An Experimental and Computational Study of Transonic Three-Dimensional Flow in a Turbine Cascade

Camus, J.-J.; Denton, J. D.; Soulis, Johannes V.; Scrivener, Colin

doi:10.1115/1.3239581

Cited by 8 publications

(6 citation statements)

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“…Increasing the outlet Mach number results in smaller Zweifel coefficients, higher row velocity ratios and higher Reynolds numbers, as presented in more aft-loaded midspan loading distributions, as shown in Figure 7.11, and slightly smaller profile losses (Chapter 6). These results regarding the effects of Mach number on loading distributions are consistent with the findings by Camus et al (1984), Duden and Fottner (1997) and Dossena et al (1997). Figure 7.12, on the other hand, show evidence of suction side separation (S 5 ) on both airfoils.…”

Section: Midspan Blade Loading Distributionssupporting

confidence: 92%

“…Due to potential probe interference effects, such as flow blockage inside the passage, the majority of the measurements have been obtained only upstream and downstream of the cascades. Flow visualization techniques, such as surface oil film visualization (Camus et al 1984;Duden and Fottner, 1997), and nonintrusive measurement techniques, such as laser Doppler anemometry and Schlieren photography (Michelassi et al, 1998), have been utilized to investigate the flow field structures inside the blade passage. Additionally, CFD has been used to provide complementary data, which may not be easily obtained from the experiments.…”

Section: Flow Compressibilitymentioning

confidence: 99%

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Endwall Flows in Transonic Turbine Cascades

Taremi¹

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The results of an investigation of the midspan and endwall flows in transonic linear turbine cascades are documented here. A family of five turbine cascades with different levels of flow turning and aerodynamic loading were used for this study to quantify the effects of these parameters on loss generation in compressible flows. Experimental data on these flows are scarce in the open literature. In addition, the application of two different passive flow control techniques for reducing the endwall losses is examined here: these are referred to as endwall contouring, and airfoil pressure-side modification. The experimental investigations were conducted in the Pratt and Whitney Canada (PWC) High-Speed Wind Tunnel Laboratory at Carleton University. The measurements were made using a seven-hole pressure probe downstream of the cascades at both design and off-design Mach numbers. In addition to the measurements, surface flow visualization was conducted to assist in the interpretation of the flow physics. The results from complementary numerical investigations are also presented, and compared with the experimental data. Overall, the examined secondary flow structures are in agreement with previous lowspeed findings. However, in contrast to low-speed results, the downstream mixing losses are mainly attributed to the dissipation of primary kinetic energy in the present study. Raising the exit Mach number results in weaker secondary flow structures and smaller secondary losses.The experimental results demonstrate that endwall contouring is a viable option for mitigating the secondary flows, particularly for the more highly-loaded cascade. The modification of the airfoil pressure surface is also found to provide a significant benefit in terms of endwall loss reduction. The differences between the measurements and the computational results highlight the need for detailed experimental investigations.ii Acknowledgments I would like to express my gratitude to my thesis supervisor, Professor Steen Sjolander, for giving me the opportunity to work on this research project. I would also like to thank him for his invaluable advice regarding the interpretation of the results, and for reviewing the text.

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Section: Midspan Blade Loading Distributionssupporting

confidence: 92%

Section: Flow Compressibilitymentioning

confidence: 99%

Endwall Flows in Transonic Turbine Cascades

Taremi¹

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“…The nozzle contours are formed using the sin curves [15]. This is a three-dimensional, transonic viscous flow problem, and experiment result was presented by J.J. Camus et al [16] . The contours of density are shown at time intervals of 1.2 up to 5.4.…”

Section: Example 2 a Mach 3 Flow Past A Forward Facingmentioning

confidence: 99%

High-order accurate and high-resolution upwind finite volume scheme for solving euler/reynolds-averaged Navier-Stokes equations

et al. 1998

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A high-order accurate explicit scheme is proposed for solving Euler/Reynolds-averaged Navier-Stokes equations for steady and unsteady flows, respectively. Baldwin-Lomax turbulence model is utilized to obtain the turbulent viscosity. For the explicit scheme, the Runge-Kutta time-stepping methods of third orders are used in time integration, and space discretization for the right-hand side (RHS) terms of semi-discrete equations is performed by third-order ENN scheme for inviscid terms and fourth-order compact difference for viscous terms. Numerical experiments suggest that the present scheme not only has a fairly rapid convergence rate, but also can generate a highly resolved approximation to numerical solution, even to unsteady problem.

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“…give results from the fully explicit cell-centred scheme with an embedded O-GH grid system for a highpressure turbine blade tested in cascade by Camus et al; 26 about 40000 points have been used. The figures show velocity vectors near to the tip end-wall and the suction surface of the blade.…”

Section: Three-dimensional Analysismentioning

confidence: 99%

The development of advanced computational methods for turbomachinery blade design

Stow

1989

Numerical Methods in Fluids

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SUMMARYThe paper describes the basic components of a turbomachinery blade design system in use within Rolls-Royce. A number of modelling aspects of the advanced computational methods in use and under development are reviewed together with areas for future research and development.A quasi-3D blade design system which is used for both compressors and turbines is described covering through-flow and blade-to-blade analysis. Various features of blade-to-blade analysis are discussed including the use of compatible design and analysis modes and coupled boundary layer analysis capable of handling attached and separated flow; examples are included to show capabilities. Advances being made in the development and application of Reynolds-averaged Navier-Stokes models are covered showing capabilities with regard to loss and heat transfer prediction.A fully coupled quasi-3D through-flow and blade-to-blade analysis system is described and results presented to show basic capabilities.The need for 3D flow analysis is discussed and the elements of a 3D blade design system presented showing how this links to the traditional quasi-3D system. Examples are given showing basic capabilities of the methods available and under development.Finally areas for future development are presented indicating the mathematical and numerical modelling problems to be addressed.

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An Experimental and Computational Study of Transonic Three-Dimensional Flow in a Turbine Cascade

Cited by 8 publications

References 0 publications

Endwall Flows in Transonic Turbine Cascades

Endwall Flows in Transonic Turbine Cascades

High-order accurate and high-resolution upwind finite volume scheme for solving euler/reynolds-averaged Navier-Stokes equations

The development of advanced computational methods for turbomachinery blade design

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