AN EXPERIMENTAL INVESTIGATION OF PRESSURE DISTRIBUTION ON THE END OF A COOLED BLADE

The pressure distribution on the end plane of a cooled blade was studied in order to facilitate control of the cooling air flow rate. The test stand consisted of a centrifugal compressor, a combustion chamber, a mixing chamber, a honeycomb damper, the test section with the investigated cascade profiles, a fuel-feed system, a control panel, and monitoring instrumentation. The investigated cascade consisted of five cylindrical blades, only one of which was cooled. The blades had a chord of 121.7 mm, a height of 120 mm, and a pitch of 83.3 mm. The mounting of the blades provided a shock-free inlet flow. The cooling air was supplied from the main flow. The pressure distribution in the radial clearance was studied with respect to the following factors: (1) air flow rate through the cascade; (2) size of the radial clearance; (3) cooling air flow rate through the blade channels; and (4) the total effect of the three factors. (Author) Edited machine trans. of Energeticheskoe Mashinostroenie (USSR) n5 p128-134 1967.