离心甩油折流环形燃烧室的性能试验

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Performance experiment of a reflection flow annular combustor with slinger

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
China Aviation Powerplant Research Institute, Zhuzhou 412002, China

摘要: 以某离心甩油折流燃烧室为研究对象, 采用试验的方法, 在不同的甩油盘转速下对其性能进行了研究.研究结果表明, 该燃烧室具有较高的总压恢复系数, 燃烧室出口温度场分布不均匀系数(OTDF)小于0.3, 燃烧室的燃烧效率η在0.99以上, 燃烧室的贫油熄火边界较窄.该研究结果为折流燃烧室的设计提供了有益的参考.
- 航空、航天推进系统 /
- 航空发动机 /
- 折流燃烧室 /
- 离心甩油盘 /
- 出口温度分布系数(OTDF) /
- 总压恢复系数 /
- 熄火边界
Abstract: An experimental study on performance of a slinger annular combustor was performed at various slinger rotary speeds.The experimental results show that it has a higher total pressure recovery coefficient and a narrow lean blowoff limit.The outlet temperature distribution factor is less than 0.3,and combustion efficiency is above 0.99.The experimental results provide technical support for this kinds of combustor design and development.
- aerospace propulsion system /
- aeroengine /
- annular combustor with slinger /
- slinger /
- outlet temperature distribution factor(OTDF) /
- total pressure recovery coefficient /
- blowoff limit

[1]	Lefebvre A H.Gas turbine combustion[M].Washington:Hemisphere Publishing Corp,1983.
[2]	Mellor A M.Design of modern turbine combustors[M].New York,NY:Academic Press Inc,1990.
[3]	Maskey H C,Marsh F X.The annular combustion chamber with centrifugal fuel injection[R].SAE-444C,1962.
[4]	Rogo C,Trauth R L.Design of high heat release slinger combustor with rapid acceleration requirement[R].SAE-740167,1974.

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