Technical Memorandum of National Aerospace Laboratory
巻
169
ページ
25
発行年
1970-02
抄録（英）
Recent trends in gas turbine engines indicate an increase in gas temperature to the turbine blades and a strong interest in cooled turbine blades. It is well known that free stream turbulence affects the nature of the flow around a body and it also affects the heat transfer rates. The present work is concerned with the turbulence in gases flowing from a gas turbine combustor. Extensive research has been made on turbulence itself and its measuring instruments. Many of these works are for isothermal flow and some studies on non isothermal flow are only for simplified conditions. One of the reasons for poor data of turbulence in hot gases is the lack of proper instruments. A recently developed instrument, the cooled film probe, should be useful in this field, and the present experiments employed this probe. A can-type combustor was designed and used for the experiments. This paper contains the description of characteristics of the combustor and the cooled film probe, as well as the results obtained for combustor performance and intensity of turbulence.
ジェットエンジン燃焼器出口ガス流の乱れの測定(Ⅰ): 冷却フィルムプローブによる方法
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