EXPERIMENTAL COLD-FLOW INVESTIGATION OF CHORDWISE STATIC PRESSURE DISTRIBUTION AROUND A TURBINE AIRFOIL.
Technical rept. 1 Apr-1 Jul 67,
AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
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The results from preliminary cold-flow tests are presented. The performance of the in-house turbine cascade rig was checked and calibrated over a cascade airflow range of 3 to 7 pounds per second. Cold-flow measurements were made to investigate the chordwise static pressure distribution around the test blade surface. Experimental data from these tests provided valuable velocity, pressure, and flow distributions around the test blade. Once the flow field around the standard blade profile is known, the gas-to-blade heat transfer coefficients around the blade can more accurately be determined. This information is important in assessing the blade cooling design requirements for future hot-flow tests. Author
- Jet and Gas Turbine Engines