Transactions of Nanjing University of Aeronautics & Astronautics
Study on Combustion Performance of the Radial Staged Combustion Chamber with Lobed Nozzles
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Abstract:
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 NOX 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.
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Project Supported:
This work was supported by the Liaoning Provincial Natural Science Joint Fund Project （No.120316013）. The authors would like to acknowledge the following people for their assistance： DU Xiaocheng，WU Zhonggang and all the staff at the Key Laboratory of Energy and Environment，Shenyang Aerospace University.
Clc Number:
V231.3
CHINA AERO-SCIENCES
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