Numerical Investigation of Low-Pressure Turbine Cascade with Unsteady Wakes

Robison, Zachary; Groß, Andreas

doi:10.2514/6.2021-1668

Cited by 3 publications

(4 citation statements)

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“…The wakes are considerably wider than for the smaller wake generator (Figure 9). (Reprinted from [42]. )…”

Section: Wake Analysismentioning

confidence: 99%

“…D = 0.04 D = 0.12 Different from the 50% reaction stage, the bar wake generators do not induce flow separation from the pressure side. (Reprinted from [42]. )…”

Section: Suction Surfacementioning

confidence: 99%

“…With turbulent endwall boundary layer and passing wakes, the total pressure losses were increased substantially over a reference case with laminar endwall boundary layer and no wakes. More recently, Romero and Gross [41] and Robison and Gross [42] performed LES of a linear 50% reaction turbine stage with L2F blades. The passing wakes were shown to greatly diminish the coherence of the HV and PV and suppress laminar boundary layer separation from the suction surface.…”

Section: Introductionmentioning

confidence: 99%

“…For the larger bar wake generator, flow separation is suppressed over the entire period. (Reprinted from[42]. )…”

mentioning

confidence: 99%

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Large-Eddy Simulation of Low-Pressure Turbine Cascade with Unsteady Wakes

Robison

Groß

2021

Aerospace

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To better understand the wake effects at low Reynolds numbers, large-eddy simulations of a 50% reaction low-pressure turbine stage and a linear cascade with two different bar wake generators were carried out for a chord Reynolds number of 50,000. For the chosen front-loaded high-lift airfoil, the endwall structures are stronger than for more traditional mid-loaded moderate-lift airfoils. By comparing the 50% reaction stage results with the bar wake generator results, insight is gained into the effect of the three-dimensional wake components on the downstream flow field.For the cases with bar wake generator, the endwall boundary layer is growing faster because of the relative motion of the endwall with respect to the freestream. The half-width of the wake is approximately matched for the larger one of the two considered bar wake generators. To improve the quality of the phase-averaged flow fields, the proper orthogonal decomposition was employed as a filter to remove the low-energy unsteady flow field content. Both the mean flow and filtered phase-averaged flow fields were analyzed in detail. Visualizations of the phase-averaged flow field reveal a periodic suppression of the laminar suction side separation from the downstream airfoil even for the smaller bar wake generator. The passage vortex is entirely suppressed for the 50% reaction stage and for the larger bar wake generator. Furthermore, the phase-averaged data for the 50% reaction stage reveal a new longitudinal flow structure that is traced back to near-wall wake vorticity. This flow structure is missing for the bar wake generator cases.

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“…The wakes are considerably wider than for the smaller wake generator (Figure 9). (Reprinted from [42]. )…”

Section: Wake Analysismentioning

confidence: 99%

“…D = 0.04 D = 0.12 Different from the 50% reaction stage, the bar wake generators do not induce flow separation from the pressure side. (Reprinted from [42]. )…”

Section: Suction Surfacementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

“…For the larger bar wake generator, flow separation is suppressed over the entire period. (Reprinted from[42]. )…”

mentioning

confidence: 99%

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