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A Study on Lean Blowout of Multi-vortexes-dome Model combustor

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Journal of Thermal Science 2013年第4期22卷 366-371页

作者： Cong Chen Yixiang Yuan Pengfu Xie Dejun Zhan Chao Yu Wenyu Cao Chunqing Tan Institute of Engineering Thermophysics Chinese Academy of Sciences University of the Chinese Academy of Sciences

The lean blowout experiments of the combustion stability device A (multi-vortexes-dome model combustor) have been carried out at atmospheric pressure. Compared with the device B (single-vortex-dome model combustor), the experimental results show that the device A has a superior lean blowout performance when the combustor reference velocity is within the range from 3.50m/s to 5.59m/s ( while the liner reference velocity is between 3.84 and 6.13m/s), and this superiority will remain stable after the inlet air flow rate reaches a certain value. In order to analyze the phenomena and experimental results, the numerical simulation method is used, and the strain rate and the cold reflux impact are employed to further explain the reason that causes the difference between the two devices' lean blowout characteristics.

关键词： lean blowout primary zone dome multi-vortexes combustor

Effects of Dielectric Barrier Discharge Plasma on the Combustion Performances of Reverse-Flow combustor in an Aero-Engine

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Journal of Thermal Science 2019年第5期28卷 1035-1041页

作者： DENG Jun PENG Changxin HE Liming WANG Shuai YU Jinlu ZHAO Bingbing Science and Technology on Plasma Dynamics Laboratory Air Force Engineering University Xi'an 710038 China AECC Hunan Aviation Powerplant Research Institute Zhuzhou 412002 China

In order to apply plasma assisted combustion(PAC) into a reverse-flow aero-engine and verify the improvement of combustion performance, a feasible approach was proposed in this work. In this approach, based on the structure characteristics of the reverse-flow combustor, a parallel plate double dielectric barrier discharge(DBD) PAC actuator was designed to generate plasma. It was installed at the front of combustor. When the actuator is driven, the original air flow is not disturbed for the device’s structure and installation. Using aviation kerosene as fuel, the effects of plasma on ignition boundary and outlet temperature of the combustor were experimentally investigated at atmosphere pressures. Through the dual high voltage differential power supply, the large gap, large area and uniform plasma discharge was achieved. The results of PAC actuator discharge indicate that inlet air temperature has a small increase of 4–9 K. After PAC is applied, the combustion performances of reverse-flow combustor in an aero-engine are remarkably improved. Experimental results indicate that ignition boundary is widened by 3.7%–12.5% because of the impact of plasma. Outlet highest temperature of combustor is raised by 19–75 K;outlet temperature distribution coefficient is reduced by 11.1%–26.6%. This research provides an effective and practicable way to implement the application of PAC in aero-engine combustor and has some engineering application significance.

关键词： aero-engine reverse-flow combustor double dielectric barrier discharge plasma assisted combustion

Experimental and numerical studies of a lean-burn internally-staged combustor

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Chinese Journal of Aeronautics 2014年第3期27卷 488-496页

作者： Fu Zhenbo Lin Yuzhen Li Lin Zhang Chi National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics School of Energy and Power Engineering Beihang University

A lean-burn internally-staged combustor for low emissions that can be used in civil avi-ation gas turbines is introduced in this paper. The main stage is designed and optimized in terms of fuel evaporation ratio, fuel/air pre-mixture uniformity, and particle residence time using commer-cial computational fluid dynamics （CFD） software. A single-module rectangular combustor is adopted in performance tests including lean ignition, lean blowout, combustion efficiency, emis-sions, and combustion oscillation using aviation kerosene. Furthermore, nitrogen oxides （NOx） emission is also predicted using CFD simulation to compare with test results. Under normal inlet temperature, this combustor can be ignited easily with normal and negative inlet pressures. The lean blowout fuel/air ratio （LBO FAR） at the idle condition is 0.0049. The fuel split proportions between the pilot and main stages are determined through balancing emissions, combustion efficiency, and combustion oscillation. Within the landing and take-off （LTO） cycle, this combustor enables 42%NOx reduction of the standard set by the 6th Committee on Aviation Environmental Protection （CAEP/6） with high combustion efficiency. The maximum board-band pressure oscillations of inlet air and fuel are below 1%of total pressure during steady-state operations at the LTO cycle specific conditions.

关键词： CFD combustor Gas turbine Low emission NOx

Numerical Study of Effect of Compressor Swirling Flow on combustor Design in a MTE

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Journal of Thermal Science 2017年第4期26卷 349-354页

作者： MU Yong WANG Chengdong LIU Cunxi LIU Fuqiang HU Chunyan XU Gang ZHU Junqiang Key Laboratory of Light-duty Gas-turbine Institute of Engineering ThermophysicsChinese Academy of SciencesBeijing100190China University of Chinese Academy of Sciences Beijing 100190 China Institute of Qingdao Light-duty Gas-turbine Qingdao 266000China

An effect of the swirling flow on the combustion performance is studied by the computational fluid dynamics(CFD) in a micro-gas turbine with a centrifugal compressor, dump diffuser and forward-flow combustor. The distributions of air mass and the Temperature Pattern Factor(as: Overall Temperature Distribution Factor-OTDF) in outlet are investigated with two different swirling angles of compressed air as 0° and 15° in three combustors. The results show that the influences of swirling flow on the air distribution and OTDF cannot be neglected. Compared with no-swirling flow, the air through outer liner is more, and the air through the inner liner is less, and the pressure loss is bigger under the swirling condition in the same combustor. The Temperature Pattern Factor changes under the different swirling conditions.

关键词： combustor CFD Compressor exit flow angle Micro Turbojet Engine (MTE)

Numerical Study on Thermoelectric Power Generator in combustor

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Journal of Thermal Science 2022年第6期31卷 2124-2136页

作者： LI Na WU Peiqin LU Xing XU Jinhai WANG Qiuwang CHEN Yitung MA Ting Key Laboratory of Thermo-Fluid Science and Engineering MOEXi’an Jiaotong UniversityXi'an 710049China School of Safety Science and Engineering Xi’an University of Science and TechnologyXi'an 710054China Department of Mechanical Engineering University of NevadaLas Vegas NV 89154-4027USA

Micro gas turbine is a typical distributed energy resource system. The temperature of the burning gas in the combustor reaches 1000 K or even more, which makes a huge temperature difference in the combustor an interesting topic for heat recovery. In this work, thermoelectric devices are used for heat recovery in the combustor of the micro gas turbine. A flow-thermal-electric multiple-physical numerical model is used for the combustor and thermoelectric device power generation system. The effect of the winglet vortex generators installed at the outer wall of the flame tube on the system performance is examined. The numerical results show that the best matching load is about 1.4 times the internal resistance which provides the maximum power output for the thermoelectric generator. Active cascade control of heat transfer enhancement elements on flame tube considering wall safety and conversion efficiency of thermoelectric generator under high temperature and large temperature drop is proposed. The numerical results show that the conversion efficiency of thermoelectric generator can be increased by more than 80%, and the average wall temperature can be reduced by 35 K by using non-uniform arrangement of the winglet vortex generators.

关键词： distributed energy resources micro gas turbine combustor thermoelectric generator winglet vortex generator

The Design and Performance of a High Temperature Rise combustor for Wind Tunnel

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Journal of Thermal Science 2011年第6期20卷 556-562页

作者： Zhang Rongchun Fan Weijun National Key Laboratory on Aero-Engines School of Jet Propulsion Beijing University of Aeronautics and Astronautics Beijing 100191 China

A high-temperature-rise combustor that can be used in high-temperature wind tunnel is introduced in this *** kerosene is used in this type of combustor,with division combustion scheme and evaporator fuel-supply device *** the performance test under atmospheric pressure,when the inlet temperature is 500K and air flow is within the range of 1.5-3.0 kg/s,the outlet temperature can be precisely regulated within the range of ***,higher uniformity of outlet temperature distribution and higher combustion efficiency can be *** the long-time working in the wind tunnel,various components of the combustor,especially the combustor liners are checked without finding any anomaly such as thermal deformation.

关键词： high temperature rise evaporator wind tunnel combustor aviation kerosene

Numerical study of convective heat transfer of a supersonic combustor with varied inlet flow conditions

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Acta Mechanica Sinica 2019年第5期35卷 943-953页

作者： W.H.Fan F.Q.Zhong S.G.Ma X.Y.Zhang State Key Laboratory of High Temperature Gas Dynamics Institute of MechanicsChinese Academy of SciencesBeijing 100190 China School of Engineering Science University of Chinese Academy of SciencesBeijing 100049China

Characteristics of convective heat transfer of a supersonic model combustor with variable inlet flow conditions were studied by numerical simulation in this *** three-dimensional flow and wall heat flux at different air inlet Mach numbers of 2.2,2.8 and 3.2 were studied numerically with Reynolds-averaged Navier-Stokes equations with a shear-stress transport(SST)k-ωturbulence model and a three-step reaction ***,ethylene was chosen as the fuel,and the fixed fuel-to-air equivalence ratio is 0.8 in all cases in this *** results of the simulations indicate that wall heat flux distribution of the combustor is very non-uniform with several peaks of wall heat flux at varied *** the low inlet Mach number of 2.2,a shock train structure is formed in the isolator,and three peaks of wall heat flux are located respectively on the backward face of the cavity,on the side wall near the fuel injection and on the bottom wall near the injection holes,and a maximum wall heat flux reaches 5.4 MW/*** the medium inlet Mach number of 2.8,there exists a much shorter shock structure with three peaks of wall heat flux similar to that of Mach number ***,as the inlet Mach number increased to 3.2,there is no shock structure upstream of fuel injections,and the combustor flow is in a supersonic mode with different locations and values of wall heat flux *** statistical results of wall heat loading show that the change of total wall heat is not monotonic with the increase of inlet Mach number,and the maximum appears in the case of Mach number being ***,for all the cases,the bottom wall takes up more than 50%of the total heat loading.

关键词： Wall heat flux Numerical simulation Ethylene Supersonic combustor

Effects of pressure oscillation on aerodynamic characteristics in an aero-engine combustor

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Chinese Journal of Aeronautics 2021年第2期34卷 454-465页

作者： Hao QIN Guanqiong TANG Xionghui WANG Design and Research Center AECC Commercial Aircraft Engine Co.Ltd.Shanghai 200241China

The effects of pressure oscillation on aerodynamic characteristics in an aero-engine combustor are investigated. A combustor test rig is designed to simulate the pressure drop characteristics of a practical annular combustor. The pressure drop characteristics are firstly measured under atmosphere condition with non-reacting flow(or cold flow), and the air mass flow proportion of each component(dome/liner) are obtained;these properties are base lines for comparison with combustion state. The combustion tests are then carried out under conditions of inlet temperature 340–450 K, fuel air ratio 0.010–0.028. The stability map and the oscillation frequencies are obtained in the tests, the results show that pressure oscillation amplitude increases with the increase of fuel air ratio. Phase trajectory reconstruction is applied to classify the pressure oscillation motion;there are three motions captured in the tests including: ‘‘disk", ‘‘ring" and ‘‘cluster". The pressure drops across the dome under strong pressure oscillation are distinctly divergent from the cold flow, and the changes of pressure drops are mainly affected by pressure oscillation amplitude, but is less influenced by pressure oscillation motion nor oscillation frequencies. Based on the mass flow conservation, the reduction of effective flow area of combustor under strong pressure oscillation is demonstrated. Liner wall temperatures are analyzed through Multiple Linear Regression(MLR)method to estimate the reduction of the air mass flow proportion of the liner cooling under strong pressure oscillation. Finally, the air mass flow proportions of each component under strong pressure oscillation are estimated, the results show that the pressure oscillation motion also has influence on air mass flow proportion.

关键词： Aerodynamic Aero-engine combustor Multiple Linear Regression Nonlinear Phase trajectory reconstruction Pressure oscillation

Experimental investigations of the spray structure and interactions between sectors of a double-swirl low-emission combustor

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Chinese Journal of Aeronautics 2020年第2期33卷 589-597页

作者： Xiongjie FAN Cunxi LIU Gang XU Chi ZHANG Jianchen WANG Yuzhen LIN School of Engineering Science University of Chinese Academy of SciencesBeijing 100190China Key Laboratory of Light-duty Gas-turbine Institute of Engineering ThermophysicsChinese Academy of SciencesBeijing 100190China National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics School of Energy and Power EngineeringBeihang UniversityBeijing 100083China

In this paper,the spray characteristics of a double-swirl low-emission combustor are analyzed by using Particle Imaging Velocimetry(PIV)and Planar Laser Induced Fluorescence(PLIF)technologies in an optical three-sector combustor test *** between sectors and the influence of main stage swirl intensity on spray structure are *** results illustrate that the swirl intensity has great effect on the flow field and spray *** spray cone angle is bigger when the swirl number is 0.7,0.9 than that when the swirl number is *** fuel distribution zone is larger and the distribution is more uniform when the swirl number is *** fuel concentration in the center area of the center plane of side sector(Plane 5)is larger than that of the center plane of middle sector(Plane 1).The spray cone angle in Plane 5 is larger than that in Plane *** width of spray cone becomes larger with the increase of Fuel-Air Ratio(FAR),whereas the spray cone angle under different fuel-air ratios are absolutely the *** results of the mechanism of spray organization in this study can be used to support the design of new low-emission combustor.

关键词： combustor Fuel-air ratio PIV PLIF Pressure drop Swirl intensity