Experimental Results of Full Scale Air-Cooled Turbine Tests

Abstract

In order to investigate several problems associated with the turbine cooling, an air-cooled two-stage axial flow turbine for an aircraft engine application was designed. Aerodynamic characteristics of the two-stage turbine without coolants were obtained first from the cold air turbine tests, and predictions of the turbine performance with supplying of coolants were made using the test results. Following these experiments, cooling tests of the first stage turbine were conducted in the range of turbine inlet gas temperatures lower than 1360 K by the another test apparatus. The descriptions of the turbine and the two test apparatus and the experimental results of the two test turbines are presented. The performance prediction, coolant effects and Reynolds number effect on the turbine performance are also described.

Cooling Characteristics of Film Cooled Turbine Vane Having Multi-Row of Ejection Holes

“…This could be indicated also by the calculation showed by the dotted line. As to Vane 52, the result of /3 = 4.45 percent shows the maximum effectiveness, 7) , of max 0.782 on the suction surface near LE, and the minimum effectiveness,77min' of 0.525 near the trailing edge among the 19 measured points, and the mean cooling effectiveness, 77m' of 0.692 was obtained. The effectiveness in TE region was lower than in LE region.…”

“…4. Chord length is 109 sin, i.e., 3.5 times larger than the actual turbine vane (7). Solidity is 1.363 and outlet angle is about 70 deg.…”