... height ( 4 5 ). For subsonic flows, the percentage of inlet flow that constitutes the tip leakage is shown to grow linearly with tip gap height. Studies involving low Mach number flows show a recirculation zone above the tip gap exit due to relative casing motion ( 3 4 6 ). In both Refs. 3 4...

... painting subsonic flow turbines turbulence Uncertainties have been estimated based on the procedure described in Ref. 21 . The mainstream velocity is kept constant within ±1%. Uncertainty in setting the blowing ratio is ±2.7%. Based on an accuracy of ±1 K for the thermocouple measurement...

..., the implications of these findings for the design of casing grooves of different depths are discussed. 20 07 2009 28 07 2009 20 10 2010 20 10 2010 aerodynamics blades compressors flow instability subsonic flow Aircraft jet engines must be capable of operating safely away...

... subsonic flow turbines turbulence Numerical flow simulation is regularly used to analyze the flow in multistage compressors and turbines of modern gas turbine engines. However, aerodynamic design methods using main stream CFD schemes have not progressed as fast as analysis methods, particularly...

... 2010 07 09 2010 gas turbines flow simulation computational fluid dynamics mechanical engineering computing compressors CAD supersonic flow subsonic flow computer aided instruction software engineering gas turbine streamline curvature modeling compressor performance...

...: Experiment and Analysis ,” ASME J. Turbomach. 0889-504X , 107 ( 2 ), pp. 436 – 449 . 19 09 2007 03 12 2007 05 05 2010 05 05 2010 blades centrifuges compressors flow measurement impellers multiphase flow Navier-Stokes equations numerical analysis subsonic flow...

... low pressure (LP) compressor built by Honeywell ( 2 ). However, they have not been used in commercial rotors. gas turbine tandem blade compressor cascade computational aerodynamics blades computational fluid dynamics gas turbines rotors subsonic flow 08 08 2007 21...

... that, for a given blowing ratio, the lowest effectiveness occurs at phase 0% for the pressure surface and at phase 25% for the suction surface. 05 07 2007 27 07 2007 10 11 2008 blades coolants cooling gas turbines Mach number pressure measurement subsonic flow testing vortices...

... the compressor operating range. compressor instability casing treatment tip clearance flow blades compressors flow instability rotors subsonic flow 14 06 2005 16 11 2006 25 09 2008 2009 American Society of Mechanical Engineers ...

... optimisation splines (mathematics) subsonic flow transonic flow turbines 07 11 2006 15 03 2007 12 02 2008 2008 American Society of Mechanical Engineers ...

... with a recess of 2.1 mm causes the average effectiveness magnitudes to decrease slightly as compared to a squealer depth of 4.2 mm . blades cooling gas turbines jet engines Mach number subsonic flow The concept of cooling a surface subjected to high mainstream temperatures by perforating...

.... 0889-504X , 121 ( 3 ), pp. 469 – 480 . blades confined flow impellers compressors transonic flow flow visualisation subsonic flow flow instability computational fluid dynamics wakes The authors have previously measured the internal impeller flow of a turbocharger transonic...

...-lift profiles for the case of an exit Mach number of the order of 0.64. Hot-wire measurements were carried out to explain the effect of the surface finish on the wake-induced transition mechanism. 17 05 2006 30 05 2006 blades turbines subsonic flow surface roughness flow...

... OF TURBOMACHINERY . Manuscript received by the ASME Turbomachinery Division, April 15, 2004; final revision, April 17, 2004. Associate Editor: D. C. Wisler. 15 April 2004 17 April 2004 05 05 2005 computational fluid dynamics subsonic flow transonic...

... to the conclusion that flow instabilities generated in the wake of the lip might be involved in the relatively fast decay of film cooling effectiveness along the trailing edge cutback. 01 10 2004 01 02 2005 cooling gas turbines subsonic flow wind tunnels turbulence aerodynamics design...

... and Aeroengine Congress and Exhibition, Atlanta, GA, June 16–19, 2003. Manuscript received by the IGTI December 2002; final revision March 2003. Paper No. 2003-GT-38934. Review Chair: H. R. Simmons. 16 June 2003 01 December 2002 01 March 2003 29 12 2004 wakes subsonic flow...

... and Exhibition, Atlanta, GA, June 16–19, 2003. Manuscript received by the IGTI December 2002; final revision March 2003. Paper No. 2003-GT-38477. Review Chair: H. R. Simmons. 16 June 2003 01 December 2002 01 March 2003 29 12 2004 compressors aerodynamics subsonic flow turbines...

.... In contrast, the natural modes of subsonic flow with favorable pressure gradients are found to be stable. In the present investigation, we have applied a previously developed formulation 1 to analyze the stability of several quasi-one-dimensional flows. These configurations, while simple, form parts...

... on the LPT boundary layer separation and their physics still requires more research. wakes boundary layer turbulence flow separation turbines subsonic flow bubbles confined flow flow simulation 29 12 2004 Contributed by the International Gas Turbine Institute (IGTI...

... compressors confined flow computational fluid dynamics Mach number subsonic flow compressible flow gas turbines The blade sections of industrial axial flow compressors require a wider range from surge to choke than typical gas turbine compressors in order to meet the high-volume flow-range...