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 10 publications

(3 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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

Self Cite

View full text Add to dashboard Cite

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

Self Cite

View full text Add to dashboard Cite

“…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

View full text Add to dashboard Cite

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.

show abstract

“…Wellborn and his team [11] used a four-stage NASA low-speed axial compressor in an experimental study to analyze the impact of shrouded stator cavity flows on multistage compressor performance and demonstrated the potential benefits of using shrouded stators with abradable coatings. Mansouri [12] analyzed the aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with an upstream generic rim seal cavity. He used CFD simulations to investigate the effects of the purge flow on the aero and thermal performances of a high-pressure turbine rotor and presents the co-relations between purge flow, cooling and sealing effectiveness, as well as losses.…”

Section: Introductionmentioning

confidence: 99%

Detailed Simulations of a Three-Stage Supercritical Carbon Dioxide Axial Compressor with a Focus on the Shrouded Stator Cavities Flow

Ghimire

Turner

2023

Processes

View full text Add to dashboard Cite

This paper describes the findings of detailed simulations performed to investigate the impact of seal teeth cavity leakage flow on the aerodynamic and thermal performance of a three-stage supercritical CO2 axial compressor. The study compares a shrouded stator configuration (with cavities) to a cantilevered stator configuration (without cavities) to highlight their differences. High-fidelity computational fluid dynamics simulations were performed using non-linear harmonic (NLH) and mixing plane assumptions, considering various possible rotor/stator interface configurations for mixing plane calculations. The key performance parameters for each case were compared, and the best-performing configuration selected for further analysis. The individual stage performance parameters are also examined and compared between the cantilevered and shrouded configurations. It was observed that in the shrouded case, the leakage flow enters the cavity downstream of the stator trailing edge and gets entrained into the primary flow upstream of the stator, leading to boundary layer changes at the hub and degradation of stator and downstream rotor performance. Vortical flow structures were also observed in the stator wells, which tended to change the flow angles around the region, thereby affecting mixing and velocity distribution, resulting in a slight deterioration of compressor performance. Additionally, the study examines windage heating due to shear work from rotating walls, including the seal teeth surface. The amount of shear work done on the leakage flow and the corresponding rise in fluid temperature were quantified, tabulated, and further compared with a simple analytical model, showing good agreement between them and, hence, validating the numerical approach used.

show abstract

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

Cited by 10 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

Detailed Simulations of a Three-Stage Supercritical Carbon Dioxide Axial Compressor with a Focus on the Shrouded Stator Cavities Flow

Contact Info

Product

Resources

About