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

Abstract

Film-cooled turbine vanes having 14 rows of round holes were designed. Two-dimensional cascade tests of two kinds of scaled vanes were carried out and cooling performances were obtained. Coolant flow distributions were controlled by the impingement and plenum chamber configuration. Higher cooling effectiveness than 0.65 was obtained for the coolant flow ratio of 4.5 percent. And it was clarified that the distributions of cooling effectiveness of the vane surface was governed by the configuration of coolant flow distribution to the cooling hole rows, and, that with using relatively greater amount of coolant to the leading edge region, higher cooling performance can be obtained. Also, numerical calculations of cooling performance and prediction for turbine application were presented.

Analysis and Test of Coolant Flow and Heat Transfer of an Advanced Full-Coverage Film-Cooled Laminated Turbine Vane

“…The numerical analysis described in the preceding paragraph necessitates static pressure distribution on the vane's outer surface as an input condition. In the first numerical work, the experimental result with a low-speed wind tunnel cascade test using unheated mainstream by Sakata et al [5] was adopted since all the vanes' profiles were the same. After the present test vanes were fabricated, the distribution was obtained from vane #2 in a high temperature cascade test.…”

“…Temperature are roughly the same as those in the present study. On the other hand, the curve for the FCFC vane is taken from the results by Sakata et al [5 ] , where the low-speed wind tunnel cascade test was conducted with the use of unheated mainstream air. As is remarked in Sakata's paper, a correction of data from room temperature conditions to elevated temperature conditions might cause a reduction of effectiveness to some extent even without the consideration of radiative heat transfer.…”