... out at low speed ( M 2 is = 0.2 ) and low inlet turbulence intensity level, with coolant mass flow rate ratio varied within the 0.5–2.5% range. Pressure probe traverses were performed downstream of the vane trailing edge to show the secondary flow field modifications and to evaluate trench additional...

... pressure distribution in the impeller and volute casing. The calculated unsteady pressure distribution is used to determine the unsteady blade loading. The calculations at the design point and at two off-design points are carried out with a multiple frame of reference and a sliding mesh technique...

...Roque Corral; Fernando Gisbert The effect of the finite extent of linear cascades on the unsteady pressure distribution of vibrating blades is assessed by means of a numerical study. The span of a reference cascade made up of flat plates has been changed to investigate its influence on the computed...

... by the IGTI, revised manuscript received October 2, 2001. Paper No. 2002-GT-30342. Review Chair: E. Benvenuti. 02 October 2001 23 01 2003 gas turbines steam turbines flow simulation actuators pressure Exhaust system of steam turbines and industrial gas turbines consists...

... to high platform heat transfer and large aerodynamic losses. The flow and thermal fields combine to give nonuniform total pressure profiles entering the turbine passage which, along with the airfoil geometry, dictate the secondary flow field. This paper presents an analysis of the effects of varying total...

...Bjo¨rn Laumert; Hans Ma˚rtensson; Torsten H. Fransson This paper presents a study of the blade pressure perturbation levels and the resulting blade forces in a high-pressure transonic turbine stage based on 3-D time dependent viscous computations. Globally, the blade pressure unsteadiness...

...P. González; I. Ulizar; R. Vázquez; H. P. Hodson Nowadays there is a big effort toward improving the low-pressure turbine efficiency even to the extent of penalizing other relevant design parameters. LP turbine efficiency influences SFC more than other modules in the engine. Most of the research...

... upon predicted pressure ratio, temperature ratio, efficiency, and slip factor; the maximum values for these parameters were predicted for the in-line tandem configuration. The minimum predicted tandem-impeller isentropic efficiency occurred at a clocking fraction of 50 percent, falling 3.8 points below...

... for these measurements was the Allison VBI stage operating in the closed vane position (vane exit Mach number≈1.1). The stage was operated at the design flow function, total to static pressure ratio, and corrected speed. Measurements were obtained at several locations on the platform and in the blade tip region. The tip...

..., and pressure-induced forces on the spool. Pressure forces are shown to lag the tip-clearance asymmetry, resulting in a tangential (i.e., whirl-inducing) force due to spool pressure. This force can be of comparable magnitude to the classical Alford force. Prediction and elucidation of the Alford force is also...

... exit with increasing interaction were identified as reduced slip, reduced blockage, and increased loss. The first two were beneficial to pressure rise, while the third was detrimental. The magnitudes of the effects were examined using different impeller–diffuser spacings and it was shown...

...Martin von Hoyningen-Huene; Alexander R. Jung This paper studies different acceleration techniques for unsteady flow calculations. The results are compared with a nonaccelerated, fully explicit solution in terms of time-averaged pressure distributions, the unsteady pressure and entropy...

... and a laidback fanshaped hole). For all three hole geometries the hole axis was inclined 30 deg with respect to the direction of the external (hot gas) flow. The flow conditions considered were the hot gas crossflow Mach number (up to 0.6), the coolant crossflow Mach number (up to 0.6) and the pressure ratio...

... the pressure recovery and loss mechanism in the volute is obtained. [S0889-504X(00)00301-9] The loss coefficients in measurement plane 1 to 4 are negative, because the loss coefficient compares the local total pressure loss to the average inlet total pressure. The local total pressure, however, depends...

... transition for boundary layers subjected to a wide range of free-stream turbulence levels and streamwise pressure gradients. In the current paper experimental results are presented that support the premise that the formation of turbulent spots is associated with transient separation. Near-wall hot-wire...

..., 1999. Manuscript received by the International Gas Turbine Institute February 1999. Paper No. 99-GT-75. Review Chair: D. C. Wisler. 07 June 1999 01 February 1999 compressors stators channel flow rotors flow simulation pressure Over the years, experience has confirmed...

...M. G. Rose; N. W. Harvey In this paper the mixing of stator wakes in turbomachinery is considered. An extension is made to the existing model of Denton (1993, ASME J. Turbomach., 115 , pp. 621–656) which addresses the effects of acceleration before mixing. Denton showed that if a total pressure...

... a test of a straight-channel diffuser designed for equivalent duty. Two builds of discrete-passage diffuser were tested, with 30 and 38 separate passages. Both the 30 and 38 passage diffusers investigated showed comparable range of unstalled operation and similar level of overall diffuser pressure...

..., and compares the results with those from the discrete-passage diffusers described in Part 1. Effects of diffuser inlet Mach number, flow angle, blockage, and axial flow nonuniformity on diffuser pressure recovery and operating range are addressed. The straight-channel diffuser investigated has 30 vanes...

... for aeroelastic applications and examine the ability of a three-dimensional time-marching Euler method to predict the relevant unsteady aerodynamics. Extensive blade surface unsteady pressure measurements were obtained over a range of reduced frequency from a test facility with clearly defined boundary conditions...