Numerical investigation on the flow and heat transfer characteristics in radial pre-swirl system with different fillet radius at the junction of inlet cavity and nozzle

Zhang, Feng; Wang, Xinjun; Li, Jun

doi:10.1016/j.applthermaleng.2016.06.117

Cited by 14 publications

(2 citation statements)

References 25 publications

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“…The high temperature of the turbine inlet directly threatens the high-pressure turbine blades and disks. To extend the life of the turbine blades and disks, a radial pre-swirl system is employed [1,2]. The airflow enters the radial pre-swirl system through the pre-swirl nozzles, then accelerates through the receiver holes into the rotor, and ultimately enters the turbine blades via a co-rotating cavity and supply holes, as illustrated in Figure 1.…”

Section: Introductionmentioning

confidence: 99%

Effect of Impellers on the Cooling Performance of a Radial Pre-Swirl System in Gas Turbine Engines

Shen,

Wang,

Liang

2024

Aerospace

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Impellers are utilized to increase pressure to ensure that a radial pre-swirl system can provide sufficient cooling airflow to the turbine blades. In the open literature, the pressurization mechanism of the impellers was investigated. However, the effect of impellers on the cooling performance of the radial pre-swirl system was not clear. To solve the aforementioned problem, tests were carried out to assess the temperature drop in a radial pre-swirl system with various impeller configurations (impeller lengths l/b ranging from 0 to 0.333). Furthermore, numerical simulations were used to investigate the flow and heat transfer characteristics of the radial pre-swirl system at high rotating Reynolds numbers. Theoretical and experimental investigations revealed that the pre-swirl jet and output power generate a significant temperature drop, but the impellers have no obvious effect on the system temperature drop. By increasing the swirl ratio, the impellers reduce the field synergy angle and thus improve convective heat transfer on the turbine disk. In addition, increasing the impeller length can reduce the volume-averaged field synergy angle and improve heat transfer, but the improvement effectiveness decreases as the impeller length increases. Thus, the study concluded that impellers could improve the cooling performance of the radial pre-swirl system by enhancing disk cooling.

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Section: Introductionmentioning

confidence: 99%

Effect of Impellers on the Cooling Performance of a Radial Pre-Swirl System in Gas Turbine Engines

Shen,

Wang,

Liang

2024

Aerospace

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“…Liao et al 13, 14 used the method of fully coupled FE/CFD to simulate the flow fields and heat transfer characteristics in rotor-stator turbine cavity with a solid domain. Zhang et al 15 investigated the influences of pre-swirl system in the flow and heat transfer characteristics of turbine.…”

Section: Introductionmentioning

confidence: 99%

Flow structures and heat transfer characteristics in a vaneless counter-rotating turbine cavity with different cooling inflows

Sui

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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The cooling air is used in the gas turbine to prevent the hot gas ingress and overheating of turbine disks. In this paper, the flow structures and heat transfer characteristics of vaneless counter-rotating turbine (VCRT) with different types of cooling inflows are numerically analyzed. The three-dimensional unsteady Reynolds-Averaged Navier-Stokes (URANS) equations with a Shear Stress Transport (SST) turbulence model are adopted. The results reveal that the inertia force, rotating effect and mainstream dominate the flow fields in VCRT cavity. The axial cooling inflow promotes the heat transfer characteristic in low pressure rotor (LPR) disk meanwhile the radial cooling inflow improves the heat transfer performance in high pressure rotor (HPR) disk. The vortexes interaction, viscous dissipation and heat transportation result in the decrease of heat transfer characteristic in the high radius region of rotor disk. The combined cooling inflow is adopted to solve the problem. It is the combination of radial cooling inlet and high position cooling inlet. The cooling air injected axially from the high position cooling inlet moves outward along the HPR disk which enhances the heat transfer characteristic. It is found that the Nusselt number and the amount of cooling air is not the simple linear relationship. The Nusselt number in HPR disk no longer increases if the high position cooling flow rate exceeds the threshold value. Compared with other types of cooling inflows, the needed amount of cooling air reduces when the combined cooling inflow is adopted. There is an optimum combined cooling flow rate which obtains the excellent heat transfer characteristics in the HPR disk.

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Study on the Effect of Impeller on the Air Supply Parameters of a Partial Intake Pre-Swirl System in an Aero-Engine

Lei,

Yang,

Lin

et al. 2023

Lecture Notes in Mechanical Engineering

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Numerical investigation on the flow and heat transfer characteristics in radial pre-swirl system with different fillet radius at the junction of inlet cavity and nozzle

Cited by 14 publications

References 25 publications

Effect of Impellers on the Cooling Performance of a Radial Pre-Swirl System in Gas Turbine Engines

Effect of Impellers on the Cooling Performance of a Radial Pre-Swirl System in Gas Turbine Engines

Flow structures and heat transfer characteristics in a vaneless counter-rotating turbine cavity with different cooling inflows

Study on the Effect of Impeller on the Air Supply Parameters of a Partial Intake Pre-Swirl System in an Aero-Engine

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