Experimental results for film cooling in 2-D supersonic flow including coolant delivery pressure, geometry, and incident shock effects

Olsen, G. C.; Nowak, Robert J.; Holden, Michael; Baker, Nathaniel R.

doi:10.2514/6.1990-605

Cited by 34 publications

(15 citation statements)

References 2 publications

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“…By introducing a coolant fluid, film cooling is used to provide heat protection for wall surfaces under high thermal load, such as turbine blades and combustion chamber and inlet walls of scramjets. Olsen et al 1 and Garg 2 gave two examples of the application of film cooling in their papers. Film cooling is applied in a scramjet engine combustor wall 1 with some hydrogen fuel injected parallel to the wall through small supersonic slots to provide a lower energy buffer layer between the engine core flow and the structure.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Film Cooling in Hypersonic Flows

Yang

Badcock

Richards

et al. 2003

36th AIAA Thermophysics Conference

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Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Film Cooling in Hypersonic Flows

Yang

Badcock

Richards

et al. 2003

36th AIAA Thermophysics Conference

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“…Olsen et al (13) performed experiments to study coolant delivery pressure, slot height and lip thickness, and incident shock effects in two-dimensional hypersonic film cooling. Some design guidelines were published as follows.…”

Section: Introduction and Reviewmentioning

confidence: 99%

“…Some design guidelines were published as follows. Coolant pressure matched to the local boundary layer edge pressure is most effective, larger slot heights are more mass effective than smaller slot heights, and lip thickness is found to have no net effect on film cooling and can therefore be set by other design considerations (13) . Incident shocks degrade film cooling effectiveness.…”

Section: Introduction and Reviewmentioning

confidence: 99%

A numerical study of hypersonic laminar film cooling

Yang

Badcock²,

Richards³

2003

Aeronaut. j.

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A computational study has been performed to investigate the effectiveness of film cooling in hypersonic laminar flows. Both the primary and the coolant flow are air. First, three different primary flow conditions are used for validation. A uniform boundary condition at the slot exit is found to give unrealistic predictions of the heat transfer rate, whilst a boundary condition involving extended coolant inlet gives improvement. Then five coolant injection rates and three slot heights are examined. It is confirmed that increasing the coolant injection rate can increase the film cooling effectiveness for laminar cases. But slot height does not play an important role under the flow conditions in this study. The computational results are compared with the experimental results and good agreement is achieved.

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“…The feeding total pressure of the film coolant was set to ensure that the exit pressure of the injection matched that of the free stream, which could have higher effectiveness when compared with the unmatched conditions. 12 The other boundaries were set as walls which were assumed to be adiabatic with no-slip boundary conditions.…”

Section: Boundary Condition and Meshmentioning

confidence: 99%

“…When the original researches of supersonic film cooling were conducted, the film gas was mainly injected into the supersonic mainstream at sonic speed, including the experiments of Goldstein et al, 8 Parthasarathy and Zakkay, 9 Cary and Hefner, 10 and Richard and Stollery. 11 Later, the supersonic injection of film coolant into supersonic mainstream were becoming the focuses of the researchers, such as the works of Olsen et al, 12 Bass et al, 13 Hunt et al 14 and Juhany et al 15 Olsen et al 12 analyzed the effects of coolant feeding pressure, slot height, and lip thickness on film cooling. Bass et al 13 conducted experiments using hydrogen and nitrogen under different conditions and correlated their data in a single line with an empirical relationship.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of supersonic film cooling in a rearward-facing slot

Chen

Shen

2017

Advances in Mechanical Engineering

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Supersonic film cooling tangentially ejected through a half Laval nozzle set in a backward-facing slot was numerically simulated to investigate the structures of flowfield and the mechanisms of heat transfer after the slot. In particular, changes in flowfield near the turning point in the cooling effectiveness curve were studied. The turning point is defined by extrapolation of the cooling effectiveness curve using a power-law relationship. The point corresponds to the streamwise position where the hot mainstream is reaching the wall protected by the film coolant and to the disappearance of the unsmooth transition points in streamwise velocity profiles, where the growth rate of velocity in wall normal direction changes gradually from one state to another. The transition of velocity becomes smooth downstream of the turning point. The unsmooth transition point also exists in other profiles of flow parameters, such as the mole fraction of film gas and the total temperature of the fluid, which are indicators of the mixing extent between the mainstream and film coolants. Moreover, the unsmooth transition point is more evident in the film coolant of nitrogen than that of helium due to the slower drop rate of effectiveness in the current configuration of the supersonic film cooling.

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Experimental results for film cooling in 2-D supersonic flow including coolant delivery pressure, geometry, and incident shock effects

Cited by 34 publications

References 2 publications

Numerical Simulation of Film Cooling in Hypersonic Flows

Numerical Simulation of Film Cooling in Hypersonic Flows

A numerical study of hypersonic laminar film cooling

Numerical simulation of supersonic film cooling in a rearward-facing slot

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