Effect of Gurney flap on flow separation and aerodynamic performance of an airfoil under rain and icing conditions

Fatahian, Hossein; Salarian, Hesamoddin; Nimvari, Majid Eshagh; Khaleghinia, Jahanfar

doi:10.1007/s10409-020-00938-3

Cited by 17 publications

(11 citation statements)

References 50 publications

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“…In the present study, the steady-state incompressible RANS equation is solved by a commercial CFD solver, Ansys Fluent v16. The RANS equation is solved with a finite-volume method for obtaining solutions [32][33][34]. The continuity, momentum, and energy equations are solved.…”

Section: Mathematical Formulationmentioning

confidence: 99%

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Hosseini¹

2021

JMES

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One way to achieve high performance in the gas turbine is to increase the inlet temperature of the turbine. Different cooling techniques have been carried out in order to protect the turbine blades which have been exposed to such high temperatures. Film cooling as an essential cooling method needs to be enhanced to meet the challenging demand. The purpose of the present research is to analyze the film cooling performance over a NACA 0012 gas turbine blade using six different injection holes with and without opening angles, separately through Computational Fluid Dynamics (CFD). 2D Reynolds-Averaged Navier-Stokes (RANS) equations are implemented to consider the heat transfer and flow characteristics by using CFD code Ansys Fluent v16. The flow is considered as steady, turbulent, and incompressible. The RANS equation is solved with the finite-volume method for obtaining solutions. The simulation results revealed that the k-ω SST turbulence model is suitable for simulating the flow characteristics and analyzing the performance of film cooling over the blade. Also, the opening angle has a significant effect on increasing the cooling efficiency for the upper blade surface. The highest value of cooling efficiency is obtained by the injection hole with an opening angle of 15° and height of D. In this configuration, the coolant injected from hole provides better cooling coverage for the entire blade which increases the cooling effectiveness.

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Section: Mathematical Formulationmentioning

confidence: 99%

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Hosseini¹

2021

JMES

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“…The Unsteady Reynolds Averaged Navier-Stokes equations (URANS) of mass and momentum are solved with the k-ɛ standard turbulence model to solve the flow field around the airfoil. This model is recommended by previous researches which has good accuracy for modeling turbulent flow over an airfoil in a heavy rain condition using a two-phase flow approach [3,[24][25][26][27].…”

Section: Continuous Phasementioning

confidence: 99%

“…The temperature is below the boiling point for present simulation, thus the impingement rain particles can adhere, extend or sputter. The impact energy E im is written as follows [25]:…”

Section: Discrete Phasementioning

confidence: 99%

Numerical simulation of the effect of rain on aerodynamic performance and aeroacoustic mechanism of an airfoil via a two-phase flow approach

et al. 2020

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In the present study, two complex physical phenomena have been completely simulated and discussed in detail to predict the aerodynamic degradation and aeroacoustic mechanism of a NACA 0012 airfoil in both dry and heavy rain conditions. For this purpose, a CFD-based multiphase model was adopted to numerically investigate the process of formation of the water film layer on the airfoil surface by coupling the Lagrangian Discrete Phase Model (DPM) and the Eulerian Volume of Fluid (VOF) models. The Ffowcs Williams-Hawkings (FW-H) method was used to predict the aerodynamic noise of the airfoil in a heavy rain condition. The results showed that there were significant degradations of the airfoil aerodynamic performance because of water film formation especially at lower angles of attack. The maximum value of lift-to-drag ratio degradation was 56% at the angle of attack of 2°. Also, the Sound Pressure Level (SPL) increased due to the rain condition. The SPL was sensitive to the raindrop impact on airfoil surface and caused to increase SPL especially in the frequency region less than 2000 Hz. By increasing the angle of attack, the SPL increased especially in the high-frequency region higher than 2500 Hz in rain condition.

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“…Since experimental tests, especially in the case of complex geometries and high Reynolds number flow, are very expensive and have limitations, researchers are focusing on efficient numerical methods to achieve acceptable results at a lower cost and closer to experimental results. Many notable researches were reported to analyze flow separation and control it by utilizing active and passive systems [22][23][24]. Besides, several efforts have been done on the aerodynamic characteristic of the airfoil with cavity [25][26][27][28].…”

Section: Introductionmentioning

confidence: 99%

Simultaneous Effect of Suction and Cavity for Controlling Flow Separation on NACA 0012 Airfoil – CFD Approach

Fatahian

2021

Gazi University Journal of Science

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Effect of Gurney flap on flow separation and aerodynamic performance of an airfoil under rain and icing conditions

Cited by 17 publications

References 50 publications

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Numerical simulation of the effect of rain on aerodynamic performance and aeroacoustic mechanism of an airfoil via a two-phase flow approach

Simultaneous Effect of Suction and Cavity for Controlling Flow Separation on NACA 0012 Airfoil – CFD Approach

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