http://scitation.aip.org/ J. Turbomach.: All Topics http://link.aip.org/link/doi/10.1115/1.3103923 Krzysztof Kosowski, Karol Tucki, and Adrian Kosowski<br/> We present the results of numerical tests of artificial neural networks (ANNs) applied in the investigations of flows in steam turbine cascades. Typical constant cross-sectional blades, as well as high-performance blades, were both considered. The obtained results indicate that ANNs may be used for ... [J. Turbomach. 132, 014501 (2009)] published Fri Sep 11, 2009. http://link.aip.org/link/doi/10.1115/1.3072716 Wladyslaw Piotrowski, Witold Elsner, and Stanislaw Drobniak<br/> This paper presents the results of tests and validations of the gamma-Re model proposed by Menter et al. (2006, A Correlation-Based Transition Model Using Local VariablesPart I: Model Formation, ASME J. Turbomach., 128, pp. 413422), which was extended by in-house correlations for onset location and ... [J. Turbomach. 132, 011020 (2009)] published Mon Sep 21, 2009. http://link.aip.org/link/doi/10.1115/1.3072715 O. Schennach, J. Woisetschlager, B. Paradiso, G. Persico, and P. Gaetani<br/> This paper presents an experimental investigation of the flow field in a high-pressure transonic turbine with a downstream vane row (1.5 stage machine) concerning the airfoil indexing. The objective is a detailed analysis of the three-dimensional aerodynamics of the second vane for different clockin ... [J. Turbomach. 132, 011019 (2009)] published Mon Sep 21, 2009. http://link.aip.org/link/doi/10.1115/1.3072714 Nicole L. Key, Patrick B. Lawless, and Sanford Fleeter<br/> Previous research has shown that vane clocking, the circumferential indexing of adjacent vane rows with similar vane counts, can be an effective means to increase stage performance, reduce discrete frequency noise, and/or reduce the unsteady blade forces that can lead to high cycle fatigue. The obje ... [J. Turbomach. 132, 011018 (2009)] published Mon Sep 21, 2009. http://link.aip.org/link/doi/10.1115/1.3106703 N. J. Fiala, I. Jaswal, and F. E. Ames<br/> Heat transfer and film cooling distributions have been acquired for a vane trailing edge with letterbox partitions. Additionally, pressure drop data have been experimentally determined across a pin fin array and a trailing edge slot with letterbox partitions. The pressure drop across the array and l ... [J. Turbomach. 132, 011017 (2009)] published Fri Sep 18, 2009. http://link.aip.org/link/doi/10.1115/1.3106031 Xue Feng Zhang and Howard Hodson<br/> The effects of Reynolds numbers and the freestream turbulence intensities (FSTIs) on the unsteady boundary layer development on an ultra-high-lift low-pressure turbine airfoil, so-called T106C, are investigated. The measurements were carried out at both Tu=0.5% and 4.0% within a range of Reynolds nu ... [J. Turbomach. 132, 011016 (2009)] published Fri Sep 18, 2009. http://link.aip.org/link/doi/10.1115/1.3106030 Nalin Navarathna, Vitalij Fedulov, Andrew Martin, and Torsten Fransson<br/> Remote laboratory exercises are gaining popularity due to advances in communication technologies along with the need to provide realistic yet flexible educational tools for tomorrow's engineers. Laboratory exercises in turbomachinery aerodynamics generally involve substantial equipment in both size ... [J. Turbomach. 132, 011015 (2009)] published Fri Sep 18, 2009. http://link.aip.org/link/doi/10.1115/1.3072522 Michael G. List, Steven E. Gorrell, and Mark G. Turner<br/> The blade-row interaction (BRI) rig at the Air Force Research Laboratory, Compressor Aero Research Laboratory, has been simulated at three axial gaps between the highly loaded upstream stator row and the downstream transonic rotor using TURBO. Previous work with the stage matching investigation (SMI ... [J. Turbomach. 132, 011014 (2009)] published Thu Sep 17, 2009. http://link.aip.org/link/doi/10.1115/1.3072520 D. C. Knezevici, S. A. Sjolander, T. J. Praisner, E. Allen-Bradley, and E. A. Grover<br/> An approach to endwall contouring has been developed with the goal of reducing secondary losses in highly loaded axial flow turbines. The present paper describes an experimental assessment of the performance of the contouring approach implemented in a low-speed linear cascade test facility. The stud ... [J. Turbomach. 132, 011013 (2009)] published Thu Sep 17, 2009. http://link.aip.org/link/doi/10.1115/1.3072492 Pieter Groth, Hans Martensson, and Clas Andersson<br/> A rotor blisk of a supersonic space turbine has previously been designed to allow for free flutter to occur in an air test rig (Groth Martensson, and Edin, 2010, Experimental and Computational Fluid Dynamics Based Determination of Flutter Limits in Supersonic Space Turbines, 132(1), p. 011010). Flut ... [J. Turbomach. 132, 011012 (2009)] published Thu Sep 17, 2009. http://link.aip.org/link/doi/10.1115/1.3103927 Edward M. J. Naylor, Cecilia Ortiz Duenas, Robert J. Miller, and Howard P. Hodson<br/> This paper presents a new design methodology for strutted S-shaped compressor ducts that allows for more aggressive designs while maintaining current levels of duct loss. A baseline duct geometry was selected, which had a radius change to length ratio that is 34% larger than current engine design li ... [J. Turbomach. 132, 011011 (2009)] published Thu Sep 17, 2009. http://link.aip.org/link/doi/10.1115/1.3072491 Pieter Groth, Hans Martensson, and Niklas Edin<br/> Turbines operating at high pressure in high velocity flow are susceptible to flutter. As reduced frequencies become sufficiently low, negative aerodynamic damping will be found in some modes. Ensuring that the total system damping is positive over the entire turbine operating envelope for all modes ... [J. Turbomach. 132, 011010 (2009)] published Wed Sep 16, 2009. http://link.aip.org/link/doi/10.1115/1.3103929 Alessandro Armellini, Filippo Coletti, Tony Arts, and Christophe Scholtes<br/> The present contribution addresses the aerothermal, experimental, and computational studies of a trapezoidal cross-sectional model simulating a trailing edge cooling cavity with one rib-roughened wall. The flow is fed through tilted slots on one side wall and exits through straight slots on the oppo ... [J. Turbomach. 132, 011009 (2009)] published Wed Sep 16, 2009. http://link.aip.org/link/doi/10.1115/1.3068331 Michael Flouros<br/> Advanced aircraft engine development dictates high standards of reliability for the lubrication systems, not only in terms of the proper lubrication of the bearings and the gears, but also in terms of the removal of the large amounts of the generated heat. Heat is introduced both internally through ... [J. Turbomach. 132, 011008 (2009)] published Wed Sep 16, 2009. http://link.aip.org/link/doi/10.1115/1.3104608 Ralph J. Volino<br/> Boundary layer separation, transition, and reattachment have been studied on a new, very high lift, low-pressure turbine airfoil. Experiments were done under low freestream turbulence conditions on a linear cascade in a low speed wind tunnel. Pressure surveys on the airfoil surface and downstream to ... [J. Turbomach. 132, 011007 (2009)] published Wed Sep 16, 2009. http://link.aip.org/link/doi/10.1115/1.3103922 Kivanc Ekici, Robert E. Kielb, and Kenneth C. Hall<br/> A nonlinear harmonic balance technique for the analysis of aerodynamic asymmetry of unsteady flows in turbomachinery is presented. The present method uses a mixed time-domain/frequency-domain approach that allows one to compute the unsteady aerodynamic response of turbomachinery blades to self-excit ... [J. Turbomach. 132, 011006 (2009)] published Tue Sep 15, 2009. http://link.aip.org/link/doi/10.1115/1.3103925 Zhao Qingjun, Du Jianyi, Wang Huishe, Zhao Xiaolu, and Xu Jianzhong<br/> In this paper, three-dimensional multiblade row unsteady NavierStokes simulations at a hot streak temperature ratio of 2.0 have been performed to reveal the effects of rotor tip clearance on the inlet hot streak migration characteristics in high pressure stage of a vaneless counter-rotating turbine. ... [J. Turbomach. 132, 011005 (2009)] published Tue Sep 15, 2009. http://link.aip.org/link/doi/10.1115/1.2812949 Brian R. McAuliffe and Metin I. Yaras<br/> Through numerical simulations, this paper examines the nature of instability mechanisms leading to transition in separation bubbles. The results of two direct numerical simulations are presented in which separation of a laminar boundary layer occurs over a flat surface in the presence of an adverse ... [J. Turbomach. 132, 011004 (2009)] published Fri Sep 11, 2009. http://link.aip.org/link/doi/10.1115/1.3103924 Sebastian Spring, Diane Lauffer, Bernhard Weigand, and Matthias Hase<br/> A combined experimental and numerical investigation of the heat transfer characteristics inside an impingement cooled combustor liner heat shield has been conducted. Due to the complexity and irregularity of heat shield configurations, standard correlations for regular impingement fields are insuffi ... [J. Turbomach. 132, 011003 (2009)] published Fri Sep 11, 2009. http://link.aip.org/link/doi/10.1115/1.3066271 Paul F. Beard, Thomas Povey, and Kamaljit S. Chana<br/> A turbine efficiency measurement system has been developed and installed on the turbine test facility (TTF) at QinetiQ Farnborough. The TTF is an engine-scale short-duration (0.5 s run time) rotating transonic facility, which can operate as either single stage (HP vane and rotor) or 1(1/2) stage (H ... [J. Turbomach. 132, 011002 (2009)] published Fri Sep 11, 2009. http://link.aip.org/link/doi/10.1115/1.3192146 John Harinck, P. Colonna, A. Guardone, and S. Rebay<br/> This paper presents a quantitative comparison of the effect of using thermodynamic models of various degrees of complexity if applied to fluid-dynamic simulations of turboexpanders operated at conditions affected by strong real-gas effects. The 2D flow field of a standard transonic turbine stator is ... [J. Turbomach. 132, 011001 (2009)] published Fri Sep 11, 2009.