... spot” features on blade tip surfaces are attributed to enhanced turbulence thermal diffusion in local regions. Other surface heat-transfer variations are attributed to flow variations induced by shock waves. Flow structure and surface heat-transfer variations are also investigated numerically when...

... reaching 1.8. Unlike other low-speed data in the open literature, the turbine blade tip heat transfer is greatly influenced by the shock wave structure inside the tip gap. Oblique shock waves are initiated near the pressure-side edge of the tip, prior to being reflected multiple times between the casing...

... as an indicator for the onset of the self-induced unsteadiness in tip leakage flow. It is discussed that the interaction between shock wave and tip leakage vortex does not initiate the self-induced unsteadiness, but might be the cause of other types of unsteadiness, such as broad-banded turbulence unsteadiness...

... separation is found. 07 06 2007 20 08 2007 01 08 2008 aerospace components blades compressors computational fluid dynamics fast Fourier transforms flow instability numerical analysis rotors shock waves transonic flow vortices Advances in gas turbine engine...

... interaction mechanism with respect to clocking was given. It was found that clocking has a minor influence on the trailing edge shocks close to the rotor exit. While in LP turbines the dominant clocking mechanism is the wake-blade interaction, in transonic turbines, shock waves must be taken into account...

... CT3 ,” ASME Paper No. 92-GT-336. Doorly , D. J. , Oldfield , M. L. G. , and Scrivener , C. T. J. , 1985 , “ Wake Passing in a Turbine Rotor Cascade ,” AGARDograph No. 390. Doorly , D. J. , and Oldfield , M. L. G. , 1985 , “ Simulation of the Effects of Shock Wave...

... custom tailoring of its mean camber line. aerodynamics aerospace engines blades boundary layers fans shock waves transonic flow The trend in using wide chord fan blades to improve the aerodynamic performance of transonic blading has been one of the more significant technological...

... by a vaned diffuser. The inlet flow to the open shrouded impeller is transonic, thus giving rise to interactions between shock waves and boundary layers and between shock waves and tip leakage vortices. These interactions generate complex flow structures which are convected and distorted through the impeller...

... engineering aircraft noise abatement Mach number supersonic flow shock waves nozzles jet engines While noise from civil aircraft has reduced significantly over the last 20 years, the downward trend is levelling off and, within the UK, predicted increases in aircraft movements are expected...

... rotor-locked shock wave field. The spatial evolution of this shock system is studied numerically for flows through two basic hard-walled configurations: a slender nacelle with large throat area and a thick nacelle with reduced throat area. With the flight Mach number set to 0.25, the spatial evolution...

... and found to correlate with the vortex blockage. 01 10 2004 01 02 2005 shock tubes shock waves compressors stators flow instability blades Mach number transonic flow supersonic flow rotors wind tunnels vortices The trend toward higher stage loadings in axial compressors...

... strength is presented that predicts the difference between close and far spacing TURBO simulations. 01 10 2004 01 02 2005 wakes shock waves computational fluid dynamics flow instability stators rotors Navier-Stokes equations flow simulation vortices blades compressors transonic...

... at solid walls. aerospace engines Navier-Stokes equations flow simulation design blades compressors fans transonic flow shock waves flow separation flow instability boundary layers turbulence external flows 01 10 2004 01 02 2005 The realizability concept proposed...

..., the flow distortion due to the shock wave and the shock boundary layer interaction must have a large effect on the flow in the inducer. In order to ensure the reliability of aerodynamic design technology, the actual supersonic flow phenomena with a shock wave must be ascertained using measurement...

... case, the instability is referred to as screech or rumble, depending on the type of acoustic mode involved. thermoacoustics shock waves flow instability impedance matrix eigenvalues and eigenfunctions boundary-value problems 13 June 2004 01 October 2003 01 March 2004...

... 03 09 2004 wakes computational fluid dynamics turbines aerodynamics clocks viscosity measurement shock waves The real flow in multistage turbomachines is inherently unsteady because of the relative blade row motion. This causes unsteady interaction of pressure fields, shock...

.... 03 June 2002 22 October 2001 27 08 2003 transonic flow compressibility computational fluid dynamics shock waves Transonic Compressor Streamline Curvature Loss Deviation Accurate and robust turbomachinery off-design performance prediction remains elusive...

... a moving shock wave that produces an entropy rise and loss is experienced. The effect of this outcome of blade-row interaction is to lower the efficiency, pressure ratio, and mass flow rate observed as blade-row axial spacing is reduced from far to close. The magnitude of loss production is affected...

... the experimental data show a maximum overturning of − 62 deg . 01 12 2001 01 03 2003 boundary layers compressors flow measurement transonic flow shock waves rotors stators Compressor performance measured in terms of pressure ratio, efficiency...

... . Hodson, H. P., 1984, “Measurements of Wake Generated Unsteadiness in the Rotor Passages of Axial-Flow Turbines,” ASME 84-GT-189. Doorly , D. J. , and Oldfield , M. L. G. , 1985 , “ Simulation of the Effect of Shock Waves on a Turbine Rotor Blade ,” ASME J. Eng. Gas Turbines Power , 107...