Simulation of Supersonic Flow Through the Tip-Section Turbine Blade Cascade With a Flat Profile

Musil, J; Příhoda, J.; Fürst, Jiří

doi:10.14311/tpfm.2019.023

Cited by 3 publications

(2 citation statements)

References 7 publications

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“…The detailed description of the numerical method can be found in [2]. Simulations were done also with the correlation based γ-Re θ transition and turbulence model by [6]; for details see [7].…”

Section: Methodsmentioning

confidence: 99%

Turbine Cascades of Last Stage Blades for Wide Range of Operating Conditions

Novák

Bobcik

Luxa

et al. 2019

IJTPP

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Recent trends in the electric energy market such as biomass, waste incineration or combined cycle power plants require innovative solutions in steam turbine design. Variable operating conditions cause significant changes in flow field surrounding the steam turbine last stage blades. Therefore, the enlargement of operating range for last stage blades presents new challenges in design of turbine cascades. Several turbine cascades were designed and analyzed by commercial and in-house software of CTU Prague. Selected profiles were experimentally validated in the high-speed wind tunnel for 2D cascade measurements of the Institute of Thermomechanics of the Czech Academy of Sciences which is equipped by an adjustable supersonic inlet nozzle, perforated inserts at side walls and adjustable perforated tailboard. Comparisons are presented of numerical results with optical and pneumatic measurements for a wide range of inlet and outlet Mach numbers for optimized hub and tip profile cascades.

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Section: Methodsmentioning

confidence: 99%

Turbine Cascades of Last Stage Blades for Wide Range of Operating Conditions

Novák

Bobcik

Luxa

et al. 2019

IJTPP

View full text Add to dashboard Cite

show abstract

“…This leads to the design of flat blades profiles that are relatively sensitive to the angle of attack. As follows from simulations of Musil et al [2], the inlet angle has a strong influence on the inlet Mach number and for some regimes even a small change of the inlet angle changes the flow from the transonic to the supersonic character.…”

Section: Introductionmentioning

confidence: 90%

CFD Simulation of Transonic Flow Through the Tip-Section Turbine Blade Cascade Intended for the Long Turbine Blade

et al. 2022

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The paper deals with numerical simulations of transonic flow through the turbine blade cascade consisting of flat profiles. The cascade is one of variants of the tip section of ultra-long blades, which were designed for the last stage of the steam turbine. CFD simulations were realized by means of the ANSYS CFX commercial software using the γ-Reθ bypass transition model completed by the two-equation SST turbulence model. Some simulations were made only by the SST turbulence model for comparison. Numerical results were compared with experimental data. Calculations performed for two nominal regimes and two computational domains. In addition to the standard computational domain, the calculation was performed for a domain with an extended output part for the suppression of reflected shock waves. The interaction of the inner branch of the exit shock wave with the boundary layer on the blade suction side leads in the both flow regimes to the flow separation followed by the transition to turbulence. The flow structure in the blade cascade obtained for the extended domain corresponds well to experimental results.

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Numerical simulation of the flow topology over NREL’s S807 airfoil at different models of turbulence

Kosiak,

Yanovych,

Uruba

et al. 2024

EPJ Web of Conf.

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Current numerical simulations investigate subsonic flow around the NREL’s S807 airfoil without an incident angle at Reynolds numbers near 2.8∙105. This work is devoted to the assessment application of various turbulence models for a numerical simulation of the formed flow around the streamlined body in commercial software ANSYS CFX. Namely, we applied Shear Stress Transport fully turbulent model (SST0, Baseline Reynolds stress model (BSL RSM) and SSG RSM for the computation of velocity deficit, degree of turbulence anisotropy, Reynolds stress components, and aerodynamic performance of the airfoil. The obtained results were validated on the basis of hot wire measurement data. Additionally, in order to validate the obtained results, a comparison with the hot-wire experimental data was also carried out. The obtained experimental and calculated data showed some differences in the wake topology. For example, in the case of hot-wire data, there is a smaller velocity deficit and a wider area of perturbation.

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Simulation of Supersonic Flow Through the Tip-Section Turbine Blade Cascade With a Flat Profile

Cited by 3 publications

References 7 publications

Turbine Cascades of Last Stage Blades for Wide Range of Operating Conditions

Turbine Cascades of Last Stage Blades for Wide Range of Operating Conditions

CFD Simulation of Transonic Flow Through the Tip-Section Turbine Blade Cascade Intended for the Long Turbine Blade

Numerical simulation of the flow topology over NREL’s S807 airfoil at different models of turbulence

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