... temperature increases the amount of deposits significantly. blades boundary layer turbulence coating techniques computational fluid dynamics cooling discs (structures) fly ash gas turbines Navier-Stokes equations temperature distribution 21 10 2010 03 12 2010 25 07 2011...

... deposits—results in lower turbulent skin friction, while roughness stretched spanwise results in higher turbulent skin friction than isotropic roughness of the same height. 07 09 2010 01 12 2010 20 07 2011 20 07 2011 aerodynamics blades boundary layer turbulence gas...

... with the reattachment process. blades boundary layer turbulence bubbles flow instability flow separation laminar flow plates (structures) The test-plate used in the present study is of 1220 mm length, 756 mm width, and 25.4 mm thickness and is made of medium-density fiber (MDF) board. The test...

... and turbulence production there is also broadly distributed. Proximity of the TLV to the pressure side of the neighboring blade also affects entrainment of flow into the incoming tip region. 05 07 2010 04 08 2010 15 07 2011 15 07 2011 boundary layer turbulence pumps rotors...

... known as boundary-layer-ingesting (BLI) inlet. aerospace components aircraft boundary layer turbulence flow control Navier-Stokes equations transonic flow 06 07 2010 02 08 2010 15 07 2011 15 07 2011 Representative B-spline patch used to parameterize...

... . 10.1115/1.2927894 27 08 2010 03 09 2010 07 07 2011 07 07 2011 boundary layer turbulence cooling flow simulation jets turbines Although the advance in metallurgy clearly increased the potential temperature of the turbine component material, the cooling methods...

...: An Experimental Investigation ,” ASME J. Turbomach. 0889-504X , 120 , pp. 530 – 540 . 11 02 2010 22 02 2010 26 04 2011 26 04 2011 blades boundary layer turbulence bubbles computational fluid dynamics cooling heat transfer Mach number transonic flow turbines...

... layer turbulence computational fluid dynamics jet engines turbines The range and endurance of aircraft cruising at high altitude is limited by multiple factors, including the operational efficiency of the low pressure turbine. As aircraft elevation is increased, the operational Reynolds...

... to their intrinsic modeling assumptions. These comparisons will assist aerodynamic designers in choosing appropriate turbulence models, and may benefit future modeling research. 25 09 2008 06 01 2010 27 09 2010 27 09 2010 aerodynamics aerospace engines boundary layer turbulence...

.... Fluid Mech. 0022-1120 , 168 , pp. 31 – 71 . 10.1017/S0022112086000289 09 04 2009 31 07 2009 22 09 2010 22 09 2010 blades boundary layer turbulence gas turbines heat transfer mass transfer wakes Increased performance of gas turbine engines has been...

... 2010 27 04 2010 bars blades boundary layer turbulence bubbles diffusion flow separation laser Doppler anemometry plates (structures) turbines wakes The flow inside turbomachinery turbine blade passages is inherently unsteady. Each blade row sheds turbulent wakes, which...

...% augmentation relative to the smooth tripped baseline. The already turbulent nature of the tripped approach flow reduces the effect that the dimples have on the downstream heat transfer coefficient. 08 10 2008 18 11 2008 25 03 2010 25 03 2010 aerodynamics blades boundary layer...

... of the ϕ 1 value, which represents the Nu ¯ / Nu ¯ 0 at zero-buoyancy condition, against R o at BP and FP locations. 20 08 2008 31 08 2008 21 01 2010 21 01 2010 boundary layer turbulence channel flow heat transfer rotational flow...

... modeling for computational fluid dynamics are also reviewed. The conclusion remains that considerable research is yet necessary to fully understand the role of roughness in gas turbines. 13 12 2007 10 09 2008 11 01 2010 11 01 2010 boundary layer turbulence computational fluid...

... of airfoils. Since the flow is subsonic, wakes from the upstream blade rows, which periodically pass through a downstream blade row, provide the dominant source of unsteadiness in the LP turbine. In this case, the wakes can reduce the size of separation. aerospace components boundary layer turbulence...

... C x downstream of the trailing edge is normalized on the nominal exit velocity for each case. At the higher Reynolds numbers, the boundary layer turbulence has decayed to about 4% of U e . A double peak is apparent, with the slightly higher peak resulting from the suction side...

... mechanisms of the shear layer ( 1 ). blades boundary layer turbulence confined flow shear turbulence wakes 27 08 2008 14 09 2008 09 07 2009 2009 American Society of Mechanical Engineers ...

... 2008 06 07 2009 aerodynamics aerospace components blades boundary layer turbulence bubbles compressors computational fluid dynamics flow measurement flow separation laminar flow pressure measurement stators wakes 2007 IGTI Best Technical Paper The leading-edge...

... of the horseshoe vortex is one in which the less dense, higher temperature fluid convects toward the endwall causing an increase in the local fluid temperature and convective heat transfer coefficient. blades boundary layer turbulence combustion equipment cooling flow measurement gas turbines jets...

... a low-pressure turbine vane. In the majority of cases, the predictions from both models are in good agreement with the experimental data. aerodynamics blades boundary layer turbulence heat transfer surface roughness turbines The optimization of cooling technologies continues...