.... Experiments were conducted with air over a range of Reynolds numbers between 7500 and 35,000 and for three different spanwise pin spacings. Experimental results indicated an increase in cylinder drag with a reduction in spanwise pin spacing. The gas turbine and electronics industries use cylinders or pin fins...

.... In nondimensional terms, these roughnesses represent compressor blade roughnesses found in actual gas turbines. Downstream pressure, velocity, and angle have been measured with a five-hole probe at 0.3 chord downstream of the blade trailing edge. For the tested roughnesses of 180 μ m , 300 μ m , 425 μ m , and 850 μ...

...P. A. Strakey; M. J. Yip Planar velocity measurements under cold-flow conditions in a swirl-stabilized dump combustor typical of land-based gas turbine combustors were carried out using two-dimensional particle image velocimetry (PIV). Axial, radial, and tangential velocity components were measured...

... to be relevant to quantifying the effects of roughness on the transition process. 27 07 2004 21 02 2005 boundary layer turbulence surface roughness gas turbines blades flow separation bubbles flow instability Bons , J. P. , McClain , S. T. , Taylor , R. P...

...J. U. Schlüter; X. Wu; S. Kim; S. Shankaran; J. J. Alonso; H. Pitsch Full-scale numerical prediction of the aerothermal flow in gas turbine engines are currently limited by high computational costs. The approach presented here intends the use of different specialized flow solvers based...

... of gas-turbine engines. Detailed measurements of the velocity field have been performed with a miniature four-wire probe at the jet exit plane, in the oncoming cross-stream boundary layer, and in a series of planes that capture the streamwise development of the vortex in the crossflow boundary layer up...

...M. I. Yaras; P. Orsi This study examines the effects of periodic inflow unsteadiness on the flow development through fishtail-shaped diffusers utilized on small gas-turbine engines. In this application, periodic unsteadiness is caused by a jet-wake type of flow discharging from each passage...

...N. J. Hughes, Research Associate; J. F. Carrotte, RR Lecturer in Aerospace Propulsion This paper describes an experimental investigation on a gas turbine combustor geometry that is typical of current aerospace applications. The isothermal investigation has concentrated on the flow approaching...

...R. W. Radomsky; K. A. Thole As highly turbulent flow passes through downstream airfoil passages in a gas turbine engine, it is subjected to a complex geometry designed to accelerate and turn the flow. This acceleration and streamline curvature subject the turbulent flow to high mean flow strains...

.... Halstead, D. E., Wisler, D. C., Okiishi, T. H., Walker, G. J., Hodson, H. P., and Shin, H., 1995, “Boundary Layer Development in Axial Compressors and Turbines, Part 3 of 4: LP Turbines,” Proc. ASME 40th International Gas Turbine and Aeroengine Congress & Exposition , Houston, TX, June 5–8, 1995, ASME...