Effect of cooling hole configurations on combustion and heat transfer in an aero-engine combustor

Dai, Huwei; Zhang, Mengjie; Ren, Yanru; Liu, Nuohao; Lin, Jiewei

doi:10.1016/j.applthermaleng.2020.115664

Cited by 29 publications

(6 citation statements)

References 35 publications

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“…In recent years, most studies mainly focused on the cooling performance with different shapes and angles of the cooling hole using the simulation method [22][23][24][25]. However, few studies have investigated the thermo-fluid-solid interaction between these two factors (film cooling hole and CMAS) [26]. Dai et al [26] primarily investigated the temperature field under the different shape of cooling hole for preventing CMAS infiltration; nevertheless, the fracture behavior of TBCs via interfacial stresses owing to the CMAS infiltration was not considered.…”

Section: Introductionmentioning

confidence: 99%

“…However, few studies have investigated the thermo-fluid-solid interaction between these two factors (film cooling hole and CMAS) [26]. Dai et al [26] primarily investigated the temperature field under the different shape of cooling hole for preventing CMAS infiltration; nevertheless, the fracture behavior of TBCs via interfacial stresses owing to the CMAS infiltration was not considered. Thus, the present study proposed thermo-fluid-solid coupling analysis of TBCs with film cooling holes, and volcano-CMAS infiltrations have been discussed using a simulation method.…”

Section: Introductionmentioning

confidence: 99%

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Interfacial Stresses of Thermal Barrier Coating with Film Cooling Holes Induced by CMAS Infiltration

et al. 2022

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To obtain high gas turbine efficiency, a film cooling hole is introduced to prevent the destruction of thermal barrier coating systems (TBCs) due to hot gases. Furthermore, environmental calcium-magnesium-aluminum-silicate (CMAS) particulates plug the film cooling hole and infiltrate the TBCs to form a CMAS-rich layer, which results in phase transformations and significant modifications in the thermomechanical properties that impact the TBCs during cooling. This study aimed to establish a three-dimensional thermo-fluid-solid coupling TBCs model with film cooling holes and CMAS infiltration to analyze the temperature and residual stress distribution via simulations. For the interfacial stress around the cooling hole at the TC/BC interface, the film cooling holes alleviated the interfacial residual stress by 60% due to the reduction in temperature by 40%. In addition, CMAS infiltration intensified the interfacial residual stress via phase transformation. As a result of the influence of larger penetration depths and expansion rates of phase transformation, a significant increase in residual stress was observed. At the beginning of CMAS infiltration, the interfacial stress would be more dominated by the effect of infiltration depth. In addition, the failure due to interfacial normal and tangential stresses was more likely to be found at the infiltration zone near the cooling hole.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Interfacial Stresses of Thermal Barrier Coating with Film Cooling Holes Induced by CMAS Infiltration

et al. 2022

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“…Machining cooling holes on high temperature resistant alloys can effectively improve the performance and service life of aero-engine [ 2 ]. Generally speaking, the machining methods of cooling holes include EDM, laser machining and traditional machining methods such as milling, drilling and hinge.…”

Section: Introductionmentioning

confidence: 99%

Simulation Analysis and Process Evaluation of Cooling Hole Forming Precision in Mask Assisted Electrochemical Machining Based on GH4169

Dai

2022

Materials

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Good heat dissipation performance of aero-engine an effectively improve the service performance and service life of aero-engine. Therefore, this paper studies the machining method of cooling holes of high-temperature existent material GH 4169 for aero-engine innovatively puts forward the mask electrochemical machining method of cooling holes and explores the entrance morphology and taper formation law of the hole structure of high-temperature resistant material GH 4169. The mathematical model of anode dissolution of cooling holes in ECM is established, and the influence of voltage and electrolyte flow rate on cooling holes in ECM is analyzed. Compared with the mask-less electrochemical machining, the inlet radius of cooling holes in mask electrochemical machining is reduced by about 16.0% and the taper is reduced by 52.8% under the same machining parameters, which indicates that the electrochemical machining efficiency of mask is higher and the machining accuracy is better. Experiments show that the diameter of the mask structure improves the accuracy of the inlet profile of the cooling hole in the ECM. The diameter of the mask increases from 2 mm to 2.8 mm, and the inlet radius of the cooling hole increased from 1.257 mm to 1.451 mm When the diameter of the mask is 2.2 mm, the taper of the cooling hole decreased by 53.4%. The improvement effect is best, and the thickness of the mask has little influence on the forming accuracy of the cooling hole.

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“…The effect of film cooling on the aerodynamic efficiency of turbine blades is becoming increasingly critical as the operating temperature of gas turbines is increased to improve performance [3]. CFD has now found its place among experimental and analytical methods for analyzing fluid flow, heat transfer [4][5][6][7][8][9][10], and diverse problems [11][12][13][14][15], and the use of this method for engineering analysis has become more common [16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Effects of Various Injection Holes with/without Opening Angles of Film Cooling on Blades of Gas Turbine: A CFD Approach

Hosseini

2021

Trends Sci

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The combustor exit temperature is steadily rising to improve the overall efficiency of the gas turbine. As a result, film cooling, the most important and necessary cooling technology, must be developed further to satisfy this demanding requirement. The film cooling performance on the NACA 0012 gas turbine blade is numerically evaluated in this research using 6 different injection holes with and without opening angles. The Computational Fluid Dynamics (CFD) software Ansys Fluent v16 is used to conduct 2-dimensional Reynolds-Averaged Navier-Stokes (RANS) flow and heat transfer analyses. The flow is assumed to be steady, turbulent, and incompressible. To obtain solutions, the incompressible RANS equations are solved using the finite-volume technique. The simulation results indicate that the SST k-ω turbulence model is appropriate for simulating flow characteristics and evaluating film cooling efficiency over the blade. Furthermore, the opening angle has a beneficial impact on the upper blade surface's cooling performance. The injection hole with an opening angle of 15º and a height of D (injection hole diameter) achieves the maximum value of cooling efficiency. The coolant injected from the hole provides greater cooling coverage for the entire blade in this configuration, increasing cooling effectiveness. HIGHLIGHTS The influence of various geometries of injection holes on the effectiveness of film cooling was investigated The low opening angle has a greater impact on film cooling than the other opening angles The injection hole with an opening angle eliminates the recirculation region after the coolant exits GRAPHICAL ABSTRACT

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Effect of cooling hole configurations on combustion and heat transfer in an aero-engine combustor

Cited by 29 publications

References 35 publications

Interfacial Stresses of Thermal Barrier Coating with Film Cooling Holes Induced by CMAS Infiltration

Interfacial Stresses of Thermal Barrier Coating with Film Cooling Holes Induced by CMAS Infiltration

Simulation Analysis and Process Evaluation of Cooling Hole Forming Precision in Mask Assisted Electrochemical Machining Based on GH4169

Effects of Various Injection Holes with/without Opening Angles of Film Cooling on Blades of Gas Turbine: A CFD Approach

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