A two-stage air-cooled axial-flow turbine for application to the FJR 710/10 turbo-fan jet engine was designed.To determine the aerodynamic performance of the turbine,a cold air test turbine was manufactured and a test was conducted without coolants in the range of total pressure ratio of 1.4～4.1 and equivalent speed of 70～110％ of the equivalent design value.The design procedures of the turbine are described and the experimental results without coolants are presented.Overall stage performance inclt the design point,(i.e.equivalent design speed and equivalent design overall pressure ratio),was different from the estimated design value,which might be partly due to the test without coolants.In order to estimate the effects of cooling air on turbine inlet mass flow characteristics,a few considerations were given.
二段空冷軸流タービン(HT-10C)の空力性能実験(設計および冷却空気を流さない場合の実験結果)
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