Effects of Effusion Cooling Pattern Near the Dilution Hole for a Double-Walled Combustor Liner—Part 1: Overall Effectiveness Measurements

Shrager, Adam C.; Thole, Karen A.; Mongillo, Dominic

doi:10.1115/1.4041148

Cited by 11 publications

(4 citation statements)

References 18 publications

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“…Shrager et al [23,24] perform thermal and aerodynamic analysis of a double-wall combustor liner. While the general impingement effusion setup is comparable, they focus on the area of dilution holes which are not included in this article's setup.…”

Section: Impingement Effusion Cooling Methods For Combustor Wallsmentioning

confidence: 99%

“…Comparing the results to recent work available shows a good agreement. Hot gas total cooling effectiveness is, in general, found to be very high with the employed doublewall combustor liner concept ( [22,23]), with effective Nusselt numbers being comparably low ( [15,17]). Data on the cooling side are less comparable due to the novel introduction of coolant cross flow at engine-similar Reynolds numbers.…”

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confidence: 99%

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Experimental Study of Impingement Effusion-Cooled Double-Wall Combustor Liners: Thermal Analysis

2021

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A new experimental study is presented for a combustor with a double-wall cooling design. The inner wall at the hot gas side features effusion cooling with 7-7-7 laidback fan-shaped holes, and the outer wall at the cold side features an impingement hole pattern with circular holes. Data have been acquired to assess the thermal and aerodynamic behavior of the setup using a new, scaled up, engine-similar test rig. Similarity includes Reynolds, Nusselt, and Biot numbers for hot gas and coolant flow. Different geometrical setups are studied by varying the cavity height between the two walls and the relative alignment of the two hole patterns at several different blowing ratios. This article focuses on the thermal performance of the setup. The temperature data are acquired using two infrared systems on either side of the effusion wall specimen. In addition to cooling effectiveness evaluations, finite element simulations are performed, yielding the locally resolved wall heat fluxes. Results are presented for three cavity heights and two longitudinal specimen alignments. The results show that the hot gas side total cooling effectiveness can achieve values as high as 90% and is mainly influenced by the effusion coverage. Impingement cooling has a small influence on overall effectiveness, and the area of influence is mainly located upstream where effusion cooling is not built up completely. The analyzed geometric variations show a major influence on cavity flow and impingement heat transfer. Small cavities lead to constrained flow and high local Nusselt numbers, while larger cavities show more equalized Nusselt number distributions. A present misalignment shows especially high influence at small cavity heights. The largest cavity height, in general, showed a decrease in heat transfer due to reduced jet momentum.

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Section: Impingement Effusion Cooling Methods For Combustor Wallsmentioning

confidence: 99%

mentioning

confidence: 99%

Experimental Study of Impingement Effusion-Cooled Double-Wall Combustor Liners: Thermal Analysis

2021

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“…Shrager et al [15,16] performed thermal and aerodynamic analysis of a double-wall combustor liner. With a general impingement-effusion setup comparable to the one in this study, they focused on the area of dilution holes which are not included in this article's setup.…”

Section: Flow Analysis In Impingement Effusion Cooling Double-wallsmentioning

confidence: 99%

Experimental Study of Impingement Effusion Cooled Double-Wall Combustor Liners: Aerodynamic Analysis with Stereo-PIV

Jackowski¹,

Elfner²,

Bauer³

et al. 2021

Energies

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A new experimental study is presented for a combustor with a double-wall cooling design. The inner wall at the hot gas side features effusion cooling with 7-7-7 laidback fan-shaped holes, and the outer wall at the cold side features an impingement hole pattern with circular holes. Data are acquired to asses the thermal and aerodynamic behavior of the setup, using a new, scaled up, engine similar test rig. Similarity includes Reynolds, Nusselt and Biot numbers for hot gas and coolant flow. Different geometrical setups are studied by varying the cavity height between the two walls and the relative alignment of the two hole patterns at two different impingement Reynolds numbers. This article focuses on the aerodynamic performance of the setup. Instationary flow data are acquired, using a high speed stereo PIV setup. For each geometrical configuration, approximately 20 planes are recorded with a data rate of 1000 by traversing the flow region of interest in the cavity between the two specimen. This fine resolution allows the reconstruction of 3D flow fields for the mean data values and an extensive analysis of transient phenomena at each plane. Time averaged data and jet-center plane transient data are presented in detail. The results show a complex flow field with a hexagonal vortex pattern in the cavity, which is mainly influenced by the cavity height and the relative alignment of the two walls. The jet Reynolds number shows small influence when analyzing normalized data. Small cavity heights show a less developed flow field with less stable vortex systems. The alignment shows a similar influence on vortex system stability, with the aligned case performing better. Additionally, statistical analysis of the jet flow and frequency domain analysis of the jet and the effusion flow are presented, showing the damping capability of the cavity, especially at increased cavity heights, and a residual low frequency pulsation of the effusion cooling inflow.

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“…Murray et al [18,19] presented an experimental facility and novel computational method to study the integrated assessment of the aero-thermal and thermo-mechanical performances of DWC structures. Using infrared thermography and particle image velocimetry techniques, Shrager et al [20,21] measured the overall effectiveness and time-averaged flow field of a DWC test panel. Furthermore, Ren et al [22] and Li et al [23] experimentally investigated heat transfer characteristics of different DWC flat plates.…”

Section: Introductionmentioning

confidence: 99%

Comparison of Showerhead Film Cooling and Double Wall Cooling in a Guide Vane Leading Edge with Hot Streak

Jinfu,

Yang,

Ran

et al. 2024

JGPP

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Under the realistic running conditions of gas turbines, the temperature at mainstream inlet is always non-uniform due to the effects of combustion process, and different types of hot streak (HS) could be found at the inlet. The existence of HS may result in some potential negative impacts on the cooling performances of vane leading edge (LE). Nowadays, the two configurations, i.e., traditional showerhead film cooling (SFC) and novel double wall cooling (DWC), have been widely used in LE designs of turbine vanes, but until now there is no comprehensive study to evaluate the two models considering HS effects. In this work, using the two cooling structures, four different temperature profiles are considered at the mainstream inlet of the cascade. The results reveal that: in both models, HS could cause a local high-temperature region on LE, and the thermal characteristics of this area are dependent on HS pattern. Compared to SFC, DWC shows a better cooling ability and a lower thermal stress on the vane surface. The cooling characteristics in DWC model are less sensitive to the HS pattern. However, the problem of the extremely high thermal stress within the pin-fins of DWC should be carefully considered.

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Effects of Effusion Cooling Pattern Near the Dilution Hole for a Double-Walled Combustor Liner—Part 1: Overall Effectiveness Measurements

Cited by 11 publications

References 18 publications

Experimental Study of Impingement Effusion-Cooled Double-Wall Combustor Liners: Thermal Analysis

Experimental Study of Impingement Effusion-Cooled Double-Wall Combustor Liners: Thermal Analysis

Experimental Study of Impingement Effusion Cooled Double-Wall Combustor Liners: Aerodynamic Analysis with Stereo-PIV

Comparison of Showerhead Film Cooling and Double Wall Cooling in a Guide Vane Leading Edge with Hot Streak

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