Studies of Heat Transfer to Gas Turbine Components.
Final rept. Jun 76-Oct 77,
CALSPAN CORP BUFFALO N Y
Pagination or Media Count:
A 180 sector of the first stage stationary inlet nozzle of the AiResearch TFE-731-2 engine was instrumented with thin-film heat-transfer gages and experiments were performed to obtain detailed heat-transfer rate distributions. It is shown that the experimental apparatus can potentially be used to study total-pressure losses in cascades. The experimental apparatus consists of a helium-driven shock tube as a short-duration source of high-temperature high-pressure gas, driving a nozzle test-section device mounted near the exit of a primary shock-tunnel receiver tank. The nozzle test-section device consists of a forward transition section with a circular opening facing the supersonic primary nozzle flow and with the external shape of a frustum of a cone. Internal contouring is provided to transform the circular-section subsonic intake flow into one filling approximately a 180 annular segment having a geometry approximating that of the entrance to the turbine stator stage in a turbojet. Detailed measurements of static pressure in the test section and heat-transfer rate on the stator sector have been obtained and are reported herein. Author
- Jet and Gas Turbine Engines