Transient analysis of upstream wake inside turbine blade passage with purge flow

Babu, Sushanlal; Anish, S.

doi:10.1016/j.ast.2019.105654

Cited by 15 publications

(5 citation statements)

References 40 publications

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“…The geometry for the present 3D simulation of the gas turbine rotor blades is selected from the experimental work of Sushanlal et al 38 Table 1 shows the geometrical parameters of the blade, and Figure 1(a) and (b) shows the geometry of the computational domain and blade, respectively. The names of various boundaries of the computational domain are labeled with the numbers as shown in Figure 1.…”

Section: Computational Methodologymentioning

confidence: 99%

“…For validating the numerical code, the static pressure coefficient ( C p ) distribution around the blade surface at blade midspan from the experimental study by Sushanlal et al 38 has been compared with the present numerical simulation. The experimental study investigated the interaction between ejected purge flow and mainstream flow in the presence of upstream disturbances/wakes.…”

Section: Computational Methodologymentioning

confidence: 99%

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Blade tip leakage flow and heat transfer characteristics over a gas turbine blade at subsonic and transonic exit conditions

Dipendrasingh,

MVV,

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The present study numerically investigates the blade tip leakage flow (TLF) over a gas turbine blade cascade at low speed ( M ex = 0.1) and transonic ( M ex = 0.92) blade exit Mach numbers, with and without shroud motion. Various blade tip flow phenomena like flow separation and reattachment, flow choking, shock-boundary layer interaction (SBLI), and tip leakage vortex (TLV) are studied, and their influence on the heat transfer coefficient (HTC) distributions over the blade tip and near tip blade suction surface is investigated. The study has found some new zones of heat transfer due to the interaction of horseshoe vortices (HSV) with the blade tip. In addition to the primary TLV, a secondary TLV is formed, which increases near tip blade suction surface heat transfer. The flow transitions to supersonic speed in the aft portion of the blade tip for the transonic case resulting in complex heat transfer distribution due to SBLI, compared to near-uniform distribution for the low speed case. This supersonic flow results in a smaller flow separation zone near the aft portion of the pressure side tip edge for the transonic case compared to the low speed case. The qualitative nature of HTC near the leading edge of the blade tip resembles for low speed and transonic cases. However, near the trailing edge of the blade tip, the qualitative nature of HTC for the transonic case shows a substantial difference due to supersonic flow compared to the low speed case.

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Section: Computational Methodologymentioning

confidence: 99%

Section: Computational Methodologymentioning

confidence: 99%

Blade tip leakage flow and heat transfer characteristics over a gas turbine blade at subsonic and transonic exit conditions

Dipendrasingh,

MVV,

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The gap between the motor's supporting barrel and the motor, and the struts for the barrel have minor influence on the aerodynamic performance of the volute-free centrifugal fan. Sushanlal and Anish 8 conducted experimental and numerical studies on low aspect ratio turbine blades, and found that the interaction between the jet purge flow and the mainstream in the presence of upstream disturbance plays an important role in the evolution of secondary flows in the blade flow passage and outlet area. Salunkhe and Pradeep 9 studied axial flow fans without and with distorted inflow, and found that stall is caused by short-scale disturbance in the absence of distortion and reverse rotation inflow distortion, [10][11][12] while stall is caused by long-scale disturbance in the case of co-rotation inflow distortion.…”

Section: Introductionmentioning

confidence: 99%

Effect of motor intrusion on the aerodynamic performances and unsteady characteristics of internal flow of a volute-free centrifugal fan

Qin

Wang

He³

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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The volute-free centrifugal fans are widely used in air conditioning and ventilation applications due to their simple configuration and easy maintenance. The motor normally intrudes towards the fan interior from the rear disc to reduce the size and achieve better compatibility. The size and geometry of the motor affects the local flow field, which may have a serious impact on the aerodynamic performances of the fan. In this paper, we numerically investigated the effect of motor intrusion on the performances and internal flow characteristics of the volute-free centrifugal fan at different flow rates. The numerical results reveal that the internal flow field varies with the increasing of motor height at all flow rates. Under large flow rate, the height of motor has more obvious influence on the static pressure and static pressure efficiency of the fan; as the height of motor increases from 0 to 4 H/8, the two values decrease by 82.8% and 49.7%, respectively. The flow is more unstable which are manifested by the intensified velocity and pressure fluctuations. Therefore, the blocking effect of motor cannot be ignored and must be taken into account for the design the volute-free centrifugal fans.

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“…Jia et al 7 pointed out that the radial-axial rim seal had a higher air-cooled aerodynamic efficiency which reduced the mainstream loss more than other types of rim seal. Sushanlal and Anish 8 analyzed the interaction effects between cylinder vortex and purge vortex.…”

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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Transient analysis of upstream wake inside turbine blade passage with purge flow

Cited by 15 publications

References 40 publications

Blade tip leakage flow and heat transfer characteristics over a gas turbine blade at subsonic and transonic exit conditions

Blade tip leakage flow and heat transfer characteristics over a gas turbine blade at subsonic and transonic exit conditions

Effect of motor intrusion on the aerodynamic performances and unsteady characteristics of internal flow of a volute-free centrifugal fan

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

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