To improve the combustor performance of multi-point injection combustion,lobe nozzle design was applied to the aero-engine model combustor,by presetting the swirl through a certain twisted angle of the edge of the lob...To improve the combustor performance of multi-point injection combustion,lobe nozzle design was applied to the aero-engine model combustor,by presetting the swirl through a certain twisted angle of the edge of the lobe outlet.Numerical simulation in combination with modelling test is used in this paper.The effects of swirl vorticity presetting onto the vortex structure,the characteristics of combustion temperature field,the combustor exit temperature field quality,the combustion efficiency,and the NOx emissions of multi-point injection combustion chamber are investigated.Compared with the conventional vortex flow at the lobe outlet edge,the results of numerical simulation and water modelling test of the swirl vorticity presetting show that the swirl presetting can efficiently enhance the range and intensity of the lobe-induced vorticities.Besides,it can improve the uniformity of the combustion temperature in the combustor chamber,together with the reduced emissions of the pollutant NOx.Moreover,compared with the conventional lobe nozzle chamber,the swirl vortex presetting can effectively improve its combustion performance.The flow simulation test results demonstrate the fluid vortex structure in the combustion chamber and validate the simulation results.展开更多
In order to investigate the effect of the radial gradation of the lobed nozzles on the flow field organization,a cold water model experimental platform for a combustion chamber with radial⁃staged 13-point lobed nozzle...In order to investigate the effect of the radial gradation of the lobed nozzles on the flow field organization,a cold water model experimental platform for a combustion chamber with radial⁃staged 13-point lobed nozzles is built.Compared with a series of combustion OH*luminescence experiments tested by the University of Cincinnati,the four corresponding working conditions of no load,partial load,cruise and take off are selected.The vortex structure,vorticity value,multi-combustion materiel field and combustion characteristics of the flow field in the radial staged combustion chamber of the lobed nozzles under the equivalence ratio,the fuel injection method,the fuel injection ratio and other factors are numerically studied.The results show that under different influencing factors,the varation trend of the hydroxyl flame field of the lobe combustion chamber is basically the same as that of the hydroxyl light emission experiment of the swirl combustion chamber,but the flame field shape is quite different.The local equivalent ratio has a greater influence on the relevant combustion performance of the combustion chamber.Under the conditions of lower equivalence ratio,three-stage air and fuel injection mode,and gradually transferring the fuel flow of the pilot circuit to the external circuit,the temperature field and flame field of the combustion chamber are more evenly distributed,the outlet temperature field quality is better,the combustion efficiency is higher,and the NO_(X) emission is relatively low.These are basically consistent with the cold test results.The cold experimental results illustrate the importance of the influence of the flow field organization on the combustion organization and verify the reliability of the calculation results.展开更多
基金supported by the Natural Science Fund of Liaoning Province Project (No. 201602566)
文摘To improve the combustor performance of multi-point injection combustion,lobe nozzle design was applied to the aero-engine model combustor,by presetting the swirl through a certain twisted angle of the edge of the lobe outlet.Numerical simulation in combination with modelling test is used in this paper.The effects of swirl vorticity presetting onto the vortex structure,the characteristics of combustion temperature field,the combustor exit temperature field quality,the combustion efficiency,and the NOx emissions of multi-point injection combustion chamber are investigated.Compared with the conventional vortex flow at the lobe outlet edge,the results of numerical simulation and water modelling test of the swirl vorticity presetting show that the swirl presetting can efficiently enhance the range and intensity of the lobe-induced vorticities.Besides,it can improve the uniformity of the combustion temperature in the combustor chamber,together with the reduced emissions of the pollutant NOx.Moreover,compared with the conventional lobe nozzle chamber,the swirl vortex presetting can effectively improve its combustion performance.The flow simulation test results demonstrate the fluid vortex structure in the combustion chamber and validate the simulation results.
基金supported by the Lia⁃oning Provincial Natural Science Joint Fund Project(No.120316013).
文摘In order to investigate the effect of the radial gradation of the lobed nozzles on the flow field organization,a cold water model experimental platform for a combustion chamber with radial⁃staged 13-point lobed nozzles is built.Compared with a series of combustion OH*luminescence experiments tested by the University of Cincinnati,the four corresponding working conditions of no load,partial load,cruise and take off are selected.The vortex structure,vorticity value,multi-combustion materiel field and combustion characteristics of the flow field in the radial staged combustion chamber of the lobed nozzles under the equivalence ratio,the fuel injection method,the fuel injection ratio and other factors are numerically studied.The results show that under different influencing factors,the varation trend of the hydroxyl flame field of the lobe combustion chamber is basically the same as that of the hydroxyl light emission experiment of the swirl combustion chamber,but the flame field shape is quite different.The local equivalent ratio has a greater influence on the relevant combustion performance of the combustion chamber.Under the conditions of lower equivalence ratio,three-stage air and fuel injection mode,and gradually transferring the fuel flow of the pilot circuit to the external circuit,the temperature field and flame field of the combustion chamber are more evenly distributed,the outlet temperature field quality is better,the combustion efficiency is higher,and the NO_(X) emission is relatively low.These are basically consistent with the cold test results.The cold experimental results illustrate the importance of the influence of the flow field organization on the combustion organization and verify the reliability of the calculation results.
