Numerical investigation of high-pressure turbine blade tip flows: analysis of aerodynamics

Vass, Peter; Arts, Tony

doi:10.1177/0957650911412871

Cited by 8 publications

(3 citation statements)

References 26 publications

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“…Tip leakage over the flat tip blade has been described by Coull and Atkins [3]. Squealer tips featuring various wall openings were examined by Vass and Arts [4]. The authors state that the full perimeter squealer features the lowest kinetic energy losses, compared to the partial suction and pressure side squealer.…”

Section: Previous Study On Blade Tip Aerodynamicsmentioning

confidence: 99%

Exploring Topology Optimisation of High Pressure Turbine Blade Tips

Vincekovic

John

Qin

et al. 2020

Volume 2B: Turbomachinery

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This work presents the aerodynamic topology optimisation of high pressure turbine rotor blade tips. Before carrying out the topology optimisation on the blade tip, some initial tip design studies were carried out. The winglet shape was optimised using two different design space setups and parameter limits. The optimum winglet design features the largest overhangs and in the case of unconstrained optimisation proved to have 1.40% greater aerodynamic efficiency. Secondly, a radial basis function based parametrisation was set up to allow the creation of single squealer line using the flat tip blade as a baseline geometry. The optimum case proved to increase efficiency 0.46% compared to the flat tip. After that, a combination of winglet and topology free squealer tips was investigated for topology optimisation. The winglet tip was parametrized as in the winglet only optimisation cases and topology free squealer walls were created using mapping of radial basis function surfaces of different complexities. It is shown that by combining both winglet and novel squealer topology optimisation, better designs of different topologies can be produced.

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Section: Previous Study On Blade Tip Aerodynamicsmentioning

confidence: 99%

Exploring Topology Optimisation of High Pressure Turbine Blade Tips

Vincekovic

John

Qin

et al. 2020

Volume 2B: Turbomachinery

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show abstract

“…They found that the strength of tip leakage flow and total pressure loss in cascade are increased with the increase of tip gap size. Vass and Arts 31 numerically computed the pressure distributions and leakage flow structures in a worn squealer tipped blade. They revealed that the kinetic loss rises remarkably in worn case compared to the original design case.…”

Section: Introductionmentioning

confidence: 99%

Effect of wear damage on aero-thermal performance of the film-cooled squealer tip in a turbine stage

Yan

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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Effects of wear damage on the aerodynamic performance, heat transfer and film cooling effect in the squealer tip region of a gas turbine stage were investigated under engine condition. Two wear parameters, including the starting-location of wear ( sl) and wear depth ( wd), were introduced to describe the degree of wear damage. Three starting-locations of wear ( sl = 32% C ax, 58% C ax and 79% C ax) and three wear depths ( wd = 0.33 mm, 0.67 mm and 1.0 mm) were selected to compute the heat transfer coefficient and film cooling effectiveness on the squealer tip at four blowing ratios ( M = 0.25, 0.5, 0.75 and 1.0). The pressure loss and isentropic efficiency of the turbine stage were calculated to assess the aerodynamic performance degradation induced by the tip wear. The results indicate that the pressure loss in the blade passage near tip region is increased and the stage efficiency is decreased with the increase of wd. Compared to the original design case at M = 0.75, the pressure loss in the rotor blade passage is increased by 7.39% and the stage efficiency is decreased by 2.22% at most after wear. As wd increases, the area-averaged heat transfer coefficient on the cavity floor is increased and film cooling effectiveness is decreased. For the worn cases at M = 0.25, 0.5, 0.75 and 1, the area-averaged heat transfer coefficient on the cavity floor is increased respectively by 87.7%, 62.3%, 71.3% and 88.0% at most, and the area-averaged film cooling effectiveness is decreased respectively by 37.2%, 26.8%, 26.7% and 22.2% at most, as compared to the original design cases.

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“…Key and Arts [8] compared flat tips and squealer tips and Vass and Arts [9] investigated different squealer designs with and without openings. Both partial and full perimeter squealers were found to operate like labyrinth seals where each squealer rim causes additional flow separation, blocking the leakage flow [10].…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary Optimisation of High Pressure Turbine Blade Tip With Turbine Inlet Capacity and Stage Reaction Constraints

Vincekovic

Qin

Shahpar

2021

Aiaa Aviation 2021 Forum

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This work deals with aerodynamic and aerothermal optimisations of high pressure turbine blade tips where a winglet turbine tip is optimised in terms of both aerodynamic efficiency and integrated heat transfer coefficient. Two constraints were introduced in the optimisation process. In particular, turbine mass flow, defined as a non-dimensional turbine inlet capacity, and stage reaction were constrained to change for up to ±0.5% from the datum values. Turbine inlet capacity and stage reaction constraints were achieved by skewing the rotor blade of turbine stage. Steady RANS simulations with k-𝜔 SST turbulence model were performed for the turbine stage using multi-block fully structured mesh and a mixing plane between the stator and the rotor domain. Gradient based optimiser was used in all the optimisations performed. Aerodynamic optimisation was performed first, with and without the constraints, followed by multidisciplinary optimisation done in three steps. By varying the objective weights to explore the Pareto front, winglet designs with considerable efficiency improvements for only minor increase in heat load were identified, featuring sharp leading edge and suction side overhangs. On the other hand, sharp edges were found to be prone to local aerodynamic heating, highlighting the importance of the aerothermal assessment of this problem.

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Numerical investigation of high-pressure turbine blade tip flows: analysis of aerodynamics

Cited by 8 publications

References 26 publications

Exploring Topology Optimisation of High Pressure Turbine Blade Tips

Exploring Topology Optimisation of High Pressure Turbine Blade Tips

Effect of wear damage on aero-thermal performance of the film-cooled squealer tip in a turbine stage

Multidisciplinary Optimisation of High Pressure Turbine Blade Tip With Turbine Inlet Capacity and Stage Reaction Constraints

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