Influence of coolant injector configuration on film cooling effectiveness for gaseous and liquid film coolants

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

doi:10.1007/s00231-011-0936-z

Cited by 18 publications

(6 citation statements)

References 25 publications

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“…Shine et al [12] investigated the effects of different coolant configuration as the length of cooling holes and the uniformity of film cooling depend on the liquid or gaseous coolants on cooling performance. The results declared that at low blowing ratios, there was no difference between the effects of different coolant on cooling.…”

Section: Methodsmentioning

confidence: 99%

The Use of Compound Cooling Holes for Film Cooling at the End Wall of Combustor Simulator

Sidik

Salimi

2014

AMM

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Gas turbine cooling can be classified into two different schemes; internal and external cooling. In internal cooling method, the coolant provided by compressor is forced into the cooling flow circuits inside turbine components. Meanwhile, for the external cooling method, the injected coolant is directly perfused from coolant manifold to save downstream components against hot gases. Furthermore, in the latter coolant scheme, coolant is used to quell the heat transfer from hot gas stream to a component. There are several ways in external cooling. Film cooling is one of the best cooling systems for the application on gas turbine blades. This study concentrates on the comparison of experimental, computational and numerical investigations of advanced film cooling performance for cylindrical holes at different angles and different blowing ratios in modern turbine gas.

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Section: Methodsmentioning

confidence: 99%

The Use of Compound Cooling Holes for Film Cooling at the End Wall of Combustor Simulator

Sidik

Salimi

2014

AMM

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“…The validation of test cases is based on the measurements made using the similar experimental setup used by Shine et al [29] and is shown in Fig. 1.…”

Section: Experiments Used For Validationmentioning

confidence: 99%

“…The temperature of the mainstream hot air remained almost constant over the entire test section length. A brief description of the various uncertainties present in the experiment is explained in [29]. The relative uncertainty in the deduced parameters has been estimated using the method due to Moffat [30].…”

Section: Experiments Used For Validationmentioning

confidence: 99%

Internal Wall-Jet Film Cooling with Straight Cylindrical Holes

Shine

Kumar

Suresh

2012

Journal of Thermophysics and Heat Transfer

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Experimental and computational results are presented that describe gaseous film-cooling performance of straight cylindrical cooling holes inside a cylindrical test section similar to a rocket combustion chamber. Experiments were performed using hot air as the core gas and gaseous nitrogen as the film coolant. A three-dimensional multispecies computational model using finite volume formulation has been developed and validated against the experimental data. Film-cooling performance is predicted for a variety of imposed geometrical parameters and blowing ratios. Results show local and spatially averaged performance change with blowing ratio due to differences in the magnitude of vortices created downstream of the coolant injection and the jet exit momentum. It is observed that higher mixing of coolant with the mainstream and high vorticity levels negates the presence of more coolant availability at higher blowing ratios and results in an optimum blowing ratio for a given geometric configuration. Higher effectiveness is obtained for the conjugate walls throughout the test section except at regions very close to the coolant injection. High conductive walls produced a negative heat flux condition immediately downstream of the coolant jet exit, indicating that a highly conductive wall is not a proper choice for internal wall-jet film-cooling applications. The results could provide useful input for analysis and optimization of straight cylindrical coolant holes.

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“…An effective cooling of the nozzle is very crucial for ensuring reliability of the rocket engines developed for space missions. However, very few studies deal with coolant film injector orientations and its effect on film cooling effectiveness [6]. In this study, experimental and computational results are presented that describe film cooling effectiveness of a nozzle segment having two types of coolant injector orientations.…”

Section: Introductionmentioning

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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Influence of coolant injector configuration on film cooling effectiveness for gaseous and liquid film coolants

Cited by 18 publications

References 25 publications

The Use of Compound Cooling Holes for Film Cooling at the End Wall of Combustor Simulator

The Use of Compound Cooling Holes for Film Cooling at the End Wall of Combustor Simulator

Internal Wall-Jet Film Cooling with Straight Cylindrical Holes

Effect of injector configuration in rocket nozzle film cooling

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