Internal wall-jet film cooling with compound angle cylindrical holes

Shine, S. R.; Kumar, Sandeep; Suresh, B. N.

doi:10.1016/j.enconman.2012.12.021

Cited by 23 publications

(13 citation statements)

References 30 publications

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“…In the past few decades, film-cooling has been widely employed to protect metal surfaces [1][2][3][4][5][6]. In film-cooling progress, jet flow (coolant) is injected through rows of holes on the metal surface, as shown in Fig.…”

Section: Introductionmentioning

confidence: 99%

Film-cooling of cylindrical hole with downstream surface dielectric barrier discharge actuators

Dai

Yang

et al. 2015

International Journal of Heat and Mass Transfer

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Section: Introductionmentioning

confidence: 99%

Film-cooling of cylindrical hole with downstream surface dielectric barrier discharge actuators

Dai

Yang

et al. 2015

International Journal of Heat and Mass Transfer

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“…In line with this study, the researchers showed that the application of cooling holes with elevated injection angles enlarged the turbulence, and higher turbulence led to the cooling performance degradation (Sarkar et al 1995). In addition, other researchers simulated a flat plate with cylindrical cooling holes to study the effects of injection angle on the effectiveness of film cooling (Nasir et al 2001, Shine et al 2013, Hale et al 2000. They highlighted that lower stream-wise injection angles perform better to have a higher film cooling effectiveness.…”

Section: Introductionmentioning

confidence: 49%

A Detailed Study of Effects of Row Trenched Holes at the Combustor Exit on Film Cooling Effectiveness

Kianpour¹,

Sidik²

2017

JSSCM

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The current research was performed in order to analyze the effects of cylindrical and row trench cooling holes with the alignment angle of 90 degrees on the film-cooling effectiveness near the combustor endwall surface at the blowing ratio of BR=3.18. The three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analyzed with the commercial finite volume package, FLUENT 6.2.26. in order to find the most effective row trenched cooling holes. The analysis was done with Reynolds averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. This combustor simulator was combined with the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the spanwise direction. In comparison with the baseline case of cooling holes, using a row trenched hole near the endwall surface increased the film-cooling effectiveness by 44% in average.

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“…Experiments were done with tangential injectors and noticed that the effects were more pronounced at higher combustion chamber pressures. The flow field associated with coolant injectors inclined in tangential and azimuthal directions employed inside a circular pipe was examined by Shine et al [34]. Higher film cooling effectiveness prevailed for the compound injection orifice compared to other configurations.…”

Section: Literature Reviewmentioning

confidence: 99%

Effect of injector configuration in rocket nozzle film cooling

2015

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List of symbols A injCross-sectional area of the nozzle at the coolant injection point (m 2 ) A throat Cross-sectional area of the throat of the nozzle (m 2 ) AR Area ratio (dimensionless) BR Blowing ratio (dimensionless) c p Specific heat (J kg −1 K −1 ) Hz Unit of frequency (cycles per second) hp Horse power (1 hp = 746 W) J Diffusion flux (kg m −2 s −1 ) p Static pressure (N m −2 ) r Radial coordinate (mm) Re Reynolds number (dimensionless) Sc Schmidt number (dimensionless) TuTurbulence intensity (%)Mass fraction of the component (dimensionless) Greek lettersDegree of film cooling effectiveness (dimensionless) ΔT Temperature difference between surface and ambient (K) Subscripts c CoolantAbstract Experimental and numerical investigations are carried out to analyze the effect of coolant injector configuration on overall film cooling performance in a divergent section of a rocket nozzle. Two different injector orientations are investigated: (1) shaped slots with a divergence angle of 15° (semi-divergent injector) (2) fully divergent slot (fully divergent injector). A 2-dimensional, axis-symmetric, multispecies computational model using finite volume formulation has been developed and validated against the experimental data. The experiments provided a consistent set of measurements for cooling effectiveness for different blowing ratios ranging from 3.7 to 6. Results show that the semi divergent configuration leads to higher effectiveness compared to fully divergent slot at all blowing ratios. The spatially averaged effectiveness results show that the difference between the two configurations is significant at higher blowing ratios. The increase in effectiveness was around 2 % at BR = 3.7 whereas it was around 12 % in the case of BR = 6. Numerical results show the presence of secondary flow recirculation zones near the jet exit for both the injectors. An additional recirculation zone present in the case of fully divergent injector caused an increase in mixing of the coolant and mainstream, and a reduction in film cooling performance.

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Internal wall-jet film cooling with compound angle cylindrical holes

Cited by 23 publications

References 30 publications

Film-cooling of cylindrical hole with downstream surface dielectric barrier discharge actuators

Film-cooling of cylindrical hole with downstream surface dielectric barrier discharge actuators

A Detailed Study of Effects of Row Trenched Holes at the Combustor Exit on Film Cooling Effectiveness

Effect of injector configuration in rocket nozzle film cooling

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