocity ranges from 60 m/s to120 m/s. These results offer new perspectives for using PAC devices to enhance aero-engine combustors' performances.
The combustion chamber is the core component of an aero-engine, and affects its reliability and security operation, even the performance of the aircraft. In this work, a Plasma-Assisted Combustion(PAC) test platform was developed to validate the feasibility of using PAC actuators to enhance annular combustor performance. Two plans of PAC(rotating gliding arc discharge plasma) were designed, Assisted Combustion from Primary Holes(ACPH) and Assisted Combustion from Dilution Holes(ACDH). Comparative experiments and analysis between conventional combustion and PAC were conducted to study the effects of ACPH and ACDH on the performances including average outlet temperature, combustion efficiency, pattern factor under four different excessive air coefficients(0.8, 1, 2, and 4), and lean blowout performance at different inlet airflow velocities. Experimental results show that the combustion efficiency is improved after PAC compared with that in normal conditions, and the combustion efficiency of ACPH increases2.45%, 1.49%, 1.04%, and 0.47%, while it increases 2.75%, 1.67%, 1.36%, and 0.36% under ACDH conditions. The uniformity of the outlet temperature field and the lean blowout performance are improved after PAC. Especially for ACPH, the widening of the lean blowout limit is8.3%, 12.4%, 12.8%, and 25% respectively when the inlet velocity ranges from 60 m/s to120 m/s. These results offer new perspectives for using PAC devices to enhance aero-engine combustors' performances.
引文
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14.Liu XJ,He LM,Yu JL,Zhang HL.Experimental investigation of effects of airflows on plasma-assisted combustion actuator characteristics.Chin Phys B 2015;24(4):045101.
15.Jiang CY,Xia SG,Zou X,He JJ.Effects of edge electric field in dielectric barrier discharges on methane combustion enhancement.High Voltage Eng 2009;35(1):26-30[Chinese].
16.Zhou SY,Che XK,Nie WS.Influence of nanosecond pulse dielectric barrier discharge plasma on the cavity performance in scramjet combustor.High Voltage Eng 2014;40(10):3032-7[Chinese].
17.He LM,Lei JP,Chen Y,Liu XJ,Chen GC,Zheng H.Experimental investigation on characteristic atmospheric ACrotating gliding arc discharge.High Voltage Eng 2017;43(9):3061-9[Chinese].
18.Zhao ML,Yang ZM,Lin YZ,Liu JL,Ge X.Conversion methods for lean ignition performances among single-sector,multi-sector and full annular combustors.J Aerospace Power 2017;32(8):1822-6[Chinese].
19.Li M,Wu EP,Suo JQ,Liang HX.Performance comparative experiment on flame tubes of a certain combustor.J Aerospace Power 2013;28(8):1689-95[Chinese].
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21.Starikovskaia SM,Kosarev IN,Krasnochub AV,Mintoussov EI,Starikovskii AY.Control of combustion and ignition of hydrocarbon containing mixtures by nanosecond pulsed discharges.Reston:AIAA;2005.Report No.:AIAA-2005-1195.
22.ELKady AM,Jeng SM,Mongia HC.The influence of primary air jets on flow and pollutant emissions characteristics within a model gas turbine combustor.Reston:AIAA;2006.Report No.:AIAA-2006-0544.
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24.Ding GY,He XM,Zhao ZQ,An BK,Song YY,Zhu YX.Effect of dilution holes on the performance of a triple swirler combustor.Chin J Aeronaut 2014;27(6):1421-9.
2.Bahr DW.Technology for the design of high temperature rise combustors.Reston:AIAA;1985.Report No.:AIAA-1985-1292
3.Suo JQ,Yu H,Zheng LX.Experimental study on lean blowout of a high temperature rise combustor.Reston:AIAA;2017.Report No.:AIAA-2017-1056.
4.Ombrello T,Won SH,Ju YG,Williams S.Flame propagation enhancement by plasma excitation of oxygen.Part I:Effects of O3Combust Flame 2010;157(10):1906-15.
5.Klimov A,Brovkin V,Bityurin V,Vinogradov V,Van Wie DMPlasma assisted combustion.Reston:AIAA;2001.Report No.AIAA-2001-0491.
6.Klimov A,Bityurin V,Brovkin V,Vystavkin N,Kuznetsov AVan Wie DM.Optimization of plasma generators for plasma assisted combustion.Reston:AIAA;2001.Report No.:AIAA-2001-2874.
7.Klimov A,Bitiurin V,Moralev I,Tolkunov B,Nikitin A,Velichko A,et al.Non-premixed plasma assisted combustion of hydrocarbon fuel in high-speed airflow.Reston:AIAA;2006.Report No.AIAA-2006-0617.
8.Kim W,Do H,Mungal MG,Cappelli MA.Flame stabilization enhancement and NOxproduction using ultra short repetitively pulsed plasma discharges.Reston:AIAA;2006.Report No.:AIAA-2006-0560.
9.Yang S,Nagaraja S,Sun WT,Yang V.Multiscale modeling and general theory of non-equilibrium plasma-assisted ignition and combustion.J Phys D Appl Phys 2017;50(43):433001.
10.Yang S,Nagaraja S,Sun WT,Yang V.A detailed comparison of thermal ignition and nanosecond pulsed plasma assisted ignition of hydrogen-air mixtures.Reston:AIAA;2015.Report No.:AIAA-2015-1615.
11.Lan YD,He LM,Guo XY.Effect of plasma on the combustion of H2/Air mixture under different initial temperature.J Propul Technol 2009;30(6):651-5[Chinese].
12.Hu HB,Xu G,Fang AB,Hang WG.Non-equilibrium plasma assisted combustion of low BTU fuels.J Eng Thermophys 2010;31(9):1603-6[Chinese].
13.Mu HB,Yu L,Li P,Tang CL,Wang JH.Zhang GJ.Enhancement of the premixed CH4/O2/He flame speed with dielectric barrier discharge.High Voltage Eng 2014;40(10):2980-5[Chinese].
14.Liu XJ,He LM,Yu JL,Zhang HL.Experimental investigation of effects of airflows on plasma-assisted combustion actuator characteristics.Chin Phys B 2015;24(4):045101.
15.Jiang CY,Xia SG,Zou X,He JJ.Effects of edge electric field in dielectric barrier discharges on methane combustion enhancement.High Voltage Eng 2009;35(1):26-30[Chinese].
16.Zhou SY,Che XK,Nie WS.Influence of nanosecond pulse dielectric barrier discharge plasma on the cavity performance in scramjet combustor.High Voltage Eng 2014;40(10):3032-7[Chinese].
17.He LM,Lei JP,Chen Y,Liu XJ,Chen GC,Zheng H.Experimental investigation on characteristic atmospheric ACrotating gliding arc discharge.High Voltage Eng 2017;43(9):3061-9[Chinese].
18.Zhao ML,Yang ZM,Lin YZ,Liu JL,Ge X.Conversion methods for lean ignition performances among single-sector,multi-sector and full annular combustors.J Aerospace Power 2017;32(8):1822-6[Chinese].
19.Li M,Wu EP,Suo JQ,Liang HX.Performance comparative experiment on flame tubes of a certain combustor.J Aerospace Power 2013;28(8):1689-95[Chinese].
20.Buriko Y,Ninogradov V,Waltrup P,Waltrup P.Influence of active radical concentration on self-ignition delay of a propane/air mixture.Reston:AIAA;2001.Report No.:AIAA-2001-3958.
21.Starikovskaia SM,Kosarev IN,Krasnochub AV,Mintoussov EI,Starikovskii AY.Control of combustion and ignition of hydrocarbon containing mixtures by nanosecond pulsed discharges.Reston:AIAA;2005.Report No.:AIAA-2005-1195.
22.ELKady AM,Jeng SM,Mongia HC.The influence of primary air jets on flow and pollutant emissions characteristics within a model gas turbine combustor.Reston:AIAA;2006.Report No.:AIAA-2006-0544.
23.Yu PX,Bai JQ,Yang H,Chen S,Pan K.Interface flux reconstruction method based on optimized weight essentially non-oscillatory scheme.Chin J Aeronaut 2018;31(5):1020-9.
24.Ding GY,He XM,Zhao ZQ,An BK,Song YY,Zhu YX.Effect of dilution holes on the performance of a triple swirler combustor.Chin J Aeronaut 2014;27(6):1421-9.