PIV Measurements of Periodically Forced Flat Plate Film Cooling Flows With High Free Stream Turbulence

Gogineni, Sivaram; Trump, D. D.; Rivir, Richard B.; Pestian, D.

doi:10.1115/96-gt-236

Cited by 7 publications

(5 citation statements)

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“…Bryanston-Cross et al (1991) carried out experiments in a transonic turbine cascade. Tisserant and Breugelsmans (1995) performed rotor blade-to-blade velocity measurements and Gogineni et al (1996) studied periodically forced flat plate film cooling. The measurements of highly three-dimensional flow with a singlecamera PIV system could have substantial errors because the out-ofplane motion of a particles perpendicular to the light sheet plane produces a systematic measurement error that increases with increasing distance from the optical axis, e.g., Lourenco (1988).…”

Section: Piv Techniquementioning

confidence: 99%

PIV Investigation of the Flow Characteristics in an Internal Coolant Passage With Two Ducts Connected by a Sharp 180° Bend

Schabacker

Bölcs

Johnson

1998

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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A PIV study of the flow in a stationary model of a smooth two-pass internal coolant passage is presented, which focuses on the flow characteristics in the sharp 180º bend and downstream of the bend where the flow is redeveloping. Because PIV in its traditional conception only allows for the investigation of two-dimensional flow, a stereoscopic digital PIV system was assembled that measures all three velocity components simultaneously. The mean-velocity field and turbulence quantities of the flow are obtained from the PIV measurements. The model of the coolant passage consists of two square ducts, each having a length of 19 hydraulic diameters, which are connected by a sharp 180º bend with a rectangular outer wall. The measurements were obtained at one flow condition with a flow Reynolds number of 50,000. A strong secondary flow motion occurs in the bend of the smooth passage that consists of two counter rotating vortices, which impinge on the outer wall and influence the flow in the downstream leg. Both of the outer corners contain regions of recirculating flow. A separation bubble, about 1.5 hydraulic diameters long, occurs on the inner wall of the return pass. In the symmetry plane, the flow recovers from the bend effect within 10 hydraulic diameters.

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Section: Piv Techniquementioning

confidence: 99%

PIV Investigation of the Flow Characteristics in an Internal Coolant Passage With Two Ducts Connected by a Sharp 180° Bend

Schabacker

Bölcs

Johnson

1998

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…As for the effectiveness distributions, the largest Sr/on /St . x/D Pedersen et al (1972) and Goldstein and Yoshida (1982). (b) f SO Hz and 1 =32 Hz data.…”

Section: Jim-energetic Stanton Number Ratio Distributionsmentioning

confidence: 96%

“…The value employed here is 0.51, compared to a range from .01 to .60 in operating turbines. In studies in which the film cooling flows (not the bulk flow) are periodically forced, Bons et al (1995) and Gogineni et al (1996) use a reduced frequency of the form which is equivalent to Da/A.D. According to these authors, magnitudes of rcifD range from 20 to 200 in operating turbines.…”

Section: Generation and Characteristics Of Flow Pulsationsmentioning

confidence: 99%

“…8 and 9 are determined from averages of local values over zID from -1.5 to 1.5. The data of Pedersen et al (1977) and Goldstein and Yoshida (1982) are compared to our LID=10 data in Figs. 8a and 9a because their injection hole lengths are long enough to produce velocity profiles which are nearly fully developed at their hole exits.…”

Section: Adiabatic Film Coolina Effectiveness Distributionmentioning

confidence: 99%

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Effects of Bulk Flow Pulsations on Film Cooling From Different Length Injection Holes at Different Blowing Ratios

Seo

Lee

Ligrani

1998

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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Bulk flow pulsations in the form of sinusoidal variations of velocity and static pressure at injectant Strouhal numbers from 0.8 to 10.0 are investigated as they affect film cooling from a single row of simple angle holes. Similar flow variations are produced by potential flow interactions and passing shock waves near turbine surfaces in gas turbine engines. Time-averaged temperature distributions, phase-averaged temperature distributions, adiabatic film cooling effectiveness values, and iso-energetic Stanton numbers show that important alterations to film cooling protection occur as pulsation frequency, coolant Strouhal number, blowing ratio, and non-dimensional injection hole length are changed. Overall, the pulsations affect film performance end behavior more significantly both as L/D decreases, and as blowing ratio decreases.

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“…The TiCL reacted with water vapor in the mainstream flow to create TiO2 particles on the "edge" of the jet where the jet and the main flow had mixed on a molecular level. Gogineni et al (1996) used particle image velocimetry (P1V) to measure velocity distributions in the near field of a film cooling jet to study the effect of freestream turbulence. Dahm et al (1991) have obtained threedimensional (and time-resolved) PLIF data to study mixing in turbulent flows, although not near surfaces.…”

Section: Cwmentioning

confidence: 99%

Quantitative Visualization of Full-Coverage Discrete-Hole Film Cooling

Fric

Campbell

Rettig

1997

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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Water tunnel experiments were carried out to study full-coverage discrete-hole film cooling for geometries applicable to gas turbine combustor liners. The cooling holes were spaced at a pitch to diameter ratio of 6.5 and had an injection angle of 20° to the cooled surface. The mainstream flow direction was in line with the cooling holes. Blowing ratios from 0.5 to 5.7 were studied, which is a range typical of combustor liners. A unique multiple plane PLIF (planar laser-induced fluorescence) technique was used to measure time-averaged film cooling concentration at various heights above the surface to be cooled. Three-dimensional data sets were generated to quantitatively visualize cooling-jet film coverage, structure, and interaction. Film coverage as close as 0.25 mm (0.010 in.) from the surface was measured, thereby yielding data that approach adiabatic film effectiveness. Two sets of film cooling experiments were conducted. One set used a model with a relatively small array of 2.54 mm (0.100 in.) holes, meant to be a large-scale model of hole sizes encountered in combustor liners. The second set used a large array of 0.51 mm (0.020 in.) nominal diameter laser-drilled holes, manufactured in the same manner as combustor liner cooling holes. The results show that near-wall film coverage is minimum for blowing ratios from 1.7 to 3.3. At blowing ratios less than 1.7 and greater than 3.3, the film coverage was improved. Jet structure and interaction was also observed. In particular, jet separation behavior and coalescence were visualized, and both were generally a function of blowing ratio.

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PIV Measurements of Periodically Forced Flat Plate Film Cooling Flows With High Free Stream Turbulence

Cited by 7 publications

References 0 publications

PIV Investigation of the Flow Characteristics in an Internal Coolant Passage With Two Ducts Connected by a Sharp 180° Bend

PIV Investigation of the Flow Characteristics in an Internal Coolant Passage With Two Ducts Connected by a Sharp 180° Bend

Effects of Bulk Flow Pulsations on Film Cooling From Different Length Injection Holes at Different Blowing Ratios

Quantitative Visualization of Full-Coverage Discrete-Hole Film Cooling

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