AEROTHERMAL PERFORMANCE-MEASUREMENTS AND ANALYSIS OF A 2-DIMENSIONAL HIGH TURNING ROTOR BLADE

The purpose of this contribution is to report on the aerothermal perfo rmance measurements and calculations carried out around a high-pressur e gas turbine rotor blade profile mounted in a two-dimensional linear cascade a, arrangement. The measurements were performed in the CT-2 fa cility; of the von Karman Institute, allowing a carl-ect simulation of the operating conditions encountered in modern aero-engines, Independ ent variations of exit Mach (0.8-1.3) and Reynolds numbers (5 x 10(5)- 2 X 10(6)), free-stream turbulence (1-6 percent) and incidence angle ( -14- +11 deg) provided the definition of a detailed data base of test results. The measured quantities were the blade velocity and convectiv e hear transfer coefficient distributions. The first objective of the paper is to open and analyze this data base, which is one of those use d at SNECMA for validation purposes. The paper shows the degree of mat urity and reliability SNECMA-ONERA Navier-Stokes solvers have now reac hed for daily use in turbine airfoil design and analysis.