Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity

Mansouri, Zakaria

doi:10.1016/j.jppr.2021.11.003

Cited by 7 publications

(2 citation statements)

References 23 publications

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“…Only one full rotor rotation is modelled with time periods equal to the rotor blade pitch (5.14 °), each period is simulated with 25 time steps, which leads to a time step t = 4.89 × 10 −6 second, and each time step is achieved with a minimum 25 sub-iterations. This time step is selected based on the work of Rahman et al [34] where they conducted a sensitivity analysis on the time discretisation using 20, 40, and 60 time steps for a time period equivalent to 12 °stator vane pitch for a high pressure turbine rotating under 9500 rpm. They found that a vane passing period discretised with 40 time steps leading to a t = 5.26 × 10 −6 second is sufficient to reach a temporal convergence.…”

Section: Numerical Setupmentioning

confidence: 99%

Heat transfer characteristics of a high-pressure turbine under combined distorted hot-streak and residual swirl: an unsteady computational study

Mansouri

Jefferson-Loveday

2022

International Journal of Heat and Mass Transfer

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Section: Numerical Setupmentioning

confidence: 99%

Heat transfer characteristics of a high-pressure turbine under combined distorted hot-streak and residual swirl: an unsteady computational study

Mansouri

Jefferson-Loveday

2022

International Journal of Heat and Mass Transfer

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“…Moreover, the slot width only had a little impact on the cooling and aerodynamic performance. Mansouri et al [13] investigated a generic rim seal and indicated the significance of selecting the optimal PF rate, which can provide a better film cooling performance and relatively less aerodynamic loss.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigations into the Effects of Rim Seal Structure on Endwall Film Cooling and Flow Field Characteristics

Lu,

Liu,

Zhang

et al. 2023

Energies

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During the practical operation of gas turbines, relatively cooled air from the compressor and the rim seal is applied in order to prevent mainstream ingestion into the space between the rotor and stator disc cavities, which can prolong the service life of hot components. On the one hand, the purge flow from the rim seal will inevitably interact with the mainstream and result in secondary flow on the endwall. On the other hand, it can also provide an additional cooling effect. In this paper, four rim seal structures, including an original single-tooth seal (ORI), a double-tooth seal (DS), a single-tooth seal with an adverse direction of the coolant purge flow and mainstream (AS) and a double-tooth seal with an adverse direction of the coolant purge flow and mainstream (ASDS), are experimentally and numerically investigated with mass flow ratios of 0.5%, 1.0% and 1.5%. The flow orientation of the coolant from the rim seal is considered as one of the main factors. The pressure-sensitive paint technique is used to experimentally measure the film cooling effectiveness on the endwall, and flow field analysis is conducted via numerical simulations. The results show that the cooling effect decreases in the cases of DS and ASDS. AS and ASDS can achieve a better film cooling performance, especially under a higher mass flow ratio. Furthermore, the structural changes in the rim seal have little impact on the aerodynamic performance. AS and ASDS can both achieve a better aerodynamic and film cooling performance.

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Parameter sensitivity analysis of the interaction between purge flow and mainstream

Gao,

Dong,

et al. 2024

Applied Thermal Engineering

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Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity

Cited by 7 publications

References 23 publications

Heat transfer characteristics of a high-pressure turbine under combined distorted hot-streak and residual swirl: an unsteady computational study

Heat transfer characteristics of a high-pressure turbine under combined distorted hot-streak and residual swirl: an unsteady computational study

Experimental and Numerical Investigations into the Effects of Rim Seal Structure on Endwall Film Cooling and Flow Field Characteristics

Parameter sensitivity analysis of the interaction between purge flow and mainstream

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