Compressible DNS of a Low Pressure Turbine Subjected to Inlet Disturbances

Chen, Liwei; Pichler, Richard; Sandberg, Richard D.

doi:10.1007/978-3-319-14448-1_48

Cited by 2 publications

(2 citation statements)

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“…The code has also been used to study the effects of unsteadiness and turbulence on low-pressure turbine blade flows and has been validated against T 106A low pressure (LP) turbine linear cascade measurements [22][23][24][25]. These LP turbine simulations were conducted by varying Reynolds number, flow coefficient and reduced frequency to investigate the steady and unsteady loss generation mechanism (such as profile and wake dilation losses) in a realistic design space.…”

Section: Computational Detailsmentioning

confidence: 99%

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Direct Numerical Simulations of a High-Pressure Turbine Vane

Wheeler

Sandberg

Sandham

et al. 2016

Journal of Turbomachinery

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In this paper, we establish a benchmark data set of a generic high-pressure (HP) turbine vane generated by direct numerical simulation (DNS) to resolve fully the flow. The test conditions for this case are a Reynolds number of 0.57 × 106 and an exit Mach number of 0.9, which is representative of a modern transonic HP turbine vane. In this study, we first compare the simulation results with previously published experimental data. We then investigate how turbulence affects the surface flow physics and heat transfer. An analysis of the development of loss through the vane passage is also performed. The results indicate that freestream turbulence tends to induce streaks within the near-wall flow, which augment the surface heat transfer. Turbulent breakdown is observed over the late suction surface, and this occurs via the growth of two-dimensional Kelvin–Helmholtz spanwise roll-ups, which then develop into lambda vortices creating large local peaks in the surface heat transfer. Turbulent dissipation is found to significantly increase losses within the trailing-edge region of the vane.

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Section: Computational Detailsmentioning

confidence: 99%

“…In any case, these near-wall streaks greatly augment the surface heat transfer but tend not to lead to turbulent breakdown. Direct numerical simulations (DNS) have up to now been limitied to low Mach number and Reynolds number turbine cases which are not directly applicable to transonic turbines [21][22][23][24][25].…”

Section: Introductionmentioning

confidence: 99%