Effects of Damaged Rotor Blades on the Aerodynamic Behavior and Heat-Transfer Characteristics of High-Pressure Gas Turbines

Dam, Thanh; Ryu, Jaiyoung

doi:10.3390/math9060627

Cited by 6 publications

(3 citation statements)

References 32 publications

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“…Comparisons of kinetic energy and shear stress were reported as well. (Mai and Ryu, 2021) compared the effects of rotor-blade damage at different locations in the LE-SS, and LE-PS regions on their aerodynamic behavior and heat-transfer using the CFD approach. Their results reported that damaged-blade cases revealed an increase in the aerodynamic force acting on the blade/vane surfaces.…”

Section: Numerical Investigation Of Effects Of Damaged and Repaired S...mentioning

confidence: 99%

Numerical investigation of effects of damaged and repaired surfaces on flow behavior of nozzle vane trailing edge

KHUMHAENG,

SUKSA,

LAOHALERTCHAI

et al. 2024

JFST

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The nozzle guide vane, which is a stationary part of a gas turbine, is a critical component of gas turbine engines because it must operate under harsh conditions with high pressure and temperature. Unfortunately, when a gas turbine runs for a long time, the turbine vane is subjected to repeated thermal load. This increases the possibility of fatigue damage and crack failure, thereby reducing the vane material's lifespan. In practice, the risk of failure at the trailing edge (TE) of a turbine vane is very high due to the reasons of shape configuration and cooling performance. The TE damage disturbs the flow physics of compressible air passing the vane TE, resulting in flow phenomena and heat convection. The study aims to numerically investigate the effects of damaged surfaces at the TE of a turbine vane on its flow behavior using computational fluid dynamics (CFD) with the SST k-w turbulence model. To simplify the simulation, the effects of the TE failure are presented by using two basic patterns, i.e., long (continuous) cutback damage, and two-short (discrete) cutback damage. To complete the investigation, a further study on the effects of repaired surfaces is included as well. The numerical results show the effects of damaged and repaired surfaces on flow behavior, particularly the vortex formation and the level of turbulent kinetic energy (TKE) in the TE region. Specifically, the damaged vane surface significantly increases the TKE level in the TE region, particularly the two-short damaged surface, which TKE shoots up to 7000-8000 m 2 /s 2 . Meanwhile, TKE in the normal and long damaged case is around 1500 and 4000 m 2 /s 2 . With the restoration of the vane surfaces, it can reduce the TKE level in the TE region. For instance, TKE is uniformly around 1750 m 2 /s 2 for the long repaired surface.

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Section: Numerical Investigation Of Effects Of Damaged and Repaired S...mentioning

confidence: 99%

Numerical investigation of effects of damaged and repaired surfaces on flow behavior of nozzle vane trailing edge

KHUMHAENG,

SUKSA,

LAOHALERTCHAI

et al. 2024

JFST

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“…In this study, the governing equation is the URANS equation, as shown in Equations ( 3) and ( 4) [23,24], and the turbulence model SST k-ω [25,26] was applied to enclose the equation.…”

Section: Boundary Condition and Governing Equationmentioning

confidence: 99%

The Effect of Airfoil Camber on Pressure Fluctuation in Bidirectional Axial-Flow Pump

Meng

Cai

et al. 2022

Processes

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To obtain the influence of airfoil camber on the internal pressure fluctuation of a bidirectional axial-flow pump, the unsteady Reynolds time-averaged Navier–Stokes (URANS) equation was solved to predict the internal flow structure under three airfoil camber cases. The airfoil camber was quantitatively controlled by airfoil camber angle. The pressure standard deviation was used to define the local pressure fluctuation intensity (PFI) inside the impeller and guide vane. Fast Fourier transform was applied to analyze the frequency-domain characteristics of the pressure signal near the impeller–straight pipe interface and impeller–guide vanes interface. The results were validated by the external characteristic test. Under the forward condition, the area of high PFI near the outlet and leading edge of the impeller increased with a decrease in airfoil camber angle, and that near the leading edge of the guide vanes shifted to the middle section with a decrease in airfoil camber angle. The main frequency of the pressure signal near the impeller–guide vanes interface was the blade-passing frequency (BPF), and the main frequency amplitude increased with a decrease in airfoil camber angle. Under the reverse condition, the high PFI area near the inlet and the leading edge of the impeller declined with the decrease in airfoil camber angle. The main frequency of the pressure signal near the impeller–straight pipe interface and impeller–guide vanes interface was the BPF, and the main frequency amplitude decreased with a decrease in airfoil camber angle.

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“…In addition, several studies employed computational fluid dynamics (CFD) to evaluate the internal characteristics and performance of gas turbines in various applications. Mai and Ryu 10,11 estimated the aerodynamics and heat-transfer effects of a damaged blade in a 1.5-stage high-pressure gas turbine. Nguyen et al 12 conducted a single-stage high-pressure gas turbine simulation to compare the effects of chemical reactions on the flow parameters.…”

Section: Introductionmentioning

confidence: 99%

Hydrogen combustion in two-stage high-pressure gas turbine—thermal and flow simulations for performance comparison with fossil fuels

Kim,

Mai,

et al. 2023

International Journal of Engine Research

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Hydrogen energy forms an attractive solution for reducing greenhouse gas emissions from gas turbine systems. Although hydrogen combustion has been widely studied for combustors, only a few studies have considered the combustion effect downstream of the combustor. This study conducted an integral simulation of the combustion and flow of a GE-E3 aero-engine under hydrogen fuel and compared its performance with that of representative fossil fuels such as Jet A in an aero-engine and methane in an industrial gas turbine. All simulations were conducted under a constant heat input at the combustor and turbine inlet temperatures. During combustion simulation, the HyChem mechanism was applied to evaluate the composition of the products in an equilibrium model. Specifically, Reynolds-averaged Navier–Stokes steady simulation of a two-stage high-pressure gas turbine was conducted using the calculated boundary condition from the combustion simulation and k − ω shear stress transport γ turbulence model. The results revealed the high velocity of the hydrogen combustion flue gas owing to its low density under a large pressure difference. Overall, the power output, thermal efficiency, and fuel consumption were improved by hydrogen combustion. The thermal and flow results of the simulation can be used to develop hydrogen gas turbines.

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Effects of Damaged Rotor Blades on the Aerodynamic Behavior and Heat-Transfer Characteristics of High-Pressure Gas Turbines

Cited by 6 publications

References 32 publications

Numerical investigation of effects of damaged and repaired surfaces on flow behavior of nozzle vane trailing edge

Numerical investigation of effects of damaged and repaired surfaces on flow behavior of nozzle vane trailing edge

The Effect of Airfoil Camber on Pressure Fluctuation in Bidirectional Axial-Flow Pump

Hydrogen combustion in two-stage high-pressure gas turbine—thermal and flow simulations for performance comparison with fossil fuels

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