Technical Memorandum of National Aerospace Laboratory
巻
193
ページ
26
発行年
1971-01
抄録（英）
JR 220,a simple lift engine, is composed of a relatively low pressure ratio,high flow rate compressor and a high temperature uncooled turbine. For the combustor, high combustion loading and considerable temperature-rise are necessary to maintain the engine performance. The authors have designed an annular-type combustor consisting of 20 fuel nozzles (duple-type swirl atomizer), air swirlers and shrouded primary combustion zone. The sizes and shapes of the combustor were estimated from a practical design method offered by the authors. As a partial improvement of the liner-air-hole arrangement and of the shroud configration, the combustor showed adequate performance as follows: (1) Maximum combustion loading obtained was 1.3 x 108 kcal/m3b atm with a pressure. loss factor of 16 at nearly atmospheric pressure. (2) Combustor exit temperature distribution factor was of the order of 0.25 at maximum temperature-rise. (3) Exit smoke and exhaust odor were almost undetectable during combustion tests under usual the -engine operating conditions.
軽量ジェットエンジンJR220の燃焼器
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